| PROPOSAL NUMBER: | 02- A1.01-8269 (For NASA Use Only - Chron: 023730 ) |
| SUBTOPIC TITLE: | Flight Deck Situation Awareness and Crew Systems Technologies |
| PROPOSAL TITLE: | Constraint-based Analysis of Aircraft Operations |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Charles River Analytics Inc.
625 Mount Auburn Street
Cambridge , MA 02138 - 4555
(617 ) 491 - 3474
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Dr. Dan L. Grecu
dgrecu@cra.com
625 Mount Auburn Street
Cambridge , MA 02138 - 4555
(617 ) 491 - 3474
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Advanced technologies for on-board data recording allow the collection of increasingly sophisticated information during aircraft operation, reflecting decisions and actions taken by the crew, external flight conditions, and the behavior of flight systems. Such data, when subjected to a systematic and focused methodology of analysis, offers a tremendous opportunity for analyzing overall crew behavior, action patterns, and responses. To do this, we propose a novel analysis framework centered on the use of constraint-based safety models. In contrast to data-driven analysis techniques, we propose an approach in which aviation safety experts would define constraint-based models of aircraft operational safety, and then apply these models against recorded data logs to detect and analyze exceedances. Data segments that reveal deviations from the model are then submitted to specialized analysis components that attempt to infer general behaviors across aircraft crews, or across individuals, to assess correlations with the detected deviations. The resulting recommendations can be incorporated in training sessions, simulated flight experiments, and actual test flights, to improve overall safety of maneuvers and performance of crew actions.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
Potential commercial applications of the proposed effort include safety critical environments, where operational data is available for processing and analysis. Immediate application areas include railway safety, control rooms for nuclear plants, and for other complex high-value ecologically-sensitive industrial processes. The proposed approach also has immediate application for aircraft safety applications in the military domain.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
The full-scope environment for Constraint-based Analysis of Aircraft Operations will have immediate benefit in supporting the Aviation Performance Measurement System (APMS). The proposed capability provides a mixed initiative approach to analyzing vast amounts of data collected during routine flights, by detecting and facilitating the analysis of behaviors that are transient, and may potentially remain undetected. The proposed effort has also integration potential with components of NASA?s Aviation Safety Program by capitalizing on the results of the Aviation System Monitoring and Modeling effort, and on the data sources it provides. The proposed approach can complement the Single Aircraft Prevention Program by integrating the results into a capability that can predict safety hazards due to technical problems, aircraft operation issues, and adverse conditions. Finally, the Constraint-based Analysis of Aircraft Operations can provide valuable input to the System-Wide Accident Prevention Program that looks into aviation safety issues associated with human error and non-procedural compliance.
| PROPOSAL NUMBER: | 02- A1.01-9623 (For NASA Use Only - Chron: 022376 ) |
| SUBTOPIC TITLE: | Flight Deck Situation Awareness and Crew Systems Technologies |
| PROPOSAL TITLE: | Cockpit System Situational Awarness Modeling Tool |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Micro Analysis & Design Inc
4949 Pearl East Circle, Suite 300
Boulder , CO 80301 - 2477
(303 ) 442 - 6947
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Mr. John Keller
jkeller@maad.com
4949 Pearl East Circle, Suite 300
Boulder , CO 80301 - 2477
(303 ) 442 - 6947
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The Cockpit System Situational Awareness Modeling Tool will use the principles of discrete event simulation to predict pilot situational awareness (SA). The human performance modeling environment of IMPRINT combined with the cognitive modeling tool ACT-R will provide a powerful tool for the designers of cockpit systems. IMPRINT can already be used to predict pilot workload and assess the effects of performance shaping factors on pilot tasks. The use of ACT-R to add the SA prediction capability will dramatically increase the usefulness of the tool. The capability of predicting pilot SA will allow design concepts to be assessed early in the design process and supplement data collected through comparatively more expensive pilot in-the-loop experiments. NASA is continuing to play an important role in the development of new operational concepts for the National Airspace System (NAS) as they explore the feasibility of transferring separation responsibility from the ground-based air traffic control system to the flight deck. The impact on the pilot?s SA of new tools designed to support these efforts must be understood to ensure that safety and efficiency of the NAS is maintained. Likewise any commercial developer of cockpit systems will benefit from the use of this tool.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
The Cockpit System Situational Awareness Modeling Tool could assist air transport cockpit designers with developing decision aids and displays that would provide new levels of pilot SA needed to support the Free Flight concept of transferring separation responsibility from the ground-based air traffic control system to the flight deck. In addition, a general aviation derivative of the tool could be used for designing cockpit systems for general aviation pilots whose wider range of experience and skills require displays and instrumentation that must be robust to situational awareness needs while inhibiting information overload.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
NASA often includes SA in the standard data collection process during simulator experiments and flight tests of new systems. The ability to predict pilot SA during the design of a new system will greatly improve the efficiency of the design process while reducing the costs. In addition, the required investigation to support the modeling effort will lead to a greater understanding of SA in aviation safety from a basic research perspective.
| PROPOSAL NUMBER: | 02- A1.02-7454 (For NASA Use Only - Chron: 024545 ) |
| SUBTOPIC TITLE: | Propulsion and Airframe Failure Data and Accident Mitigation |
| PROPOSAL TITLE: | Damage Tolerant Sandwich Composite Structures for Turbine Engine Components |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
WebCore Technologies Corp.
591 Congress Park Dr.
Dayton , OH 45459 - 0000
(937 ) 435 - 5034
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Rob Banerjee
rbanerjee@webcoreonline.com
591 Congress Park Dr.
Dayton , OH 45459 - 0000
(937 ) 435 - 5034
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
A new capability for building lightweight, damage-tolerant, and affordable composite sandwich structures for turbine engine components will be developed. The new sandwich composites proposed herein will be produced with an innovative composite core material (TYCOR), braided fabrics for the facings, and Vacuum Assisted Resin Transfer Molding (VARTM) process. The combination of these three elements will lead to an integrated composite sandwich panel that is affordable and offers improved damage tolerance compared to traditional composites. This Phase I SBIR program will comprise several technical tasks involving sandwich panel design and optimization for ballistic impact performance, mechanical testing of flat panels, VARTM molding of a full case and half case, ballistic testing of flat panels and cases, fabrication and mechanical testing of attachment flange sub-elements, and a material and process cost analysis. GE Aircraft will serve as a key partner on the program. The goal is to demonstrate that TYCOR composite panels meet the structural, manufacturing, and affordability requirements for primary, complex-shaped turbine engine components, while offering adequate damage tolerance and reduced weight compared to metallic components.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
This technology is pervasive and can be used for aerospace, marine, industrial, and transportation applications for ligtweight and durable composite structures.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
This technology can be used for general aviation aircraft engines.
| PROPOSAL NUMBER: | 02- A1.02-8080 (For NASA Use Only - Chron: 023919 ) |
| SUBTOPIC TITLE: | Propulsion and Airframe Failure Data and Accident Mitigation |
| PROPOSAL TITLE: | Development of a rugged, fuel tank compatible, oxygen concentration sensor |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Advanced Projects Research Inc
1925 MCKINLEY AVE SUITE B
LA VERNE , CA 91750 - 5800
(909 ) 392 - 8853
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Tobias Rossmann, Ph.D.
toby.rossmann@advancedprojects.com
1925 MCKINLEY AVE SUITE B
LA VERNE , CA 91750 - 5800
(909 ) 392 - 3155
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
We propose to engineer a compact, robust, optically-based sensor for measuring local oxygen concentration in aircraft fuel tanks. This system will utilize absorption of rapidly scanned Vertical Cavity Surface Emitting Diode Lasers (VCSELs) by molecular oxygen. This proposed system can measure 100 ppm to 100% oxygen in ambient temperatures from -100 to 300 F utilizing a new spectroscopic frequency domain detection scheme known as the wavelength agile spectral-harmonic (WASH) technique. The wavelength agile aspect of the laser source allows for temperature insensitive measurements of oxygen concentration over a wide range of pressures (0.1 atm to 50 atm). The system will also possess auto-calibration capabilities, the ability to withstand temporary immersion in all liquid fuels, fast time response (~100 msec), and long operating life (> 10,000 hrs).
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
There are many commercial and military applications for an accurate and rugged fuel tank oxygen concentration sensor. The fuel tank oxygen sensor could be used in both new and retrofit commercial aircraft as a control sensor for fuel tank protection systems. The reliable and precise instrument can be used to control onboard inert gas generation systems (OBIGGS) for cargo compartment fire suppression, fuel tank inerting, and emergency breathing oxygen systems (OBOGS) for passengers and crew. The key to the commercial viability of this product is the accuracy of the sensor, its ability to handle harsh environments including highly variable temperatures and pressures, and its reliability and lifetime, which we propose to engineer into the system. The long operating lifetime and stability of this measurement system in challenging operating environments are superior to existing oxygen measurement strategies.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
NASA is concerned with the prevention of hazardous and accident conditions and the mitigation of their effects when they do occur. One particular emphasis is on fire. The prevention, detection, and suppression of fires are critical goals of accident mitigation. Aircraft fires represent a small number of actual accident causes, but the number of fatalities due to in-flight, post-crash and on-ground fires is large. The proposed oxygen concentration sensor provides a key element for an inerting system for the prevention of fires in fuel tanks.
| PROPOSAL NUMBER: | 02- A1.03-7779 (For NASA Use Only - Chron: 024220 ) |
| SUBTOPIC TITLE: | Automated On-Line Health Management and Data Analysis |
| PROPOSAL TITLE: | Embedded Dual-Function Arc Fault Circuit Breaker/ Locator based on OSA |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
WILLIAMS-PYRO, INC.
200 Greenleaf street
Fort Worth , TX 76107 - 1331
(817 ) 872 - 1500
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Kartik Moorthy
Kartik.Moorthy@williams-pyro.com
200 Greenleaf Street
Fort Worth , TX 76107 - 1331
(817 ) 872 - 1500
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
This SBIR describes diagnostic and reasoning approaches that are applicable in a wide set of domains, specifically the design and development of Embedded Dual-Function Arc Fault Circuit Breaker/ Locator based on Open Systems Architecture for Aircraft Wiring Systems. An Embedded Locator And Breaker (ELaB) will be designed that will not only identify arc faults before they occur, but also provide a precise location of potential causes, such as insulation damages, that could lead to an arc. The ELaB will be a self-contained, portable test set based on open systems architecture, thus allowing state-of-the-art technologies such as Reflectometry Techniques to be integrated with existing Arc Fault Circuit Breakers (AFCB). Each ELaB will be based on VLSI/MEMS technology and will incorporate several systems on a microchip: a wiring testing and fault location system based on RF reflectometry techniques, a dynamic on-line wire failure analysis and diagnosis system based on Artificial Neural Network combined with signal processing techniques, and a switching system that automates the testing process for large bundles of multiple wires. Electromechanical adaptability of existing systems will allow on-board data transfer capabilities from wires under test to an on-board Automated Test System (ATS).
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
WPI?s proposed Embedded Dual-Function Arc Fault Circuit Breaker/ Locator based on Open Systems Architecture for Aircraft Wiring Systems will further efforts to extend the life of aging aircraft as well as reduce maintenance related costs by using Embedded Locator and Breaker (ELaB) to locate arcing conditions and determine insulation degradation within electrical wiring. ELaB will also improve safety by identifying and preventing arcing conditions before a fire can occur. Significant commercial applications exist outside of the aerospace industry including ships, vehicles, manufacturing equipment, and electrical equipment where arcing can cause fire and loss of life.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
WPI?s proposed Embedded Dual-Function Arc Fault Circuit Breaker/ Locator based on Open Systems Architecture for Aircraft Wiring Systems will further efforts to extend the life of aging aircraft as well as reduce maintenance related costs by using Embedded Locator and Breaker (ELaB) to locate arcing conditions and determine insulation degradation within electrical wiring. ELaB will improve maintenance efficiency and reduce maintenance costs by reducing the amount of maintenance time spent inspecting wire for microscopic cracks that could lead to arcing. For NASA, ELaB will also improve crewmember safety by identifying and preventing arcing conditions before a fire can occur and enhance operational readiness.
| PROPOSAL NUMBER: | 02- A1.03-8719 (For NASA Use Only - Chron: 023280 ) |
| SUBTOPIC TITLE: | Automated On-Line Health Management and Data Analysis |
| PROPOSAL TITLE: | Control of Systems with Actuator Failures |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Techno-Sciences Inc
10001 Derekwood Ln
Lanham , MD 20706 - 4388
(301 ) 577 - 6000
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Gaurav Bajpai
gaurav@technosci.com
10001 Derekwood Ln
Lanham , MD 20706 - 4388
(301 ) 577 - 6000
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
A number of fatal aircraft accidents in recent years have been linked to component failures. With the predicted increase in air traffic these numbers are likely to increase. With reduction of fatal accidents as motivation, the proposal plans to investigate design of fault tolerant control system for aircrafts undergoing actuator failures. The feasible approach for such a control scheme is to predesign various controllers anticipating these failures and switching to appropriate controller when the failure occurs. It is found that use of nominal controller when actuators fail may lead to catastrophic accidents. Switching to an appropriate controller enabled by the available redundancy in actuation allows the system to perform adequately even when these failures occur. However, the predesign for actuator failures is not trivial as the position at which the actuators fail is not known a priori. For linear systems the problem has been solved in recent literature; however failures when they occur can cause excursions into nonlinear regimes. The primary thrust of this research would be to extend the results in nonlinear control theory to accommodate actuator failures in aircraft.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
Actuator failures such as stuck control surfaces when they occur in commercial aircraft can cause catastrophic accidents and fatal loss of life. The primary application area of the proposed work is to improve the safety and performance of these vehicles in face of such failures. Since the proposed work addresses the problem of actuator failures using the systems approach these techniques will be applicable to a broad range of systems including other aerospace vehicles, ground and sea vehicles, hazardous chemical plants, nuclear power plant, robotic manipulators and others. The value addition in increased safety and performance achieved because of the control techniques to be developed from this research cannot be overestimated. Additionally, the design techniques will also provide a framework in order to synthesize fault tolerant systems making contributions to the development of autonomous systems.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
Several design techniques to be developed in the proposed work are directly applicable to improve the safety and performance of aerospace vehicles in case of components failures involving the actuators. Since NASA has a great interest in developing autonomous systems, the work will provide a means to synthesize fault tolerant systems which can continue to perform under adverse operating circumstances even after failures. These techniques prove to be invaluable when especially when the system is deployed in a remote location or when continued safety and performance are desired features of the system.
| PROPOSAL NUMBER: | 02- A1.03-9284 (For NASA Use Only - Chron: 022715 ) |
| SUBTOPIC TITLE: | Automated On-Line Health Management and Data Analysis |
| PROPOSAL TITLE: | Smart Low-Cost Electronic Module for Simultaneous Sensor and Process Faults Moni |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Intelligent Automation, Inc.
7519 Standish Place Suite 200
Rockville , MD 20855 - 2785
(301 ) 294 - 5242
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Mr. Roger Xu
hgxu@i-a-i.com
7519 Standish Place Suite 200
Rockville , MD 20855 - 2785
(301 ) 294 - 5200
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The detection and isolation of air vehicle process failures is difficult because air vehicle dynamics are nonlinear and the vehicle has many important and complicated sub-systems. The fault diagnosis performance is further complicated by the presence of sensor failures. In this proposal, Intelligent Automation, Incorporated (IAI) proposes a novel approach to perform simultaneous diagnosis of sensor and process faults for air vehicles. This algorithm can be embedded into low cost electronics. First, two independent residual vectors (RVs) for detection and isolation of the sensor and process faults are built. This is in sharp contrast to conventional methods, which can deal with either sensor failures or process failures but never both. Second, to isolate faults, the RV is transformed into a set of structured residual vectors (SRVs), where one SRV is made insensitive to a specified subset of faults, while remaining sensitive to other faults. The proposed technology is relevant to this subtopic because we will develop an electronic module that can be embedded in low cost sensor electronics to quickly identify both sensor and process faults.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
The proposed sensor and process faults diagnosis module is novel by itself and will have many practical NASA applications such as spacecraft, flight control systems, etc. The developed technology will result in an increase in inspection efficiency and inspection unit autonomy while reducing the demand on NASA maintenance personnel and the total ownership cost for NASA asset.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
Health monitoring technology has many applications such as health monitoring for engines, helicopter gearbox systems, jet and automotive engine diagnostics, and commercial and military aircraft. The jet and automobile industries are multibillion dollar industries that are commercial targets for this technology. Our goal is to develop a generic electronic module, which can be used for many systems.
| PROPOSAL NUMBER: | 02- A1.04-8884 (For NASA Use Only - Chron: 023115 ) |
| SUBTOPIC TITLE: | Aircraft Icing Systems |
| PROPOSAL TITLE: | Low-Power Aircraft Deicing System |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Continuum Dynamics, Inc.
34 Lexington Avenue
Ewing , NJ 08618 - 2302
(609 ) 538 - 0444
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Robert M. McKillip, Jr.
bob@continuum-dynamics.com
34 Lexington Avenue
Ewing , NJ 08618 - 2302
(609 ) 538 - 0444
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Two novel approaches for providing de-icing of aerodynamic surfaces are proposed for research and development. The first represents a ?snap through? actuation mechanism that can abruptly and reversibly alter the shape of aerodynamic surfaces in-flight to discrete self-locking positions. The snap-through system is ideally suited for deicing by providing mechanical debonding and removal of accreted ice with minimal weight and power requirements. The second mechanism incorporates interleaved sliding surfaces that provide suitable surface strains for debonding accreted ice on airfoils. Both systems incorporate Shape Memory Alloy (SMA) materials as their prime movers. SMA-based systems are more durable than pneumatic systems and provide higher force and strain output per unit volume than other smart material based actuators. The proposed methods offer up to an order of magnitude reduction in required power over other impulsive electromechanical technologies due to the modest currents required for SMA wire heating. In Phase I, dynamic models of each of the devices will be developed and demonstration models constructed and tested to establish effectiveness for representative deicing situations. Construction and testing of a full-scale prototype will be performed in Phase II.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
The proposed deicing system(s) for aerodynamic surfaces can be applied on all commercial aircraft certified for flight in instrument meteorological conditions. The device?s low power, light weight, small size, robust operation and potentially low cost give it a significant market advantage over current technology de-icing systems. The technology may provide enhanced icing protection for rotorcraft, with significant power reductions over current thermal surface heating systems.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
The deicing systems proposed for R&D directly supports NASA?s continuing interest in researching the most effective means for aircraft icing detection, removal, and mitigation. The resulting system could be used to help support various research programs investigating these technologies in the NASA Glenn Icing Tunnel or on NASA?s Icing Research Aircraft (Twin Otter); additionally, it may also provide technology to support various NASA initiatives in rotorcraft icing research.
| PROPOSAL NUMBER: | 02- A2.01-8024 (For NASA Use Only - Chron: 023975 ) |
| SUBTOPIC TITLE: | Propulsion System Emissions and Noise Prediction and Reduction |
| PROPOSAL TITLE: | Artificial Neural Net Chemistry Module for Large Eddy Simulations |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
CFD Research Corp
215 Wynn Dr.
Huntsville , AL 35805 - 1944
(256 ) 726 - 4800
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Steven Cannon
jls@cfdrc.com
215 Wynn Dr.
Huntsville , AL 35805 - 1944
(256 ) 726 - 4800
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Combustion Large Eddy Simulation (LES) is a vastly improved method of modeling turbulent-combustion in gas turbine combustors, and will provide improved emissions/instability prediction capability of UEET combustors. It is widely recognized that one of the best subgrid turbulence-combustion models is the Linear Eddy Mixing (LEM) model with multi-step reactions. However, this model is not commonly used in the design environment for one main reason: computational time.
In this SBIR, we propose to develop a subgrid LEM module with multi-step Jet-A kinetics that is 100 times faster than the state-of-the-art direct LEM. This new, innovative method performs off-line LEM calculations over a range of turbulence levels and compositions to train an artificial neural net (ANN). The ANN is then used to determine the chemical source terms required in the combustion LES calculation. In Phase I of this SBIR, the feasibility of developing the LEM/ANN module will be demonstrated by training a one-step, five species Jet-A fuel oxidation mechanism. The preliminary LEM/ANN module will be implemented into the CFD-ACE+ code, validation performed, and speed-up demonstrated. At the end of Phase I, the module will be delivered to NASA for incorporation into the NCC code. In Phase II, the LEM/ANN approach will be extended to include multi-step Jet-A kinetic mechanisms, and applied to UEET combustor configurations.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
The LEM/ANN chemistry module will significantly improve combustor design methods. The ability to reduce emissions, avoid combustion-driven instability, and to investigate high-payoff ideas will be possible. The software will be useful for gas turbine manufacturers, burner and boiler manufacturers, chemical processing industry, and the automotive industry. The module will be incorporated into CFDRC's commercial code, CFD-ACE+.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
The LEM/ANN chemistry module developed in this SBIR will be useful in the cost-effective design and analysis of liquid-fueled, high performance combustors. The LES combustor design tool will be used to help meet the NASA UEET emission goals. The module will be supplied to NASA for incorporation into the National Combustion Code.
| PROPOSAL NUMBER: | 02- A2.01-9022 (For NASA Use Only - Chron: 022977 ) |
| SUBTOPIC TITLE: | Propulsion System Emissions and Noise Prediction and Reduction |
| PROPOSAL TITLE: | High Temperature Polyimides for Resin Transfer Molding Process |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Triton Systems Inc.
200 Turnpike Road
Chelmsford , MA 01824 - 4000
(978 ) 250 - 4200
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Dr. Lawino Kagumba
lkagumba@tritonsystems.com
200 Turnpike Road
Chelmsford , MA 01824 - 4000
(978 ) 250 - 4200
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Triton Systems, Inc. proposes to develop novel low melt flow viscosity, environmentally friendly high temperature polyimide resin that can address the need for low cost, lightweight, complex geometry composite manufacturing. Triton has teamed with composite manufacturer and end users to assist in evaluation of its new RTM/VARTM high temperature polyimides. The proposed program will develop resins with melt flow viscosity lower than 10 poise at greater than 280?C processing temperature. High temperature RTM/VARTM resins would allow ?out-of-autoclave? manufacturing, which reduces manufacturing cost and allow for large, complex shape designs. The new high temperature resin will be applicable to propulsion systems such as aircraft gas turbines, rocket and turbine engines, and auxiliary power in aircraft and space vehicles.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
Triton has teamed with end users to evaluate the development of the new RTM/VARTM high temperature resins for compatibility with their current composite manufacturing. This teaming arrangement will assist Triton to develop the resin within the manufacturer production specifications. The potential commercial applications are aircraft jet engines, rocket and turbine engines, and auxiliary power in aircraft and space vehicles.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
Development of new low melt flow viscosity (RTM/VARTM), environmentally friendly high temperature polyimide resins would allow ?out-of-autoclave? manufacturing of large structures such as large composite tanks for the next generation Reusable Launch Vehicles (RLVs). Currently the size of the autoclave predicts the size of the components that can be fabricated, which is a limitation for development of the next RLVs.
| PROPOSAL NUMBER: | 02- A2.01-9731 (For NASA Use Only - Chron: 022268 ) |
| SUBTOPIC TITLE: | Propulsion System Emissions and Noise Prediction and Reduction |
| PROPOSAL TITLE: | Acoustic Test Method for Turbofan Engine Exhaust Systems at Cruise Conditions |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Aero Systems Engineering, Inc.
358 East Fillmore Avenue
St. Paul , MN 55107 - 1289
(651 ) 220 - 1290
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Dr. Dean F. Long
dlong@aerosysengr.com
358 East Fillmore Avenue
St. Paul , MN 55107 - 1289
(651 ) 227 - 7515
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The exhaust flow from a turbofan engine operating at typical cruise conditions generates noise as turbulent flow interacts with the basic shock cell pattern. This can be a significant source of noise within the aircraft cabin. The proposed innovation is a new method for testing the acoustics of model scale turbofan engine exhaust systems at cruise conditions in a transonic wind tunnel. This would complement the aerodynamic tests now conducted in the wind tunnel. Currently, acoustic data at cruise conditions is only obtained from costly flight tests. Wind tunnel tests are desirable to simulate the proper flight conditions, but acoustic measurements are difficult in this environment. Microphone arrays and specialized array processing techniques are required to separate model noise from tunnel induced noise and reverberation. The new method involves three specific areas of innovation: a) phased-array noise measurement methods, b) evaluating potential modifications to an existing wind tunnel, and c) evaluating means for reducing model air supply noise. Preliminary measurements demonstrate that each of these problems is solvable. The proposed research will then lead to a successful commercial ?service? to airframe manufacturers interested in increasing passenger comfort through better understanding of the noise sources that influence the passenger cabin environment.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
The principal commercial application of this research will be an expanded ?test service? available at our test laboratory to conduct model scale acoustic tests on aircraft components in a 66-inch transonic wind tunnel where aerodynamic performance measurements on exhaust nozzle systems are currently conducted. This service would be available to commercial airframe and engine manufacturers interested in minimizing cabin interior noise levels created by the operation of turbofan engines. Another application relates to acoustic diagnostics of full scale turbofan engines under test conditions. During maintenance procedures an engine is extensively tested prior to remounting on the aircraft to ensure proper operation. These tests occur in hard walled test cells, not unlike the hard walls of a wind tunnel. We have begun discussions with engine manufacturers to determine how acoustic array technology can be applied to maintenance diagnostics.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
NASA conducts acoustic measurements on aircraft systems and components in several wind tunnels. The research to be conducted on this program will complement NASA tests. The subspace methodology described in this proposal is being developed on a related Air Force SBIR and will be refined for use on this program. It is common in the field of communication but has not been applied to aeroacoustic studies. It is not restricted to the transonic problem and may provide superior performance to standard techniques now in use for the low speed aeroacoustic problem. In particular, it may improve the noise source location techniques now used to identify source locations for tests conducted in NASA wind tunnels, such as the 40- X 80-Ft wind tunnel at NASA ARC. This research will provide significant advancement of adaptive beamforming techniques applied to conventional aeroacoustic wind tunnel tests.
| PROPOSAL NUMBER: | 02- A2.02-8033 (For NASA Use Only - Chron: 023966 ) |
| SUBTOPIC TITLE: | Electric and Intelligent Propulsion Technologies for Environmentally Harmonious Aircraft |
| PROPOSAL TITLE: | The Double-Mixing Vortex Mixer/Injector |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Sun Valley Technology Inc.
26700 Renaissance Parkway, Unit 4
Warrensville Heights , OH 44128 - 5764
(216 ) 464 - 1322
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Tai-Yen Sun
svtfrank@aol.com
26700 Renaissance Parkway, Unit 4
Warrensville Heights , OH 44128 - 5764
(216 ) 464 - 1322
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The performance of the currently used Auto Thermal Reformer(ATR) in the Solid Oxide Fuel Cell (SOFC) suffers degradation from carbon depostition due to inadequate mixing of fuel/steam/air in the reformer. An innovative concept of Double-Mixing Vortex (DMV) mixer/injector is proposed to remedy the defect of the ATR. The improved mixing outcome from the DMV mixer is resulted from two consecutive mixing steps built in the device. The primary mixing is achieved by direct-impinging scheme of fuel, air, and steam jets in the fuel passages. The secondary mixing of the fluid is achieved by setting-up swirling vortex in the mixing chamber of the mixer in the later stage. Finally, extremely fine drops in the spray are formulated due to the expansion of small air/steam bubbles which are entrapped in the fuel during the mixing process in the mixing chamber. A two-fluid mixer of similar design has been tested by SUN VALLEY TECHNOLOGY (SVT) successfully in the industrial burners. The DMV mixer will be expected to achieve improved mixing of fluids and extremely fine drops in the spray for the proper fuel distribution in the ATR applications.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
The proposed Double-Mixing Vortex (DMV) mixer/injector will achieve a much superior quality for fluid mixing. It can be used in the Auto Thermal Reformer (ATR) of a Solid Oxide Fuel Cell (SOFC) for the auxiliary power unit (APU) in an aircraft. The sprays generated from this mixer/injector are extremely fine and uniform, which is great for gas-turbine-combustor or industrial-burner applications for high turn-down ratio runnings. It can also be used in the general liquid/gas or gas/gas mixing where fast mixing within a compact space is required.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
The proposed Double-Mixing Vortex (DMV) mixer/injector will achieve a much superior quality for fluid mixing. It can be used in the Auto Thermal Reformer(ATR) of a Solid Oxide Fuel Cell (SOFC) for the auxiliary power unit (APU) in an aircraft. The extremely fine sprays generated from this mixer/injector along with its high turn-down ratio will be beneficial to gas-turbine-combustor runnings. It can also be used in the desulfurizing process for the hydrocarbon fuels.
| PROPOSAL NUMBER: | 02- A2.02-9354 (For NASA Use Only - Chron: 022645 ) |
| SUBTOPIC TITLE: | Electric and Intelligent Propulsion Technologies for Environmentally Harmonious Aircraft |
| PROPOSAL TITLE: | Co-Generation of High Purity Hydrogen and Electric Power |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Ceramatec, Inc.
2425 South 900 West
Salt Lake City , UT 84119 - 1517
(801 ) 978 - 2163
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Joseph Hartvigsen
jjh@ceramatec.com
2425 South 900 West
Salt Lake City , UT 84119 - 1517
(801 ) 972 - 2455
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Hydrogen centered technologies such as fuel cells have generated much attention as a means of reducing emissions and dependence on fossil fuels. Unfortunately there are no ideal solutions to the problems of hydrogen production and storage. An innovative integrated hybrid solid state electrochemical system is proposed as a means of overcoming many of the fundamental problems pertaining to hydrogen production and purification, fuel reformation, and fuel cell operation. The proposed process is a physical, chemical and thermal integration of three operations; (1) hot electrolysis of steam to produce high purity hydrogen, (2) electrochemical partial oxidation of hydrocarbon fuel, (3) electric power generation by a solid oxide fuel cell fueled by the reformed hydrocarbon. Required process inputs are air, steam and hydrocarbon fuel, producing electric power, high purity hydrogen and an exhaust stream suitable for CO2 sequestration, containing only carbon dioxide and steam. The concept allows design flexibility in meeting the desired mix of electric power produced by the integrated solid oxide fuel cell, and high purity product hydrogen suitable for use in low temperature fuel cells. Current developments in intermediate temperature electrolyte materials will enable operation of this device in the temperature range centered around 600?aC, favorable to reforming thermodynamics.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
The proposed innovation would be generally applicable to the following non-NASA commercial applications:
(1)Aircraft and automotive auxiliary power
(2)Highway truck hotel power
(3)Fuel processing for automotive fuel cell electric vehicles
(4)Point of use hydrogen generation
(5)Stationary electric power generating plants
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
The proposed innovation would find application in meeting NASA needs related to:
(1)Fuel processing for electric aircraft propulsion and power systems
(2)Ground based hydrogen production with CO2 sequestration
| PROPOSAL NUMBER: | 02- A2.03-8342 (For NASA Use Only - Chron: 023657 ) |
| SUBTOPIC TITLE: | Revolutionary Technologies and Components for Propulsion Systems |
| PROPOSAL TITLE: | Flow Test for Rotating Chamber Pulse Detonation Engine |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
SPIRITECH Advanced Products, INC.
880 Jupiter Park Dr. #8
Jupiter , FL 33458 - 8901
(561 ) 741 - 3441
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Eric J. Gamble
egamble@spiritech.cc
880 Jupiter Park Dr. #8
Jupiter , FL 33458 - 8901
(561 ) 741 - 3441
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Pulse detonation engines hold promise to increase performance of air-breathing propulsion systems by taking advantage of the increase in cycle efficiency due to the constant-volume heat addition characteristics of detonative combustion. SPIRITECH is developing a pulse detonation engine, the Rotating Chamber PDE, which utilizes multiple combustion chambers on a rotating spool to improve inlet and nozzle performance and to eliminate the need for valves. Efficient flow of the fuel-air mixture into the detonation chambers as they rotate is critical for achieving high levels of thrust. A flow test is proposed using a rotating plate to simulate the flow characteristics into the rotating detonation chamber. This Phase I study will provide the data necessary to quantify the flow efficiency through pulse detonation engines. Additional testing of other critical PDE engine components and key technologies will be performed in the Phase II program to develop the technology base required for a prototype in Phase III.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
The potential commercial market for this device is enormous, since the successful execution of this concept could revolutionize aviation and aerospace markets.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
The Rotating Chamber PDE is a lightweight, air-breathing engine offering high specific impulse. This engine offers advantages to replace more expensive turbojets and less capable rockets in high speed aircraft. Additionally, it may be incorporated in combined cycle applications, where it is combined with a scramjet for a single-stage-to-orbit reusable launch vehicle (RLV) or as the first stage in a two-stage-to-orbit RLV using rockets or a rocket-based combined cycle for the second stage.
| PROPOSAL NUMBER: | 02- A2.03-8358 (For NASA Use Only - Chron: 023641 ) |
| SUBTOPIC TITLE: | Revolutionary Technologies and Components for Propulsion Systems |
| PROPOSAL TITLE: | Improving Off-Design Nozzle Performance Using Fluidic Injection |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
SPIRITECH Advanced Products, INC.
880 Jupiter Park Dr. #8
Jupiter , FL 33458 - 8901
(561 ) 741 - 3441
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Eric Gamble
egamble@spiritech.cc
880 Jupiter Park Dr. #8
Jupiter , FL 33458 - 8901
(561 ) 741 - 3441
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Use of fluidic injection of high-pressure air is proposed to improve nozzle performance and reduce the off-axis component of thrust at off-design flight conditions, generally at low Mach number and low pressure ratio. Hypersonic flight vehicles are typically designed with a high expansion ratio single expansion ramp nozzle (SERN) with a design point at high Mach number flight conditions. However, at low Mach number flight, lower nozzle expansion ratios are required for optimum performance. Thus, these vehicles suffer from poor performance throughout much of the low-speed flight regime. In addition, the long SERN ramp creates a significant off-axis thrust at off-design, which must be overcome by shifting the vehicle center-of-gravity or by using the vehicle?s control surfaces. This concept manages the engine and freestream flows to alleviate these problems and improve the overall vehicle performance. The Phase I effort will focus on employing 1-D and CFD analyses to prove concept feasibility and to define the injectant pressure and flow requirements. The Phase II program will focus on a preliminary design, including integration issues, design of the secondary valve and injection features, and component testing to verify overall performance gains.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
The industries within this market are large and include Airframers, Aircraft Engine Manufacturers, the DoD, and NASA. Some products that stand to benefit from this innovation are Advanced Military Aircraft, Unmanned Air Vehicles, Hypersonic Vehicles, and LO Vehicles.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
The Fluidic Nozzle benefits NASA?s development of Hypersonic and high speed vehicles by providing a lightweight, low cost aircraft system for achieving high vectoring effectiveness while maintaining optimum thrust performance. As a result, the commercial benefit is three-fold:
- It reduces aircraft weight,
- It improves nozzle performance, and
- It reduces life-cycle cost by providing a low-cost vectoring solution.
| PROPOSAL NUMBER: | 02- A2.03-8672 (For NASA Use Only - Chron: 023327 ) |
| SUBTOPIC TITLE: | Revolutionary Technologies and Components for Propulsion Systems |
| PROPOSAL TITLE: | Front Turbine Engine Concept |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
AP Solutions, Inc
21000 Brookpark Road, MS501-6
Brookpark , OH 44135 - 3191
(440 ) 331 - 7875
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Leo Franciscus
marinerleo@aol.com
21000 Brookpark Road, MS501-6
Brookpark , OH 44135 - 3191
(216 ) 433 - 3646
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
This SBIR will determine the feasibility of an innovative gas turbine engine concept which has a turbine in front of the compressor. This engine concept, referred to as the "Front Turbine Engine Concept" (FTEC), has the potentials for extending the flight speed at which turbomachinery can operate. At hight flight speeds the front turbine extracts sufficient energy from the incoming air thus reducing the air temperature into the compressor and enabling the turbomachinery to operate at high flight speeds (up to Mach 5).
Engine simulations will be conducted on the FTEC to determine the requirements of the components to match the cycle requirements over the complete flight path (takeoff to Mach 5 cruise). The most feasible engine configuraton (one or two spools) will be determined.
Preliminary design will be conducted on the front turbine to identify a prelininary turbine configuration to meet cycle requirements.
Technology requirements for all of the engine components will be assessed.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
The FTEC has potential applications for hypersonic propulsion systems up to Mach 5. The most immediate applications would be in the military arena for manned or unmanned hypersonic aircraft (cruise missile). However, It also has potential in commerical
applications in the high-speed transport arena.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
The FTEC has potential application in the high-speed transport.
| PROPOSAL NUMBER: | 02- A2.03-8862 (For NASA Use Only - Chron: 023137 ) |
| SUBTOPIC TITLE: | Revolutionary Technologies and Components for Propulsion Systems |
| PROPOSAL TITLE: | Novel Titanium-based Lattice Block Structures |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
TITECH INTERNATIONAL, INC.
4000 West Valley Boulevard
Pomona , CA 91769 - 3060
(909 ) 595 - 7455
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Edward Chen
ti_castings@msn.com
4000 West Valley Boulevard
Pomona , CA 91769 - 3060
(909 ) 595 - 7455
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Lattice Block Materials (LBM) are innovative periodic cellular materials that derive their outstanding mechanical performance from a structure of highly ordered internal triangles, rather than the properties of the parent material. To date, they have been successfully cast for many ferrous and non-ferrous metals, but not reactive metals such as titanium and gamma titanium aluminides. As titanium is a critical aerospace material, and gamma is a key candidate for many future aerospace systems, TiTech International, Inc. proposes to use its unique casting production technology to manufacture prototype titanium-based LBM in this SBIR Phase I effort. The goal is to produce titanium and g-TiAl LBM as near-net shape and affordably as possible, while meeting performance and properties requirements for future aerospace systems.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
Essentially, any application and/or industry that need superior strength-to-density within relative affordability while retaining the physical properties of titanium and gamma alloys could use LBM structures. Furthermore, those that require potential replacements for Ni-based superalloys at lower temperatures and for titanium alloys at higher temperatures could consider gamma alloys. Potential commercial applications include aero engine components, automotive engine components, and aircraft and spacecraft structural applications. Other possible uses of LBM include components for furniture, shipboard structures, building structures, automotive vehicle frames, and a potentially limitless number of other possibilities.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
Titanium and gamma alloy LBM can be used as low weight structures for numerous applications for the engine and frame for next generation space launch and hypersonic vehicles. For example, gamma LBM could be considered for engine tiles and sandwich structures for TPS.
Other potential NASA applications include aircraft engine components such as casings and nozzle flaps for next generation aircraft gas turbines.
| PROPOSAL NUMBER: | 02- A2.04-8134 (For NASA Use Only - Chron: 023865 ) |
| SUBTOPIC TITLE: | Airframe Systems Noise Prediction and Reduction |
| PROPOSAL TITLE: | Improving Binaural Simulation of Structural Acoustics |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
AUSIM, INCORPORATED
241 Polaris Avenue
Mountain View , CA 94043 - 4514
(650 ) 322 - 8746
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Agnieszka Jost
jstorckman@ausim3d.com
241 Polaris Avenue
Mountain View , CA 94043 - 4514
(650 ) 322 - 8746
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The proposed innovation is an implementation of an improved, more efficient method for processing individual Head-Related Transfer Function (HRTF) data during the process of rendering audio in a structural acoustic simulated environment. Binaural or 3D-simulated audio has been identified as a useful method for analyzing acoustic and vibro-acoustic data. The highest quality audio simulation requires the processing of HRTF data to create the most accurate 3D audio rendering; however, such processing requires an extensive amount of CPU cycles and is one of the biggest limiting factors of the complexity of the audio simulation. By significantly improving the efficiency of HRTF processing, through such techniques as Singular Value Decomposition (SVD) and Equivalent Source Reduction (ESR), the complexity of the structure being acoustically modeled can be increased. In fact, the capacity of the audio rendering engine can be increased to the point where not only single point audio sources can be modeled, but surface-defined audio sources can be defined, using an array of single-point sources. Such surface-defined audio sources make the audio simulation of vibro-acoustic systems feasible. Such a system will act as an effective tool for assessing the noise characteristics and ?sound quality? of structural acoustic prototypes.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
Commercial applications of this technology would be in the automobile industry, where millions of dollars are spent every year in order to find ways to make new vehicles operate more quietly. The acoustics analysis capabilities that would be enabled with the development of the SVD/ESR-enhanced 3D audio simulation software could be applied widely throughout the automobile business by licensing it to be integrated with existing and broadly used industrial acoustics analysis packages such as the Virtual Acoustics Sciences product line. Such a combined package would offer significantly more capability to engineers designing to optimize acoustics than any other package available today.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
When designers are given the ability to simulate the expected noise generated from an object or structure with a force applied which induces vibration, this noise can be characterized by examining its volume and tonal qualities and determinations can be made regarding how perceptually problematic the projected noise might be in field conditions. This capability will allow more accurate analysis of and experimentation with the acoustics of designs for aircraft and International Space Station structural components.
| PROPOSAL NUMBER: | 02- A2.04-9271 (For NASA Use Only - Chron: 022728 ) |
| SUBTOPIC TITLE: | Airframe Systems Noise Prediction and Reduction |
| PROPOSAL TITLE: | Development of High Frequency Excitation Devices for Noise Reduction |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
INNOVATIVE TECHNOLOGY APPLICATIONS CO.
P.O. Box 6971
Chesterfield , MO 63006 - 6971
(314 ) 576 - 1639
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Alan Cain
ITACabc@aol.com
P.O. Box 6971
Chesterfield , MO 63006 - 6971
(314 ) 576 - 1639
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The noise level of new and existing aircraft need to be reduced to meet the increasingly stringent US and international airport standards. High frequency excitation (wavelengths much shorter that amplified instabilities) of jet flows is a new technology that has the potential to reduce acoustic levels significantly in addition to lowering turbulence levels. In application, forcing is applied at frequencies that are much higher than ones associated with the large-scale, two-dimensional structures associated with the jet, but much lower than the Kolmogorov scale. The development of the jet is substantially altered through two mechanisms. First, the high-frequency forcing increases the turbulent dissipation rate. Second, it reduces the turbulent production. These two mechanisms together lead to a significant decrease in the energy in the large-scale two-dimensional motion and subsequently lowering turbulent and noise levels. One benefit of the control is that the forcing needs only to possess frequencies that are above a certain range. This single frequency requirement encompasses a wide array of potentially suitable devices.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
The engine retrofitting and new engine development market for meeting stage IV requirements for commercial aircraft is in the order of billions of dollars for the next 10 and 20 years. Phase II flight tests will guide the implementation of such systems on commercial jet engines. The experiments will be combined with scaling analysis to develop guidance for optimal system hardware designs that can be patented. These designs are of great values to aircraft and engine manufacturers.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
The proposed technology development could open the door to further understanding and breakthroughs (beyond the proposed SBIR program) by NASA researchers. These breakthroughs in noise reduction may advance the national interest in a quieter air travel industry.
| PROPOSAL NUMBER: | 02- A3.01-8246 (For NASA Use Only - Chron: 023753 ) |
| SUBTOPIC TITLE: | Small Aircraft Transportation System Technologies |
| PROPOSAL TITLE: | SATS Virtual Market Place Facilitating Traffic Flow Management |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Metron Inc
11911 Freedom Drive
Reston , VA 20190 - 2835
(703 ) 234 - 0782
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Chris Brinton
brinton@metsci.com
131 Elden Street
Herndon , VA 20170 - 2835
(703 ) 787 - 8700
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The Small Aircraft Transportation System (SATS) concept envisions a dramatic change in demand on National Airspace System (NAS) resources: a significantly increased number of flights operating as needed on Point-to-Point (PTP) routes with smaller aircraft. In addition to the increased demand on the NAS, the dynamic, ?on-demand?, nature of the SATS concept will present even greater challenges to the country?s Traffic Flow Management (TFM) system. The NAS regulates the flow of aircraft through TFM initiatives. However, the current TFM system does not perform well under uncertain demand patterns. The innovation proposed herein creates a website marketplace for providers and consumers of SATS services. More importantly, our innovation links the information from this SATS website to the Nation?s TFM system. Critical information regarding projected demand can be provided to the TFM system to allow the necessary management of the NAS. Advanced portions of this concept include interactivity between the SATS website and the TFM system to notify consumers of small aircraft transportation services regarding projected delays due to congestion along their requested route of flight at their requested flight time.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
Significant potential exists for commercial applications of the Small Aircraft Transportation System Virtual Marketplace (SATS-VMP) innovation proposed herein. The SATS-VMP web-site leverages the existing technology of the Internet and World Wide Web to create a marketplace for transactions between buyers and sellers of SATS aviation services. The development, hosting and management of the SATS-VMP web-site is an excellent commercial opportunity for this innovation. Metron Aviation has the infrastructure, expertise, staff and financial resources to host the SATS-VMP web-site. This provides commercial opportunities using multiple revenue models associated with Internet websites, including advertising and commission on sales. Metron Aviation has demonstrated the financial ability to develop and successfully market commercial aviation applications by producing the Enhanced Substitution Module (ESM), which is a commercial tool used operationally by numerous airlines to interact with the Traffic Flow Management System of the National Airspace System.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
The Small Aircraft Transportation System (SATS) concept envisions a dramatic change in demand on National Airspace System (NAS) resources: a significantly increased number of flights operating as needed on Point-to-Point (PTP) routes with smaller aircraft. In addition to the increased demand on the NAS, the dynamic, ?on-demand?, nature of the SATS concept will present even greater challenges to the country?s Traffic Flow Management (TFM) system. In order to achieve NASA?s goals for the SATS concept, modern TFM decision support systems will be necessary to enable the SATS concept by handling the increased volume as efficiently as possible. Metron Aviation has led the research and development of numerous systems that interface directly to the TFM system. Many of these systems that improve the efficiency and flexibility of the TFM system have been developed through NASA funding.
| PROPOSAL NUMBER: | 02- A3.01-8431 (For NASA Use Only - Chron: 023568 ) |
| SUBTOPIC TITLE: | Small Aircraft Transportation System Technologies |
| PROPOSAL TITLE: | Gyroplane Development and Demonstration using a Unique Bearingless Rotor System |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Global Technology Connection Inc
2839 Paces Ferry Rd. #1160
Marietta , GA 30339 - 5770
(770 ) 803 - 3001
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Ash Thakker
athakker@globaltechinc.com
2839 Paces Ferry Rd. #1160
Marietta , GA 30339 - 0000
(770 ) 803 - 3001
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
It is well known that an outstanding way to achieve a reduction in landing and takeoff speeds is with a hybrid rotary wing and fixed wing aircraft, such as a gyroplane. However, while there are two U.S. companies pursuing development of gyroplanes, Groen Brothers and Carter Copter, neither has included a rotor system that is easy to fly or can adequately control rotor blade flapping during the critical flight conditions.
A far superior rotor for gyroplanes is the Hanson Elastic Articulated (EA) bearingless rotor that grew out of Lockheed California in the early 1960s for light commercial helicopters. It was later further developed on an autogyro by Mr. Tom Hanson.Georgia Tech ASDL has been working with him in evaluating and analyzing the EA bearingless rotor. The inherent features of the EA Rotor look just as promising today, and can provide the missing link in making gyroplanes true PAVs.
This proposal seeks to fulfill the promise of the gyroplane as a personal air vehicle. In Phase I the scientific, technical, and feasibility of the proposed innovation will be demonstrated. It will include a sound business plan outline for production, with a technical plan providing for compatibility with the emerging National Airspace System architecture and a certification plan. This will be accomplished with the assistance of two other organizations in addition to ASD, LLC. These are the Georgia Tech ASDL and Eagle Aviation Technologies Inc.Based on the demonstrated technical feasibility demonstrated in Phase I, the Phase II program will be used to demonstrate through flight testing the innovative gyroplane concept. This will include testing that can be used in conjunction with the certification and business plan developed in Phase I.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
Many commercial uses of Personal Air Vehicles can be envisioned in the commercial world. Personal transport, medical transport, emergency personnel, security personnel and recreational uses.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
Under the Small Aircraft Transportation System (SATS) Technologies, NASA is seeking Personal Air Vehicle (PAV) advanced concepts that reduce the landing speed for FAR Part 23 aircraft under 6,000 pounds. Advanced concepts for roadable aircraft are also desired. This category must include a sound business plan outline for production, with a technical plan providing for compatibility with the emerging National Airspace System architecture and a certification plan to meet FARS: Part 103 (Ultra-lite vehicle, Part 21.12 (Primary Category Aircraft), Part 23 (Certified Aircraft) or Part 27 (Rotorcraft), or Part 21.191 Advisory Circular AC No: 20-27 series (Experimental Homebuilt Aircraft)
| PROPOSAL NUMBER: | 02- A3.01-9714 (For NASA Use Only - Chron: 022285 ) |
| SUBTOPIC TITLE: | Small Aircraft Transportation System Technologies |
| PROPOSAL TITLE: | Avionics Based Runway Incursion Prevention |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Rannoch Corporation
1800 Diagonal Rd. Suite 430
Alexandria , VA 22314 - 2840
(703 ) 838 - 9780
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Rick Cassell
rcassell@rannoch.com
1800 Diagonal Rd. Suite 430
Alexandria , VA 22314 - 2840
(703 ) 838 - 9780
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
This proposal describes the adaptation of an aircraft based runway incursion advisory and alerting system for general aviation applications. PathProx is a runway incursion advisory and alerting system developed by Rannoch Corporation for air carrier operations. The work proposed under Phase I of this SBIR includes the definition of the developmental needs for adapting the PathProx conflict detection and alerting collision avoidance algorithms to General Aviation (GA) operations. Systems currently being deployed by the FAA are based on a ground infrastructure where runway incursion conflict alerts generated by the system are provided to ATC. Under this operational scenario the pilot is not provided with conflict alert information in the cockpit, leaving the aircraft dependent on the ground ATC infrastructure and human response. A General Aviation runway incursion advisory and alerting system will provide the following safety benefits:
? Reduction in the likelihood of near collisions resulting from runway incursions.
? Improved pilot response in taking evasive actions following incursions.
? Provision of runway incursion alerting at airports not equipped with surface surveillance systems
? Provision of runway incursion alerting at uncontrolled (non-towered) airports
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
The result of the Phase I research proposal here would be the definition of the approach to adapting the Rannoch PathProx runway incursion alerting algorithms to General Aviation operations. During Phase II the development would proceed, which would result in the system being available commercially. The intended market is all General Aviation aircraft that are equipped with the Global Positioning System and a minimal map display.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
The availability of PathProx runway incursion alerting algorithms for General Aviation would enhance the development of Small Aircraft Transportation Systems (SATS). Specifically, it would enhance pilot situational awareness and provide improved aircraft safety in a cost-effective manner.
| PROPOSAL NUMBER: | 02- A3.02-8048 (For NASA Use Only - Chron: 023951 ) |
| SUBTOPIC TITLE: | 21st Century Air-Traffic Management |
| PROPOSAL TITLE: | Optical switches for secure quantum encryption data transmission network |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
SiWave, Inc.
400 E. Live Oak Avenue
Arcadia , CA 91006 - 5619
(626 ) 821 - 0570
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Cathleen Jones
c.jones@siwaveinc.com
400 E. Live Oak Avenue
Arcadia , CA 91006 - 5619
(626 ) 821 - 0570
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The communication network of the Air Traffic Management system requires highly reliable and secure transmission to protect the secrecy and authenticity of the information being transferred. Systems must meet that criteria and be capable of recognizing and withstanding tempering, spying and physical attacks. These requirements cannot be relaxed without diminishing severely the capability of the communication network, and the consequences of loss of security could be disastrous in the extreme. The only undecipherable encryption method is quantum cryptography in which the encryption key is encoded in a quantum property of the carrier, and detecting a quantum property destroys the quantum coherence, altering its value. This concept implementation requires that the transmission network consisting entirely of optical paths in which random polarization is not destroyed or revealed.
SiWave proposes to develop and test a low loss and hardened 32-port all-optical path switch designed for extreme environmental conditions (thermal, vibration, shock) and suitable for quantum encryption applications in this Phase 1 SBIR. During Phase II, SiWave will fabricate and test the optimized switch designed in Phase I. We will demonstrate the performance of the device for quantum encrypted data transmission applications, and propose modifications to extend its capabilities for better performance.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
For a medium port count switch such as the 32x32 switch that we propose in this Phase I SBIR, the best known application is to telecommunications, where optical crossconnects and optical add/drop multiplexers have a large market. The projected market size for optical switches in 2006 is $6B and up to $10B by 2010. Another application is to sensors where the sensor connects to the measurement device by fiber optic cable, and to distributed sensor networks where an array of sensors can be interconnected with each other and with multiple measurement systems. These switches can also be implemented in classical computers that use fiber optics. Finally, the application to secure data networks for handling financial, business and information transaction represents a potential market worth billions of dollars per year.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
The proposed optical switch from SiWave will enable NASA to create an ultra-secure and reliable quantum encryption communication network for its Air Traffic Management system. The proposed switch will be reliable and low loss and be capable of withstanding severe environmental conditions and physical attacks. In addition, such switch would be compact and low power to reduce the back-up power requirements for operation in severe conditions. SiWave's optical switch can also function as the central crossconnect or router in a high bandwidth optical network, routing multiple high data rate optical signals to different destinations. Such application would increase greatly the data communication capability of NASA, allowing scientists to share and to analyze large volume of data.
| PROPOSAL NUMBER: | 02- A3.02-8938 (For NASA Use Only - Chron: 023061 ) |
| SUBTOPIC TITLE: | 21st Century Air-Traffic Management |
| PROPOSAL TITLE: | NAS-Wide Environmental Modeling of Alternative Airspace Concepts |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Metron Inc
11911 Freedom Drive
Reston , VA 20190 - 2835
(703 ) 234 - 0789
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Dr. Terry Thompson
thompson@metsci.com
131 Elden Street
Herndon , VA 20170 - 2835
(703 ) 787 - 8700
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Leveraging extensive experience from major airspace re-design projects, Metron develops a software system to model the NAS-wide environmental consequences of new airspace concepts. The NAS Environmental Impact Model (NASEIM) is innovative in the following ways:
(1) It solves the NAS-wide data-integration problem;
(2) It solves the data-transformation problem for new airspace concepts involving new procedures, aircraft, emissions characteristics, and airspace usage; and
(3) It solves the computational-burden and scenario-comparison problems inherent in large-scale environmental modeling of new airspace concepts.
This enables NASA to determine, early in concept development, which concepts may have either adverse or beneficial effects on the environment, particularly with regard to aircraft noise. This also enables NASA to determine which elements of the new airspace concepts are causing significant environmental impacts, and to modify the concepts to ameliorate the associated environmental impacts. Key features of the Metron approach include NAS-wide modeling of impacts (not just around airports), automated adherence to concept-specific flight profiles, and the ability to model proposed concept-specific changes in operational procedures, aircraft types, and levels of noise emission. This approach also provides integrated comparison of different scenarios, quantification and localization of impacts, and analysis of the causes of differences in impact across scenarios.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
The Phase I and Phase II commercial potential for embedding NASEIM in VAMS is significant in two areas:
? Commercial firms of all types (airlines, aerospace companies, consultants, etc.) need access to a full-scale simulation environment for gauging the operational utility and feasibility of new airspace and ATM concepts; and
? The same firms will need to gauge the environmental impacts of proposed new concepts in order to show both operational and environmental feasibility. Without the latter, no new concepts will be able to survive the environmental assessment process mandated by the National Environmental Protection Act (NEPA).
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
Phases I and II embed NASEIM into VAMS and lead to NASA capabilities critical to airspace modernization
? Enables NASA to determine, early in concept development, which concepts may have either adverse or beneficial effects on the environment, particularly with regard to aircraft noise;
? Enables NASA to compare the environmental and operational benefits within a unified simulation environment that uses the same flight and trajectory data;
? Enables NASA to determine which elements of the new airspace concepts are causing the most significant environmental impacts, and, where appropriate, to modify the concepts to ameliorate the associated environmental impacts.
| PROPOSAL NUMBER: | 02- A3.02-9526 (For NASA Use Only - Chron: 022473 ) |
| SUBTOPIC TITLE: | 21st Century Air-Traffic Management |
| PROPOSAL TITLE: | A Tool for the Evaluation of Proposed TFM Initiatives |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Metron Inc
11911 Freedom Drive
Reston , VA 20190 - 2835
(703 ) 234 - 0753
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Jesse Clayton
clayton@metsci.com
131 Elden Street
Herndon , VA 20170 - 2835
(703 ) 787 - 8700
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Metron Aviation, Inc. builds a tool for Traffic Flow Management (TFM) that integrates existing and emerging technologies in the areas of modeling and operations analysis to enable the evaluation of proposed TFM initiatives (Figure 1). The key innovation of this effort is the integration of the Post Operations Evaluation Tool (POET) and the Future ATC Concepts Evaluation Tool (FACET) in order to accomplish new tasks that neither of these tools can do alone. This development leverages the following key features: FACET?s trajectory prediction and modeling capabilities, and POET?s mature database management system and operations analysis tools. By integrating the tools we provide a system that allows Traffic Flow Managers to investigate future TFM initiatives in real-time. These users then exploit the tool?s analysis capabilities to observe and compare the benefits and impacts of several proposed initiatives prior to implementing them operationally.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
The integrated tool researched in the Phase I and II efforts has FAA and Airline Operations Control (AOC) commercial potential. The tool is designed primarily for Traffic Flow Managers to allow them to model proposed initiatives prior to implementation. These individuals are already familiar with Metron?s operational POET tool. Leveraging POET analysis techniques and displays, we will be providing a TFM Decision Support Tool that is both familiar and well integrated.
Under the CDM program, AOCs use airline-specific versions of strategic planning tools such as FSM to collaborate on control decisions and allocate resources. As the propsed tool leverages models for equitable delay distributions in proposed initiatives, AOCs would benefit from the ability to provide input to such actions. Furthermore, airlines may be particularly interested in monitoring their relative performance using the equity metrics we have proposed. This tool could be marketed to airlines under the CDM program.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
NASA currently uses FACET for, as the name describes, the evaluation of future ATC concepts. Integrating POET and FACET provides NASA with rich analysis and data visualization capabilities for such evaluations. Furthermore, as the number of data sources used by FACET grow, a robust database management system, such as the one proposed in the effort, will be helpful for organizing and managing it. Though not treated explicitly in the proposal, a significant side effect of the proposed effort is that the integration of FACET with the POET database provides quick access to months of historical ETMS data currently archived by Metron.
| PROPOSAL NUMBER: | 02- A3.02-9528 (For NASA Use Only - Chron: 022471 ) |
| SUBTOPIC TITLE: | 21st Century Air-Traffic Management |
| PROPOSAL TITLE: | Efficient Air Traffic Scenario Generation |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Seagull Technology, Inc.
1700 Dell Avenue
Campbell , CA 95008 - 6902
(408 ) 364 - 8200
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Mr. David B. Signor
dsignor@seagull.com
1700 Dell Avenue
Campbell , CA 95008 - 6902
(408 ) 364 - 8200
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
We propose an innovative scenario generation application that significantly decreases the time and cost to develop complex air traffic scenarios. Our application addresses functionality including the user interface, real time displays, data processing (input/output), and compatibility with other similar applications. Unique innovations are focused on flexible user interface and simulation processing options combined with open-architecture, object-oriented software to enable rapid scenario construction and evaluation. These capabilities are lacking in current scenario generation tools and will provide significant savings to users performing analysis on new airspace operational concepts or modifications to the National Airspace System. In addition, such an application will support a number of other applications including military, firefighting, and aviation security planning, operational simulations, evaluations, and training, The proposed initial research analyzes the requirements for such an application and designs and implements an initial prototype.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
Commercial airlines can use this application to support technology investment decision making, new procedure design, operational concept robustness analysis, operations analysis, and training. The FAA may use our product with their Target Generation Facility (TGF) to provide quick-turnaround, human factors analysis of future operations concepts. There is a growing market for aerospace operation simulation worldwide to support; a) communication, navigation, and surveillance, and weather sensing equipment loading and placement analysis, b) UAV and commercial space launch scheduling and design, c) defense force strike planning and procedure development, d) firefighting mission planning and training, and e) aviation security threat analysis.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
Within NASA, our scenario generation application can be used to advance research efforts including human performance evaluation in advanced airspace concepts, advanced airspace system concept evaluation and visualization, and the study of revolutionary vehicle concept airspace integration issues. Our application is primarily aimed at providing a scenario generation and analysis tool for investigating many advanced airspace concept issues including conflict detection and resolution, airspace and airport design, en route replanning and traffic flow management decisionmaking, and environmental impact. In general, NASA simulation capabilities exist for these areas but the capability for efficient generation of new scenarios is lacking.
| PROPOSAL NUMBER: | 02- A3.02-9684 (For NASA Use Only - Chron: 022315 ) |
| SUBTOPIC TITLE: | 21st Century Air-Traffic Management |
| PROPOSAL TITLE: | Virtual National Airspace with Human Pilots and Controllers |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
AerospaceComputing, Inc.
465 Fairchild Drive, Ste. 224
Mountain View , CA 94043 - 2251
(650 ) 988 - 0388
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Hiro Kumagai
hkumagai@aerospacecomputing.com
465 Fairchild Drive, Ste. 224
Mountain View , CA 94043 - 2251
(650 ) 988 - 0388
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The behavior of the National Airspace System is the result of the real-time decisions of individual pilots and air traffic controllers. Successes or failures of the system are often due to how they react to the rapidly changing situation and information load that confronts them. A Virtual National Airspace System is proposed that utilizes live pilots and controllers. To maintain their instrument flight skills, pilots routinely use Personal Computer Aviation Training Devices (PCATD?s) that are owned and operated by flight schools, Fixed-Base Operators (FBO?s), and other private parties. Each pilot represents a potential participant in NASA air traffic simulation studies. The proposed Virtual National Airspace System incorporates the state vectors of multiple aircraft and the problems of shared frequency radio communication. Key architectural concerns for the simulation include: state vector and protocol design, simulation server and network operating in real-time with pilots and controllers, and multi-frequency voice communication. A user / pilot database can track pilots for various ratings and, thereby, provide air traffic studies with pilots screened for particular purposes, including maintaining the overall quality of the simulation.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
PCATD?s operated by flight schools and FBO?s can have more realistic simulation since the system simulates surrounding traffic and the shared frequency radio communication with air traffic controllers and other pilots. Large flight simulation facilities other than those used by NASA can benefit by ?purchasing? the miscellaneous traffic and air traffic controller services. The FAA and its contractors can use the system to train air traffic controllers in an environment with rated pilots. The simulation server can be commercially operated in a fashion similar to an Internet Service Provider.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
Once the system development is complete, it can provide realistic air traffic to flight simulations and air traffic studies on demand, at any time, at no charge. This makes NASA?s airspace simulations more complete, with miscellaneous surrounding traffic, without increasing the cost of simulation sessions. Investigations into the impact of air traffic management improvements can be done in a setting that incorporates human participants with their changing workloads. The system can also be integrated with more automated approaches so that narrower aspects of air traffic management can be studied.
| PROPOSAL NUMBER: | 02- A3.02-9734 (For NASA Use Only - Chron: 022265 ) |
| SUBTOPIC TITLE: | 21st Century Air-Traffic Management |
| PROPOSAL TITLE: | Integration of Unmanned Air Vehicles with the National Airspace System |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Applied Systems Intelligence, Inc.
11660 Alpharetta Highway
Roswell , GA 30076 - 4916
(770 ) 518 - 4228
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Wendy Elmore
welmore@asinc.com
11660 Alpharetta Highway
Roswell , GA 30076 - 4916
(770 ) 518 - 4228
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
This research refines existing associate decision aiding technology and applies it to a new, larger air traffic management (ATM) domain. We have shown in other NASA projects how our associate systems can provide Distributed Air-Ground (DAG) decision aiding to pilots, air traffic controllers, and airline dispatchers within the ATM system of a UAV free NAS. Our existing C2IT software provides decision aiding to UAV operators in combat environments in such a manner that the UAV looks much like a normal aircraft to external observers. We propose to refine our existing UAV decision aiding system so that UAV operators can collaborate effectively with the actors of the ATM system of the NAS. In particular, we shall identify the new ATM message signals and data objects required, synthesize new collaboration diagrams, and refine the finite state machine (FSM) of a UAV associate system. The associate will further the UAV?s similarities to a piloted aircraft in order to accommodate the existing decision support systems of air traffic controllers and pilots.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
Future UAV systems will be able to operate on a routine basis with other aircraft in the NAS. This capability will allow them to be used everyday without special clearances or airspace being set aside for their operation. This will make UAV?s commercially viable for missions such as atmospheric radiation measurement, pipeline monitoring, homeland security, search & rescue, intelligence gathering, surveillance, fire fighting, agricultural and environmental monitoring, aerial photography and mapping, law enforcement, and telecommunication relay to name a few.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
The results of this project will enable UAVs to smoothly interact with the NAS ATM system when they need to. They will enable the ATM system to maintain a high level of performance even during UAV operations. NASA will be able to take advantage of this capability during their UAV research and testing operations, which will make them far easier to execute than UAV operations today.
| PROPOSAL NUMBER: | 02- A4.01-7626 (For NASA Use Only - Chron: 024373 ) |
| SUBTOPIC TITLE: | Space Transportation Architecture Definition |
| PROPOSAL TITLE: | Advanced Crew Escape System Simulation Tool for Future Launch Vehicles |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
CFD Research Corp
215 Wynn Dr.
Huntsville , AL 35805 - 1944
(256 ) 726 - 4800
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Peter Liever
jls@cfdrc.com
215 Wynn Dr.
Huntsville , AL 35805 - 1944
(256 ) 726 - 4800
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
A computational technique that utilizes an innovative tightly coupled combination of CFD, 6-DoF and blast wave simulation methods is proposed for the analysis of crew escape systems for future launch vehicles. An existing high-fidelity simulation program, well validated for military crew escape systems, will be leveraged to meet the challenges of simulating escape system operation for launch abort across the flight envelope, from pre-launch to the hypersonic regime.
In Phase I, computationally efficient blast wave effect models will be integrated to simulate launch vehicle propellant explosion effects. Analytical models and available explosion test data will be combined into reduced mechanism blast wave models simulating the explosion event. The value of the improved coupled simulation capability will be demonstrated through sample computations, with and without blast wave effects, for individual and simultaneous crew member ejection, and for the escape separation of a crew vehicle.
The newly developed physical and dynamic simulation models will be further refined and validated in Phase II. In particular, the speed and accuracy of staging and escape simulations using the new blast wave models will be improved. Recent CFDRC experience in complex urban blast wave flow field modeling will be leveraged to implement a solution adaptive overset Chimera grid approach.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
Additional application areas include analysis of store release and missile launch from future hypersonic transcontinental military aircraft and crew escape systems for such vehicles, and multi-stage kinetic projectile boost and staging. Other potential new markets for the coupled CFD/6-DoF/blast wave modeling include analysis of missile proximity warhead effectiveness, explosive warhead application against chemical/biological agents, and armored vehicle protection designed to deflect incoming warheads through the initiation of blast waves in the warhead path.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
The proposed simulation technology will find direct and immediate applications with NASA and contractors in the development of NASA's Second and Third Generation Reusable Launch Vehicles. The software provides accurate and cost effective escape system simulation technology not available to NASA today. It provides significant capability advances in crucial areas of launch vehicle development: 1) definition and screening of escape strategies in the concept phase, 2) verification of escape system functionality across the flight envelope, and 3) blast wave impact on escape system functionality and safety margin. It offers risk mitigation of crew safety and survivability not available from ground or flight tests. The technology is cross-cutting for all potential architectures, and for all crew escape systems ranging from individual ejection seats to crew vehicles.
| PROPOSAL NUMBER: | 02- A4.01-8696 (For NASA Use Only - Chron: 023303 ) |
| SUBTOPIC TITLE: | Space Transportation Architecture Definition |
| PROPOSAL TITLE: | MicroSAFE (Stress Analysis and Forecasted Endurance) |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Invocon, Inc.
19221 I-45 South, Suite 530
Conroe , TX 77385 - 8703
(281 ) 292 - 9903
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Joe Hermann
jhermann@invocon.com
19221 I-45 South, Suite 530
Conroe , TX 77385 - 8703
(281 ) 292 - 9903
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The NASA SLI is to determine design approaches to a new space launch vehicle that can reduce the costs and minimize risks. Significant amounts of the cost associated with operation of the current Shuttle involves manual inspections. The challenge is to determine a means of more cost effective inspections. Proposed herein is a means for reducing the need for manual inspections while improving the quality of ?flight readiness status? information. The proposed approach also insures that this reduction in operations costs could be achieved for a minimum cost. A miniature device is proposed that can measure and compile the exact stress life in mechanical parts on a constant basis and report this information to a gathering facility via wireless radio communications. The device would be so small that one or more of them could be included on every critical life limited part designed for a particular application. The inclusion of the device on the critical part would make the part a ?smart part? that would continually measure its own health relative to stress life and would report that information when commanded. Thus maintenance personnel would only need to watch for data processing alarms to determine the replacement time.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
Commercial air service organizations all deal with life limited parts. Parts must be replaced within a specific number of operational hours. The number of hours are estimates by the builder and the controlling government safety authority. A technique that could total the exact number of stress cycles and their magnitude could allow life limited parts to be changed out only when service life has been reached. Example: PA 38 Piper aircraft. The wings have a service life of 11,000 hours. This assumes that the plane was used to the limits of the Utility Category (more stressful than Normal Category). These aircraft are being scrapped every year due to this limitation in spite of the fact that many have not even come close to their service life. Commercial operations can save money precise measurements and lives could be saved as exemplified by the recent Slurry Tanker crashes if total service life was easily available.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
This device is applicable to both retrofit and new system NASA applications. Specifically, IVC has raw data collection hardware flying on the Shuttle for purposes of measuring the exact strain loads imparted on the engine steering arms. IVC has pushed size and cost reduction of this device to the limits of conventional components. In this form, the device has a large potential market and can contribute to the optimization of replacement schedules for many ?life limited? parts. This effort has resulted in a device that measures 2.5 cm by 2.5 cm by 1.5 cm. The proposed device (measuring 5 mm by 5 mm by 2 mm ) would bond to the part or structure. Properly packaged, the device could be imbedded into composite construction to detect changes in the statistical stress life that would signal structural failure.
| PROPOSAL NUMBER: | 02- A4.01-8700 (For NASA Use Only - Chron: 023299 ) |
| SUBTOPIC TITLE: | Space Transportation Architecture Definition |
| PROPOSAL TITLE: | A New Methodology for Calculating Launch Vehicle Ascent Loads |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Dynamic Concepts Inc
P.O. Box 97
Madison , AL 35758 - 0097
(256 ) 461 - 8006
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Dr. Thomas G. Howsman
thowsman@dynamic-concepts.com
P.O. Box 97
Madison , AL 35758 - 0097
(256 ) 461 - 8006
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Determining an effective structural design of a launch vehicle is critical to both mission success and crew safety. In order to evaluate the adequacy of a launch vehicle?s structural design, the ascent loads experienced by the vehicle must be determined. Computation of the ascent loads is a complex, multi-disciplined undertaking that involves an assessment of both natural and induced environments. Currently, ascent loads are calculated primarily using a somewhat restrictive constant Mach number squatcheloid approach. A method to compute the ascent loads of a launch vehicle through a direct coupling of the six-degree-of-freedom trajectory simulation with a time correlated flexible body simulation of the structure is proposed. Load dispersions due to the statistical uncertainties associated with both environmental effects (e.g., winds) as well as vehicle uncertainties (e.g., thrust misalignment) may be assessed directly from a set of Monte Carlo runs of the synchronized trajectory and loads simulations. The Phase I research is directed at developing the necessary algorithms and providing a proof-of-concept simulation. During Phase II, a complete modular computational framework will be developed that will integrate the 6DOF trajectory tools with the loads prediction software, allowing for a more accurate and unified loads analysis of the vehicle.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
The most obvious non-NASA application for this technology is the commercial satellite launch industry. Proposed commercial reusable launch vehicles have the potential to dramatically lower payload-to-orbit costs. This proposed analytical process could enhance such vehicles by producing more optimal structural designs and reducing the potential for launch failure. The proposed technology could also be adapted to augment existing simulations of various mobile military assets such as a planes, tanks, or guided missiles, thus increasing the fidelity of the computed loads for these systems as well.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
If the proposed computational approach for ascent loads is fully developed, NASA will gain an important tool for the accurate prediction of launch vehicle loads. Clearly, NASA?s 2nd Generation RLV design must be structurally efficient in order to meet program goals. This will require accurate knowledge of vehicle loads in order to eliminate excess conservatism without jeopardizing safety. Similarly, if the Shuttle is to continue flying for many years into the future, more precise knowledge of the dynamic loads which occur during ascent may be required for future fracture and reliability analyses of the vehicle.
| PROPOSAL NUMBER: | 02- A4.01-8734 (For NASA Use Only - Chron: 023265 ) |
| SUBTOPIC TITLE: | Space Transportation Architecture Definition |
| PROPOSAL TITLE: | Dynamic Transfer Function Measurements for Cavitating Pumps |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Concepts ETI, Inc.
217 Billings Farm Road
White River Jct , VT 05001 - 9486
(802 ) 296 - 2321
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Daniel O. Baun
dob@conceptsnrec.com
217 Billings Farm Road
White River Jct , VT 05001 - 9486
(802 ) 296 - 2321
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
There are no analytical tools or experimental facilities in the world today that can quantify the dynamic transfer function for a cavitating inducer. The goal of this research is to fill this void. An innovative experimental technique is proposed where by a cavitating inducer's dynamic transfer function is quantified by mapping the flow and pressure fluctuations at the inducer exit as a function of harmonic perturbations at the inlet. A cavitating inducer can be a source of instability in a rocket engine. Due to cavitation dynamics, inlet flow perturbations maybe amplified by the inducer resulting in very large flow and pressure fluctuations in the fuel system. The resulting dynamic couplings can lead to vehicle instability (POGO) as well as generate intense dynamic loadings on the turbopump. The feasibility of implementing the technique on the Concepts NREC water flow test rig will be demonstrated in Phase I of the project. Implementation of the technique and inducer transfer function identification will occur in Phase II. The proposed dynamic transfer function characterization methodology is applicable to any high energy density turbomachine subject to impeller induced flow instabilities, such as boiler feed pumps or re-injection pumps and compressors.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
High energy density turbomachines such as gas re-injection pumps and compressors, and high-energy industrial pumps, are a source of instability. Accurate dynamic characterizations of these machines are required to ensure safe and reliable operation of the systems into which they are installed. In addition to understanding the dynamic attributes of these machines under cavitation or stalled conditions, the dynamic transfer function under normal operating conditions are also required. The methodology proposed to measure the dynamic transfer function of a cavitating inducer is transferable. The proposer is well-positioned to commercialize the technology to both aerospace and industrial customers.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
As mission requirements lead to higher power density turbopumps with lower specific weights and higher suction specific speed requirements the potential for flow-induced dynamic instabilities, both at the turbopump level and at the system level, increase. Rocket vehicle dynamic models require an accurate dynamic characterization for the inducer. The proposed experimentally measured dynamic transfer functions will provide accurate and reliable pump dynamic attributes which are necessary to assess the probability of destructive flow instabilities, such as cavitation surge and rotating cavitation, and their effect on engine component or integrated vehicle system instability.
| PROPOSAL NUMBER: | 02- A4.02-7464 (For NASA Use Only - Chron: 024535 ) |
| SUBTOPIC TITLE: | Space Structures, Materials, and Manufacturing |
| PROPOSAL TITLE: | Aluminum/Alumina Based Metal Matrix Composites from Nanometer Powder |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Technanogy, LLC
2146 Michelson Dr., Suite B
Irvine , CA 92612 - 1304
(949 ) 261 - 1420
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Debbie Shelton
dshelton@technanogy.net
2146 Michelson Dr., Suite B
Irvine , CA 92612 - 1304
(949 ) 261 - 1420
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Technanogy Air and Space and Rockwell Scientific propose a novel approach to manufacturing a low density high-performance aluminum based metal matrix composite (MMC) by consolidating nano-aluminum powder. Depending on the application, Technanogy?s nano-aluminum powder can be tailor made in terms of size and oxide shell thickness. For the current project, powders having ceramic weight contents of 15, 25, 35, 45, 55 and 65 percent will be provided to Rockwell Scientific for consolidation. During the consolidation process Rockwell will determine the ideal processing parameters for each ceramic concentration so that the process can be further developed to produce large quantities of bulk nanocrystalline Al/Al2O3 metal matrix composite material. It is expected that the consolidated Al/Al2O3 composite will have nearly theoretical density and a submicron- sized distribution of ceramic and metallic grains, and that this ultra-fine microstructure will produce a high specific strength and specific stiffness at all temperatures and excellent compatibility in hydrogen environments. The specific goal is to produce aluminum based MMCs with specific strength superior to 414MPa at 260?C. Improvement in the high temperature properties of aluminum MMCs will allow their use in many applications where they have not been used previously in NASA or commercial applications.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
Technanogy Air & Space and Rockwell Scientific are collaborating to produce Al/Al2O3 composite materials by combining Rockwell?s consolidation expertise with Technanogy?s nanoparticulate composite. The projected improvements in high temperature strength and lower CTE would impact the following NASA applications: ducting and duct flanges for carrying warm gases, wave guides, struts for airplanes or satellite structures, airplane fins, and thermal management supports.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
Technanogy Air & Space and Rockwell Scientific are collaborating to produce Al/Al2O3 composite materials by combining Rockwell?s consolidation expertise with Technanogy?s nanoparticulate composite. The projected improvements in high temperature strength and lower CTE would impact the following commercial applications: connecting rods in combustion engines, cylinder liners, engine blocks, driveshafts, alloy wheels, baseball bats, golf clubs, and bicycle frames.
| PROPOSAL NUMBER: | 02- A4.02-7982 (For NASA Use Only - Chron: 024017 ) |
| SUBTOPIC TITLE: | Space Structures, Materials, and Manufacturing |
| PROPOSAL TITLE: | Production of Single-Walled Carbon Nanotubes by Catalytic Disproportionation ... |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Southwest Nanotechnologies, Inc.
2516 Warwick Drive
Oklahoma City , OK 73116 - 4324
(405 ) 325 - 4940
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Leandro Balzano
lbalzano@ou.edu
2516 Warwick Drive
Oklahoma City , OK 73116 - 4324
(405 ) 206 - 5979
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The unmatched properties of single-wall nanotubes make them a unique product that will represent a billion-dollar market in applications that range from space to consumer products. At the University of Oklahoma, the catalytic production of SWNT has been optimized in a novel process (CoMoCAT) based on a specific catalyst formulation that yields SWNT with high selectivity. A fluidized bed reactor is particularly suitable to achieve optimal synthesis conditions and make the process continuous. A good-quality SWNT product has been consistently obtained. The present proposal will focus on the gradual improvement of the current CoMoCAT technology to make it able to operate in a continuous, larger-scale mode that will result in low SWNT costs. The anticipated results of the phase I include the development and testing of the continuous, large-scale reactor and the scale up of the purification process. Phase II is visualized as a direct application of the optimized process at an even larger scale that will incorporate the participation of strategic partners for the development of SWNT-based materials. The carbon nanotube is 100x stronger than steel, yet 1/5th the weight. SouthWest NanoTechnologies will commercialize nanotubes for their structural properties, meeting a direct need for NASA, and providing the next generation of lightweight composites for industries worldwide.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
A4.02 - Space Structures, Materials, & Mfg.
The estimated market value of carbon nanotubes is $400MM USD in FY2004. SouthWest NanoTechnologies, Inc. will focus on the near-term structural ?killer applications? in Single-Walled Carbon Nanotubes. Compiled from a variety of sources, these include composite materials, electromagnetic shielding material, and thermal materials. The aforementioned products will create the demand of the future, and result in demonstrable near-term revenue. This focus is decidedly unique, as the company has a formal relationship with a Fortune 100 company, and is currently negotiating a joint development agreement.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
With all due respect to the ongoing Contour program, we tread cautiously along what appears to be a crucial need for high-end structural technologies. As of 8/20/02, the mission is still active, though early reports indicate the spacecraft may have broken in two. NASA spokesman Don Savage was quoted in a CNN story, ?The failures hurt but they do happen.? Thus, an approval of this proposal demonstrate tangible and decisive steps toward correcting the problem at its source. Based on NASA's specific needs, this material could be formed into ultra lightweight discontinuous fiber composites for several targeted aerospace applications.
| PROPOSAL NUMBER: | 02- A4.02-8771 (For NASA Use Only - Chron: 023228 ) |
| SUBTOPIC TITLE: | Space Structures, Materials, and Manufacturing |
| PROPOSAL TITLE: | Ultrasonic Tape Laminated Cryogenic Tank Structures Processed Outside Autoclave |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Foster-Miller Inc
350 Second Ave
Waltham , MA 02154 - 1196
(781 ) 622 - 5502
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
John Player
jplayer@foster-miller.com
350 Second Ave
Waltham , MA 02154 - 1196
(781 ) 684 - 4242
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Recent designs for large aerospace structures especially cryotank structures for the second and third Generation Reusable Launch Vehicle (RLV) are driving the aerospace community to develop out-of-autoclave composite manufacturing processes to save enormous autoclave capital equipment costs. In this proposed Phase I effort, Foster-Miller will demonstrate that autoclave equivalent mechanical properties can be obtained using its Ultrasonic Tape Lamination technology coupled with its novel out-of-autoclave processing approach, solid state curing. Preliminary data from work with Northrop Grumman on the second generation RLV cryotank manufacturing program already shows that this process is feasible by achieving 90 percent of the autoclave processed properties.
Foster-Miller will utilize in house analytical equipment to perform the resin characterization essential for refining the UTL/solid state curing approach. Critical mechanical property testing will be performed to demonstrate autoclave property equity in the Phase I. Northrop Grumman will supply Foster-Miller with key logistical and tooling information to assess the cost saving potential of the refined UTL/solid state cure approach. The Air Force has shown significant interest in this technology and will be kept informed as UTL/solid state curing is developed in Phases I and II. (P-020642)
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
Foster-Miller?s Ultrasonic Tape Lamination (UTL) technology coupled with its novel out-of-autoclave processing approach, solid state curing has the potential to dramatically change the cost structure for fabricating a wide range of commercial aircraft composite components. Many of the large nacelle and flight control structures on Boeing and Airbus aircraft require multiple autoclave cycles for their manufacture, incurring substantial costs in cycle time and associated labor. Foster-Miller?s UTL/solid state bag-less cure would eliminate the need for the autoclave and perhaps more importantly, would eliminate the labor costs associated with vacuum bagging, usually performed several times during a component?s fabrication. UTL/solid state bag-less curing can also be applied to the manufacture of a wide range of other large composite structures that need high quality at low cost such as thick tubulars for offshore oil drilling, military fighter structures (JSF, F-18E/F, and V22) and military space plane structures (Air Force SOV cryotanks).
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
Foster-Miller?s UTL/solid state bag-less cure can be utilized during the manufacture of many of NASA?s large aerospace structures. The most prominent are the cryogenic fuel tanks for the next generations of reusable launch vehicle. Although the cryotanks provide the largest immediate cost savings primarily due to the elimination of autoclave capital investment, the opportunity to save manufacturing costs with this novel out-of-autoclave processing approach exists for other large space vehicle structures such as RLV wing skins, payload bay and landing gear doors. Other launch vehicles such as Delta IV rocket and its composite payload fairings also provide an excellent cost saving opportunity for the UTL/solid state bag-less technology.
| PROPOSAL NUMBER: | 02- A4.02-8845 (For NASA Use Only - Chron: 023154 ) |
| SUBTOPIC TITLE: | Space Structures, Materials, and Manufacturing |
| PROPOSAL TITLE: | Innovative Tungsten Alloys for Advanced Propulsion Systems |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Plasma Processes, Inc.
4914 Moores Mill Rd
Huntsville , AL 35811 - 1558
(256 ) 851 - 7653
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Robert Hickman
robert@plasmapros.com
4914 Moores Mill Rd
Huntsville , AL 35811 - 1558
(256 ) 851 - 7653
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Non-conventional technologies are needed to revolutionize space propulsion. Development of materials with improved properties is essential to increase performance and reduce cost. Advancements are needed for components in high powered electrical, beamed energy, and nuclear propulsion systems. Innovative Vacuum Plasma Spray (VPS) processes for fabricating net shape, tungsten-rhenium-hafnium carbide alloy components are proposed. Tungsten is being used for its high melting temperature and chemical stability. However, conventional tungsten materials have to be forged to get adequate properties. Forging tungsten into complex shapes is difficult and has limited its application. Tungsten alloys yield improved properties as compared to conventional unalloyed tungsten. It is well documented that small additions of rhenium improve the ductility of tungsten without significantly decreasing the melting point. Also, dispersion hardening by additions of HfC increases the high temperature strength by pinning grain boundaries. In Phase I, W-Re-HfC powders and process parameters will be developed to fabricate samples for characterization and hoop tensile testing. After optimization, nozzles will be fabricated and hot fire tested at ATK-Thiokol. Development of these materials will allow the production of components with unique properties and reduce the size, weight, and cost of propulsion systems.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
The results of the Phase I effort will clearly demonstrate the ability to fabricate improved tungsten alloy components. Development of these advanced materials will produce robust components with unique properties and reduce the size, weight, and cost. Potential clients for these components are NASA, DOD, Thiokol, and Aerojet. Letters from Thiokol and Aerojet for Plasma Processes ongoing R&D efforts are attached to this proposal. PPI will develop and transfer the SBIR technology to other commercial applications such as: Ballistic and tactical missiles, gun barrel liners, Arc-jet thrusters, Heat exchangers, Welding electrodes, Plasma facing components for nuclear reactors, gas turbines, automobile engines, incinerators, thermal control coatings, oxidation protective coatings, coatings for composite parts and structures, thermal barrier coatings, structural jackets on tubular combustors and nozzles, crucibles, tubes, valves, and storage vessels.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
NASA applications that net shape tungsten alloy components can be used for are high powered electrical, beamed energy, and nuclear propulsion systems. Tungsten alloys can also be used for microgravity crucibles, heat pipes, fuel cells, and components for solar themal propulsion, liquid/solid rocket motors, and other high temperature applications.
| PROPOSAL NUMBER: | 02- A5.01-7863 (For NASA Use Only - Chron: 024136 ) |
| SUBTOPIC TITLE: | Lightweight Engine Components |
| PROPOSAL TITLE: | Multilayer Fiber Interfaces for Improved Environmental Resistance and Slip |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Ultramet
12173 Montague St
Pacoima , CA 91331 - 2210
(818 ) 899 - 0236
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Jason R. Babcock, Ph.D.
jason.babcock@ultramet.com
12173 Montague St
Pacoima , CA 91331 - 2210
(818 ) 899 - 0236
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Application of ceramic matrix composites (CMC) reinforced with carbon fibers can potentially enhance the efficiency and performance, reduce the weight, improve the durability, and lower the cost of rocket engine combustion devices and turbomachinery components used in high temperature, high-stress environments. Meeting these objectives requires improvements in fiber-reinforced CMC materials and fabrication processes, particularly improved fiber/matrix interfaces, interface deposition processes, and oxidation protection. Although carbon fibers are most desirable as CMC reinforcements, their low oxidation resistance has prevented their use in high temperature oxidizing environments. In previous work, Ultramet developed a unique and innovative process, ultraviolet-enhanced chemical vapor deposition (UVCVD), which allows deposition of dense, strain-tolerant oxides at room temperature, thus avoiding heat-induced material degradation and providing excellent material performance, including enhanced oxidation protection. However, identifying a single phase that best performs the two key functions of the interface coating, oxidation protection and interface slip, simultaneously has thus far proven elusive. In this project, the UVCVD process will be developed specifically for deposition of multilayered interface coatings in which separate components will perform these two functions, resulting in optimum composite performance.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
The composite materials to be developed in this project using innovative interfaces and novel UVCVD processing will have broad commercial applicability to a range of products, including fuel-rich turbomachinery components, aircraft engine components, recuperators, ducts, and other hot gas path components, process industry components requiring high temperature capability and corrosive environment resistance (e.g. hot gas and liquid handling equipment), furnace structures, and high temperature filter elements.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
Ceramic matrix composite materials are projected to significantly increase safety and reduce costs simultaneously, while decreasing weight for space transportation propulsion. Innovative material and process technology advancements are required to enable long life, reliable, and environmentally durable materials. Specific areas of technology development that are of interest include low-cost, rapid, scalable, repeatable CMC fabrication process development for multiple space transportation propulsion applications.
| PROPOSAL NUMBER: | 02- A5.01-8602 (For NASA Use Only - Chron: 023397 ) |
| SUBTOPIC TITLE: | Lightweight Engine Components |
| PROPOSAL TITLE: | Self Healing, High Temperature Cpmposite Components |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Ceracom Inc
200 Turnpike Road
Chelmsford , MA 01824 - 1234
(978 ) 250 - 4200
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Mr. Kirk Newton
knewton@ceracominc.com
200 Turnpike Road
Chelmsford , MA 01824 - 1234
(978 ) 250 - 4200
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Ceracom will demonstrate innovative self healing carbon fiber reinforced silicon carbide (SiC) matrix ceramic matrix composite (CMC) materials that will enable the deployment of oxidation and damage resistant components for hot sections of oxygen/fuel powered propulsion systems and hypersonic vehicle surfaces. Ceracom?s unique materials system design approach to oxidation protection and self healing behavior focuses on the entire system or component and not just a surface coating. The system level approach includes innovative new materials and micro-structures for the fiber-matrix interface, new mixed oxide glassy phase matrix modifiers that impart self healing behavior to the basic SiC based matrix and coating or impregnation materials that seal the composite from oxygen ingress at temperatures over 4000oF. Ceracom?s new self healing CMC materials include alloyed and combined particle inclusions in the matrix that form an array of mixed oxide glassy phases when exposed to oxygen. This glassy phase has a controlled viscosity for a wide range of temperatures and seals micro-cracks to prevent oxygen ingress. The combination of all these approaches enables the use of carbon fiber CMC?s in many long life applications that will be needed to meet program goals for NASA?s Gen 2 and Gen 3 programs.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
The ability to use carbon fiber reinforced ceramic matrix composites in oxidizing atmospheres at elevated temperatures is the limiting factor in the wide spread commercial use of CMC?s in many commercial applications. The low cost of carbon fiber is needed to enable the insertion of CMC into commercial applications in aviation and land based gas turbine engines, burner liners and kiln hardware for commercial furnaces and applications in metals processing. The ability to suppress oxidation without the use of expensive SiC fibers will open this market to CMC?s
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
The ability to use carbon fiber reinforced ceramic matrix composites in oxidizing atmospheres at elevated temperatures is the limiting factor in the wide spread commercial use of CMC?s in many aerospace applications. If successfully developed this technology would find immediate use in high speed applications,including turbine combined cycle, rocket based combined cycle and rocket propulsion. In addition the self healing CMCs would be used as hot structures and large acreage TPS on reusable launch and space vehicles.
| PROPOSAL NUMBER: | 02- A5.01-9041 (For NASA Use Only - Chron: 022958 ) |
| SUBTOPIC TITLE: | Lightweight Engine Components |
| PROPOSAL TITLE: | Low-Cost, Polymer-Derived Interface Coatings for CMC Applications |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Starfire Systems Inc
877 25th St
Watervliet , NY 12189 - 1903
(518 ) 276 - 2112
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Lynn Tarnowski
tarnowskil@starfiresystems.com
877 25th St
Watervliet , NY 12189 - 1903
(518 ) 899 - 9336
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Starfire systems proposes a pre-ceramic polymer based interface coating for CMC applications. Starfire Systems specializes in the development and manufacture of SiC and SiOC based pre-ceramic polymer chemistry and will leverage its? developments related to ceramic forming polymers used for coating oxide filter structures with thin SiC coatings and apply these coatings to ceramic fibers for applications in CMC?s. Typically the fiber and the interface coatings account for over 70% of the cost of a high temperature CMC composites. Through the use of this simple dip coating process, the cost of the interface coating will be reduced by an order of magnitude and this may also enable the use of lower cost ceramic fibers as a second level of cost reduction. Cost advantages aside, the pre-ceramic polymer coating will also result in enhanced CMC performance and oxidation stability. The liquid pre-ceramic polymer based coating method is suitable for coating fibers, fabrics, or performs. The interface coating thickness can be varied from 5 microns thick down to sub-micron thicknesses. Preliminary work has demonstrated coatings that are smooth and continuous. This research will be aimed at optimizing the coatings for oxidation protection and composite toughening on ceramic fibers.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
Low cost, oxidation resistant fiber interface coatings will enable ceramic composites to be utilized in a wide range of applications where they are currently considered to costly, such as radiant burners, hot exhaust sections on aircraft and motor vehicles, power generation equipment such as gas turbines and even diesel engines (as the exhaust filter, in exhaust system components and the engine itself). The polymer-derived fiber coating process will also permit any of the composite fabricators to coat their own performs.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
Key NASA applications are expected to include virtually all CMC applications such as thermal protection systems, turbo-pumps, cryotanks, nozzles, thrusters, and even space structures that would take advantage of the light weight and low thermal expansion properties of CMCs.
| PROPOSAL NUMBER: | 02- A5.02-7934 (For NASA Use Only - Chron: 024065 ) |
| SUBTOPIC TITLE: | Reusable Launch Vehicle Airframe Technologies |
| PROPOSAL TITLE: | FGM HfC/Sic Composites for RlV Leading Edge Applications |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
MER Corp
7960 S. Kolb Rd.
Tucson , AZ 85706 - 9237
(520 ) 574 - 1980
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Dr. W. Kowbel
mercorp@mercorp.com
7960 S. Kolb Rd.
Tucson , AZ 85706 - 9237
(520 ) 574 - 1980
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Future RLV applications require high temperature, durable refractory composites capable of up to 4000?aF temperature use with multiple missions. Currently used technology for X-43A is highly limited in this regard. Thus a novel approach is proposed to alleviate this problem. It is based upon FGM porosity and FGM SiC/HfC coatings to address the thermal stress problem.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
military space plane and hypersonic missiles
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
future RLV
| PROPOSAL NUMBER: | 02- A5.02-8092 (For NASA Use Only - Chron: 023907 ) |
| SUBTOPIC TITLE: | Reusable Launch Vehicle Airframe Technologies |
| PROPOSAL TITLE: | High Emissivity Protective Cerablak Coatings for Metallic TPS |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Applied Thin Films Inc
1801 Maple Ave., Suite 5316
Evanston , IL 60201 - 3135
(847 ) 431 - 8026
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Kimberly Steiner
ksteiner@atfinet.com
1801 Maple Ave., Suite 5316
Evanston , IL 60201 - 3135
(847 ) 467 - 5235
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The proposed effort relates to the use of Cerablak?, an amorphous-based black oxide material, as a coating for protection of metallic thermal protection systems (TPS) to be used in reusable launch vehicles (RLVs). This material shows potential to be a coating that meets all of NASA?s requirements for TPS protection in a single material system. The basic technical requirements for a coating to protect metal TPS are a) total hemispherical emittance >0.8 to maximize re-radiation b) low catalytic efficiency (<0.3) for recombination of atomic N and O species, and c) protection against oxidation of the underlying metal substrate at temperatures up to 2000oF (1093oC) for approximately 15 minutes during each reentry. The coating material is also lightweight, low cost, and easily repairable. The proposed coating material is easily applicable by painting, and is amenable to quick field repair. Phase I work will focus on optimizing emissivity of the material and developing coatings. Phase II will focus on further developing coating for metallic TPS panels and further testing for emissivity and catalytic efficiency.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
There is a growing interest in commercial RLVs, which will require TPS systems that require minimal maintenance. Low cost, field repairable high emissivity protective coatings for TPS will be especially critical for commercial systems. High emissivity coatings are also needed in the glass industry and other processing industries.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
Metallic TPS are being pursued by NASA for next-generation RLVs to replace the currently-used ceramic TPS which requires extensive maintenance and water-proofing after each launch cycle. NASA?s long term goal is to implement multiple missions to space with rapid turnaround times which demands a robust TPS that requires minimum maintenance after each cycle. Metallic TPS systems hold great promise to meet the need, but require a robust coating that provides high emissivity, low catalytic activity, and oxidation protection of the substrate. The proposed technology offers many benefits and can be easily implemented into production.
| PROPOSAL NUMBER: | 02- A5.02-8195 (For NASA Use Only - Chron: 023804 ) |
| SUBTOPIC TITLE: | Reusable Launch Vehicle Airframe Technologies |
| PROPOSAL TITLE: | Design Sensitivities of Response/Fatigue Life of Panels to Thermo-Acoustic Loads |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Zona Technology Inc
7430 E. Stetson Drive, Suite 205
Scottsdale , AZ 85251 - 3540
(480 ) 945 - 9988
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
P.C. Chen
pc@zonatech.com
7430 E. Stetson Drive, Suite 205
Scottsdale , AZ 85251 - 3540
(480 ) 945 - 9988
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The design of the panels of future reusable launch vehicles will represent a particularly challenging task as these structural components will be subjected to some thermal effects, potentially severe random acoustic excitations and will support a complex thermal protection system (TPS). The structural dynamic behavior of the combined system is expected to display a significant nonlinearity arising not only from the combination of the acoustic and thermal effects but also from the yielding character of the TPS. A methodology for the fast and accurate prediction of the fatigue life of such nonlinear structures, involving full finite element solutions, reduced order modeling, and random response and fatigue life prediction, is rapidly maturing. The focus of the present effort is then to take these important analysis capabilities to the next level, i.e. to an efficient design tool. This task will be accomplished through the formulation and implementation of the sensitivities of the fatigue life of the panels to their geometric/material properties, boundary conditions, TPS characteristics, etc. The Phase I effort will represent a proof-of-concept on panels without TPS. The Phase II will then proceed with the structural modeling/reduced order modeling of TPS and a complete validation of the proposed design sensitivity methodology.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
The proposed design-oriented software (FRANVAL) will become the only available tool for the prediction of the response, fatigue life, and their design sensitivities of panels subjected to thermo-acoustic loads. Additionally, it will include the TPS structural modeling and its interaction with the panel. Thus, FRANVAL will cover two separate markets (panels and TPS) thereby increasing its distribution potential. ZONA intends to market FRANVAL as a standalone package. It can be adopted by structural engineers for a wide class of aerospace vehicles ranging from JSF, UAV/UCAV, supersonic transports, reusable launch vehicles, RLV/TAV and other new hypersonic aerospace vehicles. It will be an ideal design tool for the current NASA projects under its space initiative. Other than NASA, potential customers include R&D and design arms of DoD Government and private industry such as ZONA?s ZAERO software users in the structures community. With ZONA?s user/customer network, the marketing of FRANVAL is relatively straightforward.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
The Design/Analysis FRANVAL software will occupy a unique niche as there is currently no software to predict the response/fatigue life of panels subjected to thermo-acoustic loads nor evaluate the response/life design sensitivities. It will play an important role in the design of many flight vehicles including supersonic transports, reusable launch vehicles, RLV/TAV and other projects of NASA?s space initiative that are experiencing severe thermal, acoustic, or both types of excitations. The inclusion of the TPS modeling and of its interaction with the panel will provide a common platform for the development of these components and will help transition from component design to system design. Further, the reduced order modeling core of FRANVAL will lead to expedient sensitivity computations. Thus, Design/Analysis FRANVAL will also naturally support the NASA multidisciplinary optimization efforts.
| PROPOSAL NUMBER: | 02- A5.02-8749 (For NASA Use Only - Chron: 023250 ) |
| SUBTOPIC TITLE: | Reusable Launch Vehicle Airframe Technologies |
| PROPOSAL TITLE: | 2D/3D Hybrid Composite Structure Integration |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Refractory Composites, Inc.
107 North Langley Rd
Glen Burnie , MD 21060 - 6538
(410 ) 768 - 2490
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Edward Paquette
tedpaquette@rciusa.com
107 North Langley Rd
Glen Burnie , MD 21060 - 6538
(410 ) 768 - 2490
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Composite structures with complex curvature and reinforcement features frequently require assembly of 2D laminate and 3D woven structures to effect the appropriate load transfer. A very limited range of assembly methods has been available to date. RCI has developed an assembly concept that promises to reduce load concentration and assembly costs relate to the state of the art techniques. While RCI plans to demonstrate this concept on ceramic composites, the technique can bring significant improvements to organic composites.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
Complex composite structures such as aerostructures will benefit from this technology through improved technical performance and reduced assembly costs. The potential exists for complex composite aerostructures to break out into markets that are 3-5 times larger than the present markets. This composite assembly technique is applicable to commercial jet transport aerostructures and hypersonic vehicle hot aero structures.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
This innovation was created in response to low shear interface performance of C/SiC materials for RLV control surface applications but will apply to OMC, MMC and CMC aerostructures.
| PROPOSAL NUMBER: | 02- A5.03-7926 (For NASA Use Only - Chron: 024073 ) |
| SUBTOPIC TITLE: | Nuclear and Exotic Propulsion |
| PROPOSAL TITLE: | Energetic Materials For Advanced Volume Limited Propulsion Systems Applications |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Proton Aerospace
880 Jupiter Park Drive- Suite 16
Jupiter , FL 33458 - 0000
(561 ) 745 - 8481
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Robert Cavalleri
rjca@protonaerospace.com
880 Jupiter Park Drive- Suite 16
Jupiter , FL 33458 - 0000
(561 ) 745 - 8481
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Aluminum is a common fuel used in solid propellant formulations. The amount of aluminum used varies from 9%, 18% and as high as 21%. It is a known fact that the smaller the particle size, the more surface area and the higher the burn rate. Recently the manufacture of Ultra Fine Aluminum Particles (UFAP) has been easier to produce. Recent literature on UFAP testing indicates that it has burn rates up to 50% higher than standard aluminum. In addition test data indicates up to 70% higher propellant mass flux. This information forms the basis for developing higher energy density propellants. Not much attention however has been paid to the use of UFAP to replace standard aluminum in solid propellants or to use of the UFAP in hybrid or slurry propellant systems. A key data point in the efficacy of this is that test data shows that the UFAP can be used in a water burning system. The proposed effort will evaluate the use of UFAP in solid, hybrid and liquid slurry propellants.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
This technology offers the potential of reduction in propellant weight and the possibility of a attractive water based system that packages very advantageously over that of other storable liquid fuels.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
Solid Rocket Propellants, Ultra Fine Aluminum, Hybrid Propellants, Slurry Propellants, Fast Burners, Enviromentally (Green) Sensitive Propellants
| PROPOSAL NUMBER: | 02- A5.03-8079 (For NASA Use Only - Chron: 023920 ) |
| SUBTOPIC TITLE: | Nuclear and Exotic Propulsion |
| PROPOSAL TITLE: | Technologies for Momentum-Exchange/Electrodynamic-Reboost Tether Facilities |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Tethers Unlimited
19011 36th Ave W. Suite F
Lynnwood , WA 98036 - 5752
(425 ) 744 - 0400
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Robert Hoyt
hoyt@tethers.com
8114 Pebble Ct.
Clinton , WA 98036 - 5752
(425 ) 744 - 0400
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
A modular Momentum-Exchange/Electrodynamic-Reboost (MXER) tether system can provide a fully-reusable in-space propulsion system that can provide propellantless propulsion for orbital transfer, Earth-to-Orbit launch assist, and reboost of LEO spacecraft such as the ISS. By eliminating the need to launch large quantities of transfer propellant into orbit for each payload, a MXER tether system can greatly reduce the size and cost of the launch vehicle needed for each payload, and thus it can help achieve the several-orders-of-magnitude launch cost decreases needed to enable widespread commercialization of space. MXER tether systems will require several innovations, including survivable tether structures with both high-strength and conducting materials, methods for controlling electrodynamic spin-up and reboost while maintaining dynamic stability, and an architecture that can enable capabilities to be increased and qualified in a modular, incremental manner. In the proposed effort, TUI will develop designs to address all three of these needs, and develop a concept design for a low-cost flight experiment, the ?Microsatellite Tethered Orbit Raising QUalification Experiment? (?TORQUE), which will enable flight validation of these MXER Tether technologies.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
The proposed modular MXER tether technologies will enable the development of Tether Boost Facilities able to provide propellantless propulsion for a wide range of in-space commercial applications. MXER Tether Boost Facilities will provide orbit-to-orbit transfer of commercial satellites both within LEO and from LEO to GEO. An Earth-to-Orbit Tether Launch Assist facility will enable commercial single-stage Reusable Launch Vehicles to achieve useful payload fractions and reduce the cost of ETO launch down to the range of $500/kg. The commercialization potential of MXER tether technologies is evidenced by a recent $15,000 R&D contract awarded to TUI by a commercial aerospace company to investigate MXER Tether Launch Assist concepts.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
The modular MXER tether technologies will provide propellantless propulsion for NASA and DoD applications such as reboost of the International Space Station, transfer of Orbital Express propellant tanks from LEO drop-off-orbits to propellant depots in higher orbits, delivery of multiple solar power satellite modules from LEO to GEO, and boosting of science payloads from LEO to the Moon and Mars.
| PROPOSAL NUMBER: | 02- A5.03-9245 (For NASA Use Only - Chron: 022754 ) |
| SUBTOPIC TITLE: | Nuclear and Exotic Propulsion |
| PROPOSAL TITLE: | Concept for Tether Current Collection Using Grid -Sphere Electrodes |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
SRS Technologies
1800 Quail Street, Suite 101
Newport Beach , CA 92660 - 0000
(257 ) 971 - 7029
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Dr. Nobie Stone
nstone@stg.srs.com
500 Discovery Drive
Huntsville , AL 35806 - 0000
(949 ) 852 - 6900
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The generation of either propulsive thrust or electrical power with an electro-dynamic tether necessarily depends on driving a return current through the system?s electrically conducting space plasma environment. An electrical connection is, therefore, required between the plasma and each end of the tether. The voltage required to drive the current (derived from either an external power source or the orbital motion of the conducting tether through the geomagnetic field) produces a positive bias between one end of the tether and the plasma. Electrons can be effectively collected at this positive pole with a simple, passive electrode. The proposed Grid-Sphere electrode concept (shown in Exhibit 1) is particularly interesting because of its unique capability to decouple current collection from tether length and to achieve a high area-to-mass ratio, a low drag coefficient, and operational simplicity.
Phase I will include the identification of photolizable thin film materials and grid encapsulation techniques, a preliminary investigation of grid electrode current collection physics, and a top-level applications study. Phase II will include the development of a high fidelity current collection model and the design, fabrication, and functional testing of a prototype Grid-Sphere system.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
The simplicity, robustness, and efficiency of the Grid-Sphere make it an attractive alternative current collection electrode for electrodynamic space tethers. In some applications, it may even be "enabling." Potential applications include electrodynamic tether power generation, orbit control, and capture at outer planets such as Jupiter.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
The proposed device will have a very light grid structure only sufficient to resist gravitational and drag forces in space. However, the concept may be extrapolated to heavier, more rigid grids capable of self support in ground-based applications. In this case, this concept may offer commercially attractive deployment techniques for devices such as large antennas.
| PROPOSAL NUMBER: | 02- A5.04-8190 (For NASA Use Only - Chron: 023809 ) |
| SUBTOPIC TITLE: | Ground Testing of Rocket Engines |
| PROPOSAL TITLE: | Wireless Ethernet-based Data Acquisition System (WEBDAS) |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Invocon, Inc.
19221 I-45 South, Suite 530
Conroe , TX 77385 - 8703
(281 ) 292 - 9903
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Eric Krug
ekrug@invocon.com
19221 I-45 South, Suite 530
Conroe , TX 77385 - 8703
(281 ) 292 - 9903
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The feasibility of extremely low-power wireless RF sensors has been demonstrated by Invocon, Inc. and others, but the application of the technology to broader applications, particularly ground test systems, has been limited. Ground test facilities must be capable of providing reliable, laboratory grade instrumentation capabilities as part of a reconfigurable architecture in sometimes extreme environments, while simultaneously considering purchase costs, maintenance and operations costs, and upgrade costs. The proposed system shall enable the use of existing Ethernet hardware and Web-based IT resources for the configuration, acquisition, transmission and display of sensor data from extremely low-power RF sensors. Standard facility and experiment monitoring functions such as set points, alarms, data logging, and status displays will be provided, as well as the capability to integrate wireless sensor data into existing third party data acquisition and analysis tools available at the NASA ground test facilities. Configuration of individual sensors will be via a Web browser, and sensor output will be available anywhere with Internet access. By providing widespread access to miniature RF sensors, this system will enable the creation of a highly flexible, scalable, robust, wireless instrumentation backbone, which can be integrated with the existing resources of NASA rocket engine ground test facilities.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
Potential Non-NASA applications include industrial facility monitoring, building monitoring and automation, and factory control systems. Efforts to capitalize on the low cost and trained workforce associated with Ethernet-based networks for factory applications have been successful, and would likely benefit from the ability to utilize low-power RF sensors within that framework.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
In addition to the rocket engine test facilities at Stennis Space Center, this system would benefit many NASA ground test facilities, including wind tunnels, large-scale environmental chambers, and biological chambers. Monitoring of the launch pads and other Obiter processing facility resources and environments could be enhanced and further automated with the proposed system, eliminating the labor-intensive data logging activities currently used. The International Space Station, which is already outfitted with a wired and a wireless LAN, could potentially benefit from this development through the utilization of environmental and vehicle sensors, crew health monitoring sensors, and payload monitoring and control. Finally, significant benefits to the 2nd Generation RLV Integrated Vehicle Health Monitoring system or payload systems could be realized.
| PROPOSAL NUMBER: | 02- A5.04-8407 (For NASA Use Only - Chron: 023592 ) |
| SUBTOPIC TITLE: | Ground Testing of Rocket Engines |
| PROPOSAL TITLE: | Improving Test Operations Through Scalable Video Processing on Computer Clusters |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Technological Services Company
P.O. Box 2125
Clinton , MS 39060 - 2125
(601 ) 799 - 6998
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
William Nail
budnail@videcomp.com
P.O. Box 2125
Clinton , MS 39060 - 2125
(601 ) 924 - 3304
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
In today?s propulsion testing environment, the number of simultaneously captured video streams, the number and variety of video derived data products, and quality expectations are increasing, while available manpower and the desired turnaround time between tests is decreasing. This project will take advantage of recently developed super computer clustering technologies to develop new scalable data processing techniques to improve the quality, efficiency and turnaround time of video based data products. New and innovative scalable video processing software will be developed that can be applied to multiple video streams simultaneously while utilizing any number of available processors. This new software will also allow a facility to create multiple and complex data products, with an order of magnitude less operator setup and intervention because the video streams can be selected individually or as a group and assigned to processes prior to, during or after data acquisition. The processors assigned to the tasks may be dedicated or ?borrowed? from other users on the network on an as available basis. With enough processors applied to the work, the time required for completing the data processing tasks could be reduced by several orders of magnitude.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
Product, Service and Emergency Response Testing;
Sports Training Tools;
Maintenance, Critical Lift and Transportation Documentation;
Security, Construction, Traffic, and Airport Surveillance
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
Component, Assembly and Vehicle Testing;
Critical Skills Training Documentation;
Maintenance, Critical Lift and Transportation Documentation;
Surveillance, Prep and Launch Operations
| PROPOSAL NUMBER: | 02- A5.04-9371 (For NASA Use Only - Chron: 022628 ) |
| SUBTOPIC TITLE: | Ground Testing of Rocket Engines |
| PROPOSAL TITLE: | Miniature Intelligent Sensor Electronics |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
NVE CORPORATION
11409 Valley View Road
Eden Prairie , MN 55344 - 3617
(952 ) 996 - 1613
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Russ Beech
beech@nve.com
11409 Valley View Road
Eden Prairie , MN 55344 - 3617
(952 ) 996 - 1602
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The proposed system uses a combined hard-core processor/programmable-logic chip to implement the front-end control and processing functions of an intelligent sensor system. Combining these functions in a single chip is an innovation, relative to a traditional processor-only based system, because it provides re-configurable control of the sensor interface, i.e. analog and digital I/O and signal conditioning electronics, while freeing up the processor for computational tasks - yet maintaining tight coupling between the two functions. To embed intelligent functions on sensors, the proposed miniature, front-end electronics will combine at least 32 MB of RAM and a 200 MHz, 32-bit RISC processor with a flexible sensor interface that consists of two analog input and two analog output channels, with programmable gain, programmable anti-aliasing filters, and automatic calibration, and eight digital I/O channels. An Ethernet communication port will be available. The processor will be programmable using C/C++. Provisions for expansion to four each of the analog input and output channels and sixteen digital I/O channels will be included in the design. The final system will be no larger than 4" x 4" x 2". A programming kit for a PC will be part of the final development.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
This system has commercial potential in the areas of automotive and industrial testing, as well as industrial control. The versatility of the electronics will allow this system to work with nearly any type of sensor. This capability, along with multiple analog and digital I/O channels, gives the system broad utility. Relatively high computational power and both analog and digital outputs make the system useful for control applications also. Programmable Logic Controllers (PLCs) are very common for industrial automation control. The PLC, however, is a fairly simple system that does not have the computational capability that the proposed system will have. The relatively high powered processor of the proposed system will allow the implementation of powerful, complex, and versatile control systems. This capability is further enhanced by the included Ethernet capability, that allows access to the system through a common, high speed communication system
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
The proposed system has strong potential for application to ground testing of rocket engines. Multiple sensor capability, including the versatility to interface to many different types of sensors, and full programmability of each channel allow the system to support a suite of sensors in an a test instrumentation role. The integrated processor provides the capability of programming complex data processing algorithms into the system. Coupled with the analog and digital I/O channels, this creates a powerful and versatile data acquisition and control system.
| PROPOSAL NUMBER: | 02- A5.04-9486 (For NASA Use Only - Chron: 022513 ) |
| SUBTOPIC TITLE: | Ground Testing of Rocket Engines |
| PROPOSAL TITLE: | Advanced Flow Analyses in Complex Feed Systems |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Combustion Research and Flow Technology,
174 NORTH MAIN ST BLDG 3 P.O. BOX 1150
Dublin , PA 18917 - 2108
(215 ) 249 - 9780
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Vineet Ahuja
vineet@craft-tech.com
174 NORTH MAIN ST BLDG 3 P.O. BOX 1150
Dublin , PA 18917 - 2108
(215 ) 249 - 9780
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Computational analyses aiding experimental testing of rocket propulsion systems have very rigorous requirements relating to turnaround time and fidelity of analyses. The performance of rocket propulsion systems is intricately tied to the functioning of valve and feed systems, since feed systems exert flow control, regulate pressure and suppress instabilities. CFD based analyses of such systems is difficult because of their structural complexity, dynamic motion of valves, coupling with related systems, the large variation in flow conditions and the inadequacy of models in handling multi-phase flow regimes that include cavitation based instabilities. Most current CFD tools based on structured grid methodology are cumbersome and inefficient to use for such problems and fail to meet the stringent requirements to support testing. The innovation proposed here is to utilize a multi-element based unstructured framework for analyses of valve based feed systems. The technology has been proven to handle geometrically complex configurations efficiently and is complemented by a suite of adaption and grid movement capabilities that allow localized high fidelity resolution and identification of important physical phenomena. Furthermore, the technology being proposed here, has evolved from a generalized multi-phase framework that allows specification of variable thermodynamic properties and physical equations-of-state appropriate to cryogenic working fluids.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
Our proposed effort will focus on the application of a multi-element unstructured code (CRUNCH CFD) to help support design methodology and testing for propulsion systems. There is currently a need for a support tool for the evaluation of performance losses due to complex flow patterns or the onset of instabilities and prediction of unsteady pressure loads for systems with moving parts that function in harsh fluidic environments. Potential customers for this commercial product include companies currently involved in designing systems for space applications such as Boeing, Pratt & Whitney, and Aerojet. In addition to these companies, a broader market exists, comprising of industrial pump companies who would be interested in using this product for designing high energy systems such as boiler feed pumps and aircraft fuel injection systems.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
The proposed Phase I effort followed by subsequent Phase II will result in a commercial CFD tool that will address some of NASA?s needs towards developing a capability for advanced analysis in support of ground testing of rocket propulsion systems. Since the framework for the CRUNCH CFD code has a moving grid capability with grid adaption, real-time analysis of valve motion is possible. A detailed analysis of valve response and flow modulation will also be possible and an estimation of feed system response to cavitation surge and other instabilities can be predicted. Furthermore, the estimation of unsteady pressure loads will provide valuable information from a structural standpoint, thereby improving the life cycle of the propulsion system. We anticipate this tool to be used in conjunction with other design procedures, especially in its capacity to provide high-fidelity analyses in helping refine preliminary designs and identifying anomalous behavior in existing designs.
| PROPOSAL NUMBER: | 02- A6.01-7507 (For NASA Use Only - Chron: 024492 ) |
| SUBTOPIC TITLE: | Human-Automation Interaction in Aerospace Systems |
| PROPOSAL TITLE: | EGLEAN: A Modeling and Analysis Tool for Error-Tolerant Design |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Soar Technology, Inc.
3600 Green Court, Suite 600
Ann Arbor , MI 48105 - 2588
(734 ) 327 - 8000
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Dr. Scott Wood
swood@soartech.com
3600 Green Court, Suite 600
Ann Arbor , MI 48105 - 2588
(734 ) 327 - 8000
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Soar Technology, Inc. proposes to develop a human-error modeling tool that can be used by designers and engineers early in the design process to identify likely causes of human error and engineer them out of the system. This tool will combine the strengths of an accurate high-fidelity model of human performance with a simple behavior description language for hierarchical task decomposition, and a usable developer interface. This tool will facilitate rapid modeling and analysis of interface candidates allowing a broader exploration of the design space and a deeper understanding of the design tradeoffs. This tool will result in lower development and operational costs for resulting designs, and safer, more effective, and more error-tolerant systems. Although some tools exist for analyzing designs for usability, and techniques exist for identifying human error, no tool or associated technique exists that is easy enough to be used by normal engineers on a regular basis. If successful, this work will represent a significant innovation in the areas of human-system interaction and error-tolerant design.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
The tools proposed here could also support the development of new civilian command and control systems such as those used by government agencies such as the FAA, and FEMA and private sector organizations using industrial, manufacturing, and process control systems, medical information systems, transportation logistics and safety systems, and emergency response systems. The design of these systems shares with NASA applications complex domains and a high reliance on optimized human performance.
Finally, there is a strong need for such tools in education. Every university that offers classes in human-computer interaction based on the ACM SIGCHI Curricula for Human Computer Interaction includes at least one course unit on quantitative evaluation methods. This unit is typically formed around a GOMS technique. Educators need the ability to teach the concepts and techniques of cognitive modeling and quantitative evaluation without wasting time conducting evaluations by hand. The more time saved doing tedious calculations, the more time that can be spent learning the fundamental concepts.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
NASA's Strategic Plan 2000 describes a key NASA mission, to 'Maintain U.S. preeminence in aerospace research and technology' One goal of this mission, to 'Pioneer Technology Innovation,' specifically calls for NASA to develop 'virtual design processes' to 'enable air and spacecraft designers to know with a high degree of confidence that their revolutionary designs will be safe and will achieve their mission objectives before they begin the costly process of fabricating and testing prototypes'. This tool is designed to answers that need by providing an early and automated human-system interaction evaluation system.
This tool could support the development of safe and cost-effective aerospace command and control systems for robotic & human-robotic exploration, operation of launch vehicles and Earth-orbiting satellites, and the National Airspace System (NAS).
| PROPOSAL NUMBER: | 02- A6.01-9612 (For NASA Use Only - Chron: 022387 ) |
| SUBTOPIC TITLE: | Human-Automation Interaction in Aerospace Systems |
| PROPOSAL TITLE: | On-demand, Controller-based Simulation for Human-Automation Training |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Vcom3D, Inc.
3452 Lake Lynda Dr., Suite 260
Orlando , FL 32817 - 8457
(407 ) 737 - 7309
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Edward Sims
eds@vcom3d.com
Vcom3D, Inc., 3452 Lake Lynda Dr., Suite 260
Orlando , FL 32817 - 8457
(407 ) 737 - 7310
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Human control and interaction with synthetic agents and environments has tremendous potential application in intelligent tutoring, performance analysis, human factors analysis, and distributed training. To date, this application has been limited by the cost of creating and maintaining simulations. Vcom3D has developed Authoring Tools and a Web-enabled Simulation Engine that allow subject matter experts to efficiently and economically create training simulations that embed realistic, communicating ?virtual humans? in Advanced Distrbuted Learning (ADL) conformant, web-based training courses. This software has been used to create courses for job interview skills, law-enforcement, and military operations training; as well as over 30,000 copies of language skills training software. To date, however, the tools have not been applied to training human-automation interactions.
For this Phase I SBIR, we will extend our Vcommunicator? authoring tools and Extensible 3D (X3D) simulation engine to create high-performance human-automation training simulations. Key products of this project will include a new Controller-Based architecture that extends the Model-based design, as well as definition of the Controller architecture in terms of relevant industry standards. The goal is to enable cost-effective, reusable, human-automation training available over the web. For Phase II, we will develop a full prototype system and exemplar course.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
The proposed Authoring Tools and Simulation Engine will be directly applicable to a significant portion of the simulation-based e-Learning market that is projected to grow from $300M in 2002 to $37B in 2001. We will market the technology developed as part of this SBIR in two ways: 1) as enhancements to our own Synthetic Environment authoring tools and X3D Simulation Engine, and 2) by licensing the technology to other toolmakers and training course developers. By mapping our techniques into the ADL/SCORM Model and X3D Node Set, we will assure that other vendors are able to build on our architecture, while reserving our commercial rights to license our specific implementations.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
The proposed Authoring System and Simulation Engine for Model-based Human-Automation Interaction Training will allow NASA to develop new training modules that can be accessed anytime, anywhere by maintenance and assembly workers, as well as astronauts. By promoting reusability and ease of authoring/editing models, simulations, and training lessons, it will dramatically cut the cost of training course development and administration.
| PROPOSAL NUMBER: | 02- A6.02-7948 (For NASA Use Only - Chron: 024051 ) |
| SUBTOPIC TITLE: | Nanotechnology |
| PROPOSAL TITLE: | Stress-induced bandgap-shifted titania photocatalyst for hydrogen generation |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Nanoptek
250 Old Marlboro Rd.
Concord , MA 01742 - 4128
(978 ) 369 - 2654
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
John Guerra
jguerra@nanoptech.com
250 Old Marlboro Rd.
Concord , MA 01742 - 4128
(978 ) 369 - 2654
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Titania (TiO2) is known to be a photocatalyst, in that when illuminated with ultra-violet (UV) light equivalent in energy to the bandgap of titania, it becomes an electrically active semiconductor and can generate enough surface energy to dissociate hydrogen and oxygen from water. However, there is very little of UV of the required wavelength in solar light, and so hydrogen generation in sunlight is extremely inefficient. We have discovered, however, that we can shift and lower the bandgap of titania into a region where it become photocatalytically active with visible light, by creating and managing tremendous pressures within the titania thin film layer. This is done by a combination of layer thickness, template geometry, and thermal mismatch between the polycarbonate substrate and the titania. Because the layer of titania is so thin, extremely high stresses can be induced, and with them, large bandgap shift. And because of the template geometry, the thin titania stays intact in spite of the large stress because of superior mechanical and chemical adhesion to the substrate. In addition, titania has a high refractive index of 2.4, and so makes for very powerful light concentration within the film.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
Chemical storage of solar energy in the form of hydrogen, clean hydrogen fuel generation and desalination by-product for coastal cities and third world countries, photo-activated decontamination of water, recharger for micro fuel cells.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
Conversion of extraterrestrial water sources recently discovered on our moon and on Mars into hydrogen energy source using sunlight and stress-induced bandgap-shifted titania nano-structured photocatalyst. Regenerating supply of hydrogen to fuel cells using sunlight, water, and stress-induced bandgap-shifted titania nano-structured photocatalyst. Photo-activated decontamination of water on board shuttle/space station.
| PROPOSAL NUMBER: | 02- A6.02-8081 (For NASA Use Only - Chron: 023918 ) |
| SUBTOPIC TITLE: | Nanotechnology |
| PROPOSAL TITLE: | A Novel One-Step Synthesis of BN Nanotubes for Structural Components |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Materials Modification Inc
2721-D Merrilee Drive
Fairfax , VA 22031 - 4407
(703 ) 560 - 1371
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
T.S Sudarshan
sudarshan@matmod.com
2721-D Merrilee Drive
Fairfax , VA 22031 - 4407
(703 ) 560 - 1371
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Carbon nanotubes (CNT) are considered suitable for use in components for high-strength structural composites used in spacecrafts. However, structurally similar boron nitride (BN) nanotubes that promise both mechanical and electronic superiority over CNTs have not been studied in great detail so far due to the absence of facile preparative techniques. BN nanotubes exhibit good mechanical strength, chemical resistance and heat tolerance and have been predicted to be better reinforcing material than even CNTs for structural polymers.
MMI proposes to utilize its expertise in nanotechnology to develop a novel one-step process for synthesizing boron nitride nanotubes in morphologically pure form. Phase I will be used to develop the synthetic technique for BN nanotubes and test epoxy samples impregnated with the BN nanotubes prepared. Phase II will involve fabrication of prototype parts using the BN-epoxy and establishment of its superiority over CNT- and other fiber-reinforced polymers that are currently used in the fabrication of high-performance parts.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
BN nanotubes can be used as structural reinforcements for specialty polymers such as those used in automobiles and aircraft interiors. BN nanotubes may also be used in heavy duty bearings for machineries and will also find use in electronics by virtue of being a semiconductor.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
Although the specific end use envisaged for BN nanotubes is in composite polymers, other equally attractive applications relevant to NASA include energy storage, life support systems, thermal materials, nanoelectronics, nanosensors and electrostatic discharge materials.
| PROPOSAL NUMBER: | 02- A6.02-8612 (For NASA Use Only - Chron: 023387 ) |
| SUBTOPIC TITLE: | Nanotechnology |
| PROPOSAL TITLE: | Compact X-ray Tube with Carbon Nanotube Cathode |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Microwave Power Technology
1280 Theresa Avenue
Campbell , CA 95008 - 6833
(408 ) 379 - 5335
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Robert Espinosa
micpwrt@aol.com
1280 Theresa Avenue
Campbell , CA 95008 - 6833
(408 ) 379 - 5335
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
MPT proposes to construct a simple electron beam analyzer specifically for measuring the angular dispersion of the emitted electrons. With this information in hand we will then make the required adjustments in our simulation software to set the initial conditions for electrons emitted for CNT cathodes. We will then use computers to investigate candidate electrode configurations for electron guns and x-ray tubes that will provide convergent beams that can be focused to a fine spot. A model will be built to validate the computer simulations. We intend to continue this work into Phase II to develop a miniature X-ray tube operating at 40kV to 60kV with 2 Watts or more of beam power that is focused to produce a spot less than 20um in diameter. Microwave Power Technology has been researching cold cathodes and developing vacuum electron devices using carbon nanotube cathodes for 5 years. We have developed an X-ray tube that is currently being produced for hand held x-ray fluorescence spectrometer. Cold cathodes can be hard mounted to the structure of any vacuum electron device thereby reducing the part count and improving the robustness compared to devices using thermionic cathodes. Ruggedness, efficiency and projected long life make CNT powered vacuum electron devices ideal for space travel and employment in space and lunar based applications.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
Development of the focused beam x-ray tube will immediately extend the utilization of CNT cathodes to X-ray diffraction instruments and imaging that require very small focal spot and higher intensity. The ability to focus the beam from a cold cathode will also be exploited to improve the efficiency of electron beam generators that are being increasingly used in industry. Current applications include drying ink on high speed presses, non-burning destruction of toxic and odoriferous hydrocarbons, sterilization of surfaces and radiation therapy in medicine.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
Cold cathode X-ray tube provide the source for very small x-ray fluorescence and diffraction instruments that are suitable for hand held and portable applications on earth as well as space. These instruments are well suited to withstand the rigors of space travel and mounting on small rovers. . This work goes beyond the immediate exploitation for x-ray tubes and lays the foundation for employing CNT cathodes in vacuum electron devices that require focused electron beams. Future applications include other instruments using electrons as ionizers, microwave tubes for communication and electron beams for environmental control and space based manufacturing.
| PROPOSAL NUMBER: | 02- A6.02-8807 (For NASA Use Only - Chron: 023192 ) |
| SUBTOPIC TITLE: | Nanotechnology |
| PROPOSAL TITLE: | Thermal Management of Solid-State Devices Using Nanotechnology |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Atlas Scientific
1367 Camino Robles Way
San Jose , CA 95120 - 4925
(408 ) 507 - 0906
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Ali Kashani
akashani@atlasscientific.com
1367 Camino Robles Way
San Jose , CA 95120 - 4925
(408 ) 507 - 0906
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Future NASA programs will utilize solid-state devices (e.g., detectors, processors) that require cooling. Thermal management is of critical importance for a variety of solid-state devices. As the size of solid-state devices continues to shrink, device performance and reliability is limited by the ability to remove the increasing density of heat generated within these components. Furthermore, other devices such as solid-state lasers and infrared cameras require cooling and active temperature control. We propose two complimentary approaches to address these issues. The first approach is to develop thermoelectric (TE) coolers using nanotechnology. Thermoelectric materials require high electrical conductivity, but low thermal conductivity. Using nanotchnology it should be possible to significantly suppress the thermal conductivity without a corresponding reduction in electron transport. The second approach we propose is to enhance the thermal contact conductance at interfaces by taking advantage of nanotechnology.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
There are several potential commercial applications for both proposed approaches to thermal management in solid-state devices. The thermoelectric devices could be used for refrigeration and cooling from cryogenic to room temperature for a variety of devices such as high-performance electronics and IR/visible CCD/CMOS imaging cameras.
The same thermoelectric materials could also be used for power generation in the presence of an external heat source. A variety of heat sources could be utilized including waste heat from engine exhaust or heat from a radioactive isotope.
The technique for enhancing thermal conductance at interfaces could be used for the thermal management of microelectronic and nanoelectronic packages and systems. The concept could be integrated with current device technology and packaging and it would allow for an efficient method to manage excess heat generation without requiring any additional power.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
There are several NASA applications for both proposed approaches to thermal management in solid-state devices. The thermoelectric devices could be used for refrigeration and cooling from cryogenic to room temperature for a variety of devices such as microprocessors or detectors.
The same thermoelectric materials could also be used for power generation in the presence of an external heat source. A variety of heat sources could be utilized including waste heat from engine exhaust or heat from a radioactive isotope.
The technique for enhancing thermal conductance at interfaces could be used for the thermal management of space-borne microelectronic and nanoelectronic packages and systems. The concept could be integrated with current device technology and packaging and it would allow for an efficient method to manage excess heat generation without requiring any additional power
| PROPOSAL NUMBER: | 02- A6.02-8960 (For NASA Use Only - Chron: 023039 ) |
| SUBTOPIC TITLE: | Nanotechnology |
| PROPOSAL TITLE: | Ultrahigh Volumetric Energy Density PEM Fuel Cells |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Nanohmics, LLC
4302 Rimdale Dr
Austin , TX 78731 - 1222
(512 ) 415 - 8748
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Steve Savoy
ssavoy@austin.rr.com
4302 Rimdale Dr
Austin , TX 78731 - 1222
(512 ) 415 - 8748
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
A nanoassembly process for constructing ultrahigh volumetric energy density PEM fuel cell stacks is proposed. The method does not require vapor deposition techniques, bulk sintering or post-loading treatments of the membrane electrode assembly (MEA). The method enables ultimate control of two key parameters: the total catalyst to electrode volume and the total surface area of the tri-phase interface to volume of the complete MEA. A synthesis route for the formation of noble metal catalytic nanoparticles that are coated in situ with an electrically conducting carbon aerogel is proposed. Deposition of the low-density conducting coat directly on the surface of the catalyst nanoparticles will maximize the electrode/catalyst volumetric ratio. Furthermore, manipulating monolayers of the novel aerogel?coated catalyst particles will maximize the ratio of the surface area of the electrode/membrane interface to the overall MEA volume and perfluorosulfonic acid membrane using a film transfer technique.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
Methods for increasing the volumetric energy density of small-scale fuel cell devices are in high demand as the ultimate reduction in size and weight of components in portable electronic devices is highly beneficial for consumer use. The proposed effort will lead to ultrathin fuel cell stacks that have the highest volumetric efficiency of both the electrode to catalyst concentration ratio as well as the total surface area of effective tri-phase interface to the overall volume of the complete membrane electrode assembly
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
The proposed research program will lead to ultrahigh volumetric efficiency power supplies. This concern, in general, is of utmost importance for NASA terrestrial and planetary missions where the volume and mass of subsystems is critical. The proposed plan will eliminate superfluous mass and volume of a power source that is used by NASA to both drive major systems and small scale applications such as diagnostic instrumentation, probes, etc.
| PROPOSAL NUMBER: | 02- A6.02-9407 (For NASA Use Only - Chron: 022592 ) |
| SUBTOPIC TITLE: | Nanotechnology |
| PROPOSAL TITLE: | Characterization and synthesis of carbon nano-materials by LDI-IM TOF MS |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Ionwerks
2472 Bolsover Suite 255
Houston , TX 77005 - 2537
(713 ) 522 - 9880
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Michael Ugarov
mvu@ionwerks.com
2472 Bolsover Suite 255
Houston , TX 77005 - 2537
(713 ) 522 - 9880
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
This Small Business Innovation Research Phase I project addresses problems of the synthesis and separation of carbon nanotubes for a wide range of nanotechnology applications. We propose to use unique capabilities of Laser Desorption Ionization - Ion Mobility Time-of-Flight Mass Spectrometry for identification and selective deposition of carbon nano-materials produced by High-Pressure Gas-Phase Catalytic Disproportination of carbon monoxide.
We will evaluate the capabilities of the LDI-IM TOF MS system for the identification and separation of different carbon nano-phases by obtaining the mass-mobility information.
Once we have demonstrated the viability of the LDI-IM TOF MS for the identification of carbon nanophases in a wide range of masses including short nanotubes, the task of the Phase II of the project be will to use a modified LDI-IM setup for the rapid preparation of thin films of pure nanophases for testing as electron emitter surfaces, catalysts, or biologically active selected areas.
As a result of this project novel efficient technique for the characterization and synthesis of carbon nano-materials will be developed.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
The area of applications for these materials extends from high brightness electron sources to advanced polymers, bio-nanostructures and many others. Nanotubes demonstrate extremely high levels of field electron emission at low applied fields due to the concentration of electrical field around their tips. Another very likely application of nanotubes - electromagnetic shielding for electronic devices and radar absorption for stealth aircraft. Giant fullerenes have been demonstrated to achieve superconducting properties if doped with alkali ions. Fullerene materials are of interest as MALDI matrices because they efficiently absorb the laser light and can be readily functionalized with OH, CH3 and NH2 groups that provide a source of protons for charging of adsorbed biomolecules.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
The success of the project will signify a significant improvement of the improved characterization of synthesis, separation and functionalization of carbon nanotubes for applications in nanoelectronics including molecular computing and artificial quantum-structure systems.
| PROPOSAL NUMBER: | 02- A7.01-9262 (For NASA Use Only - Chron: 022737 ) |
| SUBTOPIC TITLE: | Modeling and Control of Complex Flows Over Aerospace Vehicles and Propulsion Systems |
| PROPOSAL TITLE: | Comprehensive Uncertainty Estimation for CFD |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Nielsen Engineering & Research, Inc.
526 Clyde Ave
Mountain View , CA 94043 - 2212
(650 ) 968 - 9457
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Robert E. Childs
childs@nearinc.com
526 Clyde Ave
Mountain View , CA 94043 - 2212
(650 ) 968 - 9457
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Computational fluid dynamics (CFD) is the primary tool of
aerodynamic design, and the ability to reduce and quantify
uncertainties in CFD results is essential. Efforts throughout the
CFD community are aimed at improving the accuracy of CFD methods.
The proposed work will develop computational algorithms and software
that yield comprehensive estimates of uncertainty in CFD results.
The methods involve error modeling, in which specific sources of
error, such as truncation error, and error in the transition and
turbulence modeling, are related to the errors and uncertainty
in the solution via solutions of an error equation. These methods
will be relatively comprehensive, accounting for the dominant sources
of uncertainty in typical CFD analyses, and yielding the
uncertainties in all data predicted by the CFD solution. For example, the uncertainty in distributed aerodynamic heating can be computed.
The techniques to be used in the work have been demonstrated in predictions of uncertainty due to truncation error in structured-grid
CFD data. The proposed work will extend these methods to
unstructured-grid CFD and to transition and turbulence modeling
errors.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
The proposed technology will have commercial benefit wherever CFD is
used to assess aerodynamic performance in critical applications.
This includes the design and analysis of all commercial, NASA, and
military aerospace vehicles. The technology developed will be
represented as a set of software modules that can be used with existing and new CFD solvers.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
The proposed technology will yield an improved ability to design
and optimize aerospace vehicles, including conventional flight
vehicles and launch vehicles. This will benefit NASA s core
missions.
| PROPOSAL NUMBER: | 02- A7.01-9281 (For NASA Use Only - Chron: 022718 ) |
| SUBTOPIC TITLE: | Modeling and Control of Complex Flows Over Aerospace Vehicles and Propulsion Systems |
| PROPOSAL TITLE: | Next Generation Data Management of Large-Scale CFD Simulations |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
JMSI, Inc. dba Intelligent Light
1290 Wall Steet West Third Floor
Lyndhurst , NJ 07071 - 3603
(201 ) 460 - 4700
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
David Edwards
dee@ilight.com
1290 Wall Steet West Third Floor
Lyndhurst , NJ 07071 - 3603
(201 ) 460 - 4700
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Large-scale, 3D simulations of complex configurations using Computational Fluid Dynamics (CFD) have become increasingly critical in the design of aircraft, aerospace vehicles and propulsion systems. The CFD analysis process consists of three phases: pre-processing, solver and post-processing. Multi-disciplinary techniques, which analyze phenomena such as fluid-structure interaction, introduce additional computational complexity and require non-trivial coupling between CFD and structures codes. In designing software for each of the three analytical phases, software developers tend to look at what is optimal and necessary for their particular operation. Considerations such as data sharing, archiving and interoperability are given less attention than efficiency and accuracy of physical models. As the pace of simulation increases, the sheer volume of numerical data requires that a stable and easy to operate methodology be made available to developers and users of pre-processing, post-processing and solver tools. The offeror proposes to create a software toolkit that provides an intelligent storage and retrieval mechanism for large-scale CFD simulation data, combining software libraries, database/compression methodologies and web browser-style control and query tools. This toolkit will assist those developing and maintaining solver codes as well as the analyst/designer community and greatly accelerate aerospace vehicle synthesis by enabling data sharing, storage efficiency and interoperability.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
Integration of the proposed technologies into CFD analysis codes will increase productivity and interoperability between industrial users of CFD in the Aerospace, Automotive, Propulsion and Chemical Process industries. The technologies are applicable to commercial CFD codes, those developed by the government and in-house codes as well. The technology can be extended to other forms of analysis, such as structural analysis, heat transfer and computational electromagnetics (CE). Furthermore, it can be used to assist in coupling such codes for multi-disciplinary analysis.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
NASA programs such as ASCoT, AVST and 3rd Generation RLV all have components that hope to develop new, fast tools for rapid assessment of new vehicle configurations. FAAST is one such element. The technologies proposed herein can be used by authors of these solvers and pre/post-processing tools to accelerate their development of tools. Designers and analysts can then take advantage of the benefits of the technologies in their work as well. Current NASA CFD tools that are known to the offeror are CFL3D, OVERFLOW, TLNS3D, and USM3D.
| PROPOSAL NUMBER: | 02- A7.01-9537 (For NASA Use Only - Chron: 022462 ) |
| SUBTOPIC TITLE: | Modeling and Control of Complex Flows Over Aerospace Vehicles and Propulsion Systems |
| PROPOSAL TITLE: | Active Skin for Turbulent Drag Reduction |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Aeroprobe
1700 Craft Drive, Suite 2413
Blacksburg , VA 24060 - 6374
(540 ) 231 - 3366
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Pavlos Vlachos
pvlachos@vt.edu
2000 Craft Drive, Suite 1104
Blacksburg , VA 24060 - 6374
(540 ) 951 - 3980
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Drag reduction for aerial vehicles has a range of positive ramifications: reduced fuel consumption with the associated economic and environmental consequences, larger flight range and endurance and higher achievable flight speeds. Recent numerical results yielded solid evidence that very small disturbances in the form of a spanwise traveling force wave on a surface could reduce drag by 70%. Our past efforts showed that the same effects can be accomplished by a surface deformation traveling wave.
In this work, we propose to capitalize on our previous experience to develop a revolutionary ?smart? active skin for turbulent drag reduction. Traveling waves will be induced in the smart skin via active-material actuation. This is a ?micro-adaptive? flow control technique. Micro-scale wave amplitudes and energy inputs are sufficient to produce significant benefits. This device will be adaptive in the sense that wavelength, frequency and amplitude will be controlled on-line, in real-time, to produce optimal gains as the flow conditions change. Beyond the expected technological and scientific advances made during the project duration, the most important project deliverable will be a smart skin tailored for air vehicles.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
Upon successful completion of the proposed work, we will be able to market this technology to a large number of customers in aviation and shipbuilding industry that can benefit by an efficient skin friction drag reduction method that is compatible with existing vehicle configurations. Autonomous Underwater Vehicle?s (AUV?s) represent a market that we are currently exploring. Here, drag reduction can alleviate the need for exotic power sources in order to achieve their specified speed, range and endurance while due to their unmanned character they provide a great platform for proving and maturing the technology. The improvements can be extrapolated towards ships or underwater bodies.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
Skin friction drag accounts for a significant percentage of the total drag in aerial vehicles ranging from UAV?s to commercial airlines. Even moderate viscous drag reduction improvements will result in great savings in operational cost, payload, extend range and endurance. Successful completion of the research proposed herein will revolutionarize the aeronautical and aerospace industry. NASA?s mission advancing the aeronautical and aerospace technology will be supported by the research effort proposed herein. Enhancing our understanding of the fundamental mechanics of turbulent drag and providing experimental validation of novel theories and recent computational results will be a direct benefit.
| PROPOSAL NUMBER: | 02- A7.02-7501 (For NASA Use Only - Chron: 024498 ) |
| SUBTOPIC TITLE: | Modeling and Simulation of Aerospace Vehicles in a Flight Test Environment |
| PROPOSAL TITLE: | Finite Element based Fracture Mechanics using Multidisciplinary Approach |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
MATRA
P.O. Box 1264
Carmel , CA 93921 - 1264
(831 ) 624 - 6715
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Dr. Shun Lung
kolar@redshift.com
P.O. Box 1264
Carmel , CA 93921 - 1264
(831 ) 624 - 6715
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Fracture mechanics capabilities based on finite element multidisciplinary analysis will be designed and developed. Incorporating finite element based fracture mechanics analysis will enhance the power and strength of the STARS software. An in depth literature survey will be conducted to assess the appropriate finite element methodology for modeling crack tip stress regions and associated material constitutive relations. In order to characterize fracture behavior, crack tip opening displacement, J-integral method, and virtual crack extension methods will be assessed for implementation. Feasibility of including these methods in the present software design of a multidisciplinary finite element program will be investigated.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
The development of fracture mechanics capabilities enhances the strength and applicability to monitor and perform risk assessment of structural integrity in such areas as commercial airplane structures, nuclear power plants, and other fracture and damage critical structural components in rail-roads, off-shore structures, and automobiles.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
The structural integrity and safety monitoring of NASA's shuttle programs, Flight Test Research vehicles, lauch vehicle structural integrity risk assessment will be potential beneficiaries.
| PROPOSAL NUMBER: | 02- A7.03-9554 (For NASA Use Only - Chron: 022445 ) |
| SUBTOPIC TITLE: | Flight Sensors, Sensor Arrays and Airborne Instruments for Flight Research |
| PROPOSAL TITLE: | Acoustic Shear Stress Sensor for Flight Research |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Nielsen Engineering & Research, Inc.
526 Clyde Ave
Mountain View , CA 94043 - 2212
(650 ) 968 - 9457
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Dr. Daniel A. Pruzan
dpruzan@nearinc.com
526 Clyde Ave
Mountain View , CA 94043 - 2212
(650 ) 968 - 9457
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Nielsen Engineering & Research (NEAR) is proposing to develop a robust, nonintrusive aerodynamic shear stress sensor for use in aircraft flight testing. This sensor is based on technology developed by NEAR under a previous SBIR contract. In the proposed Phase I contract, NEAR will take this established sensor concept and refine it to create an instrument which can withstand the rigors of the flight test environment. Numerical simulations, analysis, and laboratory experiments will be used to 1) advance the design of the transducers and electronics to permit accurate shear stress measurements up to 100 Pascals, 2) improve the correlation algorithm to account for large variations in speed of sound, density, and viscosity, and 3) environmentally harden the sensor to withstand the temperature, pressure, and atmospheric conditions encountered in flight. The resulting Phase I sensor design will be evaluated through environmental and wind tunnel testing. Results from this research effort will be used to develop a second generation prototype in the Phase II contract. Wind tunnel results from this second prototype will then be used to further refine the design and to generate the final sensor which ultimately will be flight-tested towards the end of the Phase II effort.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
There are many commercial applications for a robust, accurate, nonintrusive, flight-ready shear stress sensor. The U.S. Army is interested in NEAR's sensor for use in detecting the onset of dynamic stall on helicopter rotor blades. Commercial interest and a pledge of financial support for this proposed contract have been received from Goodrich Sensor Systems. Their objective is to develop shear stress sensor-based products for transport aircraft including stall warning sensors and ice/contamination sensors.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
The present proposal defines the tasks necessary to develop NEAR's shear stress technology into a flight test research instrument. The ability to generate real-time shear stress measurements accurately and reliably over a wide range of flight speeds and ambient conditions will help researchers at Dryden FRC to evaluate and expand the flight envelope of modern aircraft. Researchers at NASA Langley have also expressed interest in NEAR's technology for use as a wind tunnel instrument, and for incorporation into closed-loop flow control systems.
| PROPOSAL NUMBER: | 02- A7.03-9587 (For NASA Use Only - Chron: 022412 ) |
| SUBTOPIC TITLE: | Flight Sensors, Sensor Arrays and Airborne Instruments for Flight Research |
| PROPOSAL TITLE: | Optical Sensor for Detection of Fatigue Damage Precursors |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
MetroLaser, Inc.
2572 White Road
Irvine , CA 92614 - 6236
(949 ) 553 - 0688
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Dr. Vladimir Markov
vmarkov@metrolaserinc.com
2572 White Road
Irvine , CA 92614 - 4236
(949 ) 553 - 0688
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Reliable and operationally simple methods that can be used in the field are needed for expeditious fatigue damage and corrosion detection. We have developed a strategy for constructing a laser-based nondestructive sensor for fatigue and corrosion damage detection and monitoring in aerospace components. The sensor detects precursors to crack formation occurring as early as the first 10% of fatigue life and, therefore, can be used to identify accumulated fatigue damage prior to crack initiation. The sensor can also be used to detect the state of surface corrosion formation. During Phase I, we will demonstrate the proof-of-concept of a compact, leave-in-place, nondestructive, optical sensor with remote wireless interrogation of the retrieved data and develop a strategy for building a prototype of the instrument. During Phase II, we will further refine our work in modeling the instrument, designing its specific components, assembling it, and establishing its performance envelope. Phase II will culminate in constructing and field-testing the prototype system.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
Since over 90% of mechanical failures are due to fatigue damage, the proposed sensor will be useful in a variety of industries that employ dynamically loaded mechanical systems. Of particular significance are the commercial and military aircraft industries, where the instrument could be used to quickly verify the safety condition of many critical parts, such as engine components, fuselage panels, and landing gear. In addition, many other industries can benefit from this diagnostic tool including the automotive, power generation, shipping, and railroad industries.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
NASA requires advanced sensors to inspect critical components of airframes that are subjected to low and high-cycle fatigue. If unchecked, fatigue-induced damage in airframe components can lead to formation of cracks. Crack formation is often followed by sudden catastrophic failure of the airframe component and destruction of the aerospace vehicle. By providing a timely warning, the proposed sensor will assist in identifying potentially damaged components, and in this way will improve safety of aerospace vehicles while reducing maintenance costs.
| PROPOSAL NUMBER: | 02- A7.03-9648 (For NASA Use Only - Chron: 022351 ) |
| SUBTOPIC TITLE: | Flight Sensors, Sensor Arrays and Airborne Instruments for Flight Research |
| PROPOSAL TITLE: | Real-time Aeroelastic Measurement System (RAMS) for in-Flight Flutter Testing |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Tao of Systems Integration Inc.
471 McLaws Circle, Suite 1
Williamsburg , VA 23185 - 5525
(757 ) 220 - 5040
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Siva Mangalam
siva@taosystem.com
471 McLaws Circle, Suite 1
Williamsburg , VA 23185 - 5525
(757 ) 220 - 5040
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
A high dynamic response, Real-time Aeroelastic Measurement System (RAMS) using microns-thin hybrid sensor arrays will be developed to provide simultaneous unsteady normal-pressure and tangential shear-stress distributions on lifting surfaces undergoing bending and torsion during in-flight flutter testing. The surface signatures obtained with these sensors will be used to simultaneously obtain, in real-time, the spatial location and dynamic characteristics of unsteady flow phenomena such as boundary-layer transition, vortex flows, flow separation, and shock (flow oscillations) and boundary oscillations (flutter). Surface signatures will provide accurate information on the amplitude and frequency of the aerodynamic forcing functions, as well as the time lag between unsteady aerodynamic phenomena and the structural response of the test article. RAMS will provide flight-test researchers with an effective tool to obtain time-accurate unsteady coupling physics of the aerostructural system by sensing surface signatures coordinated with pressure, strains, and accelerations. With the proposed measurements there will be an entire force-response description of the aerostructural dynamics. RAMS will result in a comprehensive measurement technology that can be used for routine flutter flight-testing, CFD validation, development of new and advanced design tools, development of active aeroelastic wing (AAW), and the development of flutter warning and active control systems.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
RAMS will be of value to ground / flight-testing and health monitoring of fixed-wing and rotary-wing aircraft, turbo-machinery, propellers, unmanned vehicles, missiles, and space vehicles. Advanced aerospace vehicles tend to be slim and elastic, resulting in severe aeroservoelastic problems at high speeds, which require attention in both design and routine performance for safety and ride quality. All vibrating structures subjected to unsteady aerodynamic or hydrodynamic forces and moments are prone to aeroelastic and flutter problems, which could lead to catastrophic results unless properly taken care of. RAMS will be of value to the design and testing of sails of sailboats, high-rise buildings, chimneys of power and cooling towers of plants, masts of ships, and other structures subjected to vibrations in the presence of fluid flow.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
RAMS has significant potential applications for the aerospace industry. Flutter is one of the chief limiting factors in the design of more efficient and more maneuverable high-speed aerospace vehicles. The proposed innovation will significantly contribute to the important recent initiative taken by NASA DFRC to develop Active Aeroelastic Wing (AAW). Aerodynamic nonlinear effects could be severe in the high transonic Mach numbers due to, for example, changes in the flow separation and shock wave patterns with amplitude of oscillation. Nonlinear effects are likely to become more important in the future as aircraft fly faster, are more flexible, and use complex control systems. The benefits of successfully addressing the flutter problem will lead to a larger safe-flight envelope and payload for aerospace vehicles, which can be translated to economic value, while simultaneously possessing superior maneuver performance.
| PROPOSAL NUMBER: | 02- A7.04-7529 (For NASA Use Only - Chron: 024470 ) |
| SUBTOPIC TITLE: | Knowledge Engineering for Safe Systems in Lifecycle Engineering |
| PROPOSAL TITLE: | Simulation and Analysis of Socio-Technical Risk using SpecTRM |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Safeware Engineering Corporation
1520 Eastlake Ave. E., Suite 101
Seattle , WA 98102 - 3717
(206 ) 328 - 4880
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Grady Lee
lee@safeware-eng.com
1520 Eastlake Ave. E., Suite 101
Seattle , WA 98102 - 3717
(206 ) 328 - 4880
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
We propose to create model-based simulation and analysis techniques for risk management throughout the system life cycle. Rather than using traditional approaches based on failure events in static engineering designs, we will treat a system as a dynamic process that is continually adapting to achieve its ends and to react to changes in itself and its environment. The original design must not only enforce appropriate constraints on behavior to ensure safe operation, but the system must continue to operate safely as changes occur. To achieve this goal, the process leading up to an accident (loss event) can be described in terms of an adaptive feedback function that fails to maintain safety as performance changes over time to meet a complex set of goals and values. Using this definition of risk management, we will determine how to extend our commercial system engineering toolset to include model-based simulation and analysis of risk throughout the system life cycle, including complex human decision-making, software errors, system accidents (versus component failure accidents), and organizational risk factors.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
The results of this SBIR research will be potentially applicable to every NASA project where significant losses can result from the operation or lack of operation of the system. It should be particularly important in systems with significant software and human automation interaction components and in large projects where management decisions about risk are critical and need to be supported.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
The results of this SBIR project will be applicable to risk management in any safety-critical system. SpecTRM-RL, the modeling language as well as the more general SpecTRM requirements specification and analysis tools, are currently in industrial Beta test and being evaluated for adoption by companies and government agencies in the aerospace, automotive, and medical industries.
| PROPOSAL NUMBER: | 02- A7.04-9392 (For NASA Use Only - Chron: 022607 ) |
| SUBTOPIC TITLE: | Knowledge Engineering for Safe Systems in Lifecycle Engineering |
| PROPOSAL TITLE: | Networks in Organizational Risk Management |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Aptima, Inc.
12 Gill Street, Ste 1400
Woburn , MA 01801 - 1728
(781 ) 496 - 2312
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Kari Chopra
kchopra@aptima.com
12 Gill Street, Ste 1400
Woburn , MA 01801 - 1728
(781 ) 496 - 2424
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
We propose to develop a formal modeling tool, Networks in Organizational Risk Management (NORM), that allows mission planners and organizational designers to create and experiment with organizational structures that minimize risk throughout the lifecycle of a system. The core of our approach is a model of the network of interrelationships among people, knowledge, tasks, technology, organizational goals, system failures, and the surrounding environment. Our proposal is uniquely innovative in three respects. First, we seek to develop a formal quantitative model of organizational risk management rather than qualitative descriptions of theoretical aspects or recommended practices. Second, our model encapsulates a holistic view of organizational risk management, where organizations are not depicted solely as a source of errors but also as a means for detecting and responding to system failures. Finally, in contrast to conventional methods that focus on analyzing technical failures in the system, our model incorporates explicit measures of organizational phenomena such as goals, decisions, authority, communication, and informal social networks. The software tool we envision will provide capabilities for simulation, to allow mission planners to experiment with ?what-if? scenarios and optimization to generate organizational designs that minimize the losses incurred by system failures.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
The capabilities of NORM are most likely to appeal to customers who have the need to analyze and improve organizational safety or design organizations for safe operations. Examples of potential applications include air traffic control, supervisory control systems, command and control systems, ground and maritime transportation, hospital administration, construction, and manufacturing. In addition, management consulting firms provide a potential market for software licensing and consulting services. Business analysts that advise corporate management on safety issues require a deep understanding of the risks present in the organization, but are typically unacquainted with scientific methods for rigorously modeling and analyzing organizational risks.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
Formal modeling of organizational risk management is critical to a variety of NASA applications, including launch operations, the Mission to Mars, and the International Space Station (ISS). Failures such as the Challenger launch and the Mars rover illustrate the need for tools to design organizations that minimize rather than induce errors, and to identify latent errors introduced during design and construction before they manifest themselves as operational failures providing little opportunity for recovery. The challenges of constructing, maintaining, and continually expanding the ISS demand cost-effective methods for predicting the impact of new technologies on system safety prior to installation.
| PROPOSAL NUMBER: | 02- A8.01-8459 (For NASA Use Only - Chron: 023540 ) |
| SUBTOPIC TITLE: | Revolutionary Aerospace Vehicle Systems Concepts |
| PROPOSAL TITLE: | MHD Power Generation and Aerodynamic Control for Planetary Entry Vehicles |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Research Support Instruments Inc
4325-B Forbes Blvd.
Lanham , MD 20706 - 4854
(609 ) 580 - 0080
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
John Kline
kline@researchsupport.com
4325-B Forbes Blvd.
Lanham , MD 20706 - 4854
(301 ) 306 - 0010
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
When a spacecraft enters a planetary atmosphere with a velocity of 6-8 km/s, gas temperatures behind the bow shock can reach 7,000 ? 20,000 K, and the hot gas is ionized: the electrical conductivity of several hundred mho/m or higher exists behind the shock. The conductive fluid can interact with electromagnetic fields. Specifically, with a magnet and a set of electrodes at or near the surface, a magnetohydrodynamic (MHD) power generation would be possible. The generated power, estimated to be on a multi-megawatt scale for the future Mars mission, can be useful during the mission. Additionally, asymmetric MHD configuration can provide body forces for aerodynamic maneuvering and stabilization.
A successful development of this technology must be based on a comprehensive and reliable set of theoretical and computational models. Although extensive CFD codes for planetary entry exist in NASA and academia, for the planetary-entry MHD application those codes and models must be improved and enhanced, especially with regard to ionization mechanism, ionization enhancement, MHD coupling with the flow, and low-density phenomena such as ion slip. We propose to develop models that would incorporate the relevant physics, and to predict potential performance of the planetary-entry MHD power generators and aerodynamic control devices.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
While the eventual goal of understanding MHD effects in re-entry environments would be applicable to an aerospace vehicle and redefine the possible mission profiles in future space endeavors, RSI will pursue more near-term commercialization efforts. There is a clearly identified need and opportunity to develop reliable models of planetary-entry MHD power generators and aerodynamic control devices, and to make predictions of their performance. The algorithms developed in this program will find application in design efforts in next-generation re-entry vehicles (without MHD effects), in new hypersonic vehicles involving MHD power generation or control, and in terrestrial MHD power generation. Existing codes can cover the areas of MHD effects, hypersonic flow, and partially ionized flow, but they do not consider MHD effects coupled with aerothermochemically nonequilibrium flow and Hall and ion-slip effects.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
The effort will create a foundation for a breakthrough technology to help future NASA Mars and other planetary missions, and will potentially create a new power technology for Earth satellites and Trans-Atmospheric Vehicles. The tools developed in this program would be used to assess power generation performance of MHD system mounted on a Mars entry ballute, and to study force moments that can be created by an asymmetric placement of the MHD device. The results will be applicable to new NASA aerospace vehicles, and will redefine the possible mission profiles in future space endeavors
| PROPOSAL NUMBER: | 02- A8.01-9327 (For NASA Use Only - Chron: 022672 ) |
| SUBTOPIC TITLE: | Revolutionary Aerospace Vehicle Systems Concepts |
| PROPOSAL TITLE: | Commercial Framework for Bi-Level Integrated System Synthesis |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Phoenix Integration
1715 Pratt
Blacksburg , VA 24060 - 0000
(540 ) 961 - 7215
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Brett Malone
malone@phoenix-int.com
1715 Pratt
Blacksburg , VA 24060 - 0000
(540 ) 961 - 7215
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Phoenix Integration proposes a Phase I SBIR project to commercialize the BLISS methodology within the popular integration and optimization framework, ModelCenter?. This work will be significant, because a powerful and flexible algorithm will be provided to industry in a user-friendly and open integration environment. The research and modifications required to ModelCenter will revolutionize the way industry approaches optimization because of the benefits of parallel subsystem design optimization coupled with flexible, distributed code integration.
Further, the research will advance the field of engineering design by introducing commercially-available methods for hierarchical decomposition and optimization, making more complex analysis easier. The significance to industry is that more complex problems can be solver faster and easier by applying the BLISS approach to multidisciplinary problems.
The return on investment for companies will be substantial because hierarchical decomposition and optimization makes it possible to run subsystems in parallel. The benefits is better utilization of hardware cycles.
Overall, integration of the BLISS approach into Phoenix Integration?s tools will result in:
? Better integration of multiple disciplines for complex industry problems
? Easy to use interface allows end users to create BLISS optimization problems
? Better hardware utilization due to increased parallel computing
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
The short-term benefit to the manufacturing industry is the reduction of the cost of ownership and the ability to deploy collaborative design tools across the enterprise. This new breed of tool will be offered with low maintenance and streamlined deployment so large organizations can be productive quickly.
Long-term benefits are the reduced cost of goods and services provided by the large manufacturers using the collaborative environment. Engineering risk will be reduced as multi-site, multi-vendor teams will be able to share design information more effectively and make better-informed decisions.
US airframers are hungry for ways to make engineering more economical as they continue to compete with international manufacturers. Engineering costs will be reduced as cycle times are shortened. The effect of reducing engineering costs will be increased competitiveness such as the ability to offer more aggressive delivery schedules.
Phoenix will work with Boeing and NASA on the Phase II portion of the proposed work to develop innovative optimization techniques to improve the efficiency Boeing?s products. It is expected that by applying BLISS within ModelCenter for Boeing that significant performance enhancements could be realized along with fuel and range efficiency for Boeing?s platforms. This will make Boeing and the entire US aerospace market for commercial transports more competitive.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
Phoenix Integration software is currently being used as the Advanced Engineering Environment (AEE) developed for the Space Launch Initiative (SLI ). ModelCenter is the defacto standard for performing multidisciplinary trade studies and optimization.
The proposed research will benefit NASA because the BLISS approach will be beneficial the the dozens of engineers currently using ModelCenter for preliminary design. It is expected that with the next cycle of analysis for SLI, that more complex analysis tools will be introduced.
This provides an excellent opportunity for NASA to benefit from the proposed research because more engineers will be needing tools and methods support for complex analysis. BLISS as integrated with the ModelCenter interface will provide engineers the ability to easily formulate complex problems and then execute on an optimized computing grid taking advantage of parallel subsystems.
| PROPOSAL NUMBER: | 02- A8.01-9414 (For NASA Use Only - Chron: 022585 ) |
| SUBTOPIC TITLE: | Revolutionary Aerospace Vehicle Systems Concepts |
| PROPOSAL TITLE: | Design-Oriented Aeroservoelastic ZAERO Capability for 3D Configuration Shape MDO |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Zona Technology Inc
7430 E. Stetson Drive, Suite 205
Scottsdale , AZ 85251 - 3540
(480 ) 945 - 9988
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Danny Liu
danny@zonatech.com
7430 E. Stetson Drive, Suite 205
Scottsdale , AZ 85251 - 3540
(480 ) 945 - 9988
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Design-oriented steady and unsteady aerodynamic analysis tools for Aeroelastic / Aeroservoelastic evaluation lag significantly behind other multidisciplinary design optimization (MDO) developments for aerospace vehicle design. In almost all MDO studies to date involving configuration shape optimization, dynamic Aeroelastic/Aeroservoelastic constraints were left out. Flutter, gust stresses, vibration, fatigue, ride comfort, handling qualities ? all extremely important ? still cannot be accounted for in an automated design process involving configuration shape variations. Proposed here is the creation of a comprehensive design-oriented unsteady-aerodynamic methodology to enhance current MDO/MSO capabilities with Aeroelastic/Aeroservoelastic shape sensitivities. ZONA Technology?s proven ZAERO code will serve as the aerodynamic base for this development. In phase I the new methodology will provide sensitivities with respect to planform shape design variables for aerodynamic matrices, pressures, and loads. Subsonic, sonic, supersonic, and hypersonic Mach numbers will be covered as well as order reduction techniques for repetitive generation of aerodynamic matrices during optimization. Easy interfaces with general finite element codes will be introduced and validated. In phase II non-planar surfaces and general 3D wing-body sensitivity solutions and reduced-order approximations will be obtained and validated. This new general capability will fit any aerospace vehicle MDO environment, and will provide a crucial critically needed MDO building block.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
The proposed design-oriented software (ZAERO-DO) will become the unique and the only Aeroelastic/Aeroservoelastic-Aerodynamic tool for shape sensitivity/uncertainty evaluation and shape optimization of flight vehicles. ZAERO-DO will become a software standard, providing aerodynamics for Aeroelastic/Aeroservoelastic constraints throughout the full Mach number and frequency ranges. ZONA plans to package it as stand-alone software for Aerodynamic/ASE analysis/sensitivity/approximations. Shape/sizing optimization can be carried out when ZAERO-DO is interfaced with FEM software with structural shape sensitivity capabilities. It can be adopted for MDO of a wide class of aerospace vehicles: UAV/UCAV, supersonic transports, space launch vehicles, RLVs, blended wing/body, flying wings, joined-wings, hypervelocity missiles, winged projectiles (with optimized fin/canard/wing). It will be an important Aeroelastic/ASE design tool for current NASA projects: morphing aircraft and revolutionary vehicles. Potential customers include the R&D and design arms of Government and private industry, including ZAERO users (see 10.1). With ZONA?s customer network, the marketing of ZAERO-DO will be straightforward.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
Design-oriented software for producing steady and unsteady aerodynamic loads for Aeroelastic/Aeroservoelastic shape design of complex flight vehicles is still non-existent, leading to a gap in every current MDO capability for flight vehicle design. NASA has been working for many years toward achieving a universal MDO system with capabilities that would cover both sizing and shape optimization, and would include integration with advanced structures, CFD aerodynamics, and controls. The proposed methodology is aimed at providing an expedient aerodynamic computation capability for rapid evaluation of standard static and dynamic Aeroelastic/Aeroservoelastic constraints in conceptual and preliminary design, which is beyond present CFD capabilities. Thus, the proposed methodology will enhance NASA?s flight vehicle MDO system with capability for generating Aeroelastic/Aeroservoelastic sensitivity and constraints. It will support design studies for practically every category of flight vehicles including blended wing/bodies, joined-wings, supersonic transports, morphing aircraft, space planes, RLVs, Mars planes, and any revolutionary concept pursued.
| PROPOSAL NUMBER: | 02- A8.02-7852 (For NASA Use Only - Chron: 024147 ) |
| SUBTOPIC TITLE: | Revolutionary Flight Concepts |
| PROPOSAL TITLE: | UV Rigid Inflatable Wing |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Adherent Technologies, Inc.
9621 Camino del Sol NE
Albuquerque , NM 87111 - 1522
(505 ) 346 - 1685
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Dr. Ronald E. Allred
adherenttech@comcast.net
9621 Camino del Sol NE
Albuquerque , NM 87111 - 1522
(505 ) 346 - 1685
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
As the unmanned exploration of Mars and Venus becomes more of a focus area at NASA, inflatable, rigidizable wings will become an enabling technology. The successful development of this type of wing will also have significant military applications. The utility of unmanned aerial vehicles (UAVs) for the military has been dramatically demonstrated in the conflict in Afghanistan. Rigidization of inflatable wings provides several potential advantages, including reducing the vulnerability to punctures, increasing stiffness and load carrying capability, allowing a higher aspect ratio for high altitude efficiency and longer missions, and reducing weight by eliminating the make up pressurization supply. An Ultraviolet (UV) curing epoxy resin system is proposed for development for rigidizing inflatable aero-structures in the Phase I program. This technology builds on current developments for rigidization of space inflatable booms and struts using the Rigidization on Command (ROC) system. The Phase I program will address structural and manufacturing requirements for inflatable aero-structures and explore the chemistry of an UV light-curing matrix system for rigidization. Matrix chemistry will be formulated to be compatible with long storage times and cure in the space environment using photocurable cationic epoxies. A demonstration half-span wing will be deployed and rigidized at the end of the Phase I program.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
The eventual markets for inflatable spacecraft are extremely large for communications antennas and radars. In the commercial sector, over 200 satellites are expected to be launched in the next 10 years to meet consumer demand for cellular phones and other communication devices. A large number of military satellites are also expected to be launched in that timeframe. Military UAVs represent another potentially large market for UV rigidized inflatable aero-structures. The unique features of the ROC technology bring a distinct competitive advantage to the marketplace for inflatables compared to competing technologies.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
The proposed work will result in a new materials technology for rigidizable inflatable aero-structures. It is expected that the ROC technology will be adopted by the inflatables community for use by NASA and its contractors for a variety of space missions involving large antennas, mirrors, radars, and Gossamer structures such as solar sails. Rigidization of inflatable wings provides several potential advantages for planetary exploration, including reducing the vulnerability to punctures, increasing stiffness and load carrying capability, allowing a higher aspect ratio for high altitude efficiency and longer missions, and reducing weight by eliminating the make up pressurization supply.
| PROPOSAL NUMBER: | 02- A8.02-7966 (For NASA Use Only - Chron: 024033 ) |
| SUBTOPIC TITLE: | Revolutionary Flight Concepts |
| PROPOSAL TITLE: | Robust Flow Control For Radically Enhanced Natural Laminar Flow Wings |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Eidetics Corporation
3425 Lomita Blvd.
Torrance , CA 90505 - 5010
(310 ) 326 - 8228
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Michael Kerho
mike@eideticscorp.com
3425 Lomita Blvd.
Torrance , CA 90505 - 5010
(310 ) 326 - 8228
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Airfoil stagnation point control has the potential to significantly improve the performance of aircraft by producing a radically enhanced natural laminar flow (NLF) low drag wing. By controlling the stagnation point location of an NLF airfoil, the range of low drag lift coefficients can be extended by up to 100%. The objective of this Phase I proposal is to design a hinge-less variable camber full span trailing-edge for airfoil stagnation point control utilizing compliant monolithic structures. The system will provide a significantly enhanced performance envelope for any aircraft able to utilize an NLF wing. In addition to stagnation point control, the system will provide full lateral and lift distribution control of the vehicle while producing a lower radar cross-section, better battle tolerance, and increased maneuvering capability. The new design will provide increased maximum lift in the low drag bucket of the airfoil, thus providing better performance at the design point for the beginning of cruise, resulting in a higher altitude, or more payload to altitude, or more fuel to altitude for longer endurance. Additionally, the drag at low lift coefficients will also be decreased providing higher dash speeds.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
The commercialization potential is excellent for a highly aerodynamically efficient, reliable and maintainable compliant wing system utilizing stagnation point control with low observable potential. It is recognized that long endurance aircraft in the form of uninhabited air vehicles (UAVs) and high altitude aircraft are expected to play an increasingly important role in military and civilian operations from tactical reconnaissance and uninhabited combat aerial vehicles (UCAVs) to high altitude communications relays and environmental sampling. The aviation industry will be eager to exploit the advantages of the current stagnation point control based design. This new design approach will deliver the advantages sought by the mission adaptive wing concept but with much lower weight and much lower cost of manufacture, and be applicable throughout the aviation community. Both the commercial and military airframe designers will find the technology extremely appealing, allowing significant commercialization potential.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
The proposed highly aerodynamically efficient, reliable and maintainable compliant wing system utilizing stagnation point control has significant potential application in several NASA programs. The compliant trailing-edge/stagnation point control system could be fielded in several NASA aircraft including manned and unmanned systems. NASA designers will be eager to exploit the advantages of the current stagnation point control based design. This new design approach will deliver radically enhanced performance as compared to traditional laminar flow wings in a low risk package. The system will be applicable throughout NASA's aviation community.
| PROPOSAL NUMBER: | 02- B1.01-9762 (For NASA Use Only - Chron: 022237 ) |
| SUBTOPIC TITLE: | Exploiting Gravitational Effects for Combustion, Fluids, Synthesis, and Vibration Technology |
| PROPOSAL TITLE: | Void Fraction Sensor for Packed-Bed Reactors in Microgravity |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Creare Inc
P.O. Box 71
Hanover , NH 03755 - 0071
(603 ) 643 - 3800
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Christopher J. Crowley
amh@creare.com
P.O. Box 71
Hanover , NH 03755 - 0071
(603 ) 643 - 3800
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The innovative product resulting from this project is an instrument to measure void fraction in packed-bed reactors. As NASA pursues long-duration crewed missions, it will be necessary to adapt packed-bed chemical processing methods to reduced gravity to minimize the mass and volume of consumables carried from earth. Accurate measurement of void fraction is critical to (1) identify the flow regimes, and (2) quantify the liquid holdup for design and performance calculations. At present, there is no simple, easy-to-use instrument for microgravity. Capacitance-based sensors have several advantages including the potential to be very sensitive to liquid held up in the reactor, not intrude into the flow, and provide high rates of data sampling. With the conductive fluids used in reactors, a new signal-conditioning scheme is needed for capacitance-based measurements of void fraction. We will develop the new signal-conditioning scheme with an adapted version of a unique capacitance sensor previously developed at Creare. During Phase I we will prove the feasibility of the new signal-conditioning electronics using a multiphase flow facility. During Phase II we will develop the electronics package, adapt the sensor mechanical design to the configuration of packed-bed reactors, and demonstrate the prototype under packed-bed flow conditions.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
A void fraction instrument capable of being used with conductive fluids has numerous industrial and research applications in many areas including chemical processing facilities, biotechnology, and pharmaceutical manufacturing. Our innovative electronics will also optimize the performance of the void fraction instrument for use with cryogenic fluids where the relative permittivity of the liquid is low. There are a host of industrial and aerospace applications where this capability is needed.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
Crewed space activities depend upon the development of packed-bed reactors for regenerative life support systems for extraction, absorption, humidification, leaching, etc. In addition to this primary application, the same innovative electronics approach that will enable operation with conductive fluids will also optimize the sensor performance with cryogenic fluids. NASA has many obvious potential applications for this technology in propellant transfer applications and in the operation of systems that use these fluids.
| PROPOSAL NUMBER: | 02- B1.02-7843 (For NASA Use Only - Chron: 024156 ) |
| SUBTOPIC TITLE: | Gravitational Effects on Biotechnology and Materials Sciences |
| PROPOSAL TITLE: | Development of Tantalum Carbide for Microgravity Containment Cartridges |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Plasma Processes, Inc.
4914 Moores Mill Rd
Huntsville , AL 35811 - 1558
(256 ) 851 - 7653
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Scott O'Dell
scottodell@plasmapros.com
4914 Moores Mill Rd
Huntsville , AL 35811 - 1558
(256 ) 851 - 7653
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Two critical aspects for microgravity materials experiments are to ensure the safety of the International Space Station (ISS) crew/hardware and to maximize the level of obtainable science. Several of the materials processing experiments for the Quench Module Insert (QMI), one of the first Experiment Modules (EM) to be used aboard the ISS, require processing aluminum or aluminum alloys. Recent tests by NASA have shown refractory metal cartridges have limited resistance to attack from molten aluminum. In addition, these cartridge materials have relatively low emissivities which result in reduced rates of heat transfer from the heater core to samples being processed; thus, the level of obtainable science is not maximized. Recently, tantalum carbide has been identified as having a high resistance to attack by molten aluminum as well as having a significantly higher emissivity than typical refractory metal cartridge materials. Therefore, an investigation is proposed to develop methods for producing tantalum carbide on the internal and external surfaces of containment cartridges for use in microgravity furnaces. Successful completion of this work will enhance furnace efficiency by lowering power requirements and increasing quench rates, increase sample containment reliability/safety, and reduce the cost to produce sample containment cartridges.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
Commercial potential for the technology being developed during this effort is very high. Potential applications included, but are not limited to, high temperature furnace and retort components, rocket motor throat inserts, radiation shields, heat pipes, power generation equipment, nuclear components, turbines, combustion chambers, incinerators, beam and sputter targets.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
NASA?s desire to obtain the maximum amount of science from microgravity materials science experiments along with the need to provide safe and reliable containment methods to protect extremely expensive space hardware and the lives of the crews occupying those facilities more than justifies the development of the proposed technology.
| PROPOSAL NUMBER: | 02- B1.02-8039 (For NASA Use Only - Chron: 023960 ) |
| SUBTOPIC TITLE: | Gravitational Effects on Biotechnology and Materials Sciences |
| PROPOSAL TITLE: | Portable Gene Expression Array Reader for NASA Applications |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Intelligent Optical Systems Inc
2520 W. 237th Street
Torrance , CA 90505 - 5217
(310 ) 530 - 7130
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Dr. Srivatsa Venkatasubbarao
sbirproposals@intopsys.com
2520 W. 237th Street
Torrance , CA 90505 - 5217
(310 ) 530 - 7130
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
In the last few decades our understanding of life has expanded considerably with major progress in the fields of biotechnology, molecular biology, and genetics. This has culminated in deciphering the human genome. Microarray technologies have now made it possible to identify and study the expression of thousands of genes simultaneously. Currently used microarray readers are predominantly fluorescence readers for their superior sensitivity. Alternative readers that are simpler, less expensive, compact, and portable are desired for space applications and various in situ applications. Intelligent Optical Systems proposes to develop a highly sensitive, lightweight, compact, microarray reader for gene expression analysis. This proposal explores the utilization of ellipsometry in conjunction with nanoparticle-based amplification for creating an imaging microarray reader. The feasibility of the principle will be demonstrated in Phase I with commercially available oligonucleotide microarrays. The sensitivity, spatial resolution, the ease-of-use of the reader will be tested and validated to fluorescence microarray based measurements.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
The proposed device is a basic research tool and has applications in the areas of toxicology screening, pharmacogenomics, drug discovery, antibody development and other applications. One of the primary applications will be in the area of infectious diseases detection: bacterial tests, viral detection and viral load determination, viral and bacterial genotyping, and blood screening applications. The reader could also be used in cancer diagnosis.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
A simple, sensitive, portable, lightweight, microarray reader for gene expression analysis is proposed. This device will have applications for NASA in both space and earth-based laboratories. Given the compact size, portable nature, and low power requirements, it is well suited for space-based applications. The device could be very useful as a clinical diagnostics tool for various ailments and could be used in space-based applications for monitoring the health of astronauts. In addition, it could be used in the examination of samples from other planets for markers of life and in monitoring the microbes that inhabit space stations to control contamination.
| PROPOSAL NUMBER: | 02- B1.02-8784 (For NASA Use Only - Chron: 023215 ) |
| SUBTOPIC TITLE: | Gravitational Effects on Biotechnology and Materials Sciences |
| PROPOSAL TITLE: | Enhanced Blackbody Sensors for the Quench Module Insert |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Plasma Processes, Inc.
4914 Moores Mill Rd
Huntsville , AL 35811 - 1558
(256 ) 851 - 7653
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Scott O'Dell
scottodell@plasmapros.com
4914 Moores Mill Rd
Huntsville , AL 35811 - 1558
(256 ) 851 - 7653
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Experiment Modules (EM) such as the Quench Module Insert (QMI) must be comprised of robust components to minimize the need for recalibration and refurbishment/replacement on the International Space Station. A critical aspect for proper operation of the QMI is thermal performance monitoring by blackbody sensors (BBS). Significant improvements in the ability of the sensor to monitor thermal performance could be realized by improving the joint quality between BBS rings and tantalum sheathed thermocouples. Modification of the sensor ring?s surface properties to increase its apparent emissivity would also benefit thermal performance monitoring. Therefore, novel laser brazing techniques will be developed for the production of robust joints between tantalum sheathed thermocouples and BBS rings. Additionally, a tantalum carbide emissivity coating will be evaluated for use with tantalum sensor rings for improved radiative heat transfer properties. Thermal cycle testing will be conducted to evaluate the joint quality of the enhanced BBS and the bond between TaC emissivity coatings and tantalum sensor rings. During Phase II, the techniques developed during Phase I will be optimized and using these techniques flight quality BBS will be produced for testing with QMI furnaces at Marshall Space Flight Center.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
Much emphasis is currently being placed on the development of high temperature, robust joining techniques for refractory metals, ceramics and composite materials for numerous commercial applications. The joining techniques that will be developed during this research can be used for many of these applications including, but not limited to, high temperature furnace and retort components, rocket motor throat inserts, radiation shields, heat pipes, power generation equipment, nuclear components, turbines, combustion chambers, incinerators, beam and sputter targets.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
With the deployment of the International Space Station, access to microgravity for materials science experiments will increase significantly. Robust furnace instrumentation and components are needed to maximize processing performance and the quality of the science conducted. Other relevant NASA applications include, but are not limited to, other high temperature joints, attachment of adjustment blocks to refractory metal cartridges, high emissivity coatings for sample ampoule cartridge assemblies (SACA), and tantalum carbide coatings for protection from molten metals.
| PROPOSAL NUMBER: | 02- B1.03-7777 (For NASA Use Only - Chron: 024222 ) |
| SUBTOPIC TITLE: | Bioscience and Engineering |
| PROPOSAL TITLE: | Chronic Telemetric Biofluid Flow Monitoring Device |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Integrated Sensing Systems, Inc. (ISSYS)
391 Airport Industrial Dr.
Ypsilanti , MI 48198 - 7812
(734 ) 547 - 9896
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Susan (Yafan) Zhang, PhD
yafan@mems-issys.com
391 Airport Industrial Dr.
Ypsilanti , MI 48198 - 7812
(734 ) 547 - 9896
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Currently, no method exists for continuously, noninvasively monitoring flow in the vascular and other biofluidic systems. To facilitate the study of short- and long-term effects of gravity on biofluidic systems, ISSYS proposes to develop an innovative technology for direct, chronic measurement of flow in the vascular system. The proposed effort will ultimately develop a stent-based, telemetric, implantable flow monitor. Once implanted, flow data may be read noninvasively through magnetic telemetry, using a compact readout unit. This system will take advantage of state-of-the-art Microelectromechanical Systems (MEMS) technology to develop a highly stable device for real-time, noninvasive collection of flow data. The core technology will be based on a high-sensitivity capacitive MEMS pressure sensor developed by ISSYS. The system will be fully spaceworthy, itself being immune to the effects of both microgravity and hypergravity as well as shock and vibration. Once the wireless, batteryless, stent-based flow sensor is delivered by catheter, flow data may be taken continuously by means of noninvasive magnetic telemetry. Phase I for this project will demonstrate the feasibility of calculating flow rates from measured pressure gradients, after which a subsequent Phase II effort would develop the complete implantable monitor and associated readout technology.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
? Understanding normal and abnormal cardiac mechanics and function
? Understanding abnormal fluid dynamics associated with ischemic heart disease
? Understanding abnormal fluid dynamics associated with valvular dysfunction
? Improving diagnosis and treatment of heart patients through better information about heart function and progressive dysfunction as determined by flow parameters
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
? Tools to permit understanding of biofluid mechanics
? Vascular fluid distribution on short and long time scales
? Cardiac output measurement
? Macro- and micro-scale biofluid mechanics of the vascular system in various environments, including microgravity
? Understanding the role fluid physics plays in human physiological processes such as cardiovascular flows and its effect on arteriosclerosis, and pulmonary flows and asthma
| PROPOSAL NUMBER: | 02- B1.03-8019 (For NASA Use Only - Chron: 023980 ) |
| SUBTOPIC TITLE: | Bioscience and Engineering |
| PROPOSAL TITLE: | Drag &Drop, Multiphysics & Neural Net-based Lab-on-Chip Optimization Software |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
CFD Research Corp
215 Wynn Dr.
Huntsville , AL 35805 - 1944
(256 ) 726 - 4800
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
S Krishnamoorthy
jls@cfdrc.com
215 Wynn Dr.
Huntsville , AL 35805 - 1944
(256 ) 726 - 4800
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The overall objective of this project is to develop a drag and drop, component library (fluidic lego) based, system simulation and optimization software for entire lab-on-chip systems. Current approaches for biochip system design are either very inefficient (trial-and-error based) or time-consuming (high-fidelity simulation-based). The proposed tool will benefit the biochip community by tremendously shortening design optimization times (minutes).
Representation of complex, interacting physico-chemical processes of a biochip in a system design tool is a formidable challenge. Our innovative solution seeks to use state-of-the-art high-fidelity simulations to develop and train Artificial Neural Network (ANN) based models for different components of a biochip. The Phase I effort will focus on proof-of-concept by (a) Development of multiphysics simulation-based ANN models for typical components of a biochip; (b) Demonstration of capabilities of the developed ANN model through optimization of a micromixing biochip. In Phase II, we will further develop and refine ANN models to account for additional multiphysics effects (electrokinetics, biochemistry, etc.) and dynamic response. The final product will feature a comprehensive library of components along with a user-friendly graphical user interface. CFDRC is the technology leader in multiphysics simulations for the biochip industry, and very well placed to successfully undertake this challenging task.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
CFDRC will also market the software to biotechnology companies. CFDRC has an already established client base in biotechnology sector such as Aclara Biosciences (see enclosed support letter), Applied Biosystems, Caliper Technologies, Sequenom, etc.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
Microfluidic technology is inherently advantageous for space applications due to the reduced size/weight, reduced power requirements as well as the ability to process multiple analyses in a standalone mode. The ANN based system simulation and optimization software will serve as a powerful aid to NASA's own biochip development initiatives. An example is the collaboration between NASA Marshall and Caliper Technologies to create macromolecular crystals aboard the
International Space Station using Caliper's LabChip technology. The tool will also be an invaluable asset for NASA's efforts to create a customized microfluidic chip specially designed for use in the microgravity environment of space. The software also enables the transfer of CFDRC's extensive expertise in the biochip design field to NASA teams.
| PROPOSAL NUMBER: | 02- B2.01-7435 (For NASA Use Only - Chron: 024564 ) |
| SUBTOPIC TITLE: | Understanding and Utilizing Gravitational Effects on Plants and Animals |
| PROPOSAL TITLE: | Miniature, Autonomous Electrochemical Multisensors |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Bipolar Technologies
4724 Brentwood Circle
Provo , UT 84604 - 5360
(801 ) 225 - 1974
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Rodney LaFollette
rmlafollette@aol.com
4724 Brentwood Circle
Provo , UT 84604 - 5360
(801 ) 225 - 1974
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
There is an increased need for sensors to monitor environmental conditions, that are not dependent on outside power. Remote sensors are used for this purpose, but they either require wiring to a power source or periodic maintenance to replace batteries. The difficulties with each approach severely limit the ability to obtain reliable information on environmental conditions.
The purpose of this work is to develop an integrated hybrid power supply for miniature, electrochemical remote sensors to detect biological conditions. With this power supply, sensors can be truly "autonomous,". Inexpensive sensors can then be distributed throughout a domain of interest. Sensors that use the hybrid power supply can be used to detect a wide range of environ-mental phenomena, such as chemical conditions, motion, humidity and temperature, and state-of-health conditions. The end result of this work will be an autonomous "lab-on-a-chip." It will be wireless for both power and data transmission, and can detect multiple phenomena simultaneously.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
Miniature autonomous "lab on a chip" devices can be used to monitor environmental conditions, home security, and health of many engineering systems. They can be useful in scientific work as well. The emerging Bluetooth technologies would be benefited by remote autonomous multisensors described in this proposal. The potential market for these devices is tens of millions of dollars per year.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
NASA needs small environmental sensors which are convenient to use, reliable, and inexpensive. These sensors will be used to monitor environmental conditions of a wide variety. This can be done both in terrestrial and other environments.
| PROPOSAL NUMBER: | 02- B2.01-7786 (For NASA Use Only - Chron: 024213 ) |
| SUBTOPIC TITLE: | Understanding and Utilizing Gravitational Effects on Plants and Animals |
| PROPOSAL TITLE: | Implantable, space-worthy, batteryless biotelemetric monitor for animal studies |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Integrated Sensing Systems, Inc. (ISSYS)
391 Airport Industrial Dr.
Ypsilanti , MI 48198 - 7812
(734 ) 547 - 9896
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Collin Rich, PhD
collin@mems-issys.com
391 Airport Industrial Dr.
Ypsilanti , MI 48198 - 7812
(734 ) 547 - 9896
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Many biological systems depend on fluid flow and pressure to achieve their intended functions. Tools are needed that allow noninvasive, real-time collection of pressure and flow-related data to study the impact of different environments and gravity ranges on biofluidic systems. To meet this need, ISSYS proposes to develop an innovative implantable, biotelemetric, batteryless pressure monitoring system. ISSYS will take advantage of state-of-the-art Microelectromechanical Systems (MEMS) technology to develop a highly stable device for real-time, noninvasive collection of fluid pressure data. Once implanted, the device requires no additional maintenance or calibration. This space-worthy system provides sensing technology that is miniature, requires minimal power, and is tolerant of vibration and acceleration. It will facilitate our understanding of gravitational effects by supporting animal studies of fundamental biological processes in the cardiovascular, neurological, urological, and gastroenterological systems, in space and on the ground. Phase I of this project will develop a prototype implantable sensor and demonstrate basic functionality using ISSYS' existing readout technology. A subsequent Phase II effort would customize the implant for specific in vivo applications (per NASA specifications), develop implantation methods as appropriate, and refine the readout to add user-friendliness. A complete system would then be validated in an animal model.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
? Implantable sensors for conducting medical research on biological pressures in animals and humans
? Implantable sensors for monitoring and aiding treatment of congestive heart failure or pulmonary hypertension patients
? Implantable sensors for monitoring shunt performance in hydrocephalus patients
? Technology base for wireless sensors with enhanced functionality (multiple sensor inputs, actuators, etc.)
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
? Implantable sensors for measuring biological pressures in animals, both in space and terrestrial
? Sensors requiring minimal power that can non-invasively measure pressure in environments with different gravity ranges
? Wireless sensors for remotely monitoring pressure or vacuum levels in sealed containers
| PROPOSAL NUMBER: | 02- B2.03-7965 (For NASA Use Only - Chron: 024034 ) |
| SUBTOPIC TITLE: | Understanding and Utilizing Gravitational Effects on Molecular Biology and for Medical Applications |
| PROPOSAL TITLE: | Cytometer on a Chip |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Ciencia, Inc.
111 Roberts Street, Suite K
East Hartford , CT 06108 - 3653
(860 ) 528 - 9737
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Dr. Salvador M. Fernandez
fernandez@ciencia.com
111 Roberts Street, Suite K
East Hartford , CT 06108 - 3653
(860 ) 528 - 9737
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The objective of the proposed effort is to develop a novel technology that will provide a unique and powerful alternative to conventional flow cytometry. This new system, which we call a cytometer on a chip will spatially sort cells on a microarray chip based on the presence of specific cell surface receptors or other surface features. Detection and quantitation is accomplished with grating-coupled surface plasmon resonance imaging (GCSPR). This is a label-free detection technology that obviates the need for fluorescent or other types of labels. This feature and the fact that the technology is amenable to miniaturization and consumes very little power, makes the cytometer on a chip system ideally suited to the assessment of immune function in space and to cost-effective, rapid, on site clinical diagnostics. In the Phase I we will evaluate the feasibility of the proposed concept with a lymphocyte model system and we will evaluate the system?s capability to separate cell populations and to distinguish between activation state.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
The proposed grating-coupled SPR cytometer presents a number of unique benefits, which should have considerable commercial value. It is not difficult to envision an eventual implementation of the cytometer on a chip with a portable, inexpensive, hand-held device for performing sophisticated immune function profiling on site (e.g., bedside) at very low cost, with immediate results. At the other end of the application spectrum, the chips could be used in high-throughput automated instrumentation for drug discovery research applications. Both of these potential commercial applications represent significant market opportunities.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
The proposed effort addresses directly addresses some of highest priorities NASA?s priorities for the cell biology area as stated in A Strategy for Research in Space Biology and Medicine in the New Century. Specifically, it addresses the need for highly automated, miniaturized instrumentation and advanced methodologies for biophysical measurements of cell functions, for quantitative applications of flow cytometry, and for new methods for measurement of immune cell function or other cell surface receptors. It supports NASA?s programs on gravitational effects on cell biology and medical applications.
| PROPOSAL NUMBER: | 02- B2.03-8052 (For NASA Use Only - Chron: 023947 ) |
| SUBTOPIC TITLE: | Understanding and Utilizing Gravitational Effects on Molecular Biology and for Medical Applications |
| PROPOSAL TITLE: | Optical Nutrients Monitor for Bioreactor Applications in Zero Gravity |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Intelligent Optical Systems Inc
2520 W. 237th Street
Torrance , CA 90505 - 5217
(310 ) 530 - 7130
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Dr. Raghuvir Singh
sbirproposals@intopsys.com
2520 W. 237th Street
Torrance , CA 90505 - 5217
(310 ) 530 - 7130
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Intelligent Optical Systems, Inc. proposes to develop a fluorescence detection based miniature multisensor probe and detection system to monitor cell nutrient parameters in zero gravity. The proposed sensor system can be integrated into NASA?s bioreactor hardware to enhance performance. Luminescent nano-particles will be used as fluorescent indicators to provide greater signal intensity and to reduce photo-degradation. The ultimate optical nutrients monitor will be capable of detecting and monitoring vital nutrient parameters such as pH, temperature, dissolved carbon dioxide, dissolved oxygen, and glucose. The device will provide a continuous, unmanned measurement of the bioreactor?s parameters. The optical monitor will require no reagent replacement and is projected to be capable of long term unattended real-time monitoring of cell culture media.
In Phase I, we will demonstrate the feasibility and sensitivity of the optical monitoring device and the single source fluorescence system using buffers and cell culture media (lacto bacillus). In Phase II, we will construct and test a field deployable prototype monitor to be used in a NASA bioreactor project.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
In addition to space applications, the proposed sensors will find immediate use in pharmaceutical and biotechnology industries. Fermentation monitoring, cell culturing, and tissue culturing are other important applications. The food processing, water processing and beverage industries are also candidates for these sensors. The medical diagnostic and monitoring fields also have a need for blood gas sensors and glucose sensors. Bioreactors of all types will have enhanced performance through the use of the IOS sensor suite.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
Use of the proposed sensor suite will enhance the results of bioreactors to be flown in space. In the future, the bioreactor will be used for biomolecule production, natural vitamin D3 production, culturing infectious diseases, and the development treatment devices for liver-disease. Other potential space/ medical applications include be studies in bone growth, cardiac tissue growth, drug efficacy, pancreatic tissue for transplantation. The IOS sensor suite will increase the controllability and performance of bioreactors
| PROPOSAL NUMBER: | 02- B2.03-8793 (For NASA Use Only - Chron: 023206 ) |
| SUBTOPIC TITLE: | Understanding and Utilizing Gravitational Effects on Molecular Biology and for Medical Applications |
| PROPOSAL TITLE: | Organic Thin Film Transistor for Microfluidic Flow Cytometry |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Agave BioSystems Inc
401 E. State St..
Ithaca , NY 14850 - 0000
(607 ) 272 - 0002
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Joel Tabb
jtabb@agavebio.com
401 E. State St..
Ithaca , NY 14850 - 0000
(512 ) 671 - 1369
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Agave BioSystems proposes to develop and demonstrate an innovative Organic Thin Film Transistor (OTFT) to detect cell characteristics without the need for cell labeling for use in microfluidic flow cytometers. This sensor would be able to detect count all cells, whether the cells are fluorescently labeled or not. This device would easily be able to detect the presence of cells within the channel as well as give information about the cell size and even the DNA content or intactness of the cell. The fact that cells will not need to be fluorescently labeled for detection is one of the major advantages of this device, since it can be used to measure live, unperturbed cells. Microfabrication of the OTFTs and microfluidic components will allow development of inexpensive, self-contained, disposable, high-throughput devices for screening of combinatorial chemical, biochemical or biological libraries. Assisting in this project will be Prof. George Malliaras of the Department of Materials Science and Engineering of Cornell University and Dr. James F. Leary, Professor and Director of the Molecular Cytometry Unit at UTMB-Galveston.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
Because the fluidic components of these microfabricated devices would be inexpensive to generate, they would be disposable, making them ideal for a number of laboratory and clinical settings, especially those involving the detection or sorting of infectious or otherwise hazardous samples. The potential for development of high-throughput devices would allow utilization in screening of combinatorial chemical, biochemical or biological libraries.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
Current systems are not well suited for use in low gravity environments or impose a significant cost in payload size and weight. The proposed device would be small, low-weight, low power, self-contained, and disposable making it be ideal for use in low gravity environments.
| PROPOSAL NUMBER: | 02- B2.03-8921 (For NASA Use Only - Chron: 023078 ) |
| SUBTOPIC TITLE: | Understanding and Utilizing Gravitational Effects on Molecular Biology and for Medical Applications |
| PROPOSAL TITLE: | FRET Aptamer-Based Glucose Sensor for the Rotating Space BioReactor |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
OmniSite BioDiagnostics, Inc.
101 W. Sixth Street, Suite 200
Austin , TX 78701 - 2932
(512 ) 479 - 7732
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
John Bruno
bruno@spec.com
101 W. Sixth Street, Suite 200
Austin , TX 78701 - 2932
(512 ) 479 - 7732
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
OmniSite BioDiagnostics Inc. (OmniSite) proposes to develop a novel DNA aptamer against glucose for the purpose of monitoring glucose levels in the rotating space bioreactor and eventually in astronauts or other human subjects. Aptamers are short (40?60 base) DNA or RNA chains selected from a randomized library for their affinity to a given immobilized target molecule (e.g., glucose). After several iterations of affinity selection followed by PCR amplification, rare high affinity oligonucleotides from the original random library emerge and dominate the nucleic acid population. If DNA aptamers are raised against glucose and then cloned and sequenced, they can be engineered with an intrachain fluorophore and quencher pair to fluoresce upon binding of glucose, because the fluorophore would be released from its quenched state (released from fluorescence resonance energy transfer; FRET). The fluorescence intensity would be proportional to the amount of glucose bound to the aptamers, thus enabling construction of a quantitative glucose sensor. Because DNA can be heated to release any bound target molecules, the sensor could be heat and flushed to make it reusable (a desirable feature for the space bioreactor to obviate frequent sensor maintenance). The entire sensor could eventually be constructed at the end of a fiber optic cable making it miniature and implantable in the bioreactor or in human subjects.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
Clearly, if successful, this project would hold great commercial viability for the food and pharmaceutical industries for continuous or reusable (long-term) on-line sugar and metabolite monitoring in such processes as fermentations or other large-scale cell culture processes. In addition, the technology might be extremely useful as an implantable glucose sensor for humans that could be used for patients in hospitals or for in home diabetic monitoring. Other biochemically relevant targets, other than glucose, would be possible as well, making FRET-aptamers a very lucrative technology.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
The proposed DNA Aptamer-FRET system would serve as a robust,reusable, and accurate glucose sensor for NASA's rotating space bioreactor. The system may also eventually be useful as an implantable glucose sensor for monitoring of astronaut physiology.
| PROPOSAL NUMBER: | 02- B2.03-9743 (For NASA Use Only - Chron: 022256 ) |
| SUBTOPIC TITLE: | Understanding and Utilizing Gravitational Effects on Molecular Biology and for Medical Applications |
| PROPOSAL TITLE: | Discovering Stress Related Gene Transcript for Bioreactor Monitoring |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
GENEXPRESS INFORMATICS INC.
P.O. Box 200759
Austin , TX 78720 - 0759
(512 ) 659 - 4539
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Robert Chin
rchin@austin.rr.com
P.O. Box 200759
Austin , TX 78720 - 0759
(512 ) 659 - 4539
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
GeneXpress Informatics, Inc. (GXI) and Dr. James P. Chambers of the University of Texas at San Antonio propose to use GXI's patent pending, Preferential Display (PD) technology to identify and isolate stress-related gene expression transcripts for the use in developing a real-time bioreactor monitoring system. GXI's Preferential Display (PD) technology is a paradigm shift in high throughput gene expression and analysis. The PD technology eliminates redundant sequences found between tissue types or bioreactor conditions by using a novel combination of biomolecular chemistry methods and fluorescence dye assay techniques. The envisioned PD assay would provide pre-sample preparation resulting in highly purified DNA samples for introduction into a microarray DNA chip for multi-analyte detection of stress related transcripts or biosignatures thus providing real-time monitoring of the bioreactor process and condition.
In Phase I, GXI and Dr. Chambers propose to develop and demonstrate the PD technology by identifying unique gene sequences expressed by cells under the effects of simulated bioreactor stress. In Phase II, GXI and Dr. Chambers propose to develop a PD assay format for spaceflight implementation into the dead leg of a rotating wall bioreactor vessels (RWV) or on other cells, rats and tissues from the Biotechnology Facility Rack.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
The PD technology offers a revolutionary technology to isolate and identify gene expression profiles of diseased versus normal tissues for use in developing microarray chips for medical diagnosis and monitoring of diseases. The databases generated will have a wide commercial market as new drugs or drug targets.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
Reducing redundant genes and thereby reducing gene noise by PD will allow NASA medical staff to evaluate crew members at the onset of up or down regulated gene expression changes due to prolong space missions. The quantification of these genes at the onset would provide a real time monitoring capability, which is not available at this time.
| PROPOSAL NUMBER: | 02- B3.01-7618 (For NASA Use Only - Chron: 024381 ) |
| SUBTOPIC TITLE: | Advanced Spacecraft Life Support |
| PROPOSAL TITLE: | Carbon-Supported Amine Sorbent Monoliths for Carbon Dioxide Removal |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Advanced Fuel Research Inc
87 Church Street
East Hartford , CT 06108 - 3728
(860 ) 528 - 9806
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Marek Wojtowicz
marek@AFRinc.com
87 Church Street
East Hartford , CT 06108 - 3728
(860 ) 528 - 9806
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The NASA objective of expanding the human experience into the far reaches of space will require the development of regenerable life support systems. On-board carbon dioxide (CO2) removal units play a key role in such systems ensuring high quality cabin air for crew members. Similar but more compact units are needed for extravehicular activities (space suit). The overall objective is to develop a CO2-removal system that possesses substantial weight, size, and power-requirement advantages over current systems (improved CO2 adsorption and lower pressure drop). The proposed innovation involves the use and manufacture of lightweight, porous carbon monoliths with controlled pore characteristics that will serve as support for the sorbent material (amines). The objective of the Phase I study is to demonstrate the technical feasibility of the above approach. This will be accomplished in the following three tasks: (1) Preparation and Characterization of Amine Sorbents Supported on Porous Carbon Monoliths; (2) Sorbent Testing; and (3) Product Assessment. The anticipated benefits include: (a) improved heat-transfer within the sorbent (increased CO2 capacity); (b) increased specific surface area (higher amine loading and, thus, increased CO2 capacity); (c) lower pressure drop (reduced power requirements); and (d) simultaneous removal of water vapor and trace contaminants.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
The carbon materials developed in this project could find spin-off applications in fuel cells and batteries. Greenhouse gas mitigation is another potential application. DOE is aggressively pursuing technologies beyond pumped aqueous amine systems that can be used for point source reduction of CO2. These systems must offer lower cost of capture compared to the pumped amine systems. Our solid amine systems can offer higher amine loadings and, therefore, better CO2 removal compared to the pumped systems. This can translate into smaller systems, lowering capital costs. Due to a lower power requirement, operating costs are also expected to be lower. CO2 scrubbing in the medical field offers additional opportunities (inhalation drug therapy and anesthetic CO2 removal). European and US manufacturers are having more difficulty with single-use CO2 scrubbers due to the increased disposal costs. Regenerable technologies will provide reduced cost when the overall life cycle costs are counted (e.g. disposal).
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
The main application of the proposed technology would be in spacecraft life-support systems, both in cabin-air revitalization and extravehicular activities (e.g., space suit).
| PROPOSAL NUMBER: | 02- B3.01-8163 (For NASA Use Only - Chron: 023836 ) |
| SUBTOPIC TITLE: | Advanced Spacecraft Life Support |
| PROPOSAL TITLE: | A Hybrid Pyrolysis/Incineration System for Solid Waste Resource Recovery |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Advanced Fuel Research Inc
87 Church Street
East Hartford , CT 06108 - 3728
(860 ) 528 - 9806
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Michael Serio
mserio@AFRinc.com
87 Church Street
East Hartford , CT 06108 - 3728
(860 ) 528 - 9806
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Both pyrolysis and incineration steps have been considered as the key solid waste processing step for a Controlled Ecological Life Support System (CELSS). Pyrolysis is more amenable to handling mixed solid waste streams in a microgravity environment, but produces a more complex product stream. Incineration produces a simpler product stream, but the incineration of mixed solids is a complex unit operation in a microgravity environment. Pyrolysis is endothermic and requires no oxygen, while incineration is exothermic and requires oxygen. This Small Business Innovation Research Phase I project addresses the feasibility of integrating pyrolysis and incineration steps into a system for processing of spacecraft solid wastes. This integration will take advantage of the best features of each process and result in an overall reduction in the system complexity and Equivalent System Mass (ESM). The objective of the Phase I study is to demonstrate the feasiblity of this integration process using a combination of bench scale experiments and modeling studies. This will be accomplished in four tasks: 1) Design and construct bench scale unit; 2) laboratory studies on solid waste processing; 3) evaluation of laboratory results; 4) preliminary design of Phase II prototype.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
In the near term, the technology would have applications to solid waste resource recovery problems in remote areas such as underdeveloped countries, artic regions, oil production platforms, rural areas, farms, submarines, ships, etc., analogous to the uses for NASA technology developed for water purification. In the long term, the technology could be integrated with microturbines or fuel cells and have widespread use business or residential use for solid waste removal and power generation. It could also be used by the DOD in military operations.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
The proposed work would make it technically feasible to process solid waste streams in space which will benefit long term space travel, such as a mission to Mars.
| PROPOSAL NUMBER: | 02- B3.01-8462 (For NASA Use Only - Chron: 023537 ) |
| SUBTOPIC TITLE: | Advanced Spacecraft Life Support |
| PROPOSAL TITLE: | Reclamation of Space Mission Water |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Compact Membrane Systems Inc
325 Water Street
Wilmington , DE 19804 - 2410
(302 ) 999 - 7996
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Hans Glaeser
hglaeser@compactmembrane.com
325 Water Street
Wilmington , DE 19804 - 2410
(302 ) 999 - 7996
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
For long duration exploratory space missions, reclamation of water for potable and hygiene uses from waste water is of vital importance. Approximatesly 230 kg of waste water are generated from four person crew during course of normal daily activities. Physicochemical methods presently in place (e.g. phase change and/or membrane processes) reduce total organic carbon (TOC) to 30-300 mg/liter.
Compact Membrane Systems (CMS) will introduce a novel passive membrane polishing system to remove most of remaining TOC. In Phase I, CMS will first fabricate this innovative polishing system for laboratory use and demonstrate removal of typical organics (e.g. ethyl alcohol, isopropyl alcohol) from 5000 mg/liter to 500 mg/liter. CMS will also develop key basic data associated with membrane transport, system design, and energy consumption to provide key economic evaluation for Phase II optimization. With no moving parts and projected enhanced performance compared to existing systems, CMS system should provide significant value for waste water clean-up.
CMS has large commercial partners in other membrane applications. Once CMS demonstrated feasibility in Phase I we are well positioned to work with these partners in Phase II in subsequent NASA and non-NASA commercial areas.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
This novel technology has broad dual use capability. In addition to removing trace organic compounds, it has the ability to biological growth (e.g. E-coli) and biological by-products (e.g. pyrogens). Therefore, this technique can be used to remove pyrogens and related materials for water for injection. It can also be used for oxidizing materials in ultrapure water in other applications including water used in semi-conductor applications. Our close working relationship with two major membrane companies will assist our non-NASA commercialization once Phase I feasibility has been demonstrated.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
Polishing of reclamation water and overall space shuttle disinfection are both of significant importance. This program focuses on introducing passive systems for removing trace quantities of organics from reclamation water. While this program is focused on water reclamation, the technology has broad potential and should also be of value (beyond this Phase I program) for air revitalization for removing trace gas contaminants.
| PROPOSAL NUMBER: | 02- B3.01-8478 (For NASA Use Only - Chron: 023521 ) |
| SUBTOPIC TITLE: | Advanced Spacecraft Life Support |
| PROPOSAL TITLE: | Advanced Microbial Monitoring System for Space Flight Applications |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Luna Innovations Incorporated
2851 Commerce Street
Blacksburg , VA 24060 - 6657
(540 ) 552 - 5128
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Roger VanTassell
vantassellr@lunainnovations.com
2851 Commerce Street
Blacksburg , VA 24060 - 6657
(540 ) 961 - 4502
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
A critical danger of space flight programs is contamination of the spacecraft environment. Assessing environmental health requires monitoring technologies to mitigate the risk of infectious disease among the crew before, during, and after flights. The danger of infectious diseases in space is amplified by the limited medical facilities available to the crew during a mission. The contained spacecraft environment also increases the likelihood of spreading disease-causing microbes among the crew with potentially catastrophic results. This risk is compounded on missions that utilize reclaimed water. Active, in-flight microbial measurement is required to protect the health of the crew and their environment. The challenge is that any microbial measurement system must address physical and operational limitations imposed by space flight. The Luna Innovations team proposes to develop a system to meet the challenge of microbial monitoring in space. The proposed system utilizes Luna's patented interferometric biosensor technology with novel reagents and Luna's space qualified optical fiber support electronics expertise to monitor microbial contamination. Luna has previously demonstrated biosensors with affinity films for the detection of biological samples, chemicals, and metal ions and will use this experience to ensure near-term market penetration of the proposed system.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
The enabling technology platform to be developed during the proposed Phase I program will allow Luna to produce a wide range of products with immediate, near-term and long-term market impact. Research concerning a microbial monitoring system will yield high-resolution, low-cost, portable, multi-target, sensor systems for applications in 1) water quality assessment, 2) environmental monitoring, 3) food safety inspection, 4) process monitoring, 5) bioremediation, and 6) home healthcare monitoring.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
Microbial growth of surfaces as well as that in storage containers has been a huge problem for NASA since the onset of space flight. With the proposed longer-term travels as well as extended time in the space station comes an increased problem of human infection. The proposed technology platform will allow NASA to safely monitor microbial growth in long-term space flight environments. Personnel will be able to perform screening tests for surface contamination, water reclamation and decontamination, and food safety to ensure overall personnel health and structural integrity of the space flight vehicle. This technology will also serve as a means to screen decontamination practices performed in space long before overgrowth of organisms becomes a problem.
| PROPOSAL NUMBER: | 02- B3.01-8520 (For NASA Use Only - Chron: 023479 ) |
| SUBTOPIC TITLE: | Advanced Spacecraft Life Support |
| PROPOSAL TITLE: | Microwave Powered Solid Waste Stabilization and Water Recovery |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Umpqua Research Company
P.O. Box 609
Myrtle Creek , OR 97457 - 0102
(541 ) 863 - 7770
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
James E. Atwater
jatwater@urcmail.net
P.O. Box 609
Myrtle Creek , OR 97457 - 0102
(541 ) 863 - 7770
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
A Microwave Powered Solid Waste Stabilization (MPSWS) system is proposed as the primary step in the treatment of solid waste materials generated during extended manned space missions. The proposed system will recover water initially contained within the wastes and stabilize the residue with respect to microbial growth. The dry waste may then be safely stored or passed on to the next solid waste treatment process. Using microwave power in a closed system, the MPSWS will selectively and rapidly heat the water present in solid wastes. Liquid phase water will flash to steam and superheat. The steam will contact all exposed surfaces and provide an effective thermal kill of all microorganisms present, in a manner similar to that of an autoclave. Both water and heat will be recovered in a condensing heat exchanger. Applicable solid wastes include, but are not limited to, inedible plant biomass, food scraps and fecal matter.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
Commercialization opportunities exist within both governmental and private sectors. For the private sector, the primary commercialization opportunity will be in the areas of biohazard containment and elimination and environmental remediation. The proposed technology offers many attractive features which can be utilized for the safe mass reduction and stabilization by disinfection and dehydration of solid hazardous wastes. Two private sector opportunities are immediately apparent: [1] hardware for the stabilization and disinfection of hospital waste, and [2] hardware for the destruction of biohazardous materials generated during biological, pharmaceutical, and biomedical research.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
The primary NASA application of the proposed technology will be as flight hardware required by NASA and its international partners to support future long duration manned missions in space, including Mars transit, Mars base, and lunar outpost missions.
| PROPOSAL NUMBER: | 02- B3.01-8629 (For NASA Use Only - Chron: 023370 ) |
| SUBTOPIC TITLE: | Advanced Spacecraft Life Support |
| PROPOSAL TITLE: | Miniaturized Water Recovery System for Advanced Life Support Systems |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Makel Engineering,Inc.
275 Fairchild Ave. Suite 106
Chico , CA 95973 - 8833
(530 ) 895 - 2771
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Dr. Darby B. Makel
dmakel@makelengineering.com
275 Fairchild Ave. Suite 106
Chico , CA 95973 - 8833
(530 ) 895 - 2770
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Makel Engineering Incorporated (MEI) proposes to design, build and demonstrate a prototype unit to significantly improve water recovery for Advanced Life Support System (e.g. International Space Station, Moon and Mars long duration manned missions, etc.). The current ISS Life Support System includes an adsorption based regenerative carbon dioxide removal system, and a water electrolysis system to produce oxygen. The hydrogen from the water electrolysis is vented to space in the life support system such as that which has been developed for Node 3. Carbon dioxide removed from the environment and hydrogen produced as a byproduct of the water electrolysis will be the reactants for our proposed water recovery system. Our proposed system will focus on two major areas of improvement: 1) the miniaturization of the system by use of microchannel reactor technology, and 2) the improvement of water recovery efficiency by the production of ethylene instead of methane. The technology developed for this project can be easily adapted for other Life Support and ISRU applications. In addition, for long term applications, the production of ethylene enables the production of other useful products, such as ethanol, nutrients, and polyethylene for habitat structures, which will increase the cost savings even more.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
There are at least four markets which exist for our microchannel chemical reactor technology.
1. Hydrocarbon Reformer for Fuel Cells
2. Natural Gas Upgrading
3. Processing Of Green House Gases
4. Other Microchannel Reactor Applications
These markets include the following customers:
- Off-grid Data Systems
- Homes Served by Rural Electric Cooperatives
- Urban ?Load Pockets?
- High-Income/High-Consumption Households Seeking Secure Backup Power
- Dissatisfied Utility Customers
- Premium Power Customers, UPS (Uninterruptible Power Supply) Systems
- High-Cost Residential Power
- New Homes
- Grid-Challenged Customers
- Developing Markets
- Fuel Cell Vehicles
- Gas to Liquid (GTL) Production
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
Affordable planning and execution of prolonged space missions depend upon the utilization of the waste products which are formed in manned spacecraft and surface bases. The technology developed for this project can be easily adapted to make maximum use of recycled materials, fully regenerative life support systems, and local indigenous materials. Processing of these materials can yield propellants, power generation (ethanol), life support consumables (nutrients), radiation protection, construction materials (polyethylene), and advanced habitation systems for other Life Support and ISRU applications. The technology is directly applicable to advanced regenerative life support systems by providing major savings in resupply. The NASA/government market is estimated to be $10M to $50M over the next ten years.
| PROPOSAL NUMBER: | 02- B3.01-9666 (For NASA Use Only - Chron: 022333 ) |
| SUBTOPIC TITLE: | Advanced Spacecraft Life Support |
| PROPOSAL TITLE: | Mesoporous Catalysts for Ambient Temperature Aqueous Phase Oxidation |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Umpqua Research Company
P.O. Box 609
Myrtle Creek , OR 97457 - 0102
(541 ) 863 - 7770
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
James R. Akse, Ph.D.
akse@urcmail.net
P.O. Box 609
Myrtle Creek , OR 97457 - 0102
(541 ) 863 - 7770
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Innovative ambient temperature oxidation catalysts based upon transition metal containing mesoporous supports are proposed. The self-assembly of amphiphilic surfactants, co-solvents, and oxide network formers is utilized to produce monolithic gels that can be readily converted to amorphous mesoporous oxide structures by thermal treatment. Using this approach, open structured mixed transition metal oxide supports with greater than 70% porosity composed of interconnected 10-30 nm pores with surface areas greater than 500 m2/g are formed. The catalytically significant transition metal sites are then combined with noble metal sites to produce highly active oxidation catalysts capable of ambient temperature operation due to enhanced oxidation activity combined with reduced mass transfer resistance compared to conventional catalysts. The Water Recovery System (WRS) aboard the International Space Station (ISS) uses a conventional catalyst to oxidize problematic organic contaminants that are difficult to remove by other methods. To provide sufficient oxidation, the three-phase reactor operates at 130*C and 0.50 MPa. Replacement of the current catalyst with one capable of ambient temperature operation will dramatically reduce WRS energy usage and system complexity. The Phase I project will demonstrate the feasibility of this approach. The Phase II program will deliver a prototype catalyst capable of efficiently oxidizing organic contaminants at ambient temperature.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
Ambient temperature aqueous phase oxidation catalysts will have numerous commercial applications. These include the elimination of organic contaminants present in wastewater or groundwater, or as an integrated component utilized for the production of ultra-pure water. Ambient temperature operation is an extremely attractive attribute for in situ environmental clean-up using a pump and treat system or where a reactive barrier must be incorporated to contain the spread of a contaminant plume. Current non-catalytic ultra-pure water production technologies focus along specific lines which do not effectively eliminate all contaminants and which will be challenged as maximum contaminant levels are lowered in the next generation facility. Ambient temperature catalytic processes will help meet these higher water quality standards in a cost effective manner. As a result of the Phase II effort, UMPQUA Research Company (URC) will have a working prototype catalyst to help market this process.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
The most readily apparent NASA application will be as a catalyst replacement in the Volatile Removal Assembly (VRA) within the current Water Recovery System (WRS) allowing ambient temperature operation of this component, and thereby, reducing system energy usage and complexity. As such, the catalyst will be purchased as Flight Hardware by NASA, or by an aerospace contracting firm on behalf of NASA, resulting in enhanced capability in support of manned missions aboard the International Space Station (ISS) and beyond where minimization of expendables and low power requirements are highly valued. In addition, ambient temperature catalysts allow purification at the point of use wherever organic contaminants tend to accumulate due to contamination from storage containers such as in the current generation of Contingency Water Containers (CWCs) used to transfer water from the Shuttle to the ISS.
| PROPOSAL NUMBER: | 02- B3.02-7519 (For NASA Use Only - Chron: 024480 ) |
| SUBTOPIC TITLE: | Space Human Factors and Human Performance |
| PROPOSAL TITLE: | Motion Sickness and Simulator Sickness: A Hand-Held Computerized Prediction Tool |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
RSK Assessments Inc
1040 Woodcock Road, Suite 227
Orlando , FL 32803 - 3566
(407 ) 894 - 5090
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Robert Kennedy
6kennedy@bellsouth.net
1040 Woodcock Road, Suite 227
Orlando , FL 32803 - 3566
(407 ) 894 - 5090
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
In travel, for those affected by it, motion sickness is a syndrome with adverse implications for performance and reduced quality of life. In addition to space motion sickness, simulator and Virtual Reality (cyber) sickness are modern forms of the malady that have become a great concern for those that use simulators for training and for the theme-park industry that uses like devices for entertainment. Thus, being able to identify those who are susceptible to motion sickness and under which circumstances, and predicting the occurrence and severity of motion sickness episodes would be of great societal benefit. Using the extensive data collections and assessment tools developed by us, and combining them with modern, on-line, and real-time analysis software, a hand-held screening tool will be created for researchers, practitioners and industrial applications.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
The NASA applications of the proposed Hand-held Computerized Prediction Tool and Data Base (HandyQuest) would be in the areas of training, screening and science/research. This device will be designed to evaluate persons for susceptibility to motion and cybersickness, as well as evaluate for severity once symptoms emerge. This will be useful for research, as well as safety and human use applications.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
The commercial applications of the proposed Hand-held Computerized Prediction Tool and Data Base (HandyQuest) would be in the areas of training, entertainment, health care, and science. Those involved in the study, prediction, prevention, and treatment of space/motion/simulator/VR sickness would be able to access a powerful tool that would combine a rich data set with modern, easy-to-use analytical applications. This will be useful for research and safety/human use applications as well.
| PROPOSAL NUMBER: | 02- B3.02-9727 (For NASA Use Only - Chron: 022272 ) |
| SUBTOPIC TITLE: | Space Human Factors and Human Performance |
| PROPOSAL TITLE: | An Intelligent Interface Design Elicitor and Construction Assistant |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Stottler Henke Associates, Inc.
1660 S. Amphlett Blvd. Suite 350
San Mateo , CA 94402 - 2526
(650 ) 655 - 7242
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Richard Stottler
stottler@shai.com
1660 S. Amphlett Blvd. Suite 350
San Mateo , CA 94402 - 2526
(650 ) 655 - 7242
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
We propose the development of an innovative software tool that will permit developers with little or no human factors training to produce user interfaces that are well suited to the end-users and their needs, as well as to the situation in which the software will be used. Developing such a tool represents a significant challenge; thus, we suggest an integrated approach drawing upon a broad range of AI techniques. An intelligent, visually-based knowledge elicitor based on decision-centered design will guide the developer through the task capture and analysis process. The resulting task model and a battery of intelligent design advisors, assisting in everything from modality selection to graphical element distribution, will allow the system to collaborate with the developer in constructing a user-centric interface. To leverage the results of usability testing, the system will be able to automatically modify and expand this set of advisors, insuring a consistent and highly usable interface. The combination of human factors and interface design expertise supplied by Klein Associates Inc., and SHAI's Artificial Intelligence expertise will guarantee the success of this project. We will absolutely demonstrate the feasibility of our ideas through the development of a Phase I system prototype.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
The proposed system can be marketed as a tool for interface development for small and medium-sized companies that cannot maintain an in-house human factors expert.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
The proposed system can be used to help produce the array of interfaces necessary for manned missions. It will insure that these interfaces are high-quality, intuitive, and user-centric.
| PROPOSAL NUMBER: | 02- B3.03-9487 (For NASA Use Only - Chron: 022512 ) |
| SUBTOPIC TITLE: | Human Adaptation and Countermeasures |
| PROPOSAL TITLE: | Spaceflight Urine Analysis System |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Creare Inc
P.O. Box 71
Hanover , NH 03755 - 0071
(603 ) 643 - 3800
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
David Kynor
dbk@creare.com
P.O. Box 71
Hanover , NH 03755 - 0071
(603 ) 643 - 3800
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Extended exposure to microgravity during spaceflight can result in excessive bone loss. Efforts to monitor bone loss during flight, to monitor astronaut health and guide the development and use of countermeasures, are limited by the lack of real-time biosensors for bone loss. This proposal addresses development of a novel system for noninvasive, real-time measurement of urinary calcium-a key marker for bone loss. The Urine Analysis System (UAS) developed under this program will rely on a colorimetric technique that is well suited for use in conjunction with the NASA Urine Monitoring System, as well as integration into an automated "smart toilet." We have established a uniquely qualified team for this project that includes expertise in biomedical engineering, optical measurements, construction of novel biomedical devices, and an STS-90 NASA payload specialist astronaut and physician with firsthand experience in the problems associated in measurement of bone loss during spaceflight.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
The technology developed under this program has the potential to be used for home-based monitoring in patients suffering from osteoporosis. Osteoporosis affects more than 14 million American women. Current technology requires them to make periodic visits to their physician to monitor the progression of their disease and determine the effectiveness of their treatment regime. This requirement leads to problems with bed-ridden patients and reduces compliance with ambulatory patients.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
The Urine Analysis System will permit, for the first time, real-time monitoring of urinary calcium during spaceflight. The data provided by our system will allow astronauts to evaluate the extent of their bone loss during extended periods in microgravity, determine when more aggressive countermeasures are needed to prevent or limit bone loss, and monitor the effectiveness of the countermeasures. Data collected by the system will provide a valuable database for guiding continued research in bone loss prevention.
| PROPOSAL NUMBER: | 02- B3.04-8291 (For NASA Use Only - Chron: 023708 ) |
| SUBTOPIC TITLE: | Food and Galley |
| PROPOSAL TITLE: | Biodegradable Nanocomposites for Advanced Packaging |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
TDA Research, Inc.
12345 West 52nd Ave
Wheat Ridge , CO 80033 - 1917
(303 ) 940 - 2339
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Dr. Andrew Myers
amyers@tda.com
12345 West 52nd Ave
Wheat Ridge , CO 80033 - 1917
(303 ) 422 - 7819
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
TDA Research, Inc. proposes to develop a biodegradable food packaging material that will address the issues of extended-life food storage and waste disposal in space. On long-term space missions, on board the International Space Station, or on future lunar or planetary facilities, a biodegradable food packaging plastic could be disposed of in composting environments that support agricultural production. Several biodegradable polymers are commercially available, but they lack the barrier properties needed for food preservation. TDA proposes to improve the barrier properties of biodegradable plastics with our proprietary nanocomposites. Much of TDA?s nanocomposite research has focused on the careful design of surface treatments to produce nanocomposites compatible with and dispersible in targeted host polymers. We have shown that we can form well-dispersed nanocomposites with several biodegradable plastics and, in one example, have demonstrated improved barrier properties without a loss in biodegradation rates. In this project we will apply this technology to poly(lactic acid) (PLA) ? a biodegradable plastic with polystyrene-type polymer properties. PLA is an excellent packaging material, and its improved barrier properties resulting from TDA?s nanoparticles would produce a biodegradable food packaging material capable of storing foods from extended missions.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
As a biodegradable bio-based polymer, PLA can be produced domestically at low cost, eliminating dependence on foreign petroleum supplies with their corresponding demand and price fluctuations. PLA is also biodegradable - an additional important feature that realistically addresses the problems of plastic waste generation. Successful development of high barrier PLA would find application in a variety of areas including consumer packaging applications, packaging for food and food service applications, and medical packaging. PLA nanocomposites also have the potential to replace several commodity thermoplastics like polyolefins and PVC in certain applications.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
Extended duration space missions require packaged, shelf-stable food sent from earth. In a closed system such as a spacecraft, waste disposal of these packaging materials must be disposed of in a cost effective way consistent with a dynamic life support system. Biodegradable food packaging materials could be recycled in-flight in hydroponic baths or to supplement the growing medium for wheat, potatoes, or other crops that can be grown inside a spacecraft.
| PROPOSAL NUMBER: | 02- B3.04-9336 (For NASA Use Only - Chron: 022663 ) |
| SUBTOPIC TITLE: | Food and Galley |
| PROPOSAL TITLE: | Fortification of Shelf Stable Formulated Foods with Antioxidants |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Newtrition Foods
14539 Oak Chase
Houston , TX 77062 - 2287
(281 ) 286 - 3767
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Beverly Swango
swango@newtritionfoods.com
14539 Oak Chase
Houston , TX 77062 - 2287
(281 ) 286 - 3767
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The innovation proposed through the SBIR is ?Fortification of Shelf Stable Formulated Foods with Antioxidants?. The addition or incorporation of isolated antioxidants into a processed food does not insure delivery in an appropriate amount and form in the final product. Multiple chemical reactions and physical changes initiated during processing and storage could deteriorate the functionality and/or bioactivity of these antioxidants in the foods. Experiments will be conducted in existent prototype food products developed previously for NASA?s food program. Selected antioxidants from the following categories: Phenolic Compounds, Vitamins, and Carotenoids will be incorporated in the food products during the pre-preparation/mixing phase of production. Products will be sealed and thermally processed to achieve commercial sterility. All pre-processing and thermal processing parameters will be optimized to aid in retaining appropriate levels of residual antioxidants. Food Samples will be analyzed for their antioxidant content and characterization by HPLC analysis. Antimutagenic tests will be conducted to define the bioactivity of the antioxidants. The ultimate goal of this proposal is to apply the knowledge gained from the sample products to further develop a full commercial product line of antioxidant enriched Shelf Stable Foods.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
Market data indicates that the Healthy Food Market represents a substantial segment in the commercial food industry. Recent characterization of anti-inflammatory, anticancer and antioxidant activities of phytochemicals such as carotenoids, phenolic compounds and some vitamins demonstrate the potential for developing functional foods with well-established scientific proof of reported health claims. Newtrition Foods has also identified funding sources to support marketing and commercial production of these foods during future Phases of this project.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
Long Term exploration will require foods that remain palatable, nutritious, and safe to eat for a 3 ? 5 year period. This concept is highly supportive to the NASA food program due to its directed dual benefit to aid in extending the shelf life of the formulated foods, and in aiding in the protection of astronaut?s health by counter balancing some of the effects of long term exposure to low dose radiation, which can cause free radical formation in biological tissue. The formation of free radicals may compromise the quality and nutrition of the food supply during extended storage.
| PROPOSAL NUMBER: | 02- B3.05-8130 (For NASA Use Only - Chron: 023869 ) |
| SUBTOPIC TITLE: | Biomedical R&D of Noninvasive, Unobtrusive Medical Devices for Future Flight Crews |
| PROPOSAL TITLE: | Novel Medical Diagnostic Instrument based on Real-time Breath Analysis |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Los Gatos Research
67 East Evelyn Avenue, Suite 3
Mountain View , CA 94041 - 1518
(650 ) 965 - 7778
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Douglas Baer
dsblgr@earthlink.net
67 East Evelyn Avenue, Suite 3
Mountain View , CA 94041 - 1518
(650 ) 965 - 7772
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Los Gatos Research proposes to develop and test a novel medical diagnostic instrument that will non-invasively measure the ratio of the isotopic abundances of 13C to 12C in exhaled breath. The instrument, based on a new technology called Off-Axis ICOS, will be inexpensive, portable, easy to use, and report measurements with sufficient sensitivity and precision to replace mass spectrometry in 13C-labeled breath tests for diagnosis of several diseases, including diagnosis of liver fibrosis, bacterial overgrowth, pancreatitis, irritable bowel syndrome, sepsis, and infection. For the proposed program, we will develop an instrument for measurement of the gastric emptying rate for diagnosis of gastroparesis and associated conditions. We will quantify the specificity and sensitivity of the instrument by incorporating it into on-going clinical trials during Phase II. The instrument will enable long-term studies of astronaut health based on non-intrusive breath analysis and thus addresses the needs of the Biomedical Research Program. The program will involve clinical testing in human subjects to demonstrate concept efficacy and thus meet Countermeasure Readiness Level 6. At the end of the program, the instrument will be available for evaluation with human subjects in controlled laboratory conditions simulating space flight environment and thus meet Countermeasure Readiness Level 7.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
In addition to the medical applications described above, the proposed technology may be used for real-time monitoring and control of chemical processing plants from measurements of important processes gases including CO, CO2, H2O, CH4, and various hydrocarbons, and for real-time monitoring of greenhouse gases, pollutants, and stable isotopes in the stratosphere and troposphere for validation and confirmation of atmospheric chemistry and transport models.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
The proposed instrument may be used for real-time determination of the health of an astronaut in flight and/or in ground-based studies based on the measurement of the stable isotopes of CO2 in exhaled breath. The instrument may be applied for detection of a broad spectrum of medical conditions including gastroparesis and associated conditions (e.g., gastroesophageal reflux disease), diagnosis of liver fibrosis, bacterial overgrowth, pancreatitis, irritable bowel syndrome, metabolic stress, sepsis, and infection.
| PROPOSAL NUMBER: | 02- B3.05-9088 (For NASA Use Only - Chron: 022911 ) |
| SUBTOPIC TITLE: | Biomedical R&D of Noninvasive, Unobtrusive Medical Devices for Future Flight Crews |
| PROPOSAL TITLE: | Transdermal Delivery System for Therapeutic Molecules |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Lynntech, Inc.
7610 Eastmark Drive, Suite 202
College Station , TX 77840 - 4024
(979 ) 693 - 0017
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Krzysztof Kwiatkowski
krzysztof.kwiatkowski@lynntech.com
7610 Eastmark Drive, Suite 202
College Station , TX 77840 - 4024
(979 ) 693 - 0017
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The development of portable systems for use in a zero gravity environment provides both NASA and astronauts with improved response in life-threatening crisis or prevention and/or ongoing treatment of a disorder. Portable systems for astronauts include a large range of devices including biosensors and drug administration devices. Current methods for administration of therapeutic molecules to treat illness or injuries to an astronaut while in space include the use of hypodermic needles and oral ingestion. Thus there is a great need to develop a therapeutic molecule delivery system that is non-invasive, painless, and accurate (within ?10%). In this project, we will develop a non-invasive, painless, transdermal therapeutic molecule delivery device. The device will uniquely combine microencapsulation of molecules and iontophoresis into a wearable system. The Phase I research will demonstrate the feasibility of iontophoretic transfer of microencapsulated drugs through a model skin sample using a microfluidic system. In Phase II, a pharmacological study of the release rate of the therapeutic molecules from microencapsulation will allow for further optimization of the microfluidic system to produce the complete delivery device.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
As a result of Congress passing the Needlestick Safety and Prevention Act in 2000, there has been a high need to develop a non-invasive drug delivery system to replace currently used hypodermic needles. Our transdermal delivery device can be used by healthcare workers in hospitals or by patients at home to administer needed medications. This device could help drive down the high cost of healthcare (currently $1.5 trillion in the U.S.) by eliminating costs associated with treatment of accidental needlesticks. In the future the delivery device could be linked to a non-invasive monitoring device to create a closed-loop system.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
The transdermal drug delivery system will provide NASA with a device for administering accurate doses of medication to astronauts while in space that is both non-invasive and painless. This wearable device will allow astronauts to continue their duties while receiving the needed medications to prevent or treat a disorder. The device is also beneficial to NASA by providing a lightweight wearable device that is battery powered and requires minimum training to use. In the future the delivery device could be linked to a non-invasive monitoring device to create a closed-loop system.
| PROPOSAL NUMBER: | 02- B3.06-7571 (For NASA Use Only - Chron: 024428 ) |
| SUBTOPIC TITLE: | Radiation Shielding to Protect Humans |
| PROPOSAL TITLE: | Carbon based aerogel composites for radiation shielding |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Advanced Ceramics Research, Inc.
3932 E Hemisphere Loop
Tucson , AZ 85706 - 5013
(520 ) 434 - 6392
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Ranji Vaidyanathan
r.vaidyanathan@acrtucson.com
3932 E Hemisphere Loop
Tucson , AZ 85706 - 5013
(520 ) 573 - 6300
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
In this phase I SBIR program, Advanced Ceramics Research, Inc. (ACR) proposes the development of an innovative, co-curing fabrication process for composite structures with a carbon based aerogel material encapsulated by a polyethylene based composite for radiation shielding applications. The proposed technique will leverage the ACR?s experience with co-injecting highly viscous ceramic slurries into fibrous preforms. The carbon based aerogel material will be fabricated into a panel and encapsulated by polyethylene using a elevated temperature RTM technique currently used to fabricate fiber reinforced multi-resin systems. The feasibility of the approach will be demonstrated using a carbon fiber reinforced aerogel encapsulated with fiber-reinforced polyethylene. The advantage is that the radiation shielding panels will also act as a thermally insulating material and therefore, will be a multifunctional material. Co-injection will permit the fabrication of multi-layer structures that do not have to be individually laminated; hence, it is possible to fabricate high performance radiation shielding panels that would be impossible to build using conventional methods. Additionally, the fabrication process is flexible to allow the use of optimal and hybrid fiber tows and architectures necessitated by the component design requirements.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
Potential commercial applications are in the aerospace industry that requires radiation shielding materials that also need to be thermally insulating.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
NASA potential applications are for the ISS and the 3rd Gen RLV's that require lightweight radiation shielding materials.
| PROPOSAL NUMBER: | 02- B3.06-8740 (For NASA Use Only - Chron: 023259 ) |
| SUBTOPIC TITLE: | Radiation Shielding to Protect Humans |
| PROPOSAL TITLE: | Microporous Carbon for Radiation Shielding and Hydrogen Storage |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Advanced Fuel Research Inc
87 Church Street
East Hartford , CT 06108 - 3728
(860 ) 528 - 9806
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Eric Rubenstein
ericr@afrinc.com
87 Church Street
East Hartford , CT 06108 - 3728
(860 ) 528 - 9806
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Advanced Fuel Research, Inc. (AFR) has developed a technology to provide radiation shielding, while simultaneously increasing the capacity of hydrogen storage tanks. This technology uses carbon foam filler with a complex pore structure (?microporosity?). The tank with the filler has, counter-intuitively, more capacity to store hydrogen than an otherwise empty tank. This technology increases hydrogen storage capacity for existing size tanks; or alternatively, for reduced tank size/pressure, the capacity is preserved. It has the most advantage with lower pressure storage containers. AFR proposes that this existing commercial carbon foam manufacturing/processing method can be used to identify and develop an important new aerospace structural/multifunctional material, with structural strength and important radiation shielding and hydrogen fuel storage properties. The objective of the Phase I program is to demonstrate the technical and economic feasibility of the proposed method. In Phase I, a number of carbon materials will be synthesized and tested to prove and illustrate the concept and efficacy. In Phase II, an extensive parametric study will be performed with the purpose of optimizing storage and shielding performance. A prototype hydrogen storage/radiation shield system will also be designed, constructed, and tested.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
Results of the proposed research will provide advantages for many aerospace applications, including aircraft, satellites, spaced-based defense systems, and shielding sensitive military and astronomical detectors from radiation damage/background. Additionally, the advances in hydrogen storage technology, independent of the radiation shielding properties, will benefit numerous industries. In the medium term, we will apply our proprietary technology to additional gas storage systems, with applications in correspondingly more industries and markets.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
The provision of radiation shielding for a Mars mission or a Lunar base from the hazards of space radiation (galactic cosmic rays, and solar energetic particles) is a critical technology since crew safety depends upon it and present estimates of deep-space radiation equivalent dose exceed present administrative limits applicable for low Earth orbit (LEO).
| PROPOSAL NUMBER: | 02- B3.06-9611 (For NASA Use Only - Chron: 022388 ) |
| SUBTOPIC TITLE: | Radiation Shielding to Protect Humans |
| PROPOSAL TITLE: | Interfacing Design Code and Simulation Code for Biological Shielding |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
ALTERNATIVE ENERGY SOLUTIONS, INC.
PO Box 230269
Boston , MA 02123 - 0269
(617 ) 373 - 3830
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Tom Paul
tom.paul@cern.ch
PO Box 230269
Boston , MA 02123 - 0269
(617 ) 373 - 2941
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
This project builds on experience in an SBIR phase I project which successfully determined that the particle transport code Geant4 could be applied to the simulation of biological shielding. Among the many lessons learned during phase I was that while the physics and functionality embodied in Geant4 is either already excellent, or clearly extendible as needed, the great lacuna lies in its ability to understand geometries specified by other tools, most notably CAD tools. To this end, while this proposal involves continuing to work with the physics of the program, the main focus is on developing the tools to match the representation systems intrinsic to Geant4 to those used by other tools which generate geometries. Based on discussions with NASA this is by far the most pressing issue for immediate application to space radiation shielding, and is certainly crucial for all commercial applications we envisage as a small business.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
The basic idea is to provide a standard description of geometrical and material information suitable for radiation shielding and mechanical work and tools to convert between it and commercial CAD and Geant4 formats. One beauty of this approach from a commercial point of view is that, once in place, this provides interconvertibility not only between Geant4 and CAD formats, but from one CAD format to another. Such functionality has clear commercial value both to end-users employing more than one CAD system, as well as to CAD suppliers themselves, allowing them to import foreign geometries or export their own in foreign formats.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
Geant4 provides a prodigious array of physics models and generic tools which application developers may exploit in writing Monte Carlo simulations of particle interactions in materials. Such a Monte Carlo approach is complimentary to the analytical approach adopted by NASA for its core radiation shielding simulation program. One principle issue which requires further attention, and is the focus of this proposal, is related to the description of complex geometries and allowing Geant4 to import geometry descriptions from CAD packages.
| PROPOSAL NUMBER: | 02- B3.07-8143 (For NASA Use Only - Chron: 023856 ) |
| SUBTOPIC TITLE: | Biomass Production for Planetary Missions |
| PROPOSAL TITLE: | Novel Isotopic Gas Analyzer for Plant Health Monitoring |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Los Gatos Research
67 East Evelyn Avenue, Suite 3
Mountain View , CA 94041 - 1518
(650 ) 965 - 7778
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Douglas Baer
dsblgr@earthlink.net
67 East Evelyn Avenue, Suite 3
Mountain View , CA 94041 - 1518
(650 ) 965 - 7772
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Los Gatos Research proposes to develop, test and deploy a compact, rugged instrument based on a new technology called Off-Axis Integrated Cavity Output Spectroscopy for plant health monitoring. This instrument will measure several important gas-phase quantities with high sensitivity, accuracy and specificity in real time without external calibration. The target measurement quantities include: the ratio of the isotopic abundances of 13C to 12C in CO2, the ratio of the isotopic abundances of 18O to 16O in H2O, and the concentrations of CO2 and H2O in air. The instrument will be the first remotely operable, easy-to-use system capable of measuring real time multiple gas concentrations and isotopic ratios with high precision and accuracy. By significantly increasing the accuracy and precision of trace gas measurements in the field, the Off-Axis ICOS instrument will allow determination of the rate of photosynthesis, transpiration, respiration and nutrient uptake, and thus of plant health, and facilitate controlled long-term studies. In Phase I, LGR will develop and test a prototype instrument that can measure the target quantities with useful precision, accuracy and repeatability. In Phase II, LGR will deploy the instrument in the field to demonstrate ruggedness, reliability, and the ability to record measurements over extended periods.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
In addition to the applications mentioned above, the proposed technology may be used for real-time monitoring and control of chemical processing plants from measurements of important process gases including CO, CO2, H2O, CH4 and various hydrocarbons, and for real-time monitoring of greenhouse gases, pollutants, and stable isotopes in the stratosphere and troposphere for validation and confirmation of atmospheric chemistry and transport models, and for breath analysis for medical diagnostics.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
The proposed instrument will allow determination of the rate of photosynthesis, transpiration, respiration and nutrient uptake, and thus of plant health, and facilitate controlled long-term studies.
| PROPOSAL NUMBER: | 02- B3.07-8790 (For NASA Use Only - Chron: 023209 ) |
| SUBTOPIC TITLE: | Biomass Production for Planetary Missions |
| PROPOSAL TITLE: | Deployable Vegetable Production System (VEGGIE) |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Orbital Technologies Corp
Space Center, 1212 Fourier Drive
Madison , WI 53717 - 1961
(608 ) 827 - 5000
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Robert C. Morrow
morrowr@orbitec.com
Space Center, 1212 Fourier Drive
Madison , WI 53717 - 1961
(608 ) 827 - 5000
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
ORBITEC proposes to develop a deployable facility called the Vegetable Production System (VEGGIE) to produce vegetable (salad) crops to supplement prepackaged foods during long stays in space. The innovation of the VEGGIE is in providing, within a single middeck locker, a plant growing facility with a growing area of 0.5 m2 to 1.0m2, a light source sufficiently intense for crop production, a compressible nutrient and water delivery system, and a semi-passive atmospheric control system that minimizes water use without limiting gas exchange. The system would be deployed using supports composed of telescoping beams, inflatable beams, or tension rods. To minimize complexity, VEGGIE would utilize the cabin environment for temperature control and as a source of CO2. The primary goals are to provide the crew with a palatable, nutritious and safe source of fresh food and to provide the crew with a tool for relaxation and recreation. VEGGIE could be used on the ISS as well as for planetary transit missions. Project objectives are to develop mechanisms to transition the VEGGIE from a small stowed configuration to a large growing area configuration, to develop a stowable lighting system and a compressible root zone, and to evaluate crop growth in the system.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
One potential commercial application for the Deployable Vegetable Production System would be in the area of horticulture therapy which is practiced in facilities for the aged, rehabilitation hospitals and clinics, prisons, and other settings where psychological and/or physical therapy is required. Nursing homes and elderly care centers have been shown to particularly benefit from horticulture therapy and the VEGGIE could provide a low-cost, easy to use (including handicap accessibility) tool in this therapy. Another potential use is in pre-college and college level science classes. Other terrestrial applications include use as an inexpensive residential or business decorative display or recreational garden. Advantages over existing growing small systems include the ability to store it in a very small volume so it can be easily transported between locations or put out of the way when not in use, and the novelty of an expanding plant growth system.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
In the very near term, VEGGIE could be utilized as a recreational facility aboard the ISS, providing a ?hobby? for interested crew and also providing a small amount of fresh vegetables with little impact to ISS resources. It could also be easily used in habitat analogs (Arctic bases, closed chamber tests, etc.). Longer term, VEGGIE could provide a significant level of diet supplementation, improve habitat aesthetics, and provide an outlet for personal creativity. Because the system can be stowed in a very small volume, it would be efficient to transport to a Lunar or Mars base. In all cases, if vehicle internal volume becomes stressed (e.g. visiting crew, increased work load) the VEGGIE can be easily collapsed and stowed away. The VEGGIE could help fulfill NASA?s requirements for increasing the habitability of long duration stays in space by providing a reliable, low resource use plant growth system.
| PROPOSAL NUMBER: | 02- B4.01-7532 (For NASA Use Only - Chron: 024467 ) |
| SUBTOPIC TITLE: | Telescience and Outreach for Space Exploration |
| PROPOSAL TITLE: | Grid-Based Distribution of Payload Video to Experimenters |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
AZ Technology Inc
7047 Old Madison Pike, Suite 300
Huntsville , AL 35806 - 2188
(256 ) 837 - 9877
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Jim Chamberlain
jimc@aztechnology.com
7047 Old Madison Pike, Suite 300
Huntsville , AL 35806 - 2188
(256 ) 837 - 9877
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Plans to distribute International Space Station (ISS) downlink video to Remote Principle Investigators (RPI) requires Internet 2/Abilene connections, multicast network capability, and 4 Mbps+ bandwidth capacity. Our goal is to make ISS downlink video much more accessible to RPI?s, NASA centers, and education/public outreach sites by converting the downlink video to lower resolutions, unicast, and widely used commercial-off-the shelf (COTS) formats. The approach will utilize low-cost personal computers and existing NASA, public, and research networks. The innovation is a low-cost, manageable, automated scheme for routing video in a standards-based computational grid environment.
Phase I will evaluate widely-used systems and codecs that are both proprietary and open standards-based for video distribution. The feasibility of coordinated Internet-based scheduling mechanisms to simplify operations in a grid environment will be evaluated. A demonstration will distribute experiment video in a networked environment. In Phase II the most promising capabilities will be incorporated into a prototype video distribution system and tested with larger groups in a grid environment, including researchers performing "live" ISS telescience and NASA educational audiences. Also, the feasibility of incorporating the video distribution system into a Space Operations Grid supporting a variety of payload carriers will be investigated.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
A successful Internet Protocol (IP)-based video system will provide cost-effective telescience support to the experimenter as well as provide excellent Web-based viewing opportunities for education and public outreach. The immediate market is hundreds of International Space Station experiment telescience users over the next decade. Additional markets are other NASA missions, as well as military and commercial mission operations applications. Mission operations-related modules that provide additional functionality to COTS products, such as RealSystema, can be marketed as third-party add-ons.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
A successful Internet Protocol (IP)-based video system will provide cost-effective telescience support to the experimenter as well as provide excellent Web-based viewing opportunities for education and public outreach. The immediate market is hundreds of International Space Station experiment telescience users over the next decade. Additional markets are other NASA missions, as well as military and commercial mission operations applications. Mission operations-related modules that provide additional functionality to COTS products, such as RealSystema, can be marketed as third-party add-ons.
| PROPOSAL NUMBER: | 02- B4.01-7839 (For NASA Use Only - Chron: 024160 ) |
| SUBTOPIC TITLE: | Telescience and Outreach for Space Exploration |
| PROPOSAL TITLE: | Wireless Handheld Device For Distributed Ground Operations |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
AZ Technology Inc
7047 Old Madison Pike, Suite 300
Huntsville , AL 35806 - 2188
(256 ) 837 - 9877
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Gerry Myers
gerry@aztechnology.com
7047 Old Madison Pike, Suite 300
Huntsville , AL 35806 - 2188
(256 ) 837 - 9877
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Operations on the International Space Station (ISS) currently require 24/7 support from Ground Operations personnel due to the relatively new establishment of that facility on orbit. As ISS activities become commonplace, the need for continuous monitoring by Ground Operations will wane. Automated and teleoperated systems as well as ISS crew experience will allow the Flight Controllers to leave their consoles for extended periods. The expertise of those persons will still be required but on an on-call basis. Wireless hand-held devices tied into the Mission Control Center?s live voice, video, and data systems can be used by the Flight Controllers to remotely access their consoles when the need arises. With such devices, these experts can be tied-in at a moments notice to handle both routine and emergency issues. Wireless transmissions can easily be intercepted so media encryption must be integrated into the devices. Commercial wireless hand-held implementations exist that can handle streaming audio, video, and data but not in real-time, not at the same time, and not in a secure manner.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
There is a huge non-NASA market for a wireless hand-held device capable of receiving live, encrypted audio, video, and data. Military officers on the battlefield can transmit field conditions and receive orders from a commander behind the lines. Business persons can extend a virtual presence at meetings they can not attend personally. Medical professionals can check on patients or be tied into the patient room in an emergency. Spectators at sporting events can use the device to hear announcer commentary, see close-ups of players and instant replays, and monitor player stats. This market is only in its infancy and there are no clear leaders.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
Initial applications will be directed at NASA and primarily ISS. Distributed Ground Operations is the focus of this SBIR but the principles and technologies developed can be extended to other ISS operations. Devices can be marketed to Principle Investigators (PI) and Remote Principle Investigators (RPI) to allow them to remain tied into their mission/experiment while away from their control center. As emergencies arise, they can use the devices to quickly diagnose and correct the problem. The innovative technologies discovered through this SBIR can be applied to other NASA non-ISS applications. Jet Propulsion Lab (JPL), Glenn Research Center (GRC), Johnson Space Center (JSC), Marshall Space Flight Center (MSFC), and others each have some form of Mission Control Center that can be distributed wirelessly in the same manner.
| PROPOSAL NUMBER: | 02- B4.02-7759 (For NASA Use Only - Chron: 024240 ) |
| SUBTOPIC TITLE: | Space Commercialization |
| PROPOSAL TITLE: | Compact Biological Aerosol Fluorescence Detection System |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Nanohmics, LLC
4302 Rimdale Dr
Austin , TX 78731 - 1222
(512 ) 415 - 8748
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Steve Savoy
ssavoy@austin.rr.com
4302 Rimdale Dr
Austin , TX 78731 - 1222
(512 ) 349 - 0835
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Nanohmics, LLC proposes to develop a compact fluorescence particle counter, biological aerosol detection system. The prototype instrument will combine fluorescence discrimination with aerosol counting techniques to provide a reliable warning of potential increase in biological particles inside spacecraft or space station crew environment. The proposed instrument is based on an innovative measurement strategy where all aerosol particles would be sampled but only suspicious particles interrogated by a UV/blue laser to measure fluorescence. An advantage of this conditional sampling strategy is that NASA personnel will be able to make measurements on a particle-by-particle basis to determine whether aerosols contain biological material. The result is that a small concentration of biological aerosols mixed with an abundance of non-biological particles can be detected. The instrument will exploit the autofluorescence of certain molecules contained in biological material and the size of particles to distinguish potentially harmful airborne bacteria from background aerosols. Particles detected as potential biological particles can then be collected in reagent buffer for further processing in analytical instruments for positive identification. The instrument developed in the Phase II program will support NASA's goal of developing an instrument to monitor the air quality of the spacecraft environment.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
The instrument developed in this program will identify and monitor the amount of airborne contaminants around municipal solid waste recycling and composting plants; monitor and track bioaerosols in health care facilities; monitor and evaluate the bioaerosol content in structures that have little recirculation with outdoor air; monitor the concentration and source of bioaerosols in a variety of indoor industrial environments; determine the amount of bio-pesticide that is outside of crop areas; and monitor the effluents from suspect biological warfare agent production facilities for treaty verification and compliance.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
A real-time method for characterizing bioaerosols does not presently exist. The instrument would support NASA's Earth Science Enterprise program by developing an instrument for characterizing bioaerosols in the earth's atmosphere. This instrument would also support NASA's mission for a permanent presence of man in space by continuously monitoring air quality to protect crew health. Aspects of this instrument would be utilized on space probes to assess acceptability of unknown environments for human habitation.
| PROPOSAL NUMBER: | 02- B4.02-8107 (For NASA Use Only - Chron: 023892 ) |
| SUBTOPIC TITLE: | Space Commercialization |
| PROPOSAL TITLE: | A Long-Duration Commercial Microgravity Mouse Habitat: Waste/Odor Technologies |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
BIOASTRONAUTICAL SYSTEMS DEVELOPMENT CO.
975 Waite Dr.
Boulder , CO 80303 - 2731
(303 ) 492 - 2341
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
James Clawson
clawson@colorado.edu
975 Waite Dr.
Boulder , CO 80303 - 2731
(303 ) 499 - 2460
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The Bioastronautical Systems Development Company (BSDC) proposes to develop habitat technologies for conducting long-term commercial research with mice in microgravity. Our research addresses solicitation section B4.02 Space Commercialization for the design/development of microgravity payloads for space station applications that lead to commercial products or services. In partnership with BioServe Space Technologies, we ultimately seek to offer an efficient, long-duration, EXPRESS-rackcompatible microgravity mouse habitat that will address BioServe?s growing demands from commercial affiliates expressing an interest in conducting research with mice aboard the International Space Station. Our focus on mice stems from the facts that pharmaceutical and biotechnology companies perform most pre-clinical examinations (80%) with mice, transgenic laboratory animals are nearly exclusively available in mice, and mice require fewer ISS resources (crew time, mass, volume, etc.) than rats. However, odors from mouse urine are considerably more odiferous than the urine from rats, the traditional animal used in microgravity biology studies. Therefore, this research addresses odor control and sanitation technologies for mouse waste, specifically the examination of various adsorption materials (e.g. carbon, zeolite, and bedding), separating humidity and odor control, and efficacy of a catalytic scrubber.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
The primary commercial application of this hardware is to enable the marketing of microgravity research and development to biotechnology and pharmaceutical companies. For example, our subcontractor, BioServe has a strong track record of promoting spaceflight pre-clinical research on the Space Shuttle with three flight investigations sponsored by Chiron Corp. (STS-60, 63 and 77) and a recently completed spaceflight investigation sponsored by Amgen Inc. (STS-108). Amgen has expressed a strong interest in flying mice on the Space Station. They are particularly interested in flying skeletally aged mice for 4-6 weeks to explore long-duration spaceflight as a model for Type II (senile) osteoporosis (as described in Part 5: Related R/R&D). If the described combination of age related bone loss in C57BL/6J mice and spaceflight were to become a validating step before proceeding to human clinical trials for senile osteoporosis, it would be worth millions of dollars to the biotechnology and pharmaceutical industry.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
Identifying effective waste and odor technologies that can operate within the constraints of a spaceflight payload could allow the use of the Animal Enclosure Module (AEM) for extended durations aboard ISS. Increasing the duration capabilities of the AEM would allow a broader range of investigations from both the commercial and science communities. It would also relieve the current cost and schedule pressure in developing the next generation animal habitat. This work will also assist the commercial programs in supporting their customers to conducting leading edge research on near term flight opportunities.
| PROPOSAL NUMBER: | 02- B4.03-9968 (For NASA Use Only - Chron: 022031 ) |
| SUBTOPIC TITLE: | Space Commercialization Infrastructure |
| PROPOSAL TITLE: | High-Power Ferrite Stripline Circulators/Isolators |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Hotech, Inc.
262 Clifton St.
Belmont , MA 02478 - 2648
(617 ) 484 - 8444
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Hoton How
hotonhow@yahoo.com
262 Clifton St.
Belmont , MA 02478 - 2648
(617 ) 484 - 8444
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
This proposal addresses the special needs of NASA facilitating the use of space for commercial products and services. With regards to space communications antenna array systems are regularly installed with spacecrafts and satellites to transmit electromagnetic signals at high power. As such, circulators/isolators are needed to separate signal paths in T/R modules, providing protection over the receiver circuitries avoiding high-power incidence. When applied at high power, nonlinearity sets in at the ferrite junction area causing communication channels to couple with each other. This is called intermodulation which ultimately limits the usefulness of a ferrite junction to be applicable at excessive power levels. In the past we have analyzed this nonlinear problem and have identified the origin for intermodulation. We envision two techniques to be effective. The first technique is based on the DC consideration ensuring circulation action to occur without activating the adverse terms in the equations of motion responsible for intermodulation. The second technique is AC in nature, demanding the circulator operation to induce minimum excursion in the transverse component of the magnetization vector. Temperature compensated ferrites will be considered in Phase II, giving rise to stabilized operation of the circulator applied at high power.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
The Phase I research admits immediate and unique applications of power circulators/isolators to be applied for communications over distances, for example, a relay station in the continent, a ship in the ocean, an airline jet in the sky, a satellite outside the earth?s atmosphere, and a spacecraft in space. To ensure high-quality communication intermodulation interference has to be immune from a circulator/isolator junction, and to our knowledge there is no such device existent in the current market. The success of this proposed SBIR research will no doubt fulfill the need of the market, and hence its commercial potential is tremendous
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
This proposal addresses the NASA's needs in using space for commercial products and services. More specifically, this proposal addresses the NASA's goals in Space Commercialization Infrastructure for which high-quality communications are pursued to enhance commercial operation in space or commercial satellites. Antenna systems are regularly deployed with spacecrafts and satellites to allow communications with radio stations on earth. Circulators and isolators are thus needed in the T/R modules to protect the receiver circuits from high power incidence. Due to the large distances involved in space communications, the transmitters allocated in space or satellites are required to operate at high power. However, the performance of a ferrite device degrades as power increases, resulting in considerably amount of noise in communications. The proposed SBIR research is to improve circulator/isolator performance at high power, thereby enhancing the quality of communications in space or commercial satellites.
| PROPOSAL NUMBER: | 02- B5.01-7782 (For NASA Use Only - Chron: 024217 ) |
| SUBTOPIC TITLE: | Biomolecular Sensors and Effectors |
| PROPOSAL TITLE: | A Wireless Communications Platform for Implantable Microinstruments |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Integrated Sensing Systems, Inc. (ISSYS)
391 Airport Industrial Dr.
Ypsilanti , MI 48198 - 7812
(734 ) 547 - 9896
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Matthew Straayer
straayer@mems-issys.com
391 Airport Industrial Dr.
Ypsilanti , MI 48198 - 7812
(734 ) 547 - 9896
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The innovation proposed is a platform for wireless communication based on magnetic telemetry that enables implantable micro instruments without batteries to acquire instructions, sense physical and chemical parameters, perform basic signal processing and on-site conditioning, and communicate information over 15cm. The platform, including electronics hardware and a protocol for a wide range of sensing devices and interfaces, will couple with emerging micro technologies for biochemical and biophysical applications to provide long term, implantable solutions. This proposal is innovative because the expected performance gains of the batteryless technology would enable much smaller implant sizes, increased transmission distance, and longer lifetimes than what is currently available today for monitoring chemical or physical parameters internal to the human body. In addition, this platform is capable of bi-directional communication that could allow for actively responding to individual needs such as closed-loop drug delivery. The Phase I effort involves designing the overall system architecture, proving the technical feasibility, and developing a prototype circuit design. Phase II builds on this platform and increases flexibility by incorporating a number of features into the electronics that enable the compatibility of a wide variety of interfaces and flexible performance options.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
? Implantable sensors for conducting medical research on biological pressures in animals and humans
? Hemodynamic monitors for aiding treatment of congestive heart failure patients
? Wireless implantable sensors for monitoring and aiding treatment of pulmonary hypertension patients
? Intracranial pressure / shunt monitors for treatment of hydrocephalus
? Intraocular pressure monitors for research of glaucoma diagnosis and treatment
? Closed loop drug delivery, such as glucose sensing and insulin delivery
? Oxygen sensors for dynamic pacemaker algorithms
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
? Wireless telemetry communication for micro biochemical and physical instruments and sensors
? Miniaturization of instruments through integration with MEMS-based sensors
? In situ measurement and real time control of biological and physical phenomena
? Capability for automated acquisition, processing, and communication of biological data
? Miniature bioprocessing systems which allow for precise measurement and closed loop control of multiple environmental parameters such as temperature, pH, oxygen, etc.
| PROPOSAL NUMBER: | 02- B5.05-7868 (For NASA Use Only - Chron: 024131 ) |
| SUBTOPIC TITLE: | Nanoscale Self Assembly using Biological Molecules |
| PROPOSAL TITLE: | Self-assembled Dual-functionality Microspheres |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
SBA Materials, Inc.
5290 Overpass Road, Ste. 131
Santa Barbara , CA 93111 - 2048
(805 ) 683 - 6102
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Earl Danielson
earldanielson@sbamaterials.com
5290 Overpass Road, Ste. 131
Santa Barbara , CA 93111 - 2048
(805 ) 683 - 6102
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The proposed objective is to develop a nanostructured self-assembled biomedical device whose function is mediated by device design at molecular, meso- and micron scale levels. The dominant innovation is a rapid ?single-pot? microsphere self-assembly process that features biomolecule-nanoparticle attachment. Syntheses of distinct nanoparticles functionalized with different organic moieties provide means for nanoparticle-biomolecular interac-tions not previously possible, first for amplified, localized specific therapeutic delivery, second for specific cell population targeting. These functionalized hybrid moieties are cooperatively assembled into hollow microspherical units in a highly controllable process, resulting in dual-function high therapeutic capacity delivery vehicles using biomolecular recognition principles. A therapeutic agent resides on an array of functionalized nanoparticles on the interior of hollow microspheres, while an antibody or short peptide is selectively assembled on nanoparticles on the microsphere?s exterior, permitting loading of therapeutic molecules and delivery. Based on principles of hierarchi-cal self-assembly, this system?s advantages include: 1) biocompatible reagents, 2) compatability with aqueous environments, 3) functionalized nanoparticle variety permitting multifunctional device delivery systems, 4) surface-attached proteins to provide a steering mechanism, and finally, 5) an ion-based opening mechanism, consequently amplifying targeted therapeutic treatment. These innovations enhance therapeutic agent delivery and molecular imaging in numerous medical applications, including those in space.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
Nanobiomedical science, real-time imaging at cellular level, increased bgdetection of disease onset before detectable by macroscopic methods, amplified targeted delivery of gene therapeutic and chemotherapeutic agents.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
Cellular delivery system for biological, therapeutic and magnetic agents providing drug delivery, gene delivery, and medical imaging.
| PROPOSAL NUMBER: | 02- E1.01-8023 (For NASA Use Only - Chron: 023976 ) |
| SUBTOPIC TITLE: | Passive Optical |
| PROPOSAL TITLE: | Fabry-Perot Double-Cavity Optically Controlled Narrow Tunable Bandpass Filter |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
New Span Opto-Technology Inc.
9380 SW 72nd Street, B-180
Miami , FL 33173 - 5460
(305 ) 321 - 5288
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Dr. Jame J. Yang
jyang@nsotech.com
9380 SW 72nd Street, B-180
Miami , FL 33173 - 5460
(305 ) 321 - 5288
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Spectral detection and recognition employing optical filter is an important tool for NASA?s mission on studying atmospheric and surface parameters and analyzing/monitor global environment changes. It can acquire information of biology and biogeochemistry of ecosystems, global carbon cycle, global water and energy cycle, atmospheric chemistry, and natural hazards. It is particularly important that the optical filter should be narrow passband, high transmission, high out-of-band rejection, accurate tuning, large tuning range, relatively wide field of view, and large aperture. Developing extremely narrow bandwidth (sub-angstrom) tunable filters can improve measurement capability of ground-based or airborne/space-borne remote sensing systems and can benefit terrestrial and space based LIDAR for weather sensing. New Span Opto-Technology Inc. proposes herein a new all-optical controlled Fabry-Perot double-cavity filter. The cavity structure of the filter is specially designed to simultaneously achieve narrow bandpass and large free spectral range. Highly control-light sensitive photochromic material as tuning medium makes all-optical control tuning practical and attractive. Phase I will demonstrate the feasibility of the proposed all-optical controlled double-cavity filter. Phase II will optimize the device design, fabrication, and result in a compact packaged tunable optical filter for NASA and commercial applications.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
The successful development of Fabry-Perot double-cavity optically controlled narrow tunable bandpass filter will benefit military applications including terrestrial and space based LIDAR for space weather sensing, ground-based and airborne remote sensing, and target identification and tracing. Commercial applications include optical network communications, optical remote sensing for weather forecast, agriculture, and astronomy observation. The tunable bandpass filter can also be used to construct an imaging spectrometer for medical diagnostic applications.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
In NASA?s Earth science measurement program, developing extremely narrow bandwidth (sub-angstrom) tunable filters for ground-based or airborne/spaceborne remote sensing systems is very significant for improvement of current measurement capability. The proposed double-cavity F-P filter when realized can benefit greatly to NASA applications, such as analyzing and monitoring global environment changes. It can acquire information of biology and biogeochemistry of ecosystems, global carbon cycle, global water and energy cycle, atmospheric chemistry, solid Earth and natural hazards.
| PROPOSAL NUMBER: | 02- E1.01-8607 (For NASA Use Only - Chron: 023392 ) |
| SUBTOPIC TITLE: | Passive Optical |
| PROPOSAL TITLE: | Tunable etalon arrays for Earth Science Measurements |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Tanner Research Inc
2650 E. Foothill Blvd
Pasadena , CA 91107 - 3439
(626 ) 792 - 3000
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Ravi Kant Verma, Ph.D.
ravi.verma@tanner.com
2650 E. Foothill Blvd
Pasadena , CA 91107 - 3439
(626 ) 792 - 3000
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
NASA requires new passive optical devices for Earth science measurements from various platforms. These components must be compact, light, reliable, with low power consumption and must be readily integrable into larger systems. One such optical component is an array of tunable Fabry-Perot etalon filters that transmits narrow wavelengths when irradiated with a broadband light source, and where the transmission wavelength can be tuned over a broad range. Tunable Fabry-Perot etalon filters comprise two parallel mirrors with an initial gap of ca. 0.5 to 10 mm (for desired optical properties); and whose separation can be adjusted by ca. 0.5 to 1 mm (for desired tuning properties). Because of the fine dimensional and parallelism control requirements, such devices are difficult to assemble ~ we are not aware of any other group that has successfully fabricated an array of tunable etalon devices.
We have used a novel MEMS approach to fabricate an array of tunable Fabry-Perot devices. This work was performed for the Active Optics Group at NASA Langley (Dr. Natalie Clark, ph: 757 864 4662); initial prototypes were delivered along with test data. We propose to further the development of such devices under this contract and to integrate them into larger systems.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
Our device, and the key technical innovation behind it have a broad array of applications within NASA and other government agencies. They can be used for chemical/biological detection (using the enhanced spectroscopic signature it provides), for star tracker systems, and for phase correction optics.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
In the commercial world, for instance, single tunable Fabry-Perot etalon filters are in great demand as optical performance monitors for the optical telecommunications industry. Arrays of tunable filters can be used as small screen (i.e. Palm Pilot size) display devices in the transmission mode, or as the front end of an array of photodetectors in digital cameras (currently, fixed red-blue-green filters are used).
| PROPOSAL NUMBER: | 02- E1.01-8848 (For NASA Use Only - Chron: 023151 ) |
| SUBTOPIC TITLE: | Passive Optical |
| PROPOSAL TITLE: | All-digital, CMOS-based Photodiode Camera |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Radiation Monitoring Devices, Inc.
44 Hunt St
Watertown , MA 02472 - 4699
(617 ) 926 - 1167
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
James F. Christian
jchristian@RMDInc.com
44 Hunt St
Watertown , MA 02472 - 4699
(617 ) 926 - 1167
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
CCDs (Charge-Coupled Devices), and more recently, CMOS (complementary-symmetry metal-oxide-semiconductor) APS (Active Pixel Sensor) cameras have revolutionized imaging instrumentation and the many fields that utilize these instruments. Both of these technologies rely on detecting, or integrating, the analog photo-current generated in each pixel, which limits their sensitivity and bandwidth. Counting individual optical photons with a Geiger detector provides the greatest sensitivity, and represents a true digital imaging approach that facilitates signal processing at the pixel level.
This program develops a fully integrated, digital camera chip, which is an application specific integrated circuit (ASIC), that counts individual optical photons using Geiger avalanche photodiodes. This all-digital, CMOS imaging technology fulfills the demanding requirements for providing high-resolution images at ~GHz speeds char-acteristic of CMOS processing architectures. In Phase I, we will explore appropriate fabrication architectures for the ASIC and fabricate prototype pixel elements, along with the critical circuit components needed to support the pixel element. We will test the prototype devices and compare their measured performance to the initial design specifica-tions.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
Non-NASA applications include low-light-level imaging, photography, diffuse optical tomography, nuclear imaging, x-ray imaging, (nuclear medicine). The proposed ASIC camera would find widespread use in instrumentation where compact, high-speed, hi-resolution imaging detectors are used. High-performance imaging detectors currently have a large commercial market, and as such, the proposed development holds a very high potential for commercialization.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
This technology benefits many imaging applications including the following NASA applications: Airborne, spaceborne or Unmanned Aerial Vehicle (UAV) instruments for imaging and measuring climate, meteorological parameters, aerosols, clouds, water vapor and other chemical constituents of the atmosphere, vegetation index, biological productivity, chlorophyll fluorescence, 2D and 3D surface terrain mapping, and ocean color measurements.
| PROPOSAL NUMBER: | 02- E1.01-9081 (For NASA Use Only - Chron: 022918 ) |
| SUBTOPIC TITLE: | Passive Optical |
| PROPOSAL TITLE: | High-throughput Tilt-compensated Interferometer |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Manning Applied Technology
419 South Main Street
Troy , ID 83871 - 0265
(208 ) 835 - 5402
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Christopher Manning
chris@appl-tech.com
419 South Main Street
Troy , ID 83871 - 0265
(208 ) 835 - 5402
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Feasibility testing of a novel high-throughput, tilt-compensated
interferometer design is proposed. The Phase I effort will
demonstrate a prototype and two manufacturing techniques
for lowering costs. The novel optical design offers excellent
interferometric stability, inexpensive manufacture and permanent
alignment. The design is attractive for remote sensing from both
aircraft and spacecraft, as well as commercial application. There
is at least one mission in the hardware testing phase, which
this combination of optical stability and stiffness would have
greatly benefited. The design has high throughput appropriate
for remote sensing, but would also have many industrial and
medical applications, particularly non-invasive measurement
of blood glucose levels and other human metabolites. Manning
Applied Technology has the expertise to enhance the performance
of the interferometer with powerful DSP hardware and software,
making it more attractive for commercial application.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
This highly-stable interferometer for use in Fourier transform
spectrometry has widespread industrial, medical and military
applications. By far the most important application is
measurement of blood glucose and other human metabolites.
The market impact for medical applications is measured in
billions of dollars. Other applications include a range of process
control, spectral imaging, environmental and occupational health
monitoring, laboratoyr research, field measurements and remote
sensing. Conservative estimates indicate a $10 million per year
market for the technology. Cost-effectiveness insures capture of
a significant market share.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
This interferometer has many desirable features for use in
remote sensing from satellite platforms, where it could
replace some current designs. NASA and its contractors
are currently solving problems of cryocooler vibrations
disturbing interferometer alignment. This interferometer
provides excellent resistance to vibration as well as high
interferometric stability. It also has applications in air
quality monitoring for spacecraft, crew health monitoring
and laboratory research.
| PROPOSAL NUMBER: | 02- E1.01-9222 (For NASA Use Only - Chron: 022777 ) |
| SUBTOPIC TITLE: | Passive Optical |
| PROPOSAL TITLE: | Laser Chemical Etching of Spectrometer Gratings |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
LMC Instrument Corp., D/B/A REVISE INC.
79 Second Ave.
Burlington , MA 01803 - 1482
(781 ) 272 - 9888
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Michael Burns
burns@revise.com
79 Second Ave.
Burlington , MA 01803 - 1482
(781 ) 272 - 9888
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
We plan to use Laser Chemical Etching (LCE, or also called Laser Microchemical etching, LMC), a "direct etch process" capable of true high resolution 3-D etching with micron resolution, almost arbitrary depth, high aspect ration, and extremely smooth surface finish (less than 40nm RMS), to produce convex gratings for use in Offner spectrometers. LMC is vastly superior to Excimer Laser Micromachining in essentially every aspect, from LMC's much higher control, uniformity of etch, and reproducibility to LCE's ultra-clean etching with only gaseous by-products (no debris). It has a number of attributes that can make it a better choice than e-beam lithography if production is an issue. We will demonstrate that LMC will allow the production of convex infrared gratings without the fabrication limitations of e-beam/optical lithography and without the limitations of ion milling, conventional etching, excimer laser micromachining, mechanical ruling, or conventional replication processes.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
Laser Chemical Etching will allow the production of non-flat (e.g. convex), as well as flat, gratings without the limitations of e-beam /optical lithography and the limitations of ion milling, conventional etching, excimer laser micromachining, mechanical ruling, or conventional replication processes. In addition, since this is a high-throughput "direct write" technology, it can not only be used for more rapid production of gratings, it can produce unique prototypes equally quickly.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
All of the NASA imaging spectrometer projects can benefit (or could have benefied) from LMC made 3-D gratings, be they conventional, convex, or holographic. Examples are:
AVIRIS (Airborne Visible/Infrared Imaging Spectrometer)
AIS-2 (Airborne Imaging Spectrometer)
HIRIS (High Resolution Imaging Spectrometer)
MODIS (Moderate Resolution Imaging Spectrometer)
SSTI HIS (Small Satellite Technology Initiative Hyperspectral Imager)
VIMS-V (Visible Infrared Mapping Spectrometer)
| PROPOSAL NUMBER: | 02- E1.01-9581 (For NASA Use Only - Chron: 022418 ) |
| SUBTOPIC TITLE: | Passive Optical |
| PROPOSAL TITLE: | An Ultra-Narrow Tunable Optical Bandpass Filter |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
MetroLaser, Inc.
2572 White Road
Irvine , CA 92614 - 6236
(949 ) 553 - 0688
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Dr. Vladimir Markov
vmarkov@metrolaserinc.com
2572 White Road
Irvine , CA 92614 - 6236
(949 ) 553 - 0688
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
MetroLaser proposes to design and develop an innovative ultra-narrow tunable optical bandpass filter (UNTOBF) based on the properties of a dielectric photonic crystal structure with a resonant cavity. Such a structure can exhibit an ultra-narrow high-transmission band in the middle of a wide low-transmission stop-band. During Phase I, we will demonstrate experimentally the proof-of-concept for an UNTOBF with sub-angstrom bandpass and a tuning range of at least 2 nm in both visible and infrared (IR) regions. We will also develop a complete model of the functional characteristics, based on specific features of photonic crystal structures with a resonant cavity, and develop a strategy for building a prototype of the instrument. Fine-tuning of the filter will be accomplished by varying the optical cavity length. The proposed filter is expected to have an acceptance angle of at least 1? and an aperture of about 2 inches. During Phase II the compact UNBTOF prototype module will be demonstrated with an expected tunability range of 10 nm and a bandpass range of 0.01 nm. A compact, low-weight, single-assembly design of the filter will allow it to be retrofitted to existing instruments and provide a stable performance in harsh operating environments.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
The proposed ultra-narrow tunable optical bandpass filter will find commercial applications in space-based and airborne multi-spectral imaging and remote sensing systems including LIDAR stations and meteorological instruments. It will expand capabilities for high accuracy spectral measurements within the tunable narrow spectral regions necessary for resolving individual spectral features. Due to its high spectral resolution, wide tunability range, compactness, ruggedness and stability, the proposed filter will allow for innovative solutions in high-resolution spectroscopic instrumentation, especially when portable devices are of interest.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
The proposed ultra-narrow tunable optical bandpass filter will expand the capabilities of NASA?s Earth Science Enterprise for high spectral resolution and high accuracy measurements of atmospheric and surface parameters from space and airborne platforms. These include measurements of biological productivity of land and ocean, measurements of climate and meteorological parameters, and terrain mapping.
| PROPOSAL NUMBER: | 02- E1.02-8213 (For NASA Use Only - Chron: 023786 ) |
| SUBTOPIC TITLE: | Active Optical |
| PROPOSAL TITLE: | A High Repetition Rate, Low Voltage EO Q-Switch for Lightweight Pulsed Laser |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Boston Applied Technologies, Inc.
62 Kerry Dr.
Mansfield , MA 02048 - 3433
(781 ) 354 - 0054
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Dr. Yingyin Zou
kzou@bostonati.com
62 Kerry Dr.
Mansfield , MA 02048 - 3433
(508 ) 339 - 9247
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
An all-solid portable lidar system is desired as a prominent instrument for monitoring various atmospheric phenomena. Lidar return signal from targets inherently suffer from noise caused by atmospheric variations. Increasing laser energy and improving receiver photon sensitivity enable longer-range lidar capability but will not always improve the lidar system performance. The laser pulse repetition rates from most of the solid state lasers used for lidar system are in the tens Hz, which means only tens of samples are collected per second. Increasing the laser repetition rate and date collection speed can be significantly improved the return signal to noise ratio. Boston Applied Technologies proposes to develop and fabricate a novel Q-switch based upon our break through electro-optic ceramic development. The Q-switch will have high repetition rate, variable pulse width, low optical loss, low voltage, compact size and light weight, as well as the ceramic ruggedness for high power handling and long term stability. Prototype Q-switch devices will be developed and demonstrated in Phase I. The proposed Q-switch will greatly enhance and leverage NASA lidar system.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
The anticipated commercial application will in laser Q-switching. The device can also be used, with additional components and some modification, for polarization modulation and high power light modulation.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
The developed Q-switch can be used to build portable, light weight lidar system for NASA?s atmospheric sensing and monitoring. It also can be used for high power, high repetition rate laser system.
| PROPOSAL NUMBER: | 02- E1.02-8857 (For NASA Use Only - Chron: 023142 ) |
| SUBTOPIC TITLE: | Active Optical |
| PROPOSAL TITLE: | Tunable, High Power Fiber Optic Laser for Lidar Applications |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
SIGMA RESEARCH AND ENGINEERING CORP.
9801 Greenbelt Road, Suite 103
Lanham , MD 20706 - 6204
(301 ) 552 - 6300
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Marcos Sirota
marcos.sirota@sigmaspace.com
9801 Greenbelt Road, Suite 103
Lanham , MD 20706 - 6204
(301 ) 552 - 6300
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
We propose to develop a fiber laser which can be tuned over the range of 1530-1575 nm,produce high pulse energy at pulse rates from CW up to 10 KHz, has a narrow line width, and can simultaneously lase on two tunable wavelengths. Additionally, this laser will operate within the ?eye safe? range. A laser of this type would be attractive for conventional lidar and altimeter systems as well as wind lidar and DIAL systems. With the addition of a fiber amplifier this laser would eventually be capable of generating pulses on the order of tens of milli-joules, an amount suitable for space-based lidar systems. The laser output could be doubled into the near-IR range, tripled into the visible range, and quadrupled into the UV range of 382 to 394 nm.
We propose to combine the dual wavelength fiber laser developed by Jin U. Kang of Johns Hopkins University with multi-mode methods developed by Fabio Di Teodoro of the Naval Re-search Lab.
If successful, these lasers would provide a breakthrough for ground based, airborne and space based lidars due to their combination of eye safe wavelengths, high power, tunability, and capability for dual wavelength operation. Their inherent solid state structure and lack of external components make them ideal for space applications.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
A high repetition rate, tunable, high power fiber laser would mean a break through in commercial laser technology. With the capability to tune and double, triple and quadruple the output frequency, most of the visible and soft UV spectral region could be covered, producing a new tool for laboratory and field research. In the scientific lidar sector, this laser could be implemented in various types of lidar/altimeter systems used in global studies and weather modeling. In R&D labs in academia or industry this laser would be an excellent source at wavelengths where other sources are cumbersome (OPO?s), and would offer greater flexibility. In the commercial sector this laser can be implemented in airport-based instruments (i.e. ceilometers, windshear detection) and urban pollution monitoring systems where reliability, ease of maintenance and eye-safety are paramount. Other applications include remote sensing of chem-bio agents, in urban and military environments. Overall market could be measured in several hundreds to few thousand units.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
A high repetition rate, tunable, dual wavelength, high power fiber laser operating at eye safe wavelengths would be a breakthrough source for wind, water vapor, aerosol lidar, and altimetry systems. There is great need for lidar measurements of wind profiles as well as atmospheric constituents which this laser would enable, the last one particularly through its dual wavelength capability. Furthermore, a large fraction of the visible and soft UV spectral region could be covered by conversion, producing a tool for laboratory and field research not currently available. Its all fiber construction makes it a rugged compact, alignment insensitive system, ideally suited for space applications. The goal of this proposal is to demonstrate power scalability to obtain the per-pulse energies necessary for space based systems. If successful, this technology would provide a good alternative to Nd-Yag lasers for similar missions to GLAS, MLA and VCL in the future, and become a true enabler for missions with more stringent requirements.
| PROPOSAL NUMBER: | 02- E1.02-8892 (For NASA Use Only - Chron: 023107 ) |
| SUBTOPIC TITLE: | Active Optical |
| PROPOSAL TITLE: | Quantum-Cascade-Laser-Seeded OPO for DIAL |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Q-Peak Inc
135 South Road
Bedford , MA 01730 - 0000
(781 ) 275 - 9535
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Mr. Glen Rines
grines@qpeak.com
135 South Road
Bedford , MA 01730 - 0000
(781 ) 275 - 9535
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
We propose an all-solid-state, laser-based source that covers the 2.5- to 14-?Ym band and is suitable for use in airborne and space-based differential absorption lidar (DIAL) systems. The proposed DIAL transmitter would enable high-resolution, high-accuracy remote sensing of atmospheric molecular species of interest to NASA including carbon monoxide, carbon dioxide, methane and nitrous oxide as well as many others. To date there have been no sources in this region suitable for NASA DIAL missions. The proposed source is comprised of a diode-laser-pumped, Q-switched, 2-?Ym laser, which pumps a middle-wave-infrared (MWIR) optical parametric oscillator (OPO), that is injection-seeded with a quantum cascade laser (QCL) to provide a narrow linewidth. The primary innovation is the use of recently developed distributed feedback (DFB) QCLs to injection-seed a MWIR OPO for the purpose of obtaining narrow linewidth, high-pulse-energy operation in a compact, simple configuration. A secondary innovation is the specific selection of other critical system components that make the overall system suitable for airborne and space-based instrumentation. These include the all-solid-state 2-?n?Ym pump laser and the MWIR OPO, which can be constructed with either zinc germanium phosphide (ZGP) or cadmium selenide (CdSe) depending on the wavelength coverage desired.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
In addition to the NASA DIAL application there are a number of commercial and military applications for this technology. Commercial applications include pollution monitoring using the same DIAL technique and non-destructive analysis of composite materials in high-value structures such as aircraft. Military applications include IR countermearsures, 3-D imaging for target identification and ordinance guidance, multi-spectral imaging for surveillance and targeting.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
The primary NASA application for the technology proposed is in airborne and space-based DIAL systems. As note in the Related R&D section, NASA has already applied QC lasers to point-sensing instrumentation with success. This technology would allow DIAL to be extended into the MWIR region of the spectrum, which allows a very broad range of molecular species to be studied via remote-sensing as opposed to point-sensing techniques. This opens up the possibility of profiling the atmosphere more thoroughly and with high accuracy.
| PROPOSAL NUMBER: | 02- E1.02-8894 (For NASA Use Only - Chron: 023105 ) |
| SUBTOPIC TITLE: | Active Optical |
| PROPOSAL TITLE: | High-Power Pump Laser for Ozone Lidar |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Q-Peak Inc
135 South Road
Bedford , MA 01730 - 0000
(781 ) 275 - 9535
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Dr. Yelena Isyanova
isyanova@qpeak.com
135 South Road
Bedford , MA 01730 - 0000
(781 ) 275 - 9535
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
A high-priority goal in the NASA ESE Science Plan is to understand and predict the tropospheric distribution, chemistry and transport of ozone. Lidar measurements from low earth orbit can provide a global survey of tropospheric ozone and aerosol layers with high vertical resolution. These observations can be complemented by regional measurements with lidars on small aircraft at higher spatial and temporal resolution. This synergistic approach can determine the global chemical and radiative consequences of tropospheric ozone and aerosols. We propose to develop and demonstrate a key component of a laser transmitter that can meet the performance requirements of both systems. In contrast to solid state, diode-pumped, high-energy, low-pulse-rate transmitters that have been considered for ozone lidar systems, our innovative approach is to use a high-pulse-rate (1 kHz) source with similar average powers to low-pulse-rate systems, but greatly reduced energies per pulse. The resultant reduction in the number of diodes and the size of the beam-handling optics leads to a lower-cost, lighter weight system, advantages for both the satellite- and aircraft-based systems.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
The proposed high-energy MPS technology would be an extension of our existing diode-pumped product line and would offer a step-up in power and energy from our existing products, into the 100-W range now served by more conventional lamp-pumped Nd:YAG lasers. A MPS Nd:YLF laser with 100 mJ/pulse energy, 1-kHz rate and high beam quality could provide a relatively low-cost solution for precision machining applications such as marking, cutting, welding and drilling, of interest to the electronics, automotive and medical-device industry. Q-Peak, as it is now doing with the MPS product line, would strive to establish OEM relationships with systems integrators who supply machining and processing tools to end customers.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
The work proposed here has direct application to the development of aircraft and satellite-based ozone DIAL systems. The pump source would drive a nonlinear conversion system to generate UV wavelengths suited for ozone sensing from different platforms. Other NASA applications for the pump source would be in precision altimetry for earth and other planetary investigations. The source, combined with other nonlinear optics, could also serve as the DIAL transmitter for probing of other species than ozone. In particular, combined with optical parametric oscillators, the source we develop could provide broadly tunable infrared for sensing of a wide variety of molecular species.
| PROPOSAL NUMBER: | 02- E1.02-9748 (For NASA Use Only - Chron: 022251 ) |
| SUBTOPIC TITLE: | Active Optical |
| PROPOSAL TITLE: | Active Sensors |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Aculight Corporation
11805 North Creek Parkway S. Suite 113
Bothell , WA 98011 - 8803
(425 ) 482 - 1100
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Dave Shannon
dave.shannon@aculight.com
11805 North Creek Parkway S. Suite 113
Bothell , WA 98011 - 8803
(425 ) 489 - 1100
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The purpose of this Phase I program is to demonstrate the feasibility of a compact, frequency tripled Nd:Y2O3 laser system to generate 305nm and 315nm for global tropospheric ozone sensing from space. Because Nd:Y2O3 can generate output on both the 915 nm transition and the 947 nm transition, the desired ozone UV DIAL wavelengths of 305 nm and 315 nm can be generated using a SINGLE laser device that incorporates 3rd harmonic conversion. The current laser transmitter for UV DIAL monitoring of ozone from satellite platforms is relatively large and requires 2 DPSS laser sources in addition to 5 non-linear conversion steps, whereas the Nd:Y2O3 based system may require as few as 1 DPSS laser source and 2 non-linear conversion steps. The minimal component count, small size and weight, and reduced power requirement makes a DIAL laser transmitter based on Nd:Y2O3 a very attractive choice for space based remote sensing. The proposed technology would allow NASA to continue to make rapid and dramatic technological progress in global ozone mapping.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
Aculight has a strong commitment to commercialize the 900 nm laser source proposed here as the "laser engine" for several emerging commercial markets. Commercial applications for ultraviolet versions of the laser proposed in this work include; UV sources for memory repair and UV Resonance Raman spectroscopy, remote detection of explosives (i.e. TNT), production of Fiber Bragg Gratings for Telecom and fiber sensors, as well as compact sources for stereolithography (rapid prototyping).
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
In addition to NASA's need for a compact and low-cost UV laser transmitter for ozone sensing, various harmonics of the basic infrared laser can be used for remote sensing of water vapor, aerosols in the atmosphere using Lidar or DIAL, detection and monitoring of NO & NO2, and space-based UV Raman Spectroscopy instruments. Aculight will continue to develop diode-pumped solid-state laser technology for NASA's future remote sensing needs.
| PROPOSAL NUMBER: | 02- E1.02-9963 (For NASA Use Only - Chron: 022036 ) |
| SUBTOPIC TITLE: | Active Optical |
| PROPOSAL TITLE: | Ultra-compact high power micro-chip lasers |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Boston Laser Inc.
1 Upland Road
Norwood , MA 02062 - 1546
(781 ) 255 - 1780
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Tigran Sanamyan
sanamyt@bostonlaserinc.com
1 Upland Road
Norwood , MA 02062 - 1546
(781 ) 255 - 7297
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
A complete synthesis of semiconductor, solid-state as well as fiber laser technology for the mass production of miniature solid state lasers is proposed. The adaptation of micro-chip technology to semiconductor fabrication processes enables the implementation of automatic manufacturing techniques to the construction of solid-state lasers for the first time. The micro-chip is pumped by a diode laser, where both lasers are fixed onto a single heat sink using only one automatic tool involving automated vision equipment.
Pulsed operation of the micro-chip lasers is enabled by additional micro-crystal elements inside the micro-chip laser cavity, allowing also for single frequency operation. Nonlinear frequency conversion can further be implemented to cover the whole spectral range from the UV to the far IR. The micro-chip laser pulses are amplified to the sub J energy level in large core fiber amplifiers pumped by high brightness diode lasers.
The proposed micro-chip fiber laser system addresses the component need for advanced lidar instruments. By synthesizing semiconductor, micro-chip and fiber technology, a superior laser source is constructed. This novel laser source can be deployed in a variety of NASA applications, such as the measurement of planetary surface topography, general altimetry, cloud and aerosol mapping as well as mapping of wind fields.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
The eventual aim of the project is the mass production of miniature solid-state laser packages. The availability of high power coherent light at a variety of wavelengths from a mass-producible component has the potential to truly revolutionize laser technology in multiple areas. In conjunction with nonlinear frequency conversion techniques ultra-low cost RBB sources can be constructed, promoting cost competitive laser display technologies for mass markets. In conjunction with fiber amplification, laser marking and machining application traditionally covered by Nd:YAG lasers will be targeted.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
The miniaturization achievable with the unique synthesis of diode laser, solid-state laser and fiber laser technology is ideal for any air born applications. The elimination of organic materials in the construction of the proposed laser is further ideal for space born systems. Basic fiber amplified Q-switched micro-chip lasers can be used in planetary surface topography as well as general altimetry. Fiber amplified single-frequency Q-switched micro-chip lasers are further compatible with cloud and aerosol mapping. Frequency-shifted systems can further be deployed in wind laser transmitters.
| PROPOSAL NUMBER: | 02- E1.03-8224 (For NASA Use Only - Chron: 023775 ) |
| SUBTOPIC TITLE: | In Situ Terrestrial Sensors |
| PROPOSAL TITLE: | Flight-based instrumentation for in situ measurements of multiple trace gases |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Los Gatos Research
67 East Evelyn Avenue, Suite 3
Mountain View , CA 94041 - 1518
(650 ) 965 - 7874
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Manish Gupta
mglgr@mindspring.com
67 East Evelyn Avenue, Suite 3
Mountain View , CA 94041 - 1518
(650 ) 965 - 7772
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Los Gatos Research proposes to develop a novel, flight-ready, instrument based on a new technology called Off-Axis Integrated Cavity Output Spectroscopy and continuous-wave, mid-infrared quantum cascade lasers to simultaneously measure the concentrations of CO, CH4, and N2O in the stratosphere and troposphere. These species have been identified as strong greenhouse gases, have very long atmospheric lifetimes, and thus play an important role in climate change. The proposed multi-laser Off-Axis ICOS instrument will measure all three of these species simultaneously while on board a NASA aircraft. In Phase I, we will demonstrate feasibility by building a laboratory prototype Off-Axis ICOS instrument that is capable of simultaneously measuring the target species in ambient air using multiple quantum cascade lasers. We will test the performance of the instrument over extended periods using calibrated gas samples to verify measurement accuracy, precision and stability. In Phase II, LGR will deliver to NASA a multi-laser Off-Axis ICOS instrument optimized for airborne studies.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
In addition to the atmospheric monitoring applications described above, the proposed technology may be used for detection of explosives, real-time monitoring and control of chemical processing plants, and for medical diagnostics based on breath analysis.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
The proposed novel instrument platform may be applied for accurate measurements of a wide range of important atmospheric gases for validation and confirmation of atmospheric chemistry and transport models.
| PROPOSAL NUMBER: | 02- E1.03-8410 (For NASA Use Only - Chron: 023589 ) |
| SUBTOPIC TITLE: | In Situ Terrestrial Sensors |
| PROPOSAL TITLE: | Microwave Rain Gauge |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Center for Remote Sensing Inc
11350 Random Hills Rd. Suite 710
Fairfax , VA 22030 - 6044
(703 ) 385 - 7717
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Suman Ganguly
Remote703@aol.com
11350 Random Hills Rd. Suite 710
Fairfax , VA 22030 - 6044
(703 ) 385 - 7717
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
This proposal describes a plan for the Design and Development of line of sight area averaged rain measurements using microwave backscatter techniques. The line averaged (and area covered) could be made variable, from as low as 100m to several km. The individual units can thus be used for both local measurements as well as for extending the observation over rain-cells. The techniques might be extended using multi-frequency and other techniques to obtain independent estimates of drop size distribution.
Both microwave attenuation and phase-shift are potential candidates for measuring rain rates. Microwave attenuation increases with frequency up to 100 GHz. The choice of appropriate frequencies is important, and optimization may become necessary in terms of available technology, cost and accuracies. The proposed effort describes a plan to develop a versatile instrument for measuring backscattered attenuation and phase at several frequencies. Experiments performed using the instrument will allow us to infer the optimum system parameters during Phase II.
Such a system will be valuable for earth communities, scientific research, global environment, agriculture and forestry among others. It would be valuable for NASA in estimating the ground truth and calibration and for comparison with the TRMM Rain Radar.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
The high fidelity, multi-frequency, multi-parameter sensor will be an advanced scientific instrument and will be used for hydrologic, meteorlogic, agricultural, environmental, and various other applications with societal implications. The technology will also be used to measure moisture content in food-grain and for other agricultural and industrial applications.
The second product will be a modified version of the rain sensor, optimized for size, cost and portability. This product will find numerous applications throughout the world for meteorological, and hydrological monitoring.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
There are several products resulting from the proposed effort. The first product is the high fidelity, multi frequency, multi parameter, and portable rain gauge specifically developed for rain and snow research. This instrument with superior performance and quality will be used by the NASA GSFC rain measurement facility at Wallops Island. Accurate measurements of rain and snowfall will be valuable for predicting the size of storm events, maximum precipitation, and the timing of run-off; the measurements will also be useful to power utilities for estimating drainage and power delivery variables (such as loading on transmission lines, etc.)
| PROPOSAL NUMBER: | 02- E1.03-9865 (For NASA Use Only - Chron: 022134 ) |
| SUBTOPIC TITLE: | In Situ Terrestrial Sensors |
| PROPOSAL TITLE: | A Reusable and Autonomous Ocean-Atmosphere Sensor Integration System (OASIS) |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
PACIFIC GYRE
7460 Capstan Drive
Carlsbad , CA 92009 - 4682
(760 ) 918 - 9798
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Andrew Sybrandy
asybrandy@pacificgyre.com
7460 Capstan Drive
Carlsbad , CA 92009 - 4682
(760 ) 918 - 9798
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The need to acquire observations on oceanic and atmospheric physical and biogeochemical processes continues to increase. These data are presently being used as initial conditions for model forecasts, for creating climatological fields, for calibration and validation of remotely sensed data, for model data assimilation, and for flux estimates. Presently, autonomous sensor platforms have been designed as low cost expendables and are capable of taking measurements of temperature, salinity, wind speed, and bio-optics. Recent advances in the development of in situ ocean sensors will shortly allow these autonomous sensors to also obtain measurements of pCO2, nitrate, silicate, ammonium, and iron. However, as more sensors are included on the sensor package, the ability to use them as expendables is reduced dramatically. This proposal seeks to investigate the development and testing of a new low-cost sensor platform that would be capable of retrieval and reuse. The goal would be to develop a self-navigating, self-powered platform controlled via two-way satellite communication. This instrument platform could then be augmented with a wide variety of presently available oceanic and atmospheric sensors.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
Pacific Gyre is a developer and designer of state-of-the-art ocean sensors and ocean sensor platforms, which have been used by oceanographers worldwide. Development of a reusable, low-cost ocean sensor platform will allow Pacific Gyre to enhance its customer base by making it affordable for limited-budget science and commercial applications that cannot afford the continued costs associated with expendable sensor systems, research vessels, or ASV/AUVs. By having the additional features of two-way satellite communication and navigability, Pacific Gyre hopes to also access the commercial and government monitoring sectors by providing them with a very inexpensive way to remotely monitor and track specific oceanic and atmospheric features. Pacific Gyre?s goal is to develop a general instrument platform which customers can easily augment with their desired instrument suite.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
The OASIS sensor platform will allow NASA to deploy a wider suite of biogeochemical, and physical sensors in the ocean for Calibration and Validation (Cal/Val) because the OASIS is a reusable low-cost platform. NASA collects synoptic data on the oceans from space. These data are necessary for assessing annual and seasonal climatologies, intra-seasonal and climate variability, ocean prediction and weather forecasting. The sensors used to obtain these measurements require a significant amount of in situ data for Cal/Val because the installed passive sensors are sensitive to changes in the composition of the earth?s atmosphere. The use of in situ observations to calibrate all NASA products is currently not possible because high cost, and/or post-deployment calibrations requirements eliminate the possibility of installing many useful sensors on expendable platforms. The OASIS platform will enable NASA to affordably collect in-situ data for Cal/Val using a wider range of important sensors.
| PROPOSAL NUMBER: | 02- E1.04-8418 (For NASA Use Only - Chron: 023581 ) |
| SUBTOPIC TITLE: | Passive Microwave |
| PROPOSAL TITLE: | High Frequency Amplifiers for Spaceborne Microwave Radiometers |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
SOPHIA WIRELESS, INC.
14225-C Sullyfield Circle
Chantilly , VA 20151 - 0000
(703 ) 961 - 9573
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Philip Koh
pkoh@sophiawireless.com
14225-C Sullyfield Circle
Chantilly , VA 20151 - 0000
(703 ) 961 - 9573
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The goal of this work is to research and design low noise, high frequency millimeter wave devices for NASA to improve the sensitivity, reliability, size requirements, and cost of future spaceborne radiometer missions.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
The development work outlined herein has vast commercial potential. The technology researched under this contract will greatly reduce the cost of future millimeter-wave systems while improving performance and opening up new applications that were previously cost-prohibitive for high volume deployment.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
The components and devices developed under this contract directly improve the performance, cost, and manufacturability of microwave radiometers in support of Earth System science measurements of the atmosphere and Earth's surface.
| PROPOSAL NUMBER: | 02- E1.04-8946 (For NASA Use Only - Chron: 023053 ) |
| SUBTOPIC TITLE: | Passive Microwave |
| PROPOSAL TITLE: | Synthetic Thinned Aperture Radiometer Boom Using Resilient Structures Technology |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Foster-Miller Inc
350 Second Ave
Waltham , MA 02154 - 1196
(781 ) 684 - 4368
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Dr. Peter Warren
pwarren@foster-miller.com
350 Second Ave
Waltham , MA 02154 - 1196
(781 ) 684 - 4242
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The deployment of booms that support arrays of rigid panels has long been a classic problem in aerospace structural design. NASA?s recent investigations into Synthetic Thinned Aperture Radiometers have motivated a more in-depth look into the deployment of long, precise arrays of antenna panels for a wide variety of earth science missions. Existing panel boom technology is too massive, complex, and unstable for these challenging missions.
Foster-Miller, Starsys, and the University of Colorado are teaming together to develop a revolutionary new deployable boom structure specifically for supporting long arrays of precision antenna panels. This boom system is based on an emerging new class of strain energy deployable tubular truss structures that has been shown to be extremely lightweight, stiff, strong and dimensionally stable down to the nanometer level. The boom will be integrally attached to the panels, allowing for controlled, repeatable deployment that can be proven on the ground and then reliably deployed on orbit.
The Phase I program will demonstrate the feasibility and the practicality of the approach through analysis and prototype testing. Future research will fully develop the repeatedly elastic deployable approach into a complete flight system. (P-020602)
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
Virtually all spacecraft deploy some form of structure, either for communication, sensing, power generation, or heat rejection. By developing a low cost, low mass, high packaging efficiency, deployable structure, the FMI team will allow commercial spacecraft developers to reduce their launch costs and increase their design margins. The proposed innovation will be a commercially viable technology that can be applied to almost every current and future government and civilian spacecraft program.
In addition to the wide range of space applications, Foster-Miller is actively involved in developing lightweight, rapidly erected structures for terrestrial applications. These applications include emergency rescue structures and bridges, crowd control barriers and temporary shelters.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
NASA is investigating the use of Synthetic Thinned Aperture Radiometers to provide accurate measurements of the soil moisture, precipitation levels, ocean salinity, and many other important water-based measurements in various locations throughout the Earth?s ecosystem with a large, but lightweight non-rotating antenna. The proposed boom development will enable these missions at a lower risk, cost, launch mass and launch volume than existing mechanical or inflatable systems.
Other NASA Missions use rigid panels to provide high efficiency solar power generation, heat rejection and active patch antenna and radar systems. The proposed development would provide these NASA spacecraft with a low-cost, reliable, lightweight structure to provide these systems with rigid and dimensionally stable support.
| PROPOSAL NUMBER: | 02- E1.05-7685 (For NASA Use Only - Chron: 024314 ) |
| SUBTOPIC TITLE: | Active Microwave |
| PROPOSAL TITLE: | New Structures for Large Sensor Array Platforms |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
AEC-ABLE ENGINEERING CO.
7200 Hollister Ave
Goleta , CA 93117 - 2807
(805 ) 690 - 2439
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Dave Murphy
dmurphy@aec-able.com
7200 Hollister Ave
Goleta , CA 93117 - 2807
(805 ) 690 - 2447
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The success of SRTM (Shuttle Radar Topography Mission) illustrates the utility of radar interferometry from space. The intent of the proposed work is to develop system capability to deploy a one-kilometer baseline radar interferometer launched in a single mission from a standard launch vehicle. This system is enabled by on a novel deployable structure technology. This structural approach has the potential of increasing stowed packaging efficiency by a factor of >2x and decreasing linear mass density by a factor of >8x better than SRTM while maintaining equivalent strength, stability, and stiffness. The challenge of this technology is to develop methods of utilizing high modulus, low CTE (coefficient of thermal expansion) graphite fiber composites in an arrangement that does not exceed the strain limits of the material when stowed yet retains the desired stiffness and thermal stability when deployed. The approach is to add an additional order of structural hierarchy to the overall system by further optimizing the constituent columns of the truss into simple deployable truss structures themselves. Each column is comprised of a set of mutually stabilized rods that can be configured by varying the number and size of rods and stabilizers for required axial stiffness and buckling strength.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
Once sufficiently characterized, the proposed technology is envisioned to have broad applicability for any mission requiring the capability to deploy stiff, stable and extremely mass and volume efficient structures. The technology is directly applicable to sensor array structural platforms. The ability to rapidly configure large, single-mission structures will have commercialization opportunities for a wide variety of communication and imaging spacecraft. Also, economic barriers common to small payloads associated with the cost of specialty-run composites will be reduced due to the generalized nature of the construction of the proposed structure, which should also prove a benefit to the general scientific community.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
Potential NASA applications include missions requiring autonomous deployment of large baseline stable structures for sensor arrays. The capability to efficiently package large deployable structures in conventional unmanned launch vehicles will reduce dependency on the STS and therefore reduce the cost of science and increase access to space. Rapid configuration of structures based on a reduced set of generalized constituent elements will also serve to lower mission costs. One conceptual mission is described herein that has the potential to compliment and possibly surpass the dataset generated by SRTM. Other potential applications exist for non-earth imaging as well.
| PROPOSAL NUMBER: | 02- E1.05-7798 (For NASA Use Only - Chron: 024201 ) |
| SUBTOPIC TITLE: | Active Microwave |
| PROPOSAL TITLE: | Photonic Phased Array Antenna |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
AGILTRON CORPORATION
13 Henshaw Street
Woburn , MA 01801 - 4666
(781 ) 933 - 0513
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Jing Zhao
jingzhao@agiltron.com
13 Henshaw Street
Woburn , MA 01801 - 4666
(781 ) 933 - 0513
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The present invention provides an inexpensive and low loss fiberoptic manifold for lightweight, high-efficiency, electronically steerable, phased-array antennas. Our approach is sate-of-the-art in design and closely coupled with proven volume fiber optic component manufacturing techniques, holding a promise of realizing practical optical digital delay with performance and cost that have not been achieved before. By using all solid-state inorganic magneto-optic material construction, the proposed switch overcomes the limitation in speed and long-term reliability associated with other approaches. The proposed compact, light-weight, ultra reliable, and low power consumption photonic digital beamforming phase array antenna can potentially be part of spaceship?s skin eliminating the need for complex out-space antenna deployment mechanisms. The advanced technology also potentially addresses the development of next generation critical radar components for optically fed transmit/receive, signal up/down conversion, RF and DC signal distribution, and phase shifting. A high-speed and fault tolerance fiberoptic 4 bit reconfigurable true time delay device will be demonstrated in Phase I.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
There are many applications need high switching speed of less than 1 microsecond with carrier-class reliability. The proposed AGILTRON?s high-speed optical device can be a key building block for high-performance, cost-effective solutions for managing aggregated OC-192 and above optical bandwidth networks in metro environments. It provides for data rate, protocol and data format transparency and its high-speed logic interface enables unique capabilities. With a speed of less than 1 millisecond, the proposed switch supports unique light management functionalities such as multicasting and broadcasting. This dynamically controllable, intelligent switch enables virtual port expansion of previously limited high-speed communications systems, such as 10 Gigabit Ethernet Switches, high-speed Routers and OC-192 SONET Multiplexers. The proposed technology holds a promise of extending switching to dynamic reconfiguration, performance monitoring, and traffic management while power balancing, attenuation and equalization management that are inherent in the switch fabric
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
Radar is undergoing a significant change in status as a sensing instrument. New systems must accomplish more with fewer resources: power, equipment mass and volume, operating and maintenance personnel, and cost. . For NASA applications, microwave radar based sensors have proven to be ideal instruments for many Earth science applications. Examples include global freeze/thaw monitoring and soil moisture mapping, accurate global wind retrieval and snow inundation mapping, global 3-D mapping of rainfall and cloud systems, precise topographic mapping and natural hazard monitoring, global ocean topographic mapping and glacial ice mapping for climate change studies. For global coverage and the long-term study of Earth's eco-systems, space-based radar is of particular interest to Earth scientists.
| PROPOSAL NUMBER: | 02- E1.05-8783 (For NASA Use Only - Chron: 023216 ) |
| SUBTOPIC TITLE: | Active Microwave |
| PROPOSAL TITLE: | High Performance and Low Cost Hybrid Microwave Structure |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Boston Applied Technologies, Inc.
62 Kerry Dr.
Mansfield , MA 02048 - 3433
(508 ) 339 - 0278
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Dr. Hua Jiang
hjiang@bostonati.com
62 Kerry Dr.
Mansfield , MA 02048 - 3433
(508 ) 339 - 9247
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Access to the space is fundamentally very expensive. One of the most effective ways to lower the cost is obviously to reduce the weight and size of the payloads while maintaining high performance. Microwave communication is the most important and practical communication method used in the space mission, which has created a need for dramatically improved microwave devices. The agility of tunable microwave devices can efficiently reduce the size and weight of a space radar system, as well as provide the remote control functionality. In this proposal, Boston Applied Technologies, therefore, proposes a revolutionary approach to develop a unique ferroelectric/ferrite hybrid substrate using a nanophase pressure assisted sintering (PAS) technology for adaptive microwave applications. In this approach, both the ferrite and ferroelectric materials will be formed as nanocrystal phase under high pressure in one step. This low-cost nanophase PAS technology is capable to make ferroelectric/ferrite hybrid nanocrystal structure with the lowest possible material loss. The hybrid structure developed in this program will lead to a new generation of microwave devices that can be tuned either electrically, or magnetically, or both, which is particularly suitable for low cost, high performance military space applications.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
Success in the Phase I effort will lead to the commercial fabrication of a new generation of tunable microwave devices. These advanced devices will have great applications in military, space, industrial, and consumer sectors. Examples are tunable phase shifters, tunable filters, and tunable beam scan antennas.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
The technology developed in this program will greatly benefit to NASA?s space communication for reconfigurable and autonomous antennas, phase shifters and filters.
| PROPOSAL NUMBER: | 02- E1.06-8160 (For NASA Use Only - Chron: 023839 ) |
| SUBTOPIC TITLE: | Passive Infrared - Sub Millimeter |
| PROPOSAL TITLE: | Diamond-Based Sub Millimeter Backward Wave Oscillator |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
GENVAC AeroSpace Corp.
110 Alpha Park
Cleveland , OH 44143 - 2215
(440 ) 646 - 9986
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
James A. Dayton, Jr.
dayton@genvac.com
110 Alpha Park
Cleveland , OH 44143 - 2215
(440 ) 646 - 9986
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Making use of fabrication technology commonly used in the manufacture of liquid crystals and semiconductors, but not previously applied to vacuum devices, the diamond-based backward wave oscillator (BWO) will provide a miniature, energy efficient, electronically tunable and mass producible signal source in the sub mm wavelength regime. Fabricated within a shell of chemically vapor deposited (CVD) diamond, the BWO will employ a novel biplanar interdigital slow wave circuit. The dimensions of the BWO are estimated to be 0.600 inches long and 0.130 inches in diameter at 300 GHz, and a power output of 10 mW is predicted with a total power input of 198 mW for an overall efficiency of 5%. The electron source for the BWO will be a field emission cathode. The offerors have previously demonstrated a diamond field emitter that makes use of the negative electron affinity of diamond to obtain a threshold of emission for a gate voltage as low as 0.25 volts[1, 2]. Widely available, cost effective silicon fabrication technology will be used to integrate the BWO components into a single chip, avoiding conventional assembly techniques. The BWO would replace the present generation of bulky, power consuming signal sources that are unsuitable for space applications.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
Most of the applications of a sub mm oscillator of the type proposed here would be in scientific instrumentation for use in laboratories or in spectroscopy above the earth?s atmosphere. If the manufacturing process described in this proposal is successfully developed, relatively inexpensive sub mm oscillators would be available for the first time, which might open up additional commercial opportunities.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
The diamond-based sub mm BWO will provide a new class of light weight, power efficient local oscillators for use in heterodyne detection of extraterrestrial radiation above the Earth's atmosphere that will replace the bulky inefficient devices now available.
| PROPOSAL NUMBER: | 02- E1.07-7551 (For NASA Use Only - Chron: 024448 ) |
| SUBTOPIC TITLE: | Thermal Control and Cryogenic Systems |
| PROPOSAL TITLE: | Highly Effective Thermoelectric Coolers |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
SIGMA TECHNOLOGIES INTERNATIONAL INC.
10960 N. Stallard Place
Tucson , AZ 85737 - 9527
(520 ) 575 - 8013
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Doris Dziomba
ddziomba@sigmalabs.com
10960 N. Stallard Place
Tucson , AZ 85737 - 9527
(520 ) 575 - 8013
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Sigma Technologies proposes to produce a compact, efficient, solid state thermoelectric cooler that is expected to deliver hundreds of milliwatts of cooling power at low temperatures (<150 K). The proposed device fabrication process is based on Sigma?s proprietary Polymer Metal (PML) technology. In Phase I, Sigma intends to design and evaluate the refrigerator material. In Phase II, Sigma will build a complete refrigeration unit for field evaluation
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
At a reasonable cost, portable coolers will grab a huge share in the refrigeration industry market. Sectors that may benefit from this technology include the home appliance, medical, and the food and beverage industries.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
The proposed solid state, lightweight, low relative cost crycooler will have a great impact on onboard instrumentation performance and reliability, factors that are critical to mission success
| PROPOSAL NUMBER: | 02- E1.07-8301 (For NASA Use Only - Chron: 023698 ) |
| SUBTOPIC TITLE: | Thermal Control and Cryogenic Systems |
| PROPOSAL TITLE: | Nanofluid Boiling Module for Precision Cooling of Microelectronics |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
MICROENERGY TECHNOLOGIES, INC.
2007 E. Fourth Plain Blvd.
Vancouver , OR 98661 - 3957
(360 ) 694 - 3704
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Dr. Reza Shekarriz
reza@microet.com
2007 E. Fourth Plain Blvd.
Vancouver , OR 98661 - 3957
(360 ) 694 - 3704
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
MicroEnergy Technologies, Inc. (MicroET) and the University of Washington propose to demonstrate the feasibility and the major advantages of a unique high heat flux cooling module for localized cooling of distributed electronics. This technology combines innovations in heat sink design, manufacturing, and operation including an innovative micropump design to achieve heat rejection rates in excess of 1000 W/cm2 from the surface of a substrate. The most critical innovation is the use of ceramic nanoparticles suspension used as the heat rejection medium in which intense nucleate boiling produces extremely high heat fluxes. The micropump geometry is integrated into the cooling module to maintain a high enough flow rate through the parallel array of microchannels for efficient cooling. The proposed approach allows for distributed cooling without the need for external pumping and the ability to provide localized control. During Phase I, we will perform analytical and computational modeling for system design and analysis, experimentally demonstrate the significant advantages and improvements in cooling system performance.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
The final product, ultra high heat flux thermal management system, in addition to application in the aerospace and space electronics industry will have a significant commercial value to a broader industry, including defense electronics, supercomputing, and desktop computing applications. Efficient distributed cooling will reduce the risk of system failure, increase system throughput, and reduce the complexity, size, and weight of the system.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
This technology is particularly of value for the NASA?s mission for Earth Science Enterprise to track and assess global environmental processes. Minimization of the weight and size of the systems and instruments used for these studies are critical.
| PROPOSAL NUMBER: | 02- E1.07-8993 (For NASA Use Only - Chron: 023006 ) |
| SUBTOPIC TITLE: | Thermal Control and Cryogenic Systems |
| PROPOSAL TITLE: | LOW-CURRENT SUPERCONDUCTING MAGNETS OPERATING AT UP TO 10K |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Superconducting Systems, Inc.
90 Rumford Avenue
Waltham , MA 02453 - 3847
(781 ) 642 - 6702
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Shahin Pourrahimi
pourrahimi@superconductingsystems.com
90 Rumford Avenue
Waltham , MA 02453 - 3847
(781 ) 642 - 6702
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Our overall goal for this project is to develop the technologies necessary for fabrication of efficient cryogen-free superconducting magnets that can operate at temperatures of 6-10K. In the Phase I program, we will demonstrate that an efficient solenoid magnet system may be built using small diameter Nb3Sn wires employing the react-then-wind approach. As a part of this work we will fabricate an efficient 3T magnet with an operating current of 8A and an operating temperature of 10K. The magnet will be tested and then used by NASA in an ongoing R&D in the area of Adiabatic Demagnetization Refrigeration.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
This program will establish practical and economical technologies in the areas of superconductor, and superconducting magnet technologies for operation at 6-10K. The results will impact the design, fabrication, and use of superconducting magnets for applications in space, high energy physics, medical, low temperature physics, spectroscopy, imaging, and chemistry.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
Highest efficiency adiabatic demagnetization refrigerators useful for achieving very low temperatures in space missions require superconducting magnets with low operating current that work at temperatures in the range of 6-10K. This program is geared toward the development of technologies for manufacturing of such magnets.
| PROPOSAL NUMBER: | 02- E1.07-9079 (For NASA Use Only - Chron: 022920 ) |
| SUBTOPIC TITLE: | Thermal Control and Cryogenic Systems |
| PROPOSAL TITLE: | High Efficiency MEMS Based Cryocooler |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Nanohmics, LLC
4302 Rimdale Dr
Austin , TX 78731 - 1222
(512 ) 349 - 0835
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Keith Jamison
kjamison@austin.rr.com
4302 Rimdale Dr
Austin , TX 78731 - 1222
(512 ) 349 - 0835
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
New developments in micro miniaturized systems have enabled very efficient cooling systems. The key figure of merit for these devices is the specific capacity which is defined as the ratio of the heat dissipation capacity vs. the overall mass of the dissipating device. In the case of microlithographically patterned, microelectromechanical system (MEMS) components, the dimensional capabilities are extremely efficient as unique structural designs of micro-oscillating diaphragms prepared by undercut etching of vapor deposited layers enable large heat transport capabilities relative to the overall size of the devices. In particular, Stirling engines, which act as transducers for mechanical to thermal energy conversion, have shown particular promise as integrated MEMS coolers for integrated circuits and other planar detection arrays compared to their counterparts, thermoelectric coolers (TECs). To this end, Nanohmics plans to introduce two novel components to MEMS micro-cryocooler Stirling Engines systems that will dramatically improve the performance of the device. This includes replacing the silicon heat exchanger plates and flexible membranes with high thermally conductivity novel thin film materials using a MEMS processing technique and introduction of novel aerogels into the fluid heat exchanger matrix with ultra low thermal conductivities.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
Miniaturized coolers have many military and commercial applications. The largest commercial application is cooling of microprocessors and detectors. Currently, speed of microprocessors and the efficiency of detectors are limited by the amount of power that can be removed from the devices. Chip scale heat pumps will allow efficient cooling of devices enabling operation at greater speeds / power densities
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
To fulfill NASA's Earth Science Enterprise mission objectives, Nanohmics plans to develop an ultrahigh thermal efficiency MicroElectroMechanical System (MEMS) cryogenic cooling system. The system will be designed to decrease the cost and size of instruments that perform Earth Science measurements and thus lead to compact electromagnetic detection and microelectronics platforms for integration into miniature probe spacecraft.
| PROPOSAL NUMBER: | 02- E2.01-7512 (For NASA Use Only - Chron: 024487 ) |
| SUBTOPIC TITLE: | Structures and Materials |
| PROPOSAL TITLE: | Low-Cost Fabrication of an Integrated, Self-Sufficient MEMS Skin |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Anvik Corporation
6 Skyline Dr
Hawthorne , NY 10532 - 2165
(914 ) 345 - 2442
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Marc Zemel
mzemel@anvik.com
6 Skyline Dr
Hawthorne , NY 10532 - 2165
(914 ) 345 - 2442
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
One of the ultimate goals of sensor research is to build an integrated unit that harnesses its energy from its surroundings and reacts to, and transmits, any changes in its environment in a predictable and reliable manner. There are several components to this universal goal of a self-contained sensor unit: the power module, the sensor module, the control module, and the transmission module. The goal of this proposal is to develop a whole class of truly stand-alone, large-area, distributed sensor systems on a flexible substrate ? a MEMS skin.
We propose to use a two-layer flexible substrate. The first would be a copper-on-flex substrate that acts as the interconnect layer for power distribution. The second is a Si-on-flex substrate that contains the power, sensor and circuit systems. This layer would utilize a thin film amorphous Si solar cell, integrated with Anvik?s technology to integrate MEMS and IC devices. The two substrate layers would be connected using micro-via patterns in the Si-on-flex layer that can be generated using Anvik?s photo-ablation systems. Finally, using Anvik?s large-area processing capabilities we will extend this process to create a distributed sensor array that could be used in spacecraft ?health-monitoring? applications.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
The focus in this proposal has been on space related applications and therefore on large-area distributed sensors. Immediate extensions can be found in the commercial aircraft industry for these sensors. Similar applications can be found in the automotive industry for safety testing and continuous monitoring of the auto-body or the ship hull. With further development, these skins could be applied to clothing applications for military and commercial applications in the up and coming e-textile market. All these applications will be able to use the large-area stand-alone capability of these sensors.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
There are innumerable applications in free-moving sensor systems, space-based MEMS and distributed sensor networks for health monitoring of space-based systems. The technology described is independent of the exact nature of the sensor that is integrated into the system. Using an accelerometer, for example, will enable large-area distributed monitoring of vibration over complex surfaces. The use of a chemical sensor will allow applications in hazardous gas monitoring over large-areas. The integration of MEMS and the associated circuitry in a single unit is a giant step forward in improving the sensitivity and performance of these sensors. The proposed integration of a-Si based solar cells takes this to the next level where it makes the sensor truly stand-alone. The use of a flexible substrate enables applications to conformable and very-large area surfaces that were up until now not easily possible.
| PROPOSAL NUMBER: | 02- E2.01-8611 (For NASA Use Only - Chron: 023388 ) |
| SUBTOPIC TITLE: | Structures and Materials |
| PROPOSAL TITLE: | Passive Non-Rocking Vibration Isolation System for Earth Science Payloads |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
CSA Engineering Inc
2565 Leghorn St
Mountain View , CA 94043 - 1613
(541 ) 858 - 8556
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Paul Wilke
wilke@csaengineering.com
2565 Leghorn St
Mountain View , CA 94043 - 1613
(650 ) 210 - 9000
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Dynamic loads can cause big problems for satellites both during launch and during on-orbit operation. The best solution for attenuating these dynamic loads is to incorporate vibration isolation either at the launch vehicle-to-satellite interface or at the satellite-to-component interface. Conventional passive vibration isolation systems have been successfully flown at both of these interfaces. It is believed, however, that much greater isolation performance is achievable with a new type of isolation system. The innovation is to develop a passive vibration isolator that provides low-frequency axial isolation without the attendant low-frequency ?rocking? or lateral modes. In other words, the ratio of axial stiffness to rocking stiffness would be very high compared to that of a conventional isolation system. This is desirable because for whole-satellite isolation, very low rocking modes can cause guidance instabilities and for component isolation, the rocking modes can increase optical jitter. This isolation technology will be of great use in future NASA Earth Science platforms because it will provide dynamically stable structures utilizing integral vibration control. Earth-sensing instruments will perform better with significant reduction in jitter due to the non-rocking isolation systems. Similarly, NASA satellites will be better protected from launch loads with lower frequency whole-satellite non-rocking isolation systems.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
Passive non-rocking vibration isolation systems have many potential commercial applications. These applications all have a common need for low-frequency axial vibration isolation systems that do not also produce low-frequency rocking modes. Typical applications include sensitive equipment mounted on satellites such as telescopes, cameras, and other sensors whose scientific performance is very susceptible to jitter caused by dynamic loads. Ground-based applications include isolation of optical equipment on semiconductor manufacturing machines, isolation of components on optical benches, isolation of sensors on medical imaging equipment, etc. Launch isolation applications for this technology include enabling much lower frequency whole-satellite vibration isolation on small launch vehicles like Taurus and Minotaur, enabling whole-satellite vibration isolation on medium and large launch vehicles like EELV, Delta II, Atlas, etc., and enabling whole-satellite vibration isolation on Pegasus. Virtually all equipment that requires axial isolation but is inhibited by low-frequency high-amplitude rocking motion will benefit from the new technology.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
Passive non-rocking vibration isolation systems have many potential NASA applications. Similar to the potential commercial applications, these all have a common need for low-frequency axial vibration isolation systems that do not also produce low-frequency rocking modes. A primary NASA application of this technology is the large assortment of sensors to be deployed on future satellites for either Earth Science or other space missions. Most of these sensors will greatly benefit from operating in a reduced-jitter environment enabled by the use of passive non-rocking vibration isolation systems. NASA satellite missions that mount their sensors using this new isolation technology will produce better scientific data. Another large application area for NASA is to mount the entire satellite to the launch vehicle using a passive non-rocking whole-satellite vibration isolation system. This will protect the entire satellite from launch loads and add margin to ensure mission success.
| PROPOSAL NUMBER: | 02- E2.01-9200 (For NASA Use Only - Chron: 022799 ) |
| SUBTOPIC TITLE: | Structures and Materials |
| PROPOSAL TITLE: | Rational Engineering of Carbon Nanotube Surfaces |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
ZYVEX CORPORATION
1321 N. Plano Road
Richardson , TX 75081 - 2475
(972 ) 235 - 7881
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Jian Chen
jchen@zyvex.com
1321 N. Plano Road
Richardson , TX 75081 - 2475
(972 ) 235 - 7881
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Ideal multifunctional carbon nanotube/epoxy composites will find broad aerospace and earth science applications that require lightweight materials with high electrical conductivity, high mechanical strength and high thermal conductivity. Smooth carbon nanotube sidewalls, however, are incompatible with most solvents and polymers resulting in poor dispersion of nanotubes in polymer matrix, and are difficult to functionalize without altering nanotube's desirable intrinsic properties producing poor adhesion between nanotube and polymer matrix. These factors have resulted in prior studies failing to produce nanotube/polymer composites that realize their full potential. Zyvex proposes to develop a versatile, non-damaging chemistry to rationally engineer carbon nanotubes. This functionalization will enable solubility in organic solvents, which allows homogeneous dispersion of nanotubes in a polymer matrix and can also enable the enhanced adhesion between nanotube and matrix. While this technology will be widely applicable, we will concentrate on epoxy-nanotube composites. In Phase I, Zyvex will develop the proposed innovative nanotube surface chemistry, and demonstrate the fabrication of homogeneous nanotube-epoxy composites with enhanced multiple performances. In Phase II, Zyvex will focus on further improving the nanotube/epoxy adhesions by using the nanotube chemistry developed in Phase I, and will demonstrate the superior multiple performances of nanotube-epoxy composites for task-specific NASA applications.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
?Lightweight, multifunctional materials for aircrafts, automobiles and satellites.
?Lightweight, multifunctional materials for soldier armor and helmets.
?Lightweight, multifunctional materials for ballistic missiles
?Lightweight, multifunctional materials for EMI shielding.
?CNTs/epoxy composites (high CNTs loading) for Field Emission Display.
?Multifunctional adhesives.
?High thermal conducting materials and adhesives for thermal management in electronics packages.
?Multifunctional materials for coatings.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
?Lightweight, multifunctional materials for aerospace and earth science platforms (high strength booms, thrust structures, thin shells, membranes, space suits, etc.).
?Materials for high efficiency passive thermal management.
?Lightweight high strength materials for Unpiloted Aerial Vehicles (UAVs).
?Highly durable materials for long duration missions.
?Lightweight, multifunctional materials for EMI shielding.
?Multifunctional adhesives for aerospace and earth science platforms (spacecraft, launch vehicles etc.).
| PROPOSAL NUMBER: | 02- E2.01-9598 (For NASA Use Only - Chron: 022401 ) |
| SUBTOPIC TITLE: | Structures and Materials |
| PROPOSAL TITLE: | Flexible, Low CTE Composites for Precision Deployable Structures |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Foster-Miller Inc
350 Second Ave
Waltham , MA 02154 - 1196
(781 ) 684 - 4368
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Dr. Peter Warren
pwarren@foster-miller.com
350 Second Ave
Waltham , MA 02154 - 1196
(781 ) 684 - 4242
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Future spacecraft will deploy optical apertures large enough to detect life on planets around distant stars. These apertures must maintain their shape to within small percentages of a wavelength over long observations. Current deployment technologies require hinges, latches and actuators, experimentally shown to make structures unstable and unpredictable at the micron level. Compensating for thermal expansion of mechanisms adds cost and complexity and even newly developed, low CTE mechanisms add mass to the spacecraft.
Foster-Miller, Kodak and the University of Colorado have teamed to develop low CTE flexible composite materials, enabling the deployment of large, optically precise structures for spacecraft instruments. The team will combine new deployable structures, ultrasonic manufacturing, and low CTE composite design technologies to provide novel, innovative instrument support structures.
By incorporating the proposed low CTE flexible composite materials into hinges that are integral to the overall structure, this program will enable the production of instrument structures that can be repeatably deployed on the ground, folded compactly for launch, self-deploy and lock on orbit, and are thermally and dynamically stable. Because the material itself provides the deployment actuation and locking, the structures weigh no more than if they were fabricated as a monolithic, non-deployed structure. (P-020675)
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
The proposed innovation will provide lightweight deployable structures that are dimensionally stable for a wide range of applications. Spacecraft have been deploying antennae and solar arrays since the dawn of the space age. The development of this technology will provide all spacecraft with a means of deploying all manner of components with thermally stable structures that do not introduce unwanted dynamics or static loads as the spacecraft thermal load change throughout its orbit.
In addition to the myriad of applicable spacecraft structures, many terrestrial applications use flexures as a means of constraining optical components. From scientific research optical benches to production microchip photolithography tools, there are literally thousands of places where a flexible, high performance, dimensionally stable composite material would increase performance and provide market potential.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
The NASA applications that require the most dimensional stability in deployed structures are large aperture infra-red and optical telescopes. The two immediate missions that would benefit from this technology are Next Generation Space Telescope and Terrestrial Planet Finder. These missions would be able to deploy very large, stiff and dimensionally stable primary apertures in a manner not feasible with existing technology.
Many other systems would benefit from increased dimensional stability. Large radar and other antennae do not have the optical level stability requirements, but their greatly increased size makes them equally sensitive to thermally induced distortions. Large aperture systems have the additional complication that their size makes insulation impractical, increasing the need for material level thermal stability. Magnetometers, Synthetic Aperture Radars, Interferometers are all non-aperture based science instruments that also require large, precise and predictable structures.
| PROPOSAL NUMBER: | 02- E2.02-9627 (For NASA Use Only - Chron: 022372 ) |
| SUBTOPIC TITLE: | Guidance, Navigation and Control |
| PROPOSAL TITLE: | A Reconfigurable, Decentralized Framework for Formation Flying Control |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Princeton Satellite Systems
33 Witherspoon St.
Princeton , NJ 08542 - 3207
(763 ) 561 - 9246
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Joseph Mueller
jmueller@psatellite.com
33 Witherspoon St.
Princeton , NJ 08542 - 3207
(609 ) 279 - 9606
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The paradigm shift of using multiple-satellite clusters to replace large, monolithic spacecraft has been fueled by the objectives of increased robustness, greater flexibility, and reduced cost. It is our belief, however, that these objectives are not automatically met. The operational costs of monitoring and commanding a large fleet of close-orbiting satellites is likely to be unreasonable, unless the onboard software is sufficiently autonomous, robust, and reconfigurable. The decentralized agent framework that we propose here will meet these requirements.
This proposal is for a novel formation flying control system with a reconfigurable and decentralized framework. The relative orbit determination and control system is organized as a modular network of software agents, which may be adapted and evolved throughout the mission. The computational load for both orbit determination and maneuver planning is distributed equally, decreasing the chances for single-point failures and allowing for greater extensability.
The control system will run within the Princeton Satellite Systems?ObjectAgenta architecture. Agents may be added, removed or replaced post-launch to increase mission flexibility and robustness. This level of reconfigurability exceeds the state-of-the-art in traditional flight software. Additionally, the decentralized nature of the design enables the number of satellites to change post-launch, and can seamlessly support large clusters.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
Commercial applications of this control system include: synthetic aperture radar for a variety of high-resolution imaging applications, and clusters of telecommunication satellites for cellular phones or high-speed internet access.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
The application of synthetic aperture radar holds tremendous promise for NASA's Earth Science Enterprise and Office of Space Science. The autonomous determination and control of the relative position between close-orbiting satellites is an enabling technology for all science missions that intend to employ this distributed radar approach. When the satellite constellation is not earth-based, the need for a robust and reconfigurable system is that much greater.
| PROPOSAL NUMBER: | 02- E2.02-9694 (For NASA Use Only - Chron: 022305 ) |
| SUBTOPIC TITLE: | Guidance, Navigation and Control |
| PROPOSAL TITLE: | Intelligent Fault Tolerant Control of Spacecraft |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Scientific Systems Co Inc
500 West Cummings Park Suite 3950
Woburn , MA 01801 - 6580
(781 ) 933 - 5355
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Jovan Boskovic/Raman Mehra
jovan@ssci.com/rkm@ssci.com
500 West Cummings Park Suite 3950
Woburn , MA 01801 - 6580
(781 ) 933 - 5355
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
SSCI, in collaboration with Swales Aerospace, proposes to develop
an Intelligent Fault-Tolerant (IFT) control system to enhance the
performance of spacecraft Attitude Determination and Control
Subsystems (ADCS) in the presence of environmental torque disturbances, sensor noise variation, parametric and/or
structural uncertainties, and low control control authority, and
will be capable of automatically compensating for a loss of
sensors, actuators, or a combination of both through on-line
failure detection/identification, and adaptive control
reconfiguration. In particular, during the Phase I effort we plan
to demonstrate the capability of the proposed IFT-ADCS subject to
two degraded operating conditions that are commonly encountered in satellite missions: (1) Partial or total loss of on-board
gyros, and (2) Partial or total loss of Reaction Wheel Assembly
(RWA) actuators. In the former case, we propose to develop a
scheme based on a well established Interacting Multiple Model
(IMM) estimator for improved rate estimation accuracy and smooth
and robust operation subject to rate swapping (from gyro
measurement to gyroless rate estimator) or high rate slewing. In
the case of RWA failures, Magnetic Torquer Bars (MTB), or
Thrusters, or a combination of both will be employed to
accommodate for the failure. The proposed adaptive
reconfigurable control system will result in substantially
increased spacecraft on-board autonomy that will have a potential
to rescue the entire mission at its early stages despite
unexpected failures of critical components such as gyros, RWA, or
star tracker. Swales Aerospace will provide technical
and commercialization support during all phases of the project.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
Higher controller autonomy is one of the major enabling
technologies in the rapidly-growing commercial and military
satellite markets and will result in substantial cost reduction
due to: (i) Reduced human intervention for operation and
maintenance; (ii) Increased reliability and mission lifetime;
(iii) Decreased up-link and down-link bandwidth requirements;
(iv) Reduced testing and implementation costs; and (v) Decreased
software and hardware complexity. Hence the proposed autonomous intelligent fault-tolerant controller design has a great
commercial potential in both civilian and defense applications
including commercial and military satellites, and can also be
applied to aircraft, autonomous underwater and ground vehicles,
"smart" missiles, ships, robots, process control and
manufacturing systems.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
The end result of the proposed work will be the
development of a reusable flight code that captures the entire
IFT-ADCS architecture. Either in its entirety or in part, the
individual subsystem of the proposed IFT ADCS can be applied to
both current and future missions. An important part of this
effort will be the design, development, and commercialization of
a software design toolkit for the design and implementation of
IFT-ADCS for spacecraft.
| PROPOSAL NUMBER: | 02- E2.03-9706 (For NASA Use Only - Chron: 022293 ) |
| SUBTOPIC TITLE: | Command and Data Handling |
| PROPOSAL TITLE: | Bit Transparent Ternary SERDES for Intra-System Data Transfer |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Advanced Science and Novel Technology
28119 Ridgefern Court
Rancho Palos Verdes , CA 90275 - 2049
(310 ) 377 - 6029
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Vladimir Katzman
traffic405@cox.net
28119 Ridgefern Court
Rancho Palos Verdes , CA 90275 - 2049
(310 ) 377 - 6029
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Serializer/Deserializer (SERDES) components are the key components for high speed serial data transfer. Low latency, high bandwidth communications between processor nodes with upgrade ability within a box is of utmost importance in advanced NASA communication systems. Parallel architectures represent a bottleneck in terms of bandwidth and pin count. Several new standards such as Infiniband, Hypertransport, 3GIO, and RapidIO are evolving with a common direction towards serial system interconnect for next generation back-plane developments. Commercially available SERDES to support new standards have well known bit ambiguity at the deserializer output thereby requiring additional circuitry as well as software to solve this problem.
In order to overcome the bit ambiguity problem, Advanced Science and Novel Technology (ADSANTEC) proposes a novel ternary SERDES technique. The technique uses a ternary signal at the Serializer (SER) output to mark a reference bit position. The marked bit positions are used to recover a low-speed clock signal for receiver word alignment using a clock multiplier technique. The proposed concept will lead to the development of a new generation of serial data interconnect. ADSANTEC?s innovative solution will offer high throughput (up to 50Gb/s) and eliminate latency introduced by the switching fabric of existing digital interconnect approaches.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
The ternary SERDES concept can be integrated into network test equipment. According to Frost & Sullivan, the optical testing market is currently estimated at $2.3 billion and expected to grow to nearly $4 billion by 2004. ADSANTEC has an ongoing discussion with the market leader in this type of network test equipment, IXIA Inc., who potentially will be willing to support ADSANTEC with additional funding at Phase II in order to license ternary SERDES for use in a new generation of network test equipment.
Fiberspace Inc. is willing to commit Phase II fast track support in order to accelerate the development of multilevel SERDES technology and expand the total available market (TAM) of Fiberspace components. In addition, Fiberspace is willing to support ADSANTEC with laboratory space and equipment.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
The success of this program will result in commercialization of the most advanced processor interconnect back-plane, based on ternary SERDES. Its potential range of application will include a new generation of computer systems for spectral image data processing, homeland defense and a variety of digital conferencing networks. ADSANTEC?s data rate transparent and expandable interconnect will be adaptable to various types of communication networks.
Introduction of new system applications demanding the virtually unlimited throughput provided by the ternary SERDES interconnect will guarantee significant advantages with increasing interconnection network speed demands by large scale computer systems, and supercomputers. This will help the computer and system designers to increase processing power of future large conputer systems, both in NASA and industrial applications.
| PROPOSAL NUMBER: | 02- E2.04-8267 (For NASA Use Only - Chron: 023732 ) |
| SUBTOPIC TITLE: | Advanced Communication Technologies for Near-Earth Missions |
| PROPOSAL TITLE: | High-Frequency, Low-Noise Nitride-Based Power Transistors Grown on Bulk III-N |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
SVT Associates, Inc.
7620 Executive Drive
Eden Prairie , MN 55344 - 3677
(952 ) 934 - 2100
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Amir Dabiran
dabiran@svta.com
7620 Executive Drive
Eden Prairie , MN 55344 - 3677
(952 ) 934 - 2100
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
One of the main issues for III-nitride growth is the lack of a suitable native substrate. Growth on foreign substrates such as sapphire or SiC results in nitride material with a high density of defects due to large mismatches in lattice constant and thermal expansion. Nonetheless, nitride devices grown on these substrates have demonstrated optical and electronic properties that are practically unmatched by other material systems. In particular, the AlGaN/GaN high electron mobility transistors (HEMTs) constitute a leading candidate for simultaneously realizing ultrahigh-frequency low-noise amplifiers and power amplifiers. Here, we propose to use high quality bulk GaN and AlN substrates for substantial improvements in the operation of AlGaN/GaN HEMTs. We also propose a method of isolating the n-type substrate from the active layer. In this way, we take advantage of the reduced thermal and lattice mismatch, lower density of treading dislocations, and improved thermal conductance to significantly improve the dc and RF operation of these devices. Some projected HEMT device parameters to achieve are a current density > 1.5A/mm, extrinsic transconductance values > 400 mS/mm, fmax > 200 GHz, and power density > 10 W/mm at 40 GHz.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
The AlGaN-based high electron mobility (HEMT) power transistors have wide commercial markets in radar and range finding, collision avoidance, digital transmission (including HDTV, MMDS and LMDS), satellites, and automobiles and engine sensors. The high temperature and high single-transistor power capabilities would make the devices particularly useful for portable and aerospace applications. A successful Phase I effort will result in substantially improved nitride HEMTs on bulk AlN and GaN substrates with record dc and microwave properties.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
The electron transport properties at the AlGaN/GaN interface along with the high electron saturation velocity and high breakdown fields in GaN are the basis for the superior performance of nitride-based high electron mobility transistors (HEMT). These devices show high-frequency low-noise and high-power operation. Furthermore, the nitride devices are radiation hard and can operate at elevated temperatures. Applications such as satellite communication would greatly benefit from the improved performance of III-N HEMTs grown on native substrates.
| PROPOSAL NUMBER: | 02- E2.04-8621 (For NASA Use Only - Chron: 023378 ) |
| SUBTOPIC TITLE: | Advanced Communication Technologies for Near-Earth Missions |
| PROPOSAL TITLE: | Low-Loss Packaged Ka-Band (26.5 GHz) MEMS Phase Shifter |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Teravicta Technologies, Inc.
2535 Brockton Drive, Suite 500
Austin , TX 78758 - 4411
(512 ) 684 - 8700
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Robert Miracky
miracky@teravicta.com
2535 Brockton Drive, Suite 500
Austin , TX 78758 - 4411
(512 ) 684 - 8700
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
We propose to design, model and characterize a novel, packaged four-bit Ka-band (26.5 GHz) phase shifter employing ultra-low-loss ohmic contact RF MEMS switches. The novelty of this project lies in its use of an innovative package design, wherein the phase shifter is fabricated monolithically with the package underside, yielding an ultra-small surface-mountable device. This leads to a reliable, high bandwidth component. Target specifications for the packaged phase shifter chip are: 3.2 dB average insertion loss, 33 dBm continuous RF power handling, and <10 microseconds switching time. The result of this six-month Phase I project will be a proven design supported by modeling and characterization results, pointing the way to high-yield fabrication and assembly of actual packaged phase shifter chips for an antenna beam steering demonstration in Phase II. Topic E2.04 specifically identifies "low loss MEMS based RF switches" under Component Technology required products.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
- Broadband wireless access
- Wireless local area network backbones
- Telematics
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
A low-loss, packaged Ka-band phase shifter is a key component for space communications using phased array antennas. Uses of phased array antennas include: multi-platform data relay, high rate satellite-to-satellite communications in support of sensor webs, and transmission of large data volumes from space to ground
| PROPOSAL NUMBER: | 02- E2.04-9348 (For NASA Use Only - Chron: 022651 ) |
| SUBTOPIC TITLE: | Advanced Communication Technologies for Near-Earth Missions |
| PROPOSAL TITLE: | Holographic Inter-Spacecraft Transceiver System |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
PHYSICAL OPTICS CORPORATION
20600 Gramercy Place, Building 100
Torrance , CA 90501 - 1821
(310 ) 320 - 3088
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Albert Okorogu, Ph.D.
sutama@poc.com
20600 Gramercy Place, Building 100
Torrance , CA 90501 - 1821
(310 ) 320 - 3088
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
NASA is seeking communication networks that will seamlessly connect terrestrial and space-based nodes, featuring high data rates, high capacity, interactivity with orbital platforms, secure operations, and low latency. In response, Physical Optics Corporation (POC) proposes to develop a novel high-speed, cost-effective, lightweight Holographic Inter-Spacecraft Transceiver (HoIST) communication system, based on flat optics -- environmentally stable, high-efficiency, aberration-corrected large-aperture holographic optical elements (HOEs) -- for inter-spacecraft networks. The HoIST transceiver consists of transmitters that can operate in the 830-1550 nm range or the telecommunications bands S (1480 - 1525 nm), C (1528 - 1565 nm) and L (1570 - 1610 nm), and receivers based on thin multiplexed HOEs, which represent aberration and wavefront-corrected 20 in. transmission-reflection-type phase gratings, arranged in a polygonal configuration. This approach is well suited for any of the inter-spacecraft network configurations (star, ad hoc, or cluster). HoIST is low-cost, lightweight, and fully field-corrected, and supports dynamic communications between orbiting spacecraft with data rates in excess of gigabits per second. In Phase I, POC will develop a preliminary HoIST model to demonstrate its feasibility. In Phase II, an advanced optimized prototype for point-to-multi-point communications will be developed.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
Commercial applications include connection over the "last mile," where fiber optic infrastructure is unavailable. HoIST will securely and redundantly connect businesses to intranets, the Internet, and phone company carriers. Other applications include Voice over Internet Protocol (VoIP), local area networks (LANs), wide area networks (WANs) and metropolitan area networks (MANs). Many benefits of HoIST will be in the medical field, for hospital-to-hospital communications, real-time patient monitoring, remote operations, surgical procedures and patient care, especially in developing countries with limited infrastructure and little access to health and medical practitioners.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
POC's proposed HoIST will benefit many NASA applications that require secure high-speed transmission, high optical performance, low weight, compactness, simplicity, low cost, durability, environmental stability, and narrowband operation. Immediate NASA applications include inter-spacecraft network communication configurations (star, ad-hoc, and cluster), and networks that connect systems monitoring weather patterns, climatic variation, evolution of the Earth and its atmosphere, measurements of dynamic scenes and natural hazards (tornados, lightning, etc.), lidar, and some airborne imaging and sensing applications.
| PROPOSAL NUMBER: | 02- E2.05-7736 (For NASA Use Only - Chron: 024263 ) |
| SUBTOPIC TITLE: | On-Board Propulsion |
| PROPOSAL TITLE: | Pulsed Plasma Thruster Piezo-Igniter for Small Satellite |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
FACE ELECTRONICS, LC
427 West 35th Street
Norfolk , VA 23508 - 3201
(757 ) 624 - 2121
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
ALFREDO VAZQUEZ CARAZO
alfredo@faceco.com
427 West 35th Street
Norfolk , VA 23508 - 3201
(757 ) 624 - 2121
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The proposal approaches to a revolutionary new approach to providing very compact, lightweight, non-RFI/EMI ignition system to be integrated with pulsed plasma thruster (PPT) used for spacecraft attitude control. The design eliminates for the first time conventional discharge capacitor and electromagnetic transformers (heavy and EMI noisy) with a compact and highly efficient novel technology - the piezoelectric technology. The proposal has an important relevance in the current interest on improving the state of the art PPT ignition systems. The novel system uses an AC discharge generation rather than a DC and may be highly controlled to provide different timing and number of sparks to optimize the efficiency of the plasma ignition. Phase I intends to demonstrate the feasibility of the piezoelectric technology for PPT ignition. Phase II will integrate the technology and adapt it to the specifications of the current PPTs. This will lead to the final low-cost advanced flight-qualified system in Phase III. The resulting advanced propulsion system will result in reduced mass and launch/spacecraft cost for small satellites, and will be applicable to precision attitude control and station-keeping for small spacecraft as currently considered by NASA.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
The resulting revolutionary pulsed plasma thruster piezo-igniter concept offers unique benefits in the current small satellite NASA missions program for tightly controlled interferometry constellations. Fine impulse bit control achievable with small satellites enhances spacecraft attitude and positional control capabilities, providing enabling technology to optical interferometer spacecraft constellations envisioned for the future. The results of this R&D effort will improve system simplicity, reduce subsystem components, cost and weight, and increase overall thruster efficiency.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
Interest in small satellites is growing fast worldwide. Businesses, governments, universities and other organizations around the world are starting their own small satellite programs. Smaller satellites offer shorter development times, on smaller budgets and can fulfill many of the functions of their larger counterparts. Consequently, small satellites can complement the services provided by the existing larger satellites, by providing cost effective solutions to specialist communications, remote sensing, rapid response science and military missions, and technology demonstrators. Additionally, the results of this R&D will find applications in many commercial
| PROPOSAL NUMBER: | 02- E2.05-8704 (For NASA Use Only - Chron: 023295 ) |
| SUBTOPIC TITLE: | On-Board Propulsion |
| PROPOSAL TITLE: | MEMS Propulsion Technology Utilizing Decomposing Nitrous Oxide Propellant |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
AeroAstro Corp
20145 Ashbrook Place
Ashburn , VA 20147 - 3373
(228 ) 466 - 9863
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Paul Gloyer
paul.gloyer@aeroastro.com
20145 Ashbrook Place
Ashburn , VA 20147 - 3373
(703 ) 723 - 9800
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
A low cost, high performance propulsion system does not exist that can support small and micro-satellite requirements, that is not burdened with severe hazard and toxicity issues. The VACCO Micro Propulsion System (MPS) represents a leap forward in the application of ChEMS? (metal MEMS) propulsion technology for nanosat and picosat missions, however its capability is limited by reliance on low-Isp, low-density butane propellant. AeroAstro proposes to more than triple the performance of MPS by upgrading it to incorporate decomposing nitrous oxide (N2O) technology. This increase in total impulse of MPS from 33 N-s to over 100 N-s is made possible by a combination of factors including, the liquid density of N2O being approximately double that of butane, allowing twice as much propellant to be stored within the MPS volume, and the exothermal decomposition of N2O produces a hot gas with an Isp that is over two times that of cold butane. By applying AeroAstro?s nitrous oxide technology to VACCO?s MPS, it is possible to triple its performance (200% increase in delivered ∆V/unit mass) providing an enabling technology for nano-spacecraft by allowing them to perform orbit modification and formation flying that is far beyond the current norm.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
Both AFRL and DARPA have identified applications for small, highly maneuverable spacecraft that fit with AeroAstro?s Escort mission framework. Escort is a small maneuverable satellite that can be used to monitor, inspect, or service a larger host satellite. Typical DoD Escort missions applications include the ability to monitor a friendly target satellite?s environment in order to detect attacks, to actively defend a friendly target satellite against attacks by enemy satellites, to inspect a friendly target satellite in order to aid its deployment, monitor its performance and investigate any anomalies it may experience and to attack an enemy target satellite in order to temporarily or permanently disable it, possibly in a stealthy fashion. Commercial versions of the ESCORT satellite can be used to monitor high-value geosynchronous communications satellites for anomalies, assist in on-orbit testing of the communications payload, with the assistance of a tunable RF-probe, and provide imagery for marketing purposes.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
A high-performance and modular small-scale propulsion system can be very effectively incorporated on NASA science missions. Examples of this might include distributed constellation of magnetospheric sensing satellites, such as MagCon, formation flying missions, such as a distributed synthetic aperture interferometer, and as a platform for any instrument package that requires precise pointing requirements (such as PIMI, TechSat-21, and ST-5).
| PROPOSAL NUMBER: | 02- E2.06-7673 (For NASA Use Only - Chron: 024326 ) |
| SUBTOPIC TITLE: | Storage and Energy Conversion |
| PROPOSAL TITLE: | Lightweight Unitized Regenerative Fuel Cell |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Proton Energy Systems Inc
10 Technology Drive
Wallingford , CT 06492 - 1955
(203 ) 678 - 2000
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Frano Barbir
fbarbir@protonenergy.com
10 Technology Drive
Wallingford , CT 06492 - 1955
(203 ) 678 - 2000
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
This Small Business Innovation Research Phase I program addresses the development of a Proton Exchange Membrane Unitized Regenerative Fuel Cell (PEM URFC) Energy Storage System. The PEM URFC provides all the advantages of a primary fuel cell but can recharge itself from an electrical power supply providing very high-density energy storage. Configured with reversible cells, this system is the functional equivalent of a battery yet has the attractive features of a fuel cell such as high specific energy, high energy density, and long cycle life. The specific development having a significant impact on optimization of the URFC for advanced NASA missions is a lightweight cell stack design. We will rapidly transition the results of the successful Phase I into Phase II prototypes of energy storage products suitable for development into flight hardware or into commercial products.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
Back-up power for telecommunications, computer systems, individual homes, yachts
Uninterrupted power supply for remote locations
Various vehicles (particularly airborne and underwater)
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
Energy storage and conversion for Earth Science platforms, such as airborne platforms (piloted or unpiloted aircraft and balloons), terrestrial platforms, sea surface and subsurface platforms.
Energy storage and conversion for space program (spacecraft, vehicles, bases, stations)
| PROPOSAL NUMBER: | 02- E2.06-8468 (For NASA Use Only - Chron: 023531 ) |
| SUBTOPIC TITLE: | Storage and Energy Conversion |
| PROPOSAL TITLE: | High energy density Li-ion polymer batteries with nanocomposite cathodes |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
NANOPOWDER ENTERPRISES INC.
Suite 106, 120 Centennial Ave.,
Piscataway , NJ 08854 - 3908
(732 ) 885 - 1088
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Amit Singhal
amitsinghal@nanopowderenterprises.com
Suite 106, 120 Centennial Ave.,
Piscataway , NJ 08854 - 3908
(732 ) 885 - 1088
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The energy density of Li-ion batteries can be enhanced by utilizing cathodes that have significantly higher energy density than that of state-of-the-art LiCoO2. The proposed program focuses on developing novel nanocomposites with a theoretical energy density of ~ 800 Wh/kg, which is more than 60% higher than that of the practical energy density of LiCoO2. Working in collaboration with a leading developer of Li-ion batteries in Phase I, we will demonstrate that it is possible to produce stable and high energy density nanocomposite cathodes. These cathodes will lead to economical, high energy density and long cycle life rechargeable Li-ion polymer batteries at discharge rates acceptable in commercial Li-ion batteries. As part of Phase I work, the electrochemical properties of these nanocomposite cathodes will be evaluated in Li test cells with a liquid electrolyte. In Phase II, prototype batteries will be fabricated and tested for performance, along with the optimization and scaling of the powder synthesis process.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
Secondary Li-ion polymer batteries are the system of choice for several consumer applications, such as portable consumer electronics, wireless communication devices and implantable medical devices. Smaller and thinner cellular telephones and notebook computers, and emerging portable products such as, personal data assistants and palmtop computers, have created an immediate need for developing advanced rechargeable Li-ion batteries with high energy densities and longer run times. Because of their high current drain requirement, several implantable devices such as, ventricular assist devices (LVAD), implantable hearing assist devices, and some neurostimulators, need secondary batteries for use in both implantable and external battery systems.
The broader impact of the proposed program will be the availability of economical, high energy density secondary Li-ion batteries for several consumer applications. The cathode in Li-ion batteries is a very important constituent and accounts for a worldwide market of more than $250 million/year. Consequently, an economical, high energy density cathode has a major role to play as Li-ion batteries evolve in year to come.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
Rechargeable Li-ion batteries are being used in government furnished equipment (e.g., camera, laptop computers and camcorders) for space applications. Additionally, Li-ion polymer batteries can potentially replace Ni-MH batteries, which are being used for several space applications, including supplement battery pack (called Areba rechargeable battery pack) to power astronaut?s accessories (e.g., wrist computer, glove heaters) during Extravehicular Activities (EVAs), and Avionic batteries (8 modules connected in parallel, each module ~ 28V) for the Crew Return Vehicle, X-38. Furthermore, high voltage and energy Li-ion batteries (270V, 200 Ah) can also be used to power the pump for the hydraulic system in a space shuttle. Presently, a hydrogen turbine is used to power the pump; however, it has a major safety issue, and a Li-ion polymer is a potential replacement.
| PROPOSAL NUMBER: | 02- E2.06-8754 (For NASA Use Only - Chron: 023245 ) |
| SUBTOPIC TITLE: | Storage and Energy Conversion |
| PROPOSAL TITLE: | Low Cost/Mass Electrostatically Clean Solar Array (ESCA) System |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
AEC-ABLE ENGINEERING CO.
7200 Hollister Ave
Goleta , CA 93117 - 2807
(805 ) 690 - 2447
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Bill Gadsby
bgadsby@aec-able.com
7200 Hollister Ave
Goleta , CA 93117 - 2807
(805 ) 690 - 2447
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
ABLE?s Phase 1 proposal objective is to engineer a perfect electrostatic clean solar array (ESCA) based on an innovative design solution, as presented herein, and ready this technology for commercialization and use on the NASA MMS and GED missions. ABLE?s ESCA design uses flight proven materials/processes to create a perfect ESCA system that yields low cost, low mass, high reliability, high power density, and is adaptable to any cell type and coverglass thickness. A logical SBIR Phase 1, 2, and 3 sequential program approach has been conceived to allow for the effective development, validation, qualification, and protoflight/flight acceptance of an optimum ESCA panel design. This multi-phase program approach will enable the advancement of ABLE?s ESCA technology and ready it for commercialization. The proposed 6-month duration Phase 1 program will serve as the concept design and validation phase for ABLE?s ESCA technology. During the Phase 1 program ESCA requirements/goals will be defined, ABLE?s ESCA design will be developed, and representative Engineering Model hardware will be built and tested to validate the feasibility of the proposed solution. The proposed Phase 2 plan includes an 18-month duration program to serve as the qualification phase for the Phase 1 developed ESCA technology.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
The potential non-NASA commercial applications resulting from the proposed ABLE ESCA technology spans a range of high voltage/power applications (in LEO, MEO & GEO), particularly for GEO ?Comsat? missions. Electrostatic interaction and discharge (ESD) as it relates to array performance is of great concern for these applications and for the survivability of the solar array system. Features and/or the entire solution of ABLE?s ESCA design developed for NASA applications are easily implemented to achieve electrostatic cleanliness for use on these non-NASA applications. As such, development of ABLE?s ESCA technology serves the non-NASA (i.e., commercial and military) markets as well.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
The potential NASA applications resulting from the successful development of the proposed ABLE ESCA technology are primarily for advanced spacecraft of NASA?s Sun-Earth Connection Initiative, such as the NASA GSFC MMS and GED spacecraft, and high voltage/power solar array applications (for LEO, MEO & GEO). Many future NASA Sun-Earth Connection missions, and other missions that measure charged fields and particles or require high voltage/power, will require ESCA systems in order to pursue mission objectives. A perfect ESCA system, as proposed by ABLE, will enable these missions to be achieved without risk.
| PROPOSAL NUMBER: | 02- E2.06-9730 (For NASA Use Only - Chron: 022269 ) |
| SUBTOPIC TITLE: | Storage and Energy Conversion |
| PROPOSAL TITLE: | Novel Polyethers Doped with Nanoscale Insulating oxides for Lithium Battery Elec |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
H.V. Setty Enterprises Inc
12110 Red Oak Ct South
Burnsville , MN 55337 - 3312
(952 ) 894 - 2792
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
H.V. Venkatasetty
venka006@tc.umn.edu
12110 Red Oak Ct South
Burnsville , MN 55337 - 3312
(952 ) 894 - 2792
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Novel polyethers doped with insulating oxides are used to prepare solid polymer electrolytes for high energy density lithium batteries. The electrolytes are characterized for conductivity and electrochemical stability. Prototype lithium-polymer cells with high voltage cathodes will be fabricated and feasibility demonstrated for rate capability and cyclability.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
Lithium-polymer solid state batteries with high energy density and power with low cost and enhanced safety have applications in consumer products. Some of these are Laptop computers, Cellular phones , Camcorders and Personnel Digital Assistants (PDAs).
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
These advanced technology based batteries will find applications in LEO and GEO spacecraft operations. Achieving this with lithium-polymer batteries with long operating life and specific energy densities of > 100 Wh/kg is well within the range of feasibility.
| PROPOSAL NUMBER: | 02- E2.08-9561 (For NASA Use Only - Chron: 022438 ) |
| SUBTOPIC TITLE: | Power Management and Distribution |
| PROPOSAL TITLE: | High Temperature Capacitors for Power Converters |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
TRS Ceramics Inc
2820 East College Ave Suite J
State College , PA 16801 - 7548
(814 ) 238 - 7485
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Edward F. Alberta
Ed@TRSCeramics.com
2820 East College Ave Suite J
State College , PA 16801 - 7548
(814 ) 238 - 7485
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
High temperature capacitors based on a new family of ferroelectrics are proposed. The Curie temperatures of the (1-x)BiMeO3 - (x) PbTiO3 (Me = Sc, In, Yb, or Fe) family have been found to range from 450C to >600C. Multilayer ceramic capacitors based on these materials offer a distinct advance in the working temperature compared to currently available devices. The aim of this Phase I project is to fabricate prototype high temperature capacitors with capacitance values ranging from 10nF to 1microF at ~300C using standard multilayer capacitor fabrication techniques. After initial studies determine the most desirable composition(s), prototype capacitors will be fabricated and tested. Electrical testing will primarily be focused on reliability issues including HALT testing, impedance spectroscopy, insulation resistance, and leakage mechanisms. Finally, the performance of the prototype capacitors will be compared to commercially available devices.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
Potential NASA applications of the proposed high-temperature capacitors include robust high-temperature electronics, power distribution systems, and power conversion systems. The proposed devices will capable of functioning at temperatures well in excess of commercially available devices. This advance in operating temperature will reduce, or completely eliminate the need for cooling systems, thereby reducing the overall size and weight of electronic systems aboard spacecraft.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
Potential commercial applications include high power electronics, signal conditioning, avionics, and consumer electronics. Decoupling capacitors for use in high-performance computing devices offer the possibility of developing a family of high-volume products that would lower device costs to both NASA and non-NASA consumers.
| PROPOSAL NUMBER: | 02- E2.08-9689 (For NASA Use Only - Chron: 022310 ) |
| SUBTOPIC TITLE: | Power Management and Distribution |
| PROPOSAL TITLE: | Establishing High Voltage Connector Designs and Test Standards for Space Use |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Reynolds Industries, Inc
5005 McConnell Ave
Los Angeles , CA 90066 - 6734
(310 ) 823 - 5491
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Jim Rush
jrush@reynoldsindustries.com
5005 McConnell Ave
Los Angeles , CA 90066 - 6734
(310 ) 823 - 5491
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The spaceflight instrument community has a need for sub-miniature high voltage connectors that are capable of being used in spacecraft electronic applications such as transmitters, modulators, ion propulsion and other instrumentation. These connectors should be rugged, exhibit low outgassing, have different configurations matched to particular needs, and be rated to reliably operate at voltages exceeding 5,000 volts.
Existing high voltage connector designs are used for TWTAs, radar, aircraft cockpit displays, physic experiments and other applications with excellent reliability. Although these specialized high voltage connectors have been successfully adapted to similar spaceflight applications, the unique demands of space create a need for improved designs that are small and extremely reliable when operated in a vacuum environment. The proposed interconnection solution, described herein, meets this need.
NASA specifications impose requirements for selection of parts and design of spacecraft wiring systems nevertheless they do not address specific requirements for high voltage connections in spacecraft. Therefore, a need exists for a series of miniature high voltage connectors that are immune to the rigors of the space environment as well as associated application data on the derating, testing, maintenance and assembly of the high voltage interconnection systems.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
Commercial spaceflight instruments where high voltage power will be used. Other non-NASA applications would include the European Space Agency (ESA) using similar instruments, as well as, commercial applications where miniature high voltage components are used.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
Spaceflight instruments and space avionics where high voltage power will be used. High voltage connectors and cables are used in a wide variety of high reliability spaceflight instruments such as UHF and S-Band Transmitters, Space Radar Modulators, Intensified Optical and UV Cameras and Telescopes, Gamma Ray Instrumentation, Mass spectrometer Systems, Intensified lights for spacecraft docking and Ion propulsion.
| PROPOSAL NUMBER: | 02- E3.03-7924 (For NASA Use Only - Chron: 024075 ) |
| SUBTOPIC TITLE: | High Performance Computing and Networking |
| PROPOSAL TITLE: | Intelligent and Dynamic High Performance Optical Network |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Intelligent Fiber Optic Systems
650 Vaqueros Ave.
Sunnyvale , CA 94085 - 1260
(408 ) 328 - 8610
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Behzad Moslehi
bm@ifos.com
650 Vaqueros Ave.
Sunnyvale , CA 94085 - 1260
(408 ) 328 - 8610
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Next generation of high performance networks supporting reconfigurable computing, paralellel/cluster computing, optical computing as well as the Next Generation Internet (NGI) will require significant upgrades in data transport capacity, reconfigurability and survivability
Responding to NASA?s increasing need for high performance computing and networking, IFOS proposes developing a novel high performance optical network using IFOS?s innovative Intelligent and Dynamic Optical Add-Drop Multiplexer (ID-OADM). The ID-OADM combines the features of the tunable OADM with intelligent operational algorithm to minimize the ?tunability service disruption? while selecting a specified wavelength. This feature can significantly reduce the cost of deploying and operating future generations of NGI optical networks with ring topology. This approach facilitates the rapid reconfiguration of networks without the need for restructuring the network protocols or topologies.
The main goal of this Phase I project is to fabricate and demonstrated a prototype of a programmable ID-OADM using tunable BG filter based on magnetostrictive materials. For the features and performance evaluation of this prototype, a demonstrative optical ring network will be used.
In Phase II the results of Phase I will be extended towards commercialization. For this purpose, a production grade ID-OADM will be fabricated and its applications and performance in larger networks will be demonstrated.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
Low-cost, high volume production of advanced photonic components and systems is of vital importance if the US is to achieve the proliferation of Fiber-To-The-Home or Desk (FTTH or FTTD), as well as potentially distance-independent terabits-per-second (Tbps) global interconnectivity, without relying on foreign suppliers for optoelectronic components.
IFOS is committed and well positioned to actively promote and support the commercialization of any products developed under this project. The company is dedicated to bringing products from conception into the market. Our plan is to carry products through four key stages: engineering prototype, manufacturing prototype, pilot line and mass production. In addition to government projects, IFOS is collaborating in the private sector to support current commercialization and future product development through joint ventures and licensing agreements.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
The proposed intelligent dynamic optical network technology can have numerous applications in NASA?s future advanced high speed reliable and survivable optical communication and sensor networks, future Advanced Computing Technology (ACT) including high performance computing with reconfigurable architectures and optical parallel/cluster computing. Communications systems and sensors wide area networks supporting highly survivable data transport systems. The NASA/Langley Research Center could employ the IFOS solution to handle the bandwidth-intensive communications problems. Furthermore, the success of this project will lay a solid foundation and sets the stage for development of advanced intelligent optical technologies, guaranteeing the success of NASA?s Earth Science Technology Office (ESTO) in its important mission and national priorities. .
| PROPOSAL NUMBER: | 02- E3.03-8029 (For NASA Use Only - Chron: 023970 ) |
| SUBTOPIC TITLE: | High Performance Computing and Networking |
| PROPOSAL TITLE: | Next Generation Write Head for Commercial Holographic Data Storage |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Displaytech, Inc.
2602 Clover Basin Drive
Longmont , CO 80503 - 7604
(303 ) 774 - 2254
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Chris Walker
chrisw@displaytech.com
2602 Clover Basin Drive
Longmont , CO 80503 - 7604
(303 ) 772 - 2191
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Enormous data capacities and high read/write rates make optical holographic data stor-age (HDS) systems the most promising approach for next-generation computer mass-storage solutions. Recent breakthroughs in holographic recording media have dramatically accelerated the development of commercial HDS products, and have shifted the development focus to opti-mization of HDS optical systems and components. We propose here the development of an optimized HDS write-head component comprising a spatial light modulator (SLM) with inte-grated optical phase mask. This integrates essential optical beam conditioning functions into the write-head to eliminate recording-plane ?hot spots? that otherwise saturate the recording media, reducing capacity and fidelity. Our integrated approach uniquely accomplishes this without increasing HDS system cost or complexity. The use of innovative micro-optics tech-niques to fabricate the phase mask will allow SLM production to remain compatible with proven liquid-crystal-on-silicon (LCOS) microdisplay mass-production processes, ensuring write-head manufacturability. Development of this optimized write-head component will enable compact, inexpensive HDS drives offering storage capacities from 100 GB to over 1 TB and read/write rates in excess of 1 Gb/s on removable, archival media. Such drives will have widespread application, initially in professional digital video recording and in enterprise archive and backup networks, and eventually in personal computing.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
Initial holographic data storage products are expected to offer removable-media, WORM (write once read many times) functionality, and are targeted for enterprise and professional applications. Ongoing cost and performance improvements should result in products with rewrite capability and costs low enough to hit consumer and personal computing markets. Market segments for initial products where these attributes are important include: 1) professional digital video recording and digital-cinema content distribution, 2) general-purpose enterprise data archives and backup, and 3) medical image acquisition and storage.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
Initial HDS products are expected to offer removable-media, WORM (write once read many times) functionality, and are targeted for enterprise and professional applications. Ongoing cost and performance improvements should result in products with rewrite capability and costs low enough to hit consumer and personal computing markets. Of special importance to NASA, these products will be valuable for earth-sciences and geophysics data acquisition, processing, and storage.
| PROPOSAL NUMBER: | 02- E3.03-8041 (For NASA Use Only - Chron: 023958 ) |
| SUBTOPIC TITLE: | High Performance Computing and Networking |
| PROPOSAL TITLE: | Grid Computing for Commercial Applications |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
3DGeo Development Inc.
465 Fairchild Drive, Suite 227
Mountain View , CA 94043 - 2251
(650 ) 969 - 3886
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Dimitri Bevc
dimitri@3dgeo.com
465 Fairchild Drive, Suite 227
Mountain View, CA , CA 94043 - 2251
(650 ) 969 - 3886
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
This Phase I project will demonstrate a virtual computer environment that links geographically dispersed computer systems over the Internet to solve large computational problems. Ultimately, the technology will deliver compute power from dedicated sources, over the Internet, on-demand, creating a business paradigm where companies can concentrate on their core competencies, and rely on other entities to provide context technologies which are critical to business success, but which can potentially detract from the primary business objective. The ultimate goal of this paradigm (and the Phase II project) is that cpu cycles will be a commodity purchased by end users, much like electric power. Companies and Government Agencies (such as NASA) engaged in scientific computing will not be burdened with the concerns of system architecture, system maintenance, backups, and other issues associated with high performance computing. The only concern will be how many teraflops are required to solve a given problem. Once that is estimated, the teraflops of compute power can be purchased over the Internet, much like kilowatts of electric energy are purchased over the power grid. The Phase I project will implement and demonstrate an earth science computing application over the Internet on a large-scale (100 to 1000 cpu) system.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
This project has implications beyond the seismic and energy applications demonstrated herein. The concept of remote commercial scientific computing and TeraGrid utilization applies to other compute intensive fields such as: fluid flow modeling (oil and gas reservoir simulation and environmental applications), aeronautics and aerospace, biological simulation (DNA sequencing and genetic simulation), computational chemistry, astrophysics, and computational physics. This proposed project will strengthen 3DGeo's marketing push and allow 3DGeo to more effectively deliver its core imaging technology to worldwide and local markets by harnessing Internet resources.
The advanced seismic imaging technology directly impacts the discovery and recovery of hydrocarbons and could decrease the United State's dependence on imported oil and create jobs in the oil service industries. In existing oil fields, better seismic images of complicated subsurface geology reduce development costs and increase (1) the amount of hydrocarbons recovered and (2) the amount of national oil reserves.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
This product will allow effortless and efficient access to NASA computer resources that are geographically dispersed. It will also facilitate access to external computing resources for computationally intensive tasks. This will make computing resources universally available, and give NASA researchers access to tremendous compute power to solve large engineering and scientific problems on an as-needed, on-demand basis. The application developed in Phase II will be relevant for any compute intensive and data intensive NASA application. Applications in this category include: astrophysics, helioseismology, aerodynamic simulation, biological simulation computational chemistry, and computational physics, and earth science applications such as environmental applications, fluid flow modeling, and simulation of planetary interiors. The Phase II product will offer an infrastructure which will allow NASA scientists and engineers to easily and efficiently harness system-wide and third party resources in order to accomplish their computational tasks.
| PROPOSAL NUMBER: | 02- E3.04-7675 (For NASA Use Only - Chron: 024324 ) |
| SUBTOPIC TITLE: | Geospatial Data Analysis Processing and Visualization Technologies |
| PROPOSAL TITLE: | BasinTools Module 1, Online Remote Sensing Interface |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
NVision Solutions Inc.
Suite 146J, Bldg 1103, SSC
Stennis Space Center , MS 39529 - 6000
(228 ) 688 - 3951
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Socorro Harvey
sharvey@nvisionsolutions.com
Suite 146J, Bldg 1103, SSC
STennis , MS 39529 - 6000
(228 ) 688 - 3951
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
BasinTools is designed to facilitate the use of remotely sensed data by users who are not remote sensing specialist. Information from remotely sensed data would be used by a wide variety of engineers, planners, and scientist except they lack the expertise, sophisticated software, or high-end hardware to make use of the data. Federal, State, and Local Governments all have need of information derived from remotely sensed data, yet when faced with the overwhelming cost of implementation they invariably opt for more affordable, less accurate alternatives.
The proposed study prototypes the implementation of a Web-based application that is user friendly, affordable, and accurate. The prototype will provide ?canned? push button analysis of imagery a user is viewing through the Web portal and viewing results of the analyses on the fly through the custom online viewing tools. This Web based approach limits the amount of requisite user expertise, software, hardware, and computing power necessary to perform these analyses. Commercial manufacturers have employed the use of just-in-time inventory control for decades, this innovation applies the same cost saving logic to remotely sensed data; products are created and delivered on the fly with no human intervention via the Web
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
There are three areas where this prototype may have immediate impact on markets: Education; Commercial data vendors; and Application Services (precision ag, facility management, forestry). Academia won?t need expensive computer labs or sophisticated software to teach remote sensing. Commercial data vendors will allow per kilometer sales with no minimum order using automated subsetting and data delivery systems. Custom products will be created and delivered in real time. This system will enable profitable application services to fully mature, Precision Ag in stands to advance substantially, where the time between data acquisition and delivery of personalized products is reduced or eliminated entirely.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
The prototype application will allow NASA to post remotely sensed data to a Web site in real or near-real time and have that data available to users in the NASA scientific community instantly. NASA will realize the following benefits: Real-time or near-real time data availability; Store once - share enterprise level (mitigates cost of storing data on local machines); Automated- controlled distribution of data sets; Reduces the number of remote sensing software licenses required (enterprise wide); Resolves many data licensure issues by distributing only derivative products
| PROPOSAL NUMBER: | 02- E3.04-7981 (For NASA Use Only - Chron: 024018 ) |
| SUBTOPIC TITLE: | Geospatial Data Analysis Processing and Visualization Technologies |
| PROPOSAL TITLE: | Automated, Universal Software for Cloud and Cloud Shadow Detection in RS Data |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
SMH Consulting
2664 Wild Turkey Lane
Alexandria , VA 22314 - 5814
(703 ) 567 - 2411
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Stephanie Hulina
smhulina@yahoo.com
2664 Wild Turkey Lane
Alexandria , VA 22314 - 5814
(703 ) 567 - 2411
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Limitations with existing cloud cover detection (CCD) techniques for large dataset processing and new challenges presented by the increase in the quantity and quality of data in the commercial realm, offer an opportunity for R&D into new and improved methods for the detection of clouds and cloud shadows in acquired imagery. We propose to develop innovative software for automated pixel-based cloud and cloud shadow detection. The novel, iterative, self-guided approach will rely on spectral and spatial information from a limited number of bands (R-G-B or R-G-B-NIR) and will be applicable to large datasets of a wide range of commercial and government space- and air-borne imagery. Our techniques will be refined by algorithmic testing on a variety of image types and by consulting with industry experts on their assessment of the applicability of the algorithms to their data and to the needs of their end users. Further, in order to flesh out the market and requirements for successful commercialization, we propose to research novel methodologies and inputs to: (1) recovery and substitution of cloud and cloud shadow contaminated pixels, (2) on board real-time CCD processing, and (3) cloud cover monitoring, forecasting, and avoidance strategies.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
Results of the cloud and cloud shadow detection technique can be used to:
--Automatically (100%) update the cloud cover percentage metadata tag (QA/QC)
--Generate a cloud and cloud shadow mask as an additional layer sold to the end-user
--Reschedule failed acquisitions
--Assess cloud cover contamination in real-time mode, i.e. on board, during the data acquisition
--Recover data in transparent cloud shadow areas
--Substitute cloud and cloud shadow pixels representing data loss
--Develop historic cloud cover dataset with spatial and temporal resolutions higher then those currently available
--Monitor cloud cover in near-real time mode and assess its trend
--Forecast cloud cover from historic and actual cloud data
--Formulate reliable cloud avoidance strategies through complimentary use of historical and actual cloud data
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
The proposed innovations address the need within the ES community for streamlined acquisition and automated processing of very large volumes of remote sensing data. Specifically, our unique innovations for CCD address the subtopic by:
--Employing rapid analysis methodologies and algorithms
--Improving the automated process of quality assurance /quality control for science data products
--Facilitating the efficient collection of data
--Fusing data from diverse space- and air-borne sensors to derive unique, commercially useful information
| PROPOSAL NUMBER: | 02- E3.04-8647 (For NASA Use Only - Chron: 023352 ) |
| SUBTOPIC TITLE: | Geospatial Data Analysis Processing and Visualization Technologies |
| PROPOSAL TITLE: | Next Generation, Low Cost, Direct Geo-referencing of Aerial Images |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Seagull Technology, Inc.
1700 Dell Avenue
Campbell , CA 95008 - 6902
(408 ) 364 - 8200
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Dr. Sharon Houck
sharon@seagull.com
1700 Dell Avenue
Campbell , CA 95008 - 6902
(408 ) 364 - 8200
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Today, direct geo-referencing is performed with very expensive (>$50,000 in parts alone) differential GPS and inertial measurement units (IMUs) that produce precise measurements of the camera attitude and position in the sky. Further, most existing systems require the establishment of ground control points to achieve required accuracy, incurring further costs and limitations. Seagull proposes to develop a next-generation, low-cost direct geo-referencing system that will substantially reduce the cost (to <$4,000 in parts), size, and power requirements while still enabling better than 2 m spatial resolution and eliminating the need for ground control points. The innovation underlying Seagull?s position and attitude solution is our proven, advanced sensor fusion algorithms that combine differential carrier phase GPS with data from low-cost angular rate sensors and accelerometers to produce a highly accurate and stable platform attitude solution. The goal of this Phase I proposal is to leverage our recent experience in developing and deploying low cost, airborne portable sensor suites to produce a preliminary design specification for the next generation of an efficient, advanced, low cost position and attitude system for multi-sensor, multi-spectral airborne image registration without ground control points, which would then be prototyped and tested in Phase II.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
The commercial applications for this product are numerous, including precision farming, mining, coastal surveying, urban surveying, urban warfare targeting, incident management, and precision fire fighting. Although designed to be lightweight and low cost, suitable for small piloted and unpiloted aircraft, this system will also be usable in larger airframes. Commercial and scientific aerial imagery buyers and sellers will directly benefit from the order of magnitude reduction in price of obtaining direct geo-referencing position and attitude measurements.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
The value to NASA programs of this project is large. Remote imagery is a major research and commercial interest of NASA. In particular, the NASA Mission to Planet Earth and Highly Resilient UAV (Goddard) projects make extensive use of platform orientation and precise positioning technology, for which the proposed development is ideal. The availability of a low cost position and attitude system for direct geo-referencing will enable more frequent and less costly aerial photography missions.
| PROPOSAL NUMBER: | 02- E3.05-9615 (For NASA Use Only - Chron: 022384 ) |
| SUBTOPIC TITLE: | Data Management and Visualization |
| PROPOSAL TITLE: | Commercial GIS extension for visualization of large unstructured geospatial data |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
ProLogic, Inc
1000 Technology Drive
Fairmont , WV 26554 - 8824
(304 ) 363 - 1157
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Chetan Desai
chetan@prologic-inc.com
1000 Technology Drive
Fairmont , WV 26554 - 8824
(304 ) 363 - 1157
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The proposed innovation is new technology to enable the visualization of large unstructured geospatial datasets, such as LIDAR (LIght Detection And Ranging) data, within a commercial desktop Geographic Information System (GIS). The proposed architecture uses a high performance computing (HPC) platform to process the datasets and create visualization models, and then integrates 3D visualization into a GIS environment. For this research, cluster computing (a collection of interconnected commodity PCs implementing parallel processing techniques) will serve as the ?back-end?, with visualization and GIS integration provided through an extension to the ArcGIS system.
The significance of the innovation is that it would:
* Provide users new ability to visualize large datasets at their full resolution at varying scales;
* Be implemented as a commercial GIS software extension, thus:
- leveraging geospatial data and geoprocessing techniques supported by GIS systems
- extending capability without requiring users to learn a new software interface;
* Enable users to process the data faster and more efficiently, using real-time data browse within the GIS?s display window;
* Incorporate the necessary computing power to process the large unstructured datasets for visualization (for now, through the use of cluster computing?future hardware improvements would provide additional high-performance computing platforms).
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
There are numerous applications of the proposed innovation for commercial organizations and non-NASA agencies. Some of these applications include:
* Weather Investigations: The 3D point cloud model often represents weather data. This extension could greatly facilitate the modeling and predicting of weather phenomena.
* Defense Applications: This extension has great potential in the defense market. Much research has been conducted regarding feature extraction and target identification of high-density data. For example, DARPA is currently working on a project called Jigsaw, which is aimed at target verification and identification. This extension could greatly advance that endeavor.
* Disaster Response: This extension could be very useful for disaster response agencies like FEMA. FEMA requires high-resolution terrain models and is very interested in LIDAR data. This extension could enable FEMA to process the large dataset in a fast efficient manner. Fast processing is critical for effective response to natural disasters.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
Some applications for the NASA organization include:
* Planetary applications: This extension can be used to generate terrain from satellite-based LIDAR systems for Mars exploration. The spatial analysis capabilities will enable NASA to accurately choose optimal landing sites or base stations.
* Outreach: A variation of the proposed extension could be used in museums or classrooms as a way to teach non-technical personal about different types of remote sensing data and their uses.
* Earth Science Applications: This extension could enhance the wide variety of Earth Science investigations conducted within NASA.
| PROPOSAL NUMBER: | 02- E4.01-8282 (For NASA Use Only - Chron: 023717 ) |
| SUBTOPIC TITLE: | Innovative Tools and Techniques Supporting the Practical Uses of Earth Science Observations |
| PROPOSAL TITLE: | Ultra Wide band Water Sensor |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Intelligent Automation, Inc.
7519 Standish Place Suite 200
Rockville , MD 20855 - 2785
(301 ) 294 - 5229
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Eric van Doorn
evandoorn@i-a-i.com
7519 Standish Place Suite 200
Rockville , MD 20855 - 2785
(301 ) 294 - 5200
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
We propose to use Ultra Wide Band Radar (UWB) as a sensor for soil moisture and water content of snowpack. The key innovations are the application of UWB to form Synthetic Aperture images using a UWB radar mounted on a Unmanned Air Vehicle (UAV). Initial results indicate excellent sensitivity of UWB to moisture. Key features of UWB for this application are low power, ?ghost free? SAR imaging, and sub inch ranging accuracy.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
Military applications are many for UAV mounted radar visions systems, including home land defense, area surveillance, and scouting operations. Commercial applications include management of snow cover at ski resorts.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
Direct NASA applications are water detection (Mars), and earth science projects. The sensor can also be used for accurate terrain profiling in situations where satellite imagery is not available.
| PROPOSAL NUMBER: | 02- E4.01-8501 (For NASA Use Only - Chron: 023498 ) |
| SUBTOPIC TITLE: | Innovative Tools and Techniques Supporting the Practical Uses of Earth Science Observations |
| PROPOSAL TITLE: | Universal Stabilized Platform for Hyperspectral Sensors |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
OPTO-KNOWLEDGE SYSTEMS, INC. (OKSI)
4030 Spencer St. Suite 108
Torrance , CA 90503 - 2442
(310 ) 371 - 4445
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Nahum Gat
nahum@oksi.com
4030 Spencer St. Suite 108
Torrance , CA 90503 - 2442
(310 ) 371 - 4445
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Airborne hyperspectral sensors of the pushbroom and whiskbroom type build up spatial imagery one strip (pushbroom) or one pixel (whiskbroom) at the time. As the platform undergoes attitude changes in flight (yaw, pitch, roll), the line of sight moves around and the collected imagery suffers from geometrical distortions. This affects every instrument built and operated that is subject to atmospheric disturbances. The distorted images can not be well geo-registered for incorporation into a GIS data base. Available solutions are (i) software correction to the images based on flight attitude data collected using a strap down gyro system, or (ii) mounting the sensor on a stabilized platform. The former is a difficult and unreliable process, while the latter is a very expensive solution, impractical with many small air crafts. Examples for the former include the AVIRIS low altitude flights that require a significant effort after which the data are still not completely registered.
OKSI proposes a much less expensive solution in which the sensor is strapped to the aircraft but to compensate for the aircraft motion the sensor line of sight is continuously stirred, using a closed loop control system. Since the mass to be controlled is very low, the actuation and control system will be simple and relatively inexpensive. Such line of sight stabilizer can be adapted to other hyperspectral sensors with a relative small effort.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
To fulfill the promise of hyperspectral imaging in various remote sensing applications, data must be compatible with GIS applications. The proposed stabilizer system will significantly reduce the level of effort that is required for aircraft motion compensation and geo-referencing imagery and therefore will result in major cost savings to sensor operators, processors and VAR of data products.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
With the proposed solution, NASA's airborne instruments can be better stabilized at a lower cost to improve overall image quality and eliminate complex data processing steps.
| PROPOSAL NUMBER: | 02- E4.02-9651 (For NASA Use Only - Chron: 022348 ) |
| SUBTOPIC TITLE: | Advanced Educational Processes and Tools |
| PROPOSAL TITLE: | Rich Annotation of Images |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Innovative Decision Technologies, Inc.
9000 CYPRESS GREEN DR, 107
JACKSONVILLE , FL 32256 - 5509
(904 ) 636 - 6374
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Pramod Jain
pramod@indent.org
9000 CYPRESS GREEN DR, 107
JACKSONVILLE , FL 32256 - 5509
(904 ) 636 - 6374
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Objective is to significantly enhance the ability to describe, catalog, search and retrieve images through the use of rich annotations (RA) of features in an image. Traditional approaches rely on text-based notes and keywords in metadata; proposed approach will use annotation layer (AL). AL contains drawings and icons to mark features, and domain specific properties to describe the features. Properties of features are described using a structured format with controlled vocabulary. AL is created in a web browser-based Rich Annotation Workbench (RAW) using Scalable Vector Graphics.
RAW will foster collaboration between earth scientists and educators, and foster productive use by novice users through ability to: a) overlay multiple AL on image, b) share, reuse and extend domain specific annotation palette.
RAW has commercial applications in: Digital Asset Management, telemedicine, and e-learning.
Approach is to: create domain specific annotation palettes; enhance our existing iAnnotate platform to create RAW; define RDF-based metadata model for RA; integrate with existing Earth Sciences digital library metadata repositories of NASA-GCMD and DLESE.
Anticipated results: Phase I, prove feasibility that RA of features can be metadata for images; Phase II, enhance and commercialize RAW to be an annotation service in a variety of domains.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
National Science Digital Library (NSDL) can use web-based RAW for authoring image based content by describing features of an image in annotation layers. This will significantly increase the use of digital images in education material at all levels.
Sharable Content Object Reference Model (SCORM) compliant Computer-Based Instruction, Training and Testing. Annotation system can be applied to instruction and testing in areas that involve image analysis and interpretation, like medicine, reconnaissance, and meteorology.
Tele-medicine systems can use annotation for remote diagnosis, treatment and monitoring of patients based on images captured at remote locations. RAW can facilitate rich communication between specialists, general physicians and patients.
General-purpose web-based annotation service for annotating images. RAW will be a cost effective solution for businesses that deal with paper-based blueprints: architects, builders, property managers and real estate companies. These businesses will benefit by keeping track of dynamic data electronically as annotations versus marking up paper-based layouts.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
Annotation service to Global Change Master Directory (GCMD) of NASA and ADEPT/DLESE/NASA (ADN).
GCMD may use RAW to create richer feature based metadata for images in their collection. RAW will provide a significantly more effective capability to catalog, search and retrieve images because it uses a structured format and controlled vocabulary to describe the features. The ability of annotation layers to visually describe features in an image can be very appealing to users. In addition, the task of creating such rich metadata for images is made less onerous.
ADN may use RAW to foster collaboration between earth scientists and educators. Web browser based user friendly tool with domain specific annotation palette will make the task of creating education content less daunting. Educators will be able to search using a rich set of criteria on annotation properties, and create new annotations on top of annotations done by previous users.
| PROPOSAL NUMBER: | 02- E4.02-9815 (For NASA Use Only - Chron: 022184 ) |
| SUBTOPIC TITLE: | Advanced Educational Processes and Tools |
| PROPOSAL TITLE: | EarthTutor: An Earth Science Satellite Imagery Tutor |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Stottler Henke Associates, Inc.
1660 S. Amphlett Blvd. Suite 350
San Mateo , CA 94402 - 2526
(650 ) 655 - 7242
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Dr. Sowmya Ramachandran
sowmya@shai.com
1660 S. Amphlett Blvd. Suite 350
San Mateo , CA 94402 - 2526
(650 ) 655 - 7242
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
We propose to develop EarthTutor, an Intelligent Tutoring System that extends NASA's Image2000 software, and an accompanying authoring tool used to create new tutorials. The system will be innovative in that it delivers a learning experience that is more visual, interactive, and adaptive than experiences offered by current remote sensing learning materials. EarthTutor aims to offer the benefits of a one-on-one human instructor. EarthTutor will demonstrate image processing and Earth science skills and concepts, ask questions, offer challenges, monitor and assess the student, and provide contextual guidance. EarthTutor will run tutorials created with the separate authoring tool. The tool will be basic enough to allow teachers to construct tutorials to fit one's curriculum, but also powerful enough to allow advanced authors to create highly-interactive tutorials that engage students in unprecendented ways. SHAI will work with SEE, CIPE, and educators to design and implement a library of tutorials that simultaneously teach image processing skills and Earth science principles to students.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
SHAI will market EarthTutor to Earth science-related curriculum providers. We will apply EarthTutor's technologies to other sciences that use image processing tools. SHAI will also approach educational game makers.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
EarthTutor will provide Image2000 with a cutting-edge educational component. The system will be an effective Earth science learning tool for K-12, undergraduate, and graduate students as well as principal investigators. Image processing tutoring technology can also be applied to other sciences of interest to NASA.
| PROPOSAL NUMBER: | 02- H1.01-9980 (For NASA Use Only - Chron: 022019 ) |
| SUBTOPIC TITLE: | Process and Human Factors Engineering Technologies |
| PROPOSAL TITLE: | A DISCRETE EVENT SIMULATION MODEL FOR SPACEPORT OPERATIONS (SPACESIM) |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Nevins Software, Inc.
P.O. Box 308
Morris , IL 60450 - 8462
(815 ) 941 - 2406
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Mike Nevins
mnevins@nevinssoftware.com
P.O. Box 308
Morris , IL 60450 - 8462
(815 ) 941 - 2406
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The NASA vision for the spaceport of the future entails the transition over time from very high-cost, research oriented space launches with a relatively low frequency of launches to an environment where spaceports are commercialized for the space transportation industry and are required to support multiple launches per day in a safe, cost-effective manner. The spaceport of the future may resemble, from an operational perspective, our current airports and seaports of today and will need to resolve many similar issues to these transportation hubs. These issues include (1) safe and secure spaceport operations, (2) efficient movement of machinery and people through the spaceport, and (3) cost-efficient, affordable, and timely spaceport operations. Discrete event simulation has been used to assess detailed processes at modern day seaports. Like seaports, spaceport operations are labor intensive and require extensive use of personnel and machinery. The ability to conduct seaport operations efficiently has been improved significantly through proper utilization of seaport assets. This foundation provides a solid footing from which research for efficient spaceport operations can be based. An object-oriented discrete event simulation system is proposed that will address spaceport operations in the context of aerospace safety, mobility, and efficiency. The simulation system will be built upon the Java programming language to provide for maximum portability and will utilize XML for standards-based data interchange. Development of the simulation model will provide the underlying basis for follow-on activities such as 2D and 3D animation and visualization capabilities. Technology transfer of lessons learned in the development of seaport simulation models will be utilized. The overall goal of the spaceport simulation model is to maximize throughput, operational safety, and resource utilization and minimize overall cost of operations.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
The potential commercial applications for the SPACESIM model are limitless. As the spaceport industry is commercialized and our society accepts space transportation as a common mode of transportation, SPACESIM will be able to be used at spaceports worldwide to ensure that operations are conducted in a cost-efficient manner. In addition, the SPACESIM model has potential integration possibilities with other transportation simulations to provide macro level ?end-to-end? simulations of an entire transportation grid including all modes of transportation. The benefits to society are that cost will be driven down over time to the point that space transportation is affordable to the overall at-large population.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
The results of the Phase I and Phase II research activities will be a powerful, flexible, object-oriented discrete event simulation system for spaceport operations. The simulation model will provide spaceport planners with the necessary tools to conduct ?what-if? scenarios to facilitate decision-making and to improve throughput, minimize operational bottlenecks and delays, and maximize resource utilization.
| PROPOSAL NUMBER: | 02- H2.01-7744 (For NASA Use Only - Chron: 024255 ) |
| SUBTOPIC TITLE: | In Situ Resources Utilization of Planetary Materials for Human Space Missions |
| PROPOSAL TITLE: | Carbothermal Lunar Regolith Processing System (CLRPS) |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Orbital Technologies Corp
Space Center, 1212 Fourier Drive
Madison , WI 53717 - 1961
(608 ) 827 - 5000
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Robert J. Gustafson
gustafsonr@orbitec.com
Space Center, 1212 Fourier Drive
Madison , WI 53717 - 1961
(608 ) 827 - 5000
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
ORBITEC proposes to develop an integrated carbothermal lunar regolith processing system (CLRPS) to produce oxygen and a variety of other useful materials to support future lunar exploration activities. The CLRPS utilizes carbothermal reduction of regolith via a direct energy source to extract oxygen, silicon, iron, ceramics, and other useful by-products from lunar regolith. The CLRPS products would be used for life support, propellant applications, solar cells (Si), electric wire or metal parts (Fe) and other infrastructure development (e.g. ceramics/bricks, fibers for composites, etc.). The CLRPS concept eliminates many of the problems found with other lunar oxygen production approaches, such as the continuous need for high-temperature containers from Earth, reagents that are consumed during processing, and extensive beneficiation of the lunar regolith prior to processing. The CLRPS would be designed to operate virtually anywhere on the surface of the Moon and the technology could be extended for use on Mars or various asteroids. Phase I will involve prototype design and testing, research and design of the support systems, and investigation of available direct energy heating sources. Phase II will involve design, development, and testing of a closed-loop prototype CLRPS unit.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
Development of technologies required for the processing of carbon monoxide could lead to methods of removing carbon monoxide and carbon dioxide from the atmosphere, and in support of reducing harmful emissions from waste streams in terrestrial processes. Processes developed here may have direct application to commercial exploitation of space resources through direct energy processing while creating propellants for return missions to Earth.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
The results of this effort are applicable to future exploration and/or colonization missions to the Moon, Mars and beyond. Efficient and reliable production of oxygen and metals on the Moon will enhance and/or enable a variety of solar system exploration programs by providing a very cost-effective supply of oxygen in addition to other raw materials. The CLRPS products would be used for life support, propellants, solar cells (Si), electric wire or metal parts (Fe) and other infrastructure development (e.g. ceramics/bricks, fibers for composites, etc.). Processes that are developed here for oxygen production from CO/CO2 may have direct applications on Mars.
| PROPOSAL NUMBER: | 02- H2.02-7631 (For NASA Use Only - Chron: 024368 ) |
| SUBTOPIC TITLE: | Human Centered Computing |
| PROPOSAL TITLE: | A Head Mounted Display Without Focus/Fixation Disparity |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Dimension Technologies Inc
315 Mt Read Blvd
Rochester , NY 14611 - 1982
(585 ) 436 - 3530
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Jesse Eichenlaub
jbe@dti3d.com
315 Mt Read Blvd
Rochester , NY 14611 - 1982
(585 ) 436 - 3530
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
This small Business Innovation Research Phase I Project will investigate a method of eliminating the focus/fixation disparity in a head mounted display. The disparity between focus and fixation points in head mounted stereoscopic viewing systems often creates a problem for the viewer in terms of eyestrain, defocused images, or inability to fuse images. Such problems show up most when objects are represented across a wide range of distances from the user, or when the system is used to superimpose virtual information onto real world scenes. Past attempts at matching the focus and fixation distance in head mounted displays have involved complicated servo mechanisms and eye trackers to change the apparent distance to the screen as the observer gazes at different areas of the scene. This proposed project will demonstrate a novel, less complicated way of creating images in which the focus and fixation distances are matched for objects from several inches to infinity without using eye tracking, measuring equipment, or moving parts. The proposed device will create several convergent ray bundles for each displayed image point in such a way that the bundles all intersect to form a light point at a distance that is coincident with the fixation distance.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
The technology to be investigated in this proposal could find application in head mounted virtual reality systems for simulation applications, particularly vehicle simulations, plus head mounted enhanced reality systems in which graphics and information is superimposed on a direct view of the real world for training, education, navigation for delivery personnel, recreational travel, etc.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
Broadly speaking, the most likely applications for this technology within NASA are in a) simulator and training environments in which expense or space constraints favor the use of head mounted VR devices as opposed to domes or out the window configurations, especially in situations where close in objects such as the cockpit interior or hand manipulated items must be presented, and b) inspection and maintenance scenarios where information is superimposed on real world, close by objects.
| PROPOSAL NUMBER: | 02- H2.02-8945 (For NASA Use Only - Chron: 023054 ) |
| SUBTOPIC TITLE: | Human Centered Computing |
| PROPOSAL TITLE: | Crew Activity Analyzer |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Foster-Miller Inc
350 Second Ave
Waltham , MA 02154 - 1196
(781 ) 684 - 4320
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Dr. Rajesh Kumar
rkumar@foster-miller.com
350 Second Ave
Waltham , MA 02154 - 1196
(781 ) 684 - 4242
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Future space missions will require planning for human interactions in a confined and potentially harsh environment over extended periods of time. The study of human behavior in simulated environments is one means of planning for these missions. The proposed innovative Crew Activity Analyzer (CAA) will provide NASA with an efficient and cost-effective tool for automatically identifying patterns of group activity from image data of these simulated environments. The CAA will be more objective and accurate than using human observers to process the information from visual images. The CAA concept is based on computer vision algorithms developed by Foster-Miller. The tool will provide an automated means for determining patterns and timing of group activity. Human involvement in processing of the image data will be minimal. Phase I objectives are to 1) select and prioritize the group activities to be analyzed, 2) validate method for segmentation of image data, 3) develop suitable techniques for tracking individuals and 4) perform validation experiments, including computing metrics of individual and collaborative time and space usage. (P-020614)
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
The proposed Crew Activity Analyzer (CAA) has potential application by researchers using videotapes or other image recording to document the behavior of individuals interacting in groups. The military, the airline industry, university researchers, research hospitals, the Federal Aviation Administration, and the Federal Railroad Administration all are concerned about group interaction and team performance, and employ image recording in their research. The CAA might also be used for analyzing the activity of animals in a zoo or research environment.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
Planning for International Space Station missions and future missions to deep space employs earth analogs and simulator facilities to gather data on human interaction in these confined environments. The Crew Activity Analyzer (CAA) will provide the means to accurately and quickly determine patterns of group activity in these environments from image data.
| PROPOSAL NUMBER: | 02- H2.02-8957 (For NASA Use Only - Chron: 023042 ) |
| SUBTOPIC TITLE: | Human Centered Computing |
| PROPOSAL TITLE: | BrahmsVE: Proof of Concept for Human/Agent Intelligent Augmentation |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
DigitalSpace Corp
343 Soquel Avenue, Suite 70
Santa Cruz , CA 95062 - 2305
(831 ) 338 - 9400
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Bruce Damer
damer@digitalspace.com
343 Soquel Avenue, Suite 70
Santa Cruz , CA 95062 - 2305
(831 ) 338 - 9400
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
This proposal seeks to extend the existing BrahmsVE environment to support a semi-autonomous "intelligent" agent operating inside a 3D virtual world on the web. We are calling this agent the Personal Bot Assistant (PBA) and it will be paired with an agent-astronaut driven either by the user or by the Brahms model-based simulator. The PBA should allow us to provide a test bed for one of the canonical scenarios of human-centered computing research: the interaction and task sharing between a human and a mobile agent. Once completed, the PBA-astronaut simulation will be subjected to a "virtual test fixture" within a re-creation of both the FMARS/Haughton-Mars Project surface habitat and the International Space Station.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
The growing popularity of ?robot games? and ?robot wars? for K-12, college, and adult audiences suggests that BrahmsVE and the PBA could be a basis for the creation of a successful multiplayer online game both as a learning tool and as a pay-per-play tournament environment. From factory automation to security systems, complex environments where humans work in tandem with mobile agents or other autonomous machine systems all need a comprehensive model-based environment with high fidelity 3D re-creation during both design and operations phases. The military will be using semi and fully autonomous agents working closely to support troops and command in surveillance and combat missions throughout the 21st Century. Therefore we expect a great deal of interest surrounding production systems in this space. The emerging era of wireless, wearable personal assistants is picking up momentum with ever more sophisticated cell phones and other handheld devices. In a real sense, each of these devices represents the pairing of humans with machines as the BrahmsVE PBA project will study.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
Numerous projects within NASA ranging from the Personal Satellite Assistant at Ames to the Mobile Agents project of interest to several NASA centers could benefit from the addition of ?intelligent? agents within a virtual world simulation. In addition, many of these projects are already employing Brahms. Putting more complexity in the virtual world agent in BrahmsVE will offload some of the modeling requirements at the Brahms level and generate better data on agent performance in simulated and possibly in physical space. Rapid, iterative design of a mobile agent in a virtual world can be made possible by changing both the Brahms model, where appropriate, and the script locally controlling the agent in the 3D world, where appropriate. Local algorithms in the virtual agent could then be downloaded into the physical robot, as is done today with Brahms Mobile Agents Architecture.
| PROPOSAL NUMBER: | 02- H2.02-9556 (For NASA Use Only - Chron: 022443 ) |
| SUBTOPIC TITLE: | Human Centered Computing |
| PROPOSAL TITLE: | Intelligent Procedure Tracking and Assistance |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Metrica, Inc.
8620 N. New Braunfels, Suite 603
San Antonio , TX 78217 - 6363
(281 ) 461 - 7884
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
David M. Kortenkamp, Ph.D.
korten@traclabs.com
1012 Hercules
Houston , TX 77058 - 2722
(210 ) 822 - 2310
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
This is a proposal to build an innovative procedure tracking and
assistance system for application to space station. Space station
crew members are currently hindered by a lack of integration between
procedures and telemetry. We propose a software system that will
probabilistically track the execution of a procedure using telemetry.
In addition to tracking, the software will also assist in executing
the procedure by prompting for missing steps or handling routine
verification. At the core of the software system is a probabilistic
reasoning technique that can track multiple possible outcomes
simultaneously. We also propose a crew proxy that will mediate the
flow of information between the procedure tracking and assistance
software and the crew member. A crew interface will be developed for
a hand-held computer. This will free crew members from their control
stations and allow for procedure assistance at any place in the space
station. In developing this system, Metrica will be working with
consultant Reid Simmons of Carnegie Mellon University. Metrica's
previous experience in procedure tracking and assistance and crew
interface design combined with Dr. Simmons' experience with the Task
Description Language and probabilistic reasoning techniques creates an
ideal team to complete this project successfully.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
Increasingly complex electronic devices and software require equally
complex procedures to operate them effectively. Procedure tracking
and assistance systems that can be deployed in a light-weight fashion
and that can intelligently assist users in their nominal and
off-nominal operations would be of enormous commercial significance.
Embedded in a hand-held device (and downloadable from a WWW site)
could be procedures for everything from fixing a car to setting up a
home theater. We will initially work with procedure oriented
industries where there is telemetry feedback such as health care and
machine diagnosis and maintenance.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
NASA currently has no automated way to track or assist crew members as they execute procedures on space station or space shuttle. Ground controllers and other crew members are used. This is costly and not safe because of delays. Also, crew members are currently limited to viewing procedures in PDF format at a workstation, even if where they execute procedures is remote from the workstation. Tis project will give NASA the capability to track and assist in crew procedure executing, enhancing safety and reducing cost.
| PROPOSAL NUMBER: | 02- H3.01-7506 (For NASA Use Only - Chron: 024493 ) |
| SUBTOPIC TITLE: | Thermal Control Systems for Human Space Missions |
| PROPOSAL TITLE: | Nanostructured Aerogel Systems for Cold Volume Enclosures |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Aspen Aerogels, Inc.
184 Cedar Hill St.
Marlborough , MA 01752 - 3017
(508 ) 481 - 5058
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Don Young
dyoung@aerogel.com
184 Cedar Hill St.
Marlborough , MA 01752 - 3017
(508 ) 481 - 5058
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Spacecraft design parameters limit and trade off volume, mass, power usage, and cost to maximize system performance. One example of this necessary tradeoff is the design of the rectangular cold volume enclosures. The solution will have to be thin walled to maximize usable volume, an excellent thermal insulator, low density, and low cost. An effective and lightweight approach has been developed using Aspen Aerogels, Inc?s nanostructured aerogel materials. AAI?s patent pending, composite aerogels are a new class of extremely low density materials that offer highly unusual design, mechanical and thermal properties. The combination of nanometer scale pore structure and very low density appear be ideally suited for thermal insulation in weight sensitive applications such as spacecraft. The flexibility of the materials will enable enclosure designers to minimize and in some cases eliminate seam leakage. The resulting AAI aerogel product would have a lower density, cost, thermal conductivity, and therefore energy usage compared to current SOA solutions. Other design possibilities are discussed that may further minimize the energy usage of the cold volume enclosure.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
Practical and effective design concepts suitable for insulation of spacecraft cold volume enclosures will have been developed and documented. Such thermal insulation designs shall be suitable not only for next generation space structures, but also for other existing space vehicles where cold storage is needed ? anywhere where cold (or warm) storage is needed. This system is relevant for NASA research aircraft, spacecraft like the Shuttle, and space structures like the International Space Station. The developed materials could be used in terrestrial applications such as large cold rooms, cryogenic pipe overwrap, and Dewar insulation.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
In addition to the benefits to NASA, thermal insulation data for aerogel materials will have been developed to better characterize how these unique materials perform to mitigate thermal exposure. This information will lead to a better understanding of aerogels and how to optimize thermal enclosures for optimum protection, versatility, energy usage, and weight. Large commercial markets for these intelligent designs and materials are waiting to be served. This includes military and civilian aircraft, water heaters, commercial and residential white goods (refrigerators, dish washers, freezers, etc.), and piping insulation.
| PROPOSAL NUMBER: | 02- H3.01-7556 (For NASA Use Only - Chron: 024443 ) |
| SUBTOPIC TITLE: | Thermal Control Systems for Human Space Missions |
| PROPOSAL TITLE: | Transparent Integration of SINDA/G into Patran |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Network Analysis Inc
7855 S River Parkway, Ste. 101
Tempe , AZ 85284 - 1825
(480 ) 756 - 0512
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Ron Behee
ron@sinda.com
7855 S River Parkway, Ste. 101
Tempe , AZ 85284 - 1825
(480 ) 756 - 0512
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The purpose of this project is to produce a transparent integration of SINDA/G into the MSC.Patran FEA modeling system. This product will be oriented towards both the beginning thermal analyst and the advanced SINDA user. The transparent integration will allow a new user to use advanced features involving convection, surface-to-surface radiation, heaters, and other advanced thermal features without knowing the format of SINDA/G or thermal radiation codes. Experienced SINDA users will not be limited by the simple boundary conditions typically associated with FEA thermal codes, but will have the full power of SINDA/G. Because of the popularity of MSC.Patran in the aerospace world for building MSC.Nastran structural models, this graphical modeling environment is ideal for producing SINDA/G thermal models in order to enhance the concurrent engineering processes of aerospace hardware design. The popularity of Patran makes it available to a high percentage of thermal engineers in the aerospace community. Also many thermal engineers already know how to use Patran, reducing the learning curve for this product and eliminating the need to learn another modeling system.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
The SINDA/G integration into MSC.Patran has application for all areas of thermal design within the aerospace community. This product will integrate advanced thermal features such as radiation and ablation into a popular graphical modeling environment for the design of spacecraft, propulsion systems, electronic equipment, reentry vehicles, aircraft, and various other aerospace hardware. The integration of SINDA/G into MSC.Patran will help in the concurrent engineering process by allowing thermal engineers to use the same modeling tools that many structural engineers use in the aerospace industry. It will also allow CAD data to be directly incorporated into thermal models. In addition, it will allow thermal models to be radiation independent so models can be more easily exchanged between companies that use different thermal radiation and orbital heating codes.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
The SINDA/G integration into MSC.Patran has application for all areas of thermal design within NASA. This product will integrate advanced thermal features such as radiation, ablation and the GFSSP (Generalized Fluid System Simulation Program) into a popular graphical modeling environment for the design of propulsion systems, reentry vehicles, electronic equipment, and various thermal design projects associated with the International Space Station. The integration of SINDA/G into MSC.Patran will help in the concurrent engineering process at NASA centers by allowing thermal engineers to use the same modeling tools that structural engineers use for building MSC.Nastran models. It will also allow CAD data to be directly incorporated into thermal models. In addition, it will allow thermal models to be radiation independent so contractors or different NASA centers can run the same Patran based thermal model utilizing different thermal radiation and orbital heating codes.
| PROPOSAL NUMBER: | 02- H3.01-9346 (For NASA Use Only - Chron: 022653 ) |
| SUBTOPIC TITLE: | Thermal Control Systems for Human Space Missions |
| PROPOSAL TITLE: | Orbital Pump for Microgravity Applications |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Fluid Flow Technologies, L.L.C.
28112 Meadow Dr.
Evergreen , CO 80439 - 8346
(303 ) 670 - 4964
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Greg Glatzmaier
greg.glatzmaier@att.net
28112 Meadow Dr.
Evergreen , CO 80439 - 8346
(303 ) 670 - 4964
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
This proposed work will develop a new pump design, which is based on a uniquely generated orbital motion. The pump is intrinsically sealed and mechanically balanced, resulting in quiet, safe operation. The pump design has no seals, valves, bearings, complex mechanical linkages, or drive motor. Its simplicity promises to provide a pump, which is compact and reliable, has low mass, and possesses quiet, safe operation, ideal for long-term, space-based, microgravity applications.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
A large market for this design applies to pumping liquid chemicals in the chemical industry. Key features for this application are its monolithic structure and hermetic seal. These features would result in increased safety and reliability for handling toxic or otherwise hazardous fluids. A related market is a compressor for industrial gases. Again, the safety and reliability features are expected to give it advantages over other designs. An interesting consumer product application is a portable air compressor for use with pneumatic tools. This product would be marketed for construction work as well as home use.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
The unique features of this pump design make it potentially useful for a variety of applications for NASA. These include liquid pumping for liquid transfer operations in microgravity environments. Pumping cryogenic liquids is among these applications. Other space-based applications include gas compression and pumping for gas transfer and storage operations. Gas compression for space-based refrigeration, heat pump, and cryogenic cycles also may be of great value to NASA.
| PROPOSAL NUMBER: | 02- H3.02-8762 (For NASA Use Only - Chron: 023237 ) |
| SUBTOPIC TITLE: | Spaceport and In-Space Cryogenic Fluids, Handling, and Storage Technologies |
| PROPOSAL TITLE: | Novel Lightweight, Low-Cost, Aerogel Materials as Insulation for Cryogenic Tanks |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Aspen Aerogels, Inc.
184 Cedar Hill St.
Marlborough , MA 01752 - 3017
(508 ) 481 - 5058
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Redouane Begag
rbegag@aerogel.com
184 Cedar Hill St.
Marlborough , MA 01752 - 3017
(508 ) 481 - 5058
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Future spacecrafts require greatly improved and lighter reusable cryogenic tank insulation and TPS to achieve the ambitious goal of reducing the cost of delivering a payload to orbit by an order of magnitude. Recently, Aspen Aerogels developed a new class of flexible aerogels called "Ultra-lightweight &hard cellulose aerogel". The new aerogel is 100 times stronger and harder than regular aerogel and has density and thermal characteristics as silica aerogel (low thermal conductivity ~ 12.8 mW/m.K and low density ~ 0.04 - 0.09 g/cc). The originality of this concept is based on the low cost fabrication, the lightweight, the flexibility, and the high thermal performance of the innovative material. Moreover, our new high temperature insulation version based carbide aerogels demonstrated unparalleled high temperature oxidation resistance under oxyacelylene torch test. Aspen proposes to use these two classes of aerogels in a multilayered sandwich configuration to insulate cryogenic tanks and protect the spacecraft structure. We believe that the application of the proposed integrated TPS/Cryogenic insulation concept will satisfy all requirements to be used in cryogenic tanks and will greatly reduce the weight of the propellant tanks and the boil-off rate of the propellant (thus reduce the size of the tanks).
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
Ultra-lightweight cellulose and carbide aerogels will find a large number of commercial applications from the aerospace industry, military applications to high energy physics and power generation. We also anticipate considerable interest for high temperature furnace and incinerator application. Aspen Aerogels now has unparalleled depth and width of aerogel technology base, and will have large production capability in 2003 to launch the widespread and large scale commercialization of aerogels in many applications.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
Successful completion of this project will lead to widespread use of cellulose aerogel insulation in cryogenic and medium temperature applications: cryogenic storage, refrigeration/freezer/cryogenic preservation systems, feedlines and space suits.
Aspen Aerogels strongly believe that this new aerogel material, which has a very low cost of fabrication compare to silica aerogel, is one of the promising insulation materials for the next generation of spacecraft. Also, NASA has shown a particular interest in Aspen's carbide aerogels. The carbide aerogels are considered to be a good candidate for TPS application.
| PROPOSAL NUMBER: | 02- H3.02-8774 (For NASA Use Only - Chron: 023225 ) |
| SUBTOPIC TITLE: | Spaceport and In-Space Cryogenic Fluids, Handling, and Storage Technologies |
| PROPOSAL TITLE: | A 20K Cooler for the Spaceport of Liquid Hydrogen |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Atlas Scientific
1367 Camino Robles Way
San Jose , CA 95120 - 4925
(408 ) 507 - 0906
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Ali Kashani
akashani@atlasscientific.com
1367 Camino Robles Way
San Jose , CA 95120 - 4925
(408 ) 507 - 0906
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
For the future spaceport and storage of liquid hydrogen NASA requires cryocoolers that can provide more than 10W of cooling at 20K. The closed-cycle cooling alternatives currently available for such applications are not well suited to their requirements. In many cases reliability is low and vibration high. In other cases coolers are too massive and inefficient. This proposal describes a two-stage pulse tube cooler (PTC) that combines a bootstrap staging configuration with an innovative second-stage regenerator design and a unique load-interface. The proposed cooler contains three innovative concepts that together will overcome the limitations of current cryocooler technologies: (1) the matrix for the second stage regenerator will be made from a newly-patented material having a heat capacity in excess of all other known materials, including lead (Pb), over a wide range of low temperatures (85K down to 15K), (2) the material for the second-stage regenerator will be formed into a novel matrix geometry, and (3) a unique load-interface will be an integral part of the cooler giving it the capability to cool distributed loads efficiently. The proposed pulse tube will be lightweight, efficient, reliable, vibration free, and easy to integrate into cryogenic dewars.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
There are a number of commercial applications. A partial list includes:
?Superconducting electronics
?Superconducting magnets for MRI systems
?Superconducting magnets for power generation and energy storage
?SQUID magnetometers for heart and brain studies
?HTS filters for the communication industry
?Liquefaction of industrial gases
?Cryopumps for semiconductor manufacturing
?Radio astronomy
As an example, a market of about $100 million/year currently exists for G-M cooler-based cryopumps for sputtering systems used in the semiconductor industry. Sputtering systems normally have several cryopumps per unit with each cryopump costing $20-25,000. The more reliable PTC package will cost about the same as current G-M units and will be less expensive to maintain due to the lack of oil and rubbing surfaces.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
Missions to Mars that involve the in-situ manufacture of propellant which will require the capability to store seed hydrogen for long periods of time. To accomplish this, a small lightweight cryocooler mounted on the storage vessel that is capable of sub-cooling the liquid, intercepting parasitic heat leaks, and re-liquefying hydrogen vapor will be required. The proposed two-stage pulse-tube cooler is ideally suited to such applications.
For missions that will involve transportation or in-situ liquefaction of liquid cryogens such as hydrogen, neon, and oxygen, the proposed two-stage pulse-tube cooler is again ideally suited. The presence of two stages allows cooling at two temperatures. The proposed cooler is easily modified to liquefy both hydrogen and neon at the low temperature stage, and oxygen, for example, at the higher temperature stage.
To improve the ultimate signal to noise ratio obtainable from cryogenic IR focal plane arrays (FPA), it is desirable to have on-focal plane, high-resolution, analog-to-digital (A/D) data converters. Such A/D converters, based on the Josephson effect, together with supporting technology, are currently in various stages of development. The proposed two-stage pulse-tube cooler is ideally suited to these applications as well.
| PROPOSAL NUMBER: | 02- H3.02-9543 (For NASA Use Only - Chron: 022456 ) |
| SUBTOPIC TITLE: | Spaceport and In-Space Cryogenic Fluids, Handling, and Storage Technologies |
| PROPOSAL TITLE: | Highly Reliable LOX Pump for Vehicle Loading Operations |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Barber-Nichols Inc.
6325 West 55th
Arvada , CO 80002 - 2777
(303 ) 421 - 8111
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Bill Batton
bbatton@barber-nichols.com
6325 West 55th
Arvada , CO 80002 - 2777
(303 ) 421 - 8111
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
This proposal will present an innovative Phase I research and design plan for a reliable LOX pumping system for use in NASA vehicle loading. Due to seal problems with the current LOX loading pumps, the main focus of the Phase I effort will involve design and development of an innovative sealing solution that does not use a failure prone mechanical seal. The seal solution proposed is a combination of a labyrinth seal with N2 buffer gas and pump out vanes on the backside of the pump impeller. This will provide a positive seal with no oxygen leak and have no wearing parts. In addition to this simple and reliable sealing arrangement, other crucial components will be designed for the pump to have the highest reliability and performance. One specific area will be minimization of heat leak from the motor and bearings to the LOX. This will reduce the LOX boil-off that must be vented during loading. Finally, a redundant parallel pumping system will be developed to ensure the highest reliability during vehicle loading at NASA
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
Outside of NASA, a big market would exist in LNG transfer and ship offloading. Some of these LNG pumps can be very large. Many of these large pumps are typically submersible pumps, which have a large amount of power lost as windage in the motor (due to presence of liquid). This overhung pump with non-contacting seal would not have LNG in the motor and bearings and thus would not have these losses. The bearings could also be lubricated with grease and thus would last longer. Nitrogen could be used as a buffer gas for this application as it will remain a gas at LNG temperatures. The LNG pump market is already big and is growing. This pump would compete well against the alternatives and have great opportunities in this market.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
The new seal design can be immediately applied to retrofit existing LOX loading pumps. The new pump design concept can fill new requirements for all NASA LOX pumping applications for ground use. In addition to the LOX loading applications, the proposed pump with innovative seal could be used for the hydrogen loading pumps as well. The buffer gas will need to be changed to helium since it will not liquefy at liquid hydrogen temperatures and will vent off as the nitrogen gas does with oxygen. The only down side here is that helium is more expensive than nitrogen, but the flow will be small and pales in comparison to the boiled-off hydrogen that is vented during loading.
| PROPOSAL NUMBER: | 02- H3.02-9617 (For NASA Use Only - Chron: 022382 ) |
| SUBTOPIC TITLE: | Spaceport and In-Space Cryogenic Fluids, Handling, and Storage Technologies |
| PROPOSAL TITLE: | System for Helium/Hydrogen Recovery from Waste Gas Streams |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
PHPK Technologies Inc
535 Enterprise Drive
Westerville , OH 43081 - 8846
(614 ) 436 - 9114
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Kenneth Kreinbrink
kkreinbrink_phpk@Ameritech.net
535 Enterprise Drive
Westerville , OH 43081 - 8846
(614 ) 436 - 9114
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The continuing rising costs of helium warrants the investigation into economic processes that will separate helium gas from gas streams that would normally be considered waste gas. These waste gas streams are typically generated from operations where helium purging of hydrogen storage or propellant equipment is performed. As a result of these operations, helium contaminated with hydrogen, nitrogen, and small amounts of air is vented to the atmosphere where it is not recoverable in a practical or economic manner. The system proposed in this investigation will recover helium and possibly hydrogen from these waste gas streams and purify it to a level where it can be recycled for practical usage. Cryogenic processes as well as other gas separation techniques will be incorporated into a complete integrated system to accomplish this gas recovery. The Phase I effort is intended to define and analyze a gas recovery system that will be practical for helium recovery in both commercial and NASA related programs where helium is routinely used and vented in significant quantities. The purpose of the investigation is to provide sufficient process information for the design of large scale hydrogen and helium recovery system.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
Companies that develop and test hydrogen fueled rocket engines at large testing complexes have large quantities of cryogenic storage and other volumes that require helium as a purge gas or pressurizing gas for the high pressure liquid hydrogen propellant supply vessels. The helium gas used in these applications becomes mixed with hydrogen and possibly other gases and is typically expelled as waste gas to atmosphere after use. The proposed system would be capable of capturing and separating the helium and hydrogen from waste gas streams instead of venting these two gases to atmosphere. Substantial cost saving could be realized by recycling these expensive gases in the test facility instead of buying additional helium.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
Since almost all of NASA?s launch and other propellant related test operations use helium and hydrogen, this system would be capable of recovering these valuable gases to the point that they could be separated and recycled for the next operation. Since some propellant densification operations will exhaust waste streams comprised of helium and hydrogen, this gas separation system would be a major economic benefit in these operations. The use of this gas recovery system operating in conjunction with the NASA?s gas usage operations could result in substantial cost savings that is realized over a relatively short period of time.
| PROPOSAL NUMBER: | 02- H3.02-9677 (For NASA Use Only - Chron: 022322 ) |
| SUBTOPIC TITLE: | Spaceport and In-Space Cryogenic Fluids, Handling, and Storage Technologies |
| PROPOSAL TITLE: | Hermetically Sealed, Free Piston, Cylindrical Linear Pump |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Thortek
101 River Drive
Irvine , KY 40336 - 1117
(606 ) 723 - 2289
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Douglas Thorpe
doug.thorpe@thortek.biz
101 River Drive
Irvine , KY 40336 - 1117
(606 ) 723 - 2289
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
An extremely simple Hermetically Sealed, Positive Displacement Linear Pump is presented that would electro-magnetically shuttle a floating piston inside of a tube. The proposed Linear Pump will eliminate potential leak paths and multiple maintenance problems for the LOX pumps at the Kennedy Space Center. The Linear Pump consists of only three parts and is based upon a Permanent Magnetic Linear Coupler, a linear motor, and a free-piston internal combustion engine. The three parts are: 1 or 2 free pistons that are electro-magnetically shuttle back & forth inside of a cylindrical linear motor and 2 or 4 check valves that control the direction of fluid. A leak-proof, low maintenance Linear Pump that can handle adverse conditions is immediately needed in the hazardous chemical, cryogenic and nuclear industries. The pump can operate in a stepper motor fashion and vary its pumping speed from maximum to 0% output. By connecting a linear shaft to the free piston, the Linear Pump can become an Electro-Mechanical Actuator or a combined Reciprocating Control Valve/EMA. By removing electrical power, the EMA could easily be back-driven. All moving parts (poppets on the check valves and the free-piston) operate within the confines of the sealed fluid. By replacing the poppet check valves with EMA valves, we can operate the pump as a small scale hydroelectric generator.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
A highly economical, robust, low maintenance, hermetically sealed, Free Piston Linear Pump will have major advantages over most positive displacement and centrifugal pumps in applications where the fluid does not contain particulates that will prevent the proper operation of the check valves. The proposed hermetically sealed pump will eliminate all maintenance and hazardous emissions (and their clean air purges) associated with dynamic seals and rotary bearings. The proposed linear pump can be placed in-line of low viscous fluid systems and act as either the primary or the boost pumping system. By connecting a linear shaft to the free piston, the Linear Pump can become an Electro-Mechanical Actuator or a combined Hermetically Sealed Control Valve/EMA. The biggest reason why EMA?s are not being considered for use in the $2.5B per year Aerospace Actuator Market is that they can not be back-driven. By removing electrical power, the EMA could easily be back-driven.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
An insulated, highly economical, robust, low maintenance, hermetically sealed, Free Piston Linear Pump will have major advantages over the existing non-insulated centrifugal pumps in the application of pumping LOX. The proposed hermetically sealed pump will eliminate all maintenance and hazardous emissions (and their clean air purges) associated with dynamic seals and rotary bearings.
| PROPOSAL NUMBER: | 02- H3.02-9814 (For NASA Use Only - Chron: 022185 ) |
| SUBTOPIC TITLE: | Spaceport and In-Space Cryogenic Fluids, Handling, and Storage Technologies |
| PROPOSAL TITLE: | Spaceport and In-Space Cryogenic Fluids, Handling, and Storage |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Wilson Composite Technologies, Inc.
1004 River Rock Drive, Suite 240
Folsom , CA 95630 - 0208
(916 ) 989 - 4812
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Doug Hender
brian_wilson@wilsoncomposites.com
1004 River Rock Drive, Suite 240
Folsom , CA 95630 - 0208
(916 ) 989 - 4812
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
This program builds on prior R&D contracts of which some are completed and some are ongoing by Wilson Composite Technologies (WCT). The principal support area will be from a contract entitled ?Long Term Storage of Liquid Hydrogen in Space?, which has a goal of 20 year storage with a 2% boil-off loss. This program will build upon the results of that prior contract by utilizing foam insulation technology and blanket multiple layer insulation (MLI) techniques. The program will design cryogenic tanks and pressurized containers for use both in the transport environment from Earth to Mars and also for location on the Mars surface as part of a permanent installation. Design of a suitable cryocooler will be included in the container technology for conversion of cryogenic vapors back to liquids. Detailed thermal analysis will be conducted to create optimum insulation. Mounting systems and connections will be analyzed and designed for minimal thermal input to the storage containers and overall mission loads will be considered for structural design. A complete matrix of tank sizes and shapes will be provided as a result of a thermal and design analysis. This will enable future selection of final sizes for these transport and storage containers.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
Commercial applications are also considered for non-NASA uses. There are various commercial launch vehicles such as the Pegasus, Aquarius and Scorpius vehicles, which will require cryogenic tanks, both for launch and for application in earth orbit and for potential geo-synchronous orbital use. Government programs, such as the near term Airborne Laser project, the potential Space Based Laser project, the IHPRPT advanced liquid propulsion system and the Air Force Space Initiative and future launch vehicle programs will all require long term storage of cryogens. The more basic commercial applications will apply to cryogenic and corrosive chemical transport and storage. Liquid Natural Gas (LNG) requires storage and transport from LNG tankers. Food transport with flash freezing and long haul containers has also initiated the use of cryogenic cooling with consequent storage and dispensing systems.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
NASA commercial applications are considered to relate to anything other than a military application. This will involve two series of programs. The first is the NASA commercial applications for future requirements of interplanetary missions, comet fly-bys, and international space station requirements. The matrix of applications for both size and shape of cryogenic containers will be important for these NASA missions. The NASA program entitled Human Exploration and Development of Space will be an obvious future application for this technology. Plans for replacement of the existing space shuttle vehicle with a new design of reusable launch vehicle (RLV) will also include this technology. As the International Space Station expands and its space life and mission expand, long-term storage will become a requirement.
| PROPOSAL NUMBER: | 02- H3.02-9883 (For NASA Use Only - Chron: 022116 ) |
| SUBTOPIC TITLE: | Spaceport and In-Space Cryogenic Fluids, Handling, and Storage Technologies |
| PROPOSAL TITLE: | Cryogenic Propellant Insulation Program |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
TECHNOLOGY APPLICATIONS, INC.
5445 Conestoga Court, #2A
Boulder , CO 80301 - 2724
(303 ) 443 - 2262
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Mark Allen
mallen@techapps.com
5445 Conestoga Court, #2A
Boulder , CO 80301 - 2724
(303 ) 443 - 2262
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Technology Applications, Inc. (TAI) is proposing to demonstrate feasibility of cryogenic propellant insulation technologies that improve the thermal performance, operational efficiencies, durability, reliability, and safety of these systems in earth, space, and extraterrestrial environments. The new technology, which employs microspheres as the insulating medium, provides for robust, low-maintenance storage systems and transfer lines well suited for the on/off operation that is typical for space launch operations. Microspheres perform over 1.6 times better than perlite, approach multilayer insulation (MLI) performance under proper vacuum, and limit heat leak to the level of foam insulation if vacuum is completely lost. They perform as well or better than any of the above insulation materials in a soft vacuum condition. This means less vacuum maintenance to be performed. Transfer line and dewar test articles will be manufactured to address microsphere containment and compaction issues. Microspheres can be used to insulate areas that have complicated geometry; require intermittent access, such as around instrumentation and piping components; or for applications that require formability and minimal weight. The innovations are applicable for high efficiency storage, handling, and distribution systems for spaceport cryogenic facilities, reusable launch vehicles, and the transport and storage of cryogenic propellants on Mars.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
The transport, distribution, and storage of liquefied gases requires an effective insulation system to minimize boil-off rates and the energy required for the reliquefying plants as low as possible. New insulation options are needed that are durable, efficient, and low cost. The primary commercial applications include transfer lines and storage vessels for medical, industrial gas air separation, liquefied natural gas, semi-conductor, and food-freezing industries. The aerospace instry utilizes commercial insulated systems for aircraft and space applications, which need advanced insulations in some cases that are capable of covering the temperature range from helium storage to space reentry temperatures. Low and high temperature superconductors require insulated systems for helium and nitrogen, respectively. Academic institutions use cryogenic distribution and storage in their research laboratories. According to one commercial supplier who supplies vacuum jacket system for these applications, the vacuum transfer line market alone is currently $20-30M per year.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
NASA/KSC has identified several insulation applications that are directly related to efficient storage and transfer of cryogenic propellants on earth and in space. Thermally-efficient, low-cost improvements are needed for the existing LC-39 cryogenic loading systems. The Space Launch Initiative will require new insulation for both cryogen transfer and storage.
NASA/SSC consumes many pounds of liquid hydrogen and oxygen each year in support of propulsion system development. Vacuum-jacketing does not exist on many liquid transfer and vent lines. Even liquid hydrogen lines are unjacketed in localized areas. Vent lines are frequently bare, which presents safety hazards including the formation of enriched oxygen. Other lines are foam-insulated, which degrades starting with the first thermal cycle and is lost after 3-5 years of operation. In addition to safety issues, the poor or non-existing insulation presents substantial economic losses from both the steady state heat load and cool-down losses.
| PROPOSAL NUMBER: | 02- H3.03-9396 (For NASA Use Only - Chron: 022603 ) |
| SUBTOPIC TITLE: | Spaceport/Range Instrumentation and Control Technologies |
| PROPOSAL TITLE: | Circular Mass Spectrometer for High Speed Gas Analysis |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Monitor Instruments Company,LLC
290 East Union Road
Cheswick , PA 15024 - 2107
(724 ) 265 - 1212
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Dr. Guenter Voss
monitor1@nauticom.net
290 East Union Road
Cheswick , PA 15024 - 2107
(724 ) 265 - 1212
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The circular cycloidal mass spec (our patent application 10/981,511) is derived from the standard linear cycloid analyzer. Instead of crossed uniform electric and magnetic fields, the electric field has circular symmetry. Thus the ion trajectories proceed periodically around the center. This provides long trajectories (high resolution) within a small analyzer, typically 50 mm in diameter (low weight, low cost). We propose the arrangement of two concentrically arranged analyzers, the inner one for H2 and He separation and the outer one for N2, O2, and Ar. Five collectors allow the simultaneous continuous registration of all gases without scanning the field (high speed analysis). The pumping system will contain an ion getter triode pump and a non-evaporable getter pump combination. As an inlet we propose a fast 1-step membrane inlet. The complete unit will require less than 3500 cm3 with a weight of ca. 10 kg.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
-Fast process control in petrochemical and chemical plants
-Portable instruments for onsite analysis
-Isotope ratio analyzer for medical and biological investigations
-Security control, portable detector for explosives and toxics
-Environmental monitor
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
-Miniature mass spec for hazardous gas detection
-Gas chromatograph mass spec in harsh environments
-Miniaturized mass spec for N2, CO2, NH4, O2, and hydrazine
-Onboard gas monitor for the space shuttles
| PROPOSAL NUMBER: | 02- H3.03-9517 (For NASA Use Only - Chron: 022482 ) |
| SUBTOPIC TITLE: | Spaceport/Range Instrumentation and Control Technologies |
| PROPOSAL TITLE: | Hybrid Data System and Ion Detector for TOF Mass Spectrometry |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Ionwerks
2472 Bolsover Suite 255
Houston , TX 77005 - 2537
(713 ) 522 - 9880
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
William Burton
wmburton@ionwerks.com
2472 Bolsover Suite 255
Houston , TX 77005 - 2537
(713 ) 522 - 9880
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Previous phase II work has resulted in a compact Time-of-Flight mass spectrometer developed for sensitive detection of hydrogen and oxygen leaks prior to and during the few seconds after engine start and before launch of the space shuttle. The main challenges for this application--sensitivity, accuracy, dynamic range, response time, and ruggedness--have been met in the current prototype. The sensitivity and utility of the TOF is now principally limited by the saturation of the Micro-channel-plate detector, which can handle only a few million counts per second. An approach to overcome this limitation using a new type of data system in conjunction with a combined microchannelplate/discreet ion multiplier is the subject of this phase I.
We propose to increase the dynamic range of time of flight mass spectrometry by creating a data acquisition and detector system that simultaneously performs analog and multianode single ion pulse-counting time-of-flight measurements to inrease the dynamic range of a time to digital converter (TDC) for the cases when a mass peak comprises more than one ion arriving simultaneously the detector.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
The proposed hybrid data system and ion detector would be well suited for commercial mass-spectrometry instruments requiring both sensitivity to single ions and wide dynamic range for processing high ion flux mass peaks without distortion. Such requirements will soon become commonplace in analysis of chemical, biological, and environmental samples as the optimization of mass?spectrometer instrument designs continues. These instruments include combined Gas Chromatograph/Mass Spectrometers (GC/MS), MALDI, and Electrospray mass-spectrometers.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
This hybrid data system and hybrid ion detector would provide significant improvements in the performance, operating life, and operational simplicity of the existing Time-of-Flight mass-spectrometer for leak detection and enable use of the instrument in a broader range of chemical detection, quantitation, and monitoring applications. Performance would be improved by increasing measurement dynamic range. The operating life of the instrument would be increased through simplification of the ion detector; and operational simplification would be achieved by reducing the amount of control electronics needed. The smaller form-factor of the data system would simplify mass-spectrometer use in a non-laboratory environment.
| PROPOSAL NUMBER: | 02- H3.03-9695 (For NASA Use Only - Chron: 022304 ) |
| SUBTOPIC TITLE: | Spaceport/Range Instrumentation and Control Technologies |
| PROPOSAL TITLE: | Ka-Band PAA for Satellite Telemetry System for RLVs & Aircraft |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Paratek Microwave, Inc.
6935N Oakland Mills Road
Columbia , MD 21045 - 4719
(443 ) 259 - 0140
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Jeff Henderson
jhenderson@paratek.com
6935N Oakland Mills Road
Columbia , MD 21045 - 4719
(443 ) 259 - 0140
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The proposed antenna is a Radial-Waveguide Array (RWA) that will operate at Ka band, 25.5-27.5 GHz in transmit and receive for left-hand, right-hand. This Phase I effort will develop the phase shifter element and control distribution layer. This planar antenna has the ability to reconfigure its beam width from a narrow, directive beam to a sector-wide beam. The design is easily scaleable to support the desired gain for the specific link. The design and the Parascan? phase shifter technology that makes this antenna possible are unique to Paratek Microwave, Inc. This antenna will enable NASA to realize a space-based telemetry system for their reusable launch vehicles, with substantial savings from their terrestrial-based telemetry systems and revolutionize broadband network links for both terrestrial and SATCOM communication networks.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
This antenna has the potential to revolutionize broadband network links for both terrestrial and SATCOM communication networks. Due to the scalability of the array once the frequency and parameters are defined, the size (and thus price) of the antenna can be specified to support both ends of a terrestrial broadband wireless link such as the local multipoint distribution system (LMDS), hub and customer premise equipment.
The projected price point of such an array is significantly lower than such solutions as the Boeing Connexion phased array antenna, which costs in excess of $500K.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
This antenna will enable NASA to realize a space-based telemetry system for their reusable launch vehicles, with substantial savings from their terrestrial-based telemetry systems.
The proposed antenna is a Radial-Waveguide Array (RWA) that will operate at Ka band, 25.5-27.5 GHz in transmit and receive for left-hand, right-hand. This Phase I effort will develop the phase shifter element and control distribution layer. This planar antenna has the ability to reconfigure its beam width from a narrow, directive beam to a sector-wide beam. The design is easily scaleable to support the desired gain for the specific link, which will support other SATCOM networks or point-to-point links.
| PROPOSAL NUMBER: | 02- H3.04-8592 (For NASA Use Only - Chron: 023407 ) |
| SUBTOPIC TITLE: | Electromagnetic Physics Measurements, Control, and Simulation Technologies |
| PROPOSAL TITLE: | Differencing Electrostatic Optical Sensor (DEOS) |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
PHYSICAL OPTICS CORPORATION
20600 Gramercy Place, Building 100
Torrance , CA 90501 - 1821
(310 ) 530 - 7892
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Dr. Michael Reznikov
poc@socal.rr.com
2545 West 237th Street, Suite B
Torrance , CA 90505 - 5228
(310 ) 320 - 3088
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
In response to NASA?s need for miniature sensors for detecting and measuring electrostatic potential and charge distribution generated on payloads, spacecraft, and landers, Physical Optics Corporation (POC) proposes to develop an innovative Differential Electrostatic Optical Sensor (DEOS). DEOS will measure the quasi-stationary (steady state or low frequency) charge induced in its electrodes by a local electrostatic field. Modulation, rectifying, integration, and optical attenuation will be accomplished by the optically driven structure of three cantilevered membranes. The compact, micro-electro-mechanical systems (MEMS) device will have a very low optical power consumption, will require no galvanic link to the source of an electrostatic field, and will have no vulnerability to electromagnetic influences. The unique DEOS design will permit it to be safely used in any environment, including toxic and explosive vapors, liquid and solid propellants, the ionosphere of earth, and in the atmospheres or on the surfaces of other planets. In Phase I, POC will fabricate a laboratory model and demonstrate the feasibility of the DEOS technology. In Phase II, POC will design and fabricate an engineering prototype for field-testing.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
POC?s Differential Electrostatic Optical Sensor will have several commercial applications in mapping electrostatic fields, and in the transportation and power industries for measuring ionization and triboelectric charges to prevent undesirable electrostatic discharge that could harm both personnel and equipment.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
The fully developed, compact, and durable DEOS will be used in electromagnetic physics measurements of Human Exploration and Development of Space (HEDS) Enterprise of NASA.
As a part of environmental research, DEOS will be very useful in experiments of the Jet Propulsion Laboratory?s (JPL?s) New Millennium Program. In particular, it will benefit the Geospace Electrodynamic Connections (GEC) mission.
| PROPOSAL NUMBER: | 02- H3.04-8787 (For NASA Use Only - Chron: 023212 ) |
| SUBTOPIC TITLE: | Electromagnetic Physics Measurements, Control, and Simulation Technologies |
| PROPOSAL TITLE: | Distributed Fiber-optic Electrostatic Potential Sensor System for Spacecrafts |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Renka Corporation
Two Corporation Way
Peabody , MA 01960 - 7996
(978 ) 532 - 3800
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Quishi Chen
qchen@renka.com
Two Corporation Way
Peabody , MA 01960 - 7996
(978 ) 532 - 3800
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
We propose to demonstrate the feasibility of using a distributed fiber-optic sensor system to monitor high electrostatic voltages and surface electrical charge density on spacecraft components. Based on functional material jacketed FBG sensors and WDM technologies, the sensor system features noise immunity to electromagnetic interference, good electrical isolation, and is compact and lightweight. A unique multi-channel demodulation approach is proposed, which allows tens or hundreds of sensors to be integrated through an optical fiber and to share a single light source. This system will be particularly useful for detection/monitoring of hazardous electrostatic potentials and/or large surface charges on spacecraft surfaces. It also provides real-time multi-points measurement of surface charge, which could benefit scientific research in understanding surface charging in the plasma environment.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
The distributed fiber-optic voltage sensing system will find great applications in military, industrial, and consumer sectors, such as aerospace and power transmission. The resultant WDM demodulation approach can be used in many similar multi-sensor monitoring systems, such as multi-point temperature and/or pressure monitoring for ships, trains or airplanes.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
The technology developed in this program will provide secure, safe and multi-point monitoring of spacecraft surface charging. This will be of benefit to NASA? technologies on Electromagnetic Physics Measurements, Control, and Simulation. It is particularly useful for NASA missions where there is relative high plasma density and ease of electrostatic charging and sparking.
| PROPOSAL NUMBER: | 02- H3.05-8617 (For NASA Use Only - Chron: 023382 ) |
| SUBTOPIC TITLE: | Wireless Power Transmission |
| PROPOSAL TITLE: | Powering Satellites Using a 2 Micron Crystal Fiber Laser |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Lasergenics Corporation
6830 Via Del Oro, Suite 103
San Jose , CA 95119 - 1353
(408 ) 363 - 9791
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Richard Schlecht
schlecht@lasergenics.com
6830 Via Del Oro, Suite 103
San Jose , CA 95119 - 1353
(408 ) 363 - 9791
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The objective of our proposed program is to demonstrate a high power single crystal fiber laser of Tm, Ho:YAG at 2 microns, an eye-safe wavelength, that can be used to power satellites. This system would be very efficient, light in weight and quite small in size. The efficiency and size of the laser would in large part be due to the fact that the laser is to be diode pumped and the single crystal fibers will be double-clad. These two developments have led to the demonstration of fiber lasers that have output powers over 100 Watts. The single crystal fibers will lead to increases in efficiency and power capability and therby reduce these systems further.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
A high power two micron laser will have many commercial applications as a high power compact laser at this wavelength does not exist at this time. This wavelength is very useful for medical and dental applications. It is the proper wavelength for several medical procedures. A high power 2 micron source that is single mode, as our design can be readily developed to be, will find application as an OPO pump. This can lead to a broadly tunable source for investigating molecular and atmospheric effects.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
Beyond the satellite power application, this laser device could find wide application in NASA because of its eye-safe wavelength. Two microns can be used to probe the atmosphere to monitor and study aerosols and particles. This system could replace the CO2 laser for this application.It could also find use in rangefinding. As a pump for an OPO, this system could be of significant use for studying the atmosphere of earth and other planets.
| PROPOSAL NUMBER: | 02- H3.06-8369 (For NASA Use Only - Chron: 023630 ) |
| SUBTOPIC TITLE: | Propellant Depots |
| PROPOSAL TITLE: | The cryogenic evaluation of typical and experimental filament winding materials |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
HYPERCOMP ENGINEERING, INC.
1080 North Main Suite #2
Brigham City , UT 84302 - 1470
(435 ) 734 - 1166
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
James Patterson
jamesp@hypercompeng.com
1080 North Main Suite #2
Brigham City , UT 84302 - 1470
(435 ) 734 - 1166
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
HyPerComp Engineering proposes to conduct a series of material tests to evaluate the performance of standard and experimental filament winding materials in cryogenic pressure vessel applications. The need for high performance lightweight storage of cryogenic materials only intensifies. Some obvious aerospace applications include cryogenic fuel storage for liquid propellant rockets and satellite systems; for commercial applications there are requirements for a new generation of liquefied natural gas containers (LNG) for the ever increasing demand for improved and more efficient energy transportation systems.
Attempts have been made to expand the limited knowledge of basic material properties and capabilities at extremely cold temperatures through testing with various forms of material coupons. The difficulty with this approach is in being able to apply the biaxial stress/strain state that the material will see in an actual pressure vessel to any degree of certainty. By testing the candidate materials in actual filament wound pressure vessels, in typical cryogenic pressurization sequences, the data gathered will be exactly representative of the performance that can be expected. This is the data required to design and qualify high performance filament wound composite pressure vessels for safe and reliable cryogenic applications.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
Improvements in commercial filament wound composite pressure vessels are constantly being sought after. Any advance in technology that can make these products lighter, safer, or more cost effective to fabricate is readily incorporated into their design and fabrication. HyPerComp Engineering believes the information what will be obtained through this SBIR will prove very valuable in the development of filament wound composite pressure vessels for use in the storage and transportation of liquefied natural gas as well as other commercially valuable gases stored or transported in liquid form.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
The technology obtained from this proposed study will be of special value in the development of high performance filament wound composite pressure vessels used in aerospace and defense applications. Liquefied gaseous fuel storage for booster systems as well as satellite systems are prime candidates to benefit from the information that will be gathered in this proposed effort. The data is expected to significantly effect the design and successful qualification of high performance (light weight) pressure vessels for all cryogenic applications.
| PROPOSAL NUMBER: | 02- H3.07-7490 (For NASA Use Only - Chron: 024509 ) |
| SUBTOPIC TITLE: | Space Nuclear Power For Human Missions |
| PROPOSAL TITLE: | Thermochemical Energy Conversion Engine for Electricity Generation |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
ECOTERA ENERGY, INC.
5340 Millertown Pike, Suite 131
Knoxville , TN 37924 - 2139
(865 ) 483 - 3520
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Dr. George Courville
george@ecotera.com
5340 Millertown Pike, Suite 131
Knoxville , TN 37924 - 2139
(865 ) 689 - 7290
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
NASA is interested in the development of highly advanced systems, subsystems and components to enable future robotic and manned missions. A key requirement for these challenging missions will be the development of high efficiency power conversion systems with increased power density. Ecotera Energy proposes an innovative gas turbine improvement, the Thermochemical Energy Conversion (TEC) engine, which has important advantages for space missions over alternatives. TEC engines use a closed?cycle gas turbine and the unique feature of an active working fluid that reversibly dissociates creating greater expansion through the turbine and recombining prior to compression during each cycle. This results in a reduction in the fraction of turbine power required to turn the compressor and an increase in the heat transfer coefficient compared to recuperators with non-dissociating working fluids. For NASA, these features mean increased energy efficiency (over 45%) and higher power density (500 w/Kg) than existing systems in the same power range, which will reduce mass allocations for electricity generation on space missions. Other advantages of TEC include: easy scaling from a few kWe to MWe; operation with any thermal energy source including methane, hydrogen, solar thermal, and reactor waste heat; enhanced heat rejection; and quiet, hermetically sealed operation.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
Engines based on the TEC concept will have superior thermal efficiency and power density to alternative energy converters in the range of a few kilowatts to a few hundred kilowatts. The TEC engine is suitable for use as a solar thermal energy converter, biofuel/biomass converter, industrial waste heat recovery systems, and remote power services using indigenous fuels. Cross-cutting applications include commercial aircraft auxiliary power units, turbofan engines, combined cooling, heat and power systems, hybrid electric vehicle power systems, distributed generation, village power and man-portable power units. There is a worldwide need for more efficient modular power units with lower emissions.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
Systems incorporating the TEC engine would support advancements in NASA?s Space Solar Power and Dynamic Solar Power Programs, and Brayton and Stirling Space Nuclear Power Systems. The advanced heat rejection design, high power density, and quiet operation are additional benefits of TEC power supplies on spacecraft as well as for satellite and science station power sources and space auxiliary power systems. TEC technology could also be configured to provide power for aircraft propulsion.
A complete TEC system could integrate multiple technologies such as oil-free turbomachinery, high speed turbo alternators, and Brayton and Stirling power conversion systems.
| PROPOSAL NUMBER: | 02- H3.07-8994 (For NASA Use Only - Chron: 023005 ) |
| SUBTOPIC TITLE: | Space Nuclear Power For Human Missions |
| PROPOSAL TITLE: | An Ultra-Lightweight, High Performance Carbon-Carbon Space Radiator |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Allcomp Inc
209 Puente Ave.
City of Industry , CA 91746 - 2304
(626 ) 369 - 1273
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
William Miller
bill.miller@allcomp.net
209 Puente Ave.
City of Industry , CA 91746 - 2304
(626 ) 369 - 1273
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
As one of two key parts of heat rejection systems in power conversion technologies for solar or nuclear electric propulsion, radiators reject the waste thermal energy generated in the power conversion process to space. An advanced radiator should provide high thermal rejection performance with minimum mass while satisfying the structure requirements. Traditional metal based radiators and single phase pumped heat transport loops are inadequate for emerging demands in near and far term space explorations; metal based radiators usually are over 8 ~ 10kg/m2. Carbon-Carbon (C-C) composite materials are ideal candidates to solve the above challenges in new generation space radiators because of their series of advantages, such as very low density, high thermal conductivity, good mechanical properties, high flexibility and variability in properties by material construction et al. In combination with heat pipes, two-phase Capillary Pumped Loops (CPL) and Loop Heat Pipes (LHP) or other two-phase heat transport loops, overall thermal performance and reliability of the space radiators can be significantly improved and realized by reducing radiator mass, which is a big portion of overall spacecraft mass. Hence, we propose to research and develop advanced high temperature C-C radiators for space solar or nuclear power conversion and other space systems.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
Power systems currently under development for deep space exploration is a prime example of an application that would benefit significantly by this research and development. A five fold reduction in radiator specific mass is achievable and needed to meet the demanding challenge of space exploration. The proposed C-C radiator design has wide ranging application in both low and high-radiated temperatures, as well as for small and large power conversion systems.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
Carbon-carbon radiators in the form of heat exchangers are expected to emerge in aerospace applications, particularly in high performance military aircraft, and hypersonic vehicles where high temperatures pose severe design issues.
| PROPOSAL NUMBER: | 02- H3.07-9957 (For NASA Use Only - Chron: 022042 ) |
| SUBTOPIC TITLE: | Space Nuclear Power For Human Missions |
| PROPOSAL TITLE: | An Advanced SiC Power Switch for Deep Space Power Systems |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
UNITED SILICON CARBIDE, INC.
100 Jersey Ave., Building D
New Brunswick , NJ 08901 - 3200
(732 ) 565 - 9500
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Petre Alexandrov
uscalexandrov@yahoo.com
100 Jersey Ave., Building D
New Brunswick , NJ 08901 - 3200
(732 ) 565 - 9500
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
We propose to design and fabricate advanced SiC power switch aimed at up to several kilowatt power system applications. The power switch is expected to lead to (i) substantially reduced volume and weight of space power systems, (ii) greatly expanded operating temperature range, and (iii) drastically improved power efficiency and enhanced radiation tolerance. In Phase I, we propose to design, optimize, and compare different SiC power switch structures. DC and high-speed transient characteristics will be systematically studied over a wide temperature range. Concentration will be focused on achieving operations with highest possible power density, efficiency, and speed over a wide temperature range. We also propose to perform experimental work to develop all of the critical process technologies in Phase I. In Phase II, we shall apply the developed technology to fabricate the advanced 4H-SiC power switches up to 5 kW and use them to demonstrate the operation of a motor control system showing the true advantages of an all-SiC power converter.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
There are numerous applications for the advanced power switch including the mass market of switch-mode power supplies (SMPSs), power factor correctors (PFCs), power converters, and motor controllers. The power switch is ideal for all the medium power level systems where volume, mass, minimum passive cooling, high frequency (smaller capacitor/ inductor) with dramatically improved power efficiency are important for order-of-magnitude improvements in system level performance. It also has important applications for deep oil drilling due to its high temperature capability. At higher frequencies, the device would find additional industrial and commercial applications in semiconductor IC fabrication instruments, RF heating, wireless communication base stations, TV station transmitters and satellite links.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
NASA deep space power electronic applications including compact,
light and high efficiency energy conditioning and conversion systems; Compact, high speed, and high efficiency power supply systems; Propulsion and space vehicle power systems capable of high power density (250X higher than Si state-of-the-art), wide operating temperature range (70-600K) and light and compact (75% reduction in weight and size in comparison to Si sota).
| PROPOSAL NUMBER: | 02- H3.09-9224 (For NASA Use Only - Chron: 022775 ) |
| SUBTOPIC TITLE: | Spaceport Command, Control, and Monitor Technologies |
| PROPOSAL TITLE: | New and Improved Classifiers for Fault Diagnosis |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Intelligent Automation, Inc.
7519 Standish Place Suite 200
Rockville , MD 20855 - 2785
(301 ) 294 - 5238
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Chiman Kwan
ckwan@i-a-i.com
7519 Standish Place Suite 200
Rockville , MD 20855 - 2785
(301 ) 294 - 5200
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Many existing fault classification algorithms use Bayesian approach to fuse different classifiers. One notable problem is that the Bayesian approach cannot distinguish between consistent but low probability data and inconsistent data. Moreover, the Bayesian approach cannot properly handle incomplete and uncertain evidence caused by measurement noise or interferences.
Here Intelligent Automation, Inc. (IAI) and its consultant Prof. Henry Leung of the University of Calgary, jointly propose two ways to improve the performance of existing fault classification algorithms. First, we propose to apply the latest development in classification theory known as Support Vector Machines (SVM) to improve the accuracy of classifiers. SVM has several attractive advantages, including global optimal solutions, no over-training problems, explicit bounds on achievable performance, and better recognition performance than most learning systems for a wide range of applications. Second, we propose to apply Dempster-Shafer (DS) theory to fuse several classifier outputs together. DS theory has several advantages such as commutative and associative properties, which means the identification results are independent of the order in which the data is presented. The most important advantage is that DS theory can explicitly take the evidence uncertainty into account. Hence the system will be very robust to noise and uncertainties.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
The proposed algorithm can be used for both military and commercial systems. Military applications include components in the Future Combat Systems, and Joint Strike Fighter. Commercial applications include bearings, pumps, gearboxes, etc. The market size will be the same as the NASA market.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
In this Phase 1 and Phase 2, we intend to apply the proposed technology to some selected systems by pur partner at Boeing with respect to some specific NASA systems such as Main Propulsion System, Thermal Control System, etc. We expect to produce both software and hardware products. The market size for the anticipated products is estimated to be more than 10 million dollars.
| PROPOSAL NUMBER: | 02- H3.10-7616 (For NASA Use Only - Chron: 024383 ) |
| SUBTOPIC TITLE: | Solar Power Generation and Power Management |
| PROPOSAL TITLE: | High Power Platform for the Stretched Lens Array |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
AEC-ABLE ENGINEERING CO.
7200 Hollister Ave
Goleta , CA 93117 - 2807
(805 ) 690 - 2434
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Mike Eskenazi
meskenazi@aec-able.com
7200 Hollister Ave
Goleta , CA 93117 - 2807
(805 ) 690 - 2447
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The proposed innovative solar array is based on combining two cutting edge technologies, the SquareRigger solar array structure and the Stretched Lens Array (SLA), to produce an extremely lightweight, high efficiency, high power, high voltage and low stowed volume solar array suitable for very high power applications. This solar array uses SquareRigger, which is believed to be the best-demonstrated structural approach for deploying extremely large photovoltaic blankets in terms of low mass, low stowed volume and high stiffness and the SLA Fresnel concentrator, which is believed to be the best demonstrated photovoltaic system, in terms of the desirable combination of low cost, high efficiency (30%), ultra-low mass (>500 W/kg blanket) and high voltage (>1000V). The proposed concentrator elements are highly optimized versions of the extremely successful Deep Space 1 SCARLET solar array components. During the first phase of the SBIR preliminary design and analysis (structure, power and mass) of the solar array system will be performed and reported and a mechanically functional mock-up of the dual-deck SLA photovoltaic blanket will be fabricated. It is envisioned that a full size (5m x 2.5m) SLA SquareRigger array will be built and tested for mass power and structural properties during phase 2.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
SLA SquareRigger is potentially applicable to all earth-orbiting commercial high power satellites providing the benefits of reduced cost and mass. The projected near term doubling of power of high power GEO communication satellites from the current range of 15 kW to over 30kW provides a very likely application.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
The innovative SLA SquareRigger solar array developed in this program will potentially enable numerous future NASA and DOD missions requiring the critical combination of high power, low cost, low mass, high efficiency (minimal deployed area), high voltage and compact stowage for launch. Specific NASA applications for SLA SquareRigger are broad and include Space Solar Power (SSP), deep space probes, Solar Electric Propulsion (SEP) tugs, earth orbiting science satellites and high radiation missions.
| PROPOSAL NUMBER: | 02- H3.10-8485 (For NASA Use Only - Chron: 023514 ) |
| SUBTOPIC TITLE: | Solar Power Generation and Power Management |
| PROPOSAL TITLE: | Improved Efficiency and Stability in Lightweight Polymeric Photovoltaic Devices |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Physical Sciences Inc
20 New England Business Ctr
Andover , MA 01810 - 1077
(978 ) 689 - 0003
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Susan Pasco Gardner
gardner@psicorp.com
20 New England Business Ctr
Andover , MA 01810 - 1077
(978 ) 689 - 0003
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Polymeric photovoltaic devices are attractive for NASA?s space and terrestrial applications because of their light weight and low production cost. However, current devices suffer from instability and short lifetimes. The stability and lifetime of polymeric photovoltaic devices can be extended by increasing the charge mobility through the conjugated polymer. This increase in mobility reduces the opportunity for device degradation through trapped charges. Physical Sciences Inc. (PSI) proposes to increase the charge mobility by developing a three-component blend of conjugated polymers and fullerenes which will simultaneously increase the efficiency and stability of the device by increasing the hole mobility of the composite. The photovoltaic devices constructed with the polymer are predicted to have a tenfold increase in stability compared to devices fabricated with a blend of a single conjugated polymer and fullerenes.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
The proposed approach to increasing the stability of conjugated polymer photovoltaic devices will greatly improve the feasibility of these devices for use in NASA space missions as well as in the private sector. Potential non-military applications include photovoltaic appliques for tents, backpacks and large outdoor shelters.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
By increasing the stability and efficiency of lightweight polymeric photovoltaic devices, NASA will be able to utilize them for applications such as satellites, space suits, and rovers. The potential specific power of > 1000 W/kg will allow much greater feasibility for the use of conjugated polymers in photovoltaic devices.
| PROPOSAL NUMBER: | 02- H4.01-7827 (For NASA Use Only - Chron: 024172 ) |
| SUBTOPIC TITLE: | Extravehicular Activity Productivity |
| PROPOSAL TITLE: | Nitrous Oxide Propulsion System |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Pioneer Astronautics
11111 W. 8th Ave., Unit A
Lakewood , CO 80215 - 5516
(303 ) 980 - 0890
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Robert Zubrin
zubrin@aol.com
11111 W. 8th Ave., Unit A
Lakewood , CO 80215 - 5516
(303 ) 980 - 0890
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The Nitrous Oxide Propulsion System (NOPS) is a new Extravehicular Mobility Unit (EMU) thruster concept using nitrous oxide as a monopropellant. Liquid monopropellants are often used in propulsion systems where simplicity of design, restartable/control on demand, and repeatability is desired. Unfortunately, many monopropellants are toxic and dangerous, ruling them out for EMU thruster application. Thus, EMU thrusters have relied upon cold gaseous nitrogen, which offers very low specific impulse and propellant mass fraction. A NOPS, however, uses nitrous oxide, a readily available safe and storable propellant which is not toxic, has performance comparable to hydrazine, and does not decompose spontaneously like hydrogen peroxide. Furthermore, Pioneer Astronautics has demonstrated a system that decomposes N2O into a breathable mix of oxygen and nitrogen. Thus, for example, an EMU propelled by a NOPS would provide an astronaut with a large emergency backup supply of oxygen. Such a dual use system could also have great utility as the propulsion system for manned spacecraft, such as the International Space Station or the Space Shuttle, where safety is paramount and breathing gas reserves are desired. Replacing current liquid monopropellant thrusters with NOPS would greatly reduce ground processing time and costs, while providing comparable performance.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
The Nitrous Oxide Propulsion System has the potential of promoting use of liquid monopropellant rockets. Currently, the difficulty and cost in safely handling and storing conventional liquid monopropellants has hindered their use. The NOPS would not have these limitations. Hydrazine is commonly used as a monopropellant in attitude control thrusters in spacecraft. Unfortunately, hydrazine is extremely toxic. NOPSs, however, use a benign monopropellant, and so much less care and expense is necessary. NOPSs would be much more profitable and attractive to use than current common monopropellant rockets systems, and should be able to dominate the market for liquid monopropellant propulsion systems, such as are used in attitude control of spacecraft. Currently, some 1000 satellites are planned for launch in the next 10 years, and all will need attitude control systems. These satellites and their necessary replacements thus guarantee the NOPS a large and highly lucrative commercial market.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
The NOPS propulsion system concept, due to its inherent safety, is an attractive propulsion system for a Manned Maneuvering Unit (MMU) or SAFER system, as the N2O monopropellant greatly out performs cold N2 thrusters used on current MMUs in both specific impulse and propellant storability, because its 5 times as dense at ? the pressure as compressed N2. In addition, Pioneer Astronautics has also demonstrated that N2O can be decomposed into a breathable mixture of N2 and O2, offering the potential for a combined spacesuit breathing/MMU propulsion system, with greatly increased endurance and mobility compared to current systems. If manned spacecraft were to use a NOPS it would allow the propellant aboard the Space Station or interplanetary spacecraft to be used as a backup to the life support system. Transporting air reserves to the Space Station as N2O would significantly reduce logistics costs by drastically cutting transport tankage mass.
| PROPOSAL NUMBER: | 02- H4.01-8164 (For NASA Use Only - Chron: 023835 ) |
| SUBTOPIC TITLE: | Extravehicular Activity Productivity |
| PROPOSAL TITLE: | Organic Rubber Aerogel as Thermal Insulation and Radiation Shield |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Aspen Aerogels, Inc.
184 Cedar Hill St.
Marlborough , MA 01752 - 3017
(508 ) 481 - 5058
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Je Kyun Lee
jekyun@aerogel.com
184 Cedar Hill St.
Marlborough , MA 01752 - 3017
(508 ) 481 - 5058
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
NASA is seeking innovative thermal insulation materials for extravehicular activity (EVA) systems that improve performance in low ambient pressure, reduce cost and weight, and increase durability and human comfort. Aspen Aerogels Inc. (AAI) proposes to demonstrate an organic rubber based aerogel insulation material that will provide superior thermal insulation, and inherent radiation protection for NASA?s EVA mission applications. AAI?s proposed solution will be based on organic polymer rubber materials such as Polyurethane (PU), Ethylene Propylene Diene Monomer (EPDM), and Polybutadiene (PB) Rubbers, thus exhibiting the flexibility, resiliency, toughness and durability typical of the parent polymer, yet with the low density and superior insulation properties associated with the aerogels. The rubbery behavior of the proposed materials will overcome the weak and brittle nature of conventional inorganic and organic aerogel insulation materials. Additionally, because of the high content of hydrogen in their structure the proposed aerogels will also provide inherent radiation protection for EVA activities. They will also exhibit inherent hydrophobicity due to their hydrocarbon molecular structure. Overall, the rubber based organic aerogel will provide exceptional thermal insulation, radiation shielding, and flexibility for NASA?s crewmember protection and space hardware and vehicles including other commercial applications.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
The proposed organic rubber based aerogels will be used for thermal insulation and radiation shielding of many commercial applications as follows: garment, glove, and footwear, commercial aircraft, racing car insulation, ovens/furnaces, lasers, sport apparel, Cryogenic tanks, pipes, and other equipment, liquefied gas transport, black bodies, footwear, portable apparatus for warming, storing, and/or transporting food and medicine, sleeping bags and pads, and military and recreation tent, any other equipment that utilize a form of insulation against heat. They can be recycled for impact modifier and/or filler for conventional plastics.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
The successful completion of organic rubber based aerogels will simultaneously improve thermal insulation and radiation shielding performances, reduce weight and cost, and apply to NASA?s EVA systems for Thermal Micrometeorite Garment (TMG). Others include as follows: other apparel, glove, and footwear of crew members to protect from heat and space radiation, the space shuttle and MARS exploration spacecraft, and vehicles, and many other hardware that utilize a form of insulation against heat.
| PROPOSAL NUMBER: | 02- H4.01-8659 (For NASA Use Only - Chron: 023340 ) |
| SUBTOPIC TITLE: | Extravehicular Activity Productivity |
| PROPOSAL TITLE: | Fuel Cell/Li-ion Battery Hybrid Power System for Space Suits |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Lynntech, Inc.
7610 Eastmark Drive, Suite 202
College Station , TX 77840 - 4024
(979 ) 693 - 0017
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Jeremy Steinshnider
jeremy.steinshnider@lynntech.com
7610 Eastmark Drive, Suite 202
College Station , TX 77840 - 4024
(979 ) 693 - 0017
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
With the ongoing construction of the international space station (ISS), as well as the ever growing desire for manned missions to Mars, the duration and complexity of extravehicular activity (EVA) periods will increase. As a result, electrical power systems with higher capacities and broader capabilities necessary for extended EVA missions are urgently needed. Currently, electrical power is supplied by a variety of secondary (rechargeable) batteries, all with relatively low energy densities (30 ? 90 Wh/kg) and fewer charge/discharge cycles than desired at a substantial monetary cost. Achieving the increased capacity required for extended EVA periods will be difficult, if not impossible, with secondary batteries. A Monopolar? proton exchange membrane (PEM) fuel cell/Li-ion battery hybrid system, utilizing a rechargeable hydrogen storage unit, has both high efficiency and high power?to?weight and ?volume ratios. Lynntech Inc.?s patented Monopolar? PEM fuel cell technology is easily integrated with commercially-available hydrogen storage, Li-ion batteries, and power management controllers, making it ideally suited for the ever increasing demands of NASA and other aerospace
applications.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
Lynntech is heavily committed to developing hybrid power supplies utilizing Monopolar? fuel cells for portable electronics for both the government and commercially. With worldwide sales of portable electronics power packs at 620 million units in 2002 and projections approaching 1 billion units by 2007, Lynntech is receiving interest from industry and will pursue licensing opportunities in this market. With the move to wireless capability, portable electronics have dramatically increased power consumption and reduced battery operation time. Rechargeable batteries such as lithium ion can not keep up with the power demands of mobile phones, PDAs, or notebook computers.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
Lynntech?s patented Monopolar? PEM fuel cell, when coupled with a Li-ion battery in a hybrid configuration, has both the high efficiency and high power to weight and volume ratios required for current and future EVA applications. With this hybrid power system, the multiple batteries currently used for space suit operations can be replaced with a single, centralized unit. The hybrid power system has the potential for much longer operating times than current rechargeable batteries alone. The components of a hybrid power system can be made lightweight at low cost, making it ideally suited for NASA and other aerospace applications.
| PROPOSAL NUMBER: | 02- H5.01-8713 (For NASA Use Only - Chron: 023286 ) |
| SUBTOPIC TITLE: | Automated Rendezvous and Docking and Capture |
| PROPOSAL TITLE: | Autonomous Optical Navigation for Planetary Orbiters |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Microcosm, Inc.
401 Coral Circle
El Segundo , CA 90245 - 4622
(310 ) 726 - 4100
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Dr. James R. Wertz
jwertz@smad.com
401 Coral Circle
El Segundo , CA 90245 - 4622
(310 ) 726 - 4100
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Using standard spacecraft attitude determination sensors, in particular a star sensor and planet sensors, an autonomous navigation system will be developed for planetary orbiters, offering absolute navigation accuracy on the order of ?100 m. This capability directly supports automated rendezvous and docking missions in Earth orbit as well as at other solar system bodies, such as Mars. The navigation solution depends only on measurements of the distance to the center of the central body, determined by measuring its angular diameter, and the direction to the center of the body in inertial space. These measurements are made by imaging the planetary disk, determining its centroid and angular diameter, and simultaneously imaging the star background. Relative navigation between chaser and target spacecraft is achieved via intersatellite communication of each individual vehicle?s absolute navigation solution. Microcosm offers substantial experience in autonomous space navigation, including our development of an optical autonomous navigation system for the Air Force, which was flown on the TAOS spacecraft in 1994. Microcosm is also involved in ongoing work through the USAF to develop an autonomous rendezvous and docking capability for on-orbit servicing of Earth orbiters.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
Non-NASA applications for this autonomous navigation system would be communications satellites, like GEO satellites. They could reduce ground operations costs substantially by eliminating the need for ground tracking. Implementing autonomous navigation on GEO satellites would also enable the application of autonomous stationkeeping maneuvers as well, since the spacecraft would now be able to determine its own drift, it could also enact autonomous orbit control to maintain the desired orbital position. Ground commanding would not be necessary to stationkeep the satellite.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
This technology is applicable for autonomous spacecraft navigation for Earth orbiters or orbiters about any other solar system body. Mars mission orbiters would be direct beneficiaries of such a technology. Rendezvous and docking applications in Earth orbit or in orbit about other planets would also benefit. Relative navigation could be achieved with communication of the real-time absolute navigation information between two vehicles. Close formations could also make use of the relative navigation information. Distributed constellations of satellites could save on operations costs substantially, eliminating the need for ground-based orbit determination for all satellites in the constellation.
| PROPOSAL NUMBER: | 02- H5.02-8627 (For NASA Use Only - Chron: 023372 ) |
| SUBTOPIC TITLE: | Robotics Assistance, Assembly, Maintenance, and Servicing |
| PROPOSAL TITLE: | Achievability control theory for hybrid human-robot systems |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Raven Research Corporation
1950 Mountain View Road
Lenoir City , TN 37771 - 7820
(865 ) 986 - 1166
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
John Draper
draperjv@bellsouth.net
1950 Mountain View Road
Lenoir City , TN 37771 - 7820
(865 ) 986 - 1166
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The objective of the proposed project is the development of technology for more efficient and effective human-computer supervision of complex systems. Systems that combine humans and robots in a cooperative manner may be termed hybrid systems. Hybrid systems offer advantages over both purely automated systems and purely manual systems in many circumstances. However, future hybrid systems will be asked to perform in more challenging environments than existing systems. This gives rise to a serious need to develop methods for integrating humans more closely?and more efficiently?than is now possible. We propose to develop Achievability Control Theory (ACT), which synergistically combines human and machine capabilities and enhances the flexibility and effectiveness of hybrid robotic and automated systems. This innovation is generally relevant for the development of future hybrid systems in several applications and particularly for NASA space construction, maintenance, and exploration activities. These activities involve humans interacting with automated assets in situations that are dynamic and unpredictable. The proposed research encompasses the development of a theory and an analytical approach to achieve synergistic performance in dynamic environments along with the collection of supporting data through basic experiments.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
Many potential non-NASA applications also exist. On the civilian side, these include Transportation assets routing & scheduling, hybrid-automated air traffic control, robotic search & rescue (mobile robots), flexible manufacturing system control, hybrid-automated project management for complex system development, and robotic assembly line planning and control. There are also potential academic and educational applications, including: industrial engineering training and research, robotics & automation research, computer science, and human factors & cognitive sciences.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
Given the broad use of computer control schemes in the modern economy, it seems that there may be a many applications for a new, more flexible automation control model. A few potential applications specific to NASA include: (1) Human-telerobot interaction in orbital or planetary missions including construction, maintenance, and exploration; (2) mission planning for human-robot interactive tasks like EVA; and multi-robot supervision during construction, maintenance, or exploration
| PROPOSAL NUMBER: | 02- H5.02-9559 (For NASA Use Only - Chron: 022440 ) |
| SUBTOPIC TITLE: | Robotics Assistance, Assembly, Maintenance, and Servicing |
| PROPOSAL TITLE: | A High Resolution Ultra-wide FOV Telepresence Display |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Sensics
10706 Cardington Way #202
Cockeysville , MD 21030 - 3071
(410 ) 628 - 8887
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Lawrence Brown
larry@sensics.com
10706 Cardington Way #202
Cockeysville , MD 21030 - 0000
(443 ) 226 - 2967
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
NASA has embarked on an ever more ambitious
path of developing modular space exploration systems, and
human exploration missions. To enable missions
that are envisioned for the future, advances in
the human/robotic interface are required. This
proposal provides a new telepresence interface, based
on an ultra-wide field-of-view (FOV) HMD. This fully
immersive HMD has a FOV which nearly matches the unobstructed
human visual field, and maintains high resolution throughout.
By combining this immersive display with a custom
camera system and appropriate software, a telepresence
system capable of high-fidelity depth perception, FOV and
resolution is possible. This tool would be a significant
benefit to human operators of robotic systems.
In Phase 1 we will design a tiled, wide FOV camera array
and appropriate 3D software to interface between this
array and the HMD. The product of Phase 2 will be a
complete working telepresence system with custom camera array
and HMD. There are strong commercialization opportunities in the
engineering services industry and various government
agencies, as they are known users of telepresence systems
for remote operation of robots and vehicles.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
The ultra-wide field of view of the proposed system
will allow users a much greater sense of immersion in the
displayed enviroment--be it virtual or remote.
The new level of telepresence immersion will
enable much more practical police, rescue and hazmat
applications to emerge. It is also well known
that the US military is increasing its reliance
on remotely piloted vehicles and this system
would work equally well in the battlefield
environment. Entertainment applications will
also emerge: for example, allowing individuals to "step
on the field" during a professional sporting
event via telepresence.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
The proposed ultra-wide FOV telepresence system will
enable a new level of operator control over robotic
systems for payload manipulation, docking and similar
tasks. The enhanced FOV and depth perception
will also allow operators of exploration vehicles
greater understanding of the remote terrain---leading
to more efficient exploration and faster, safer
navigation for the remote vehicle. Finally,
playing back the immersive visual experience
recorded on a distant planet for non-NASA
personnel may provide a dramatic marketing tool
for the agency.
| PROPOSAL NUMBER: | 02- H5.02-9632 (For NASA Use Only - Chron: 022367 ) |
| SUBTOPIC TITLE: | Robotics Assistance, Assembly, Maintenance, and Servicing |
| PROPOSAL TITLE: | Novel Force Sensor for Robotics |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Sensortex Inc
515 Schoolhouse Road
Kennett Square , PA 19348 - 1741
(610 ) 444 - 2383
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
William Biter
wbiter@sensortex.com
515 Schoolhouse Road
Kennett Square , PA 19348 - 1741
(610 ) 444 - 2383
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Measuring small loads in small cable/wires is needed to sense force or torque in robotic joints. Load monitoring is normally done using a load cell with strain gauges, which have a low-level output and requires a rigid structure for the strain gauge attachment, resulting in a bulky structure where space is at a premium. In addition, the low level signal requires extensive signal conditioning in the often electrically noisy environment.
The proposed system is based on a new sensor technology, consisting of a stress sensitive wire that can be embedded or cast at the center of a structure. This composite with the sensor wire now becomes a flexible load cell, with load ranges based on the composite size. In addition, the output is at higher level from a low impedance source, giving the system good noise immunity. Since the sensor is magnetic-based, it is possible to excite and detect the signal without physical contact if desired to give even more flexibility.
The use of a flexible force transducer is a novel and unique approach, only possible with this new sensor. This approach can also be modified to measure torque, flexing and vibration as well as loads.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
This proposal addresses an application for a new technology, fabrication of a load cell based on embedding a wire sensor inside a composite. Other applications of the basic technology include embedding in composites to monitor internal strain, both initially and as the composite ages. Such sensors can be used to monitor the health of advanced composites used for airframes and space applications, as well as more conventional structures such as buildings, bridges, etc.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
Robotics are taking a more active role in various aspects of space exploration. This proposal addresses an improvement in methods of monitoring / measuring the force exerted by the robot. The proposed approach will improve one small aspect of designing / fabricating a robotic arm but a crucial component. Any robotic arm requires accurate knowledge of the force being applied. The proposed concept shrinks the size and increases the possible configuration for this particular component. This particular approach addresses the smaller range of force measurements, primarily those using cables for transmission of force (e.g. hands)
| PROPOSAL NUMBER: | 02- H5.03-8178 (For NASA Use Only - Chron: 023821 ) |
| SUBTOPIC TITLE: | Non-Destructive Evaluation, Health Monitoring and Life Determination of Aerospace Vehicles/Systems |
| PROPOSAL TITLE: | Resilient Space-Qualified Non-Destructive Evaluation Miniature System by Microma |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
LEEOAT Company
2631 Colibri Lane
Carlsbad , CA 92009 - 4304
(760 ) 438 - 1439
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Eli Wiener-Avnear
leeoat@worldnet.att.net
2631 Colibri Lane
Carlsbad , CA 92009 - 4304
(760 ) 438 - 1439
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Based on its unique micromachining technology, LEEOAT Company will develop, design, fabricate and test the resilient space qualified NDE miniature system for space deployment. In Phase I of the SBIR program, LEEOAT Company will design and simulate the imaging system for NDE of avionic components and structures. We will reduce-to-practice and conduct theoretical simulations to predict the system performance. Finally, we will estimate the cost/effort for the fabrication and testing of the NDE system in Phase II of the program.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
The development of the resilient, cost-effective NDE miniature system for space application, will open a large window of commercial opportunities in nonmedical and medical applications, as well as in high-technology manufacturing quality control.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
The development of the "Resilient Space Qualified NDE miniature system by micromachining," under the SBIR program, will provide NASA a real-time noninvasive analytical space-deployable tool for on-line structural evaluation of future modular space exploration systems. The light-weight, miniaturization and cost-effectiveness of the innovated NDE system, will result enormous benefits to NASA, in maintenance, safety assurance and qualification of future space components.
| PROPOSAL NUMBER: | 02- H5.03-9144 (For NASA Use Only - Chron: 022855 ) |
| SUBTOPIC TITLE: | Non-Destructive Evaluation, Health Monitoring and Life Determination of Aerospace Vehicles/Systems |
| PROPOSAL TITLE: | Acoustic Emission Sensor for Spacecraft Applications |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Los Gatos Research
67 East Evelyn Avenue, Suite 3
Mountain View , CA 94041 - 1518
(650 ) 965 - 3459
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
An-Dien Nguyen
a.d.nguyen@lgrinc.com
67 East Evelyn Avenue, Suite 3
Mountain View , CA 94041 - 1518
(650 ) 965 - 7772
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Sensors offering accurate real-time monitoring and prediction of damages on vehicle subsystems are important for NASA to reduce both time and costs required for operations involving vehicle inspection. Fiber Bragg Gratings are promising candidates for such sensors because of their high sensitivity in detecting crack growth in metals, delaminations in fiber composites, and chemical degradation. While silica based fiber sensors have been developed for spacecraft strain and stress monitoring , they lack the sensitivity required for advanced monitoring applications, such as detecting weak acoustic wave signals initiated by aerospace structure?s micro-cracks in a noisy, vibrating environment experienced by space systems. Los Gatos Research proposes a high performance acoustic emission sensor based upon inscribing surface relief Bragg gratings in polymer waveguides. The combined superior mechanical property of polymer waveguides and inherent wavelength-encoded nature of the output of waveguide Bragg gratings offer a cost-effective, high detection sensitivity solution to NASA?s Vehicle Health Monitoring program. The Phase I program will demonstrate the acoustic emission response by the polymer waveguides and their applications for real-time monitoring and prediction of damages on vehicle subsystems.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
Potential commercial applications include in situ monitoring of stress and strain in buildings, bridges, automobiles, composite structures. Development of polymer Bragg gratings can find applications in the optical network industry such as wavelength division multiplexing, add/drop multiplexing, and gain flattening.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
The proposed acoustic emission sensor can be used for crack initiation detection and real time health monitoring in spacecraft, space vehicle launch and landing facilities, and payloads.
| PROPOSAL NUMBER: | 02- H5.03-9178 (For NASA Use Only - Chron: 022821 ) |
| SUBTOPIC TITLE: | Non-Destructive Evaluation, Health Monitoring and Life Determination of Aerospace Vehicles/Systems |
| PROPOSAL TITLE: | Exploiting Unusual Characteristics of Photonic Crystals for Novel Optical Device |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Intelligent Fiber Optic Systems
650 Vaqueros Ave.
Sunnyvale , CA 94085 - 1260
(408 ) 328 - 8610
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Dr. Dario Falquier
df@ifos.com
650 Vaqueros Ave.
Sunnyvale , CA 94085 - 1260
(408 ) 328 - 8610
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
This Small Business Innovation Research project proposes to utilize the emerging technology of Photonic Crystals to realize novel optical components. These devices will help pave the road towards commercially viable, high speed, large bandwidth, and miniature all-optical circuits. In particular, the Phase I portion of this project will focus on development of devices based on the ultrarefractive effect in photonic crystals. One such device is an Ultracompact Wavelength Spectrometer. The ultrarefractive effect in photonic crystals enables this and other devices by producing angular deflection of optical beams that is both extremely large in magnitude and also a very strong function of the input wavelength, as compared to standard materials. The expected result of this work is that IFOS will offer some of the first commercially-viable photonic-crystal-based components and modules. Collaboration with leaders in this field at the Technical University of Hamburg-Harburg, will help IFOS accomplish the objectives of this project.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
The developments of this proposal will result in commercial availability of novel products based on photonic crystal technology, such as an ultracompact wavelength spectrometer. This product will find applications throughout the field of optical sensing. In addition, this effort will establish the photonic crystal technology itself as commercially viable and thus open the door for additional photonic crystal devices, such as high-performance miniature optical circuits, to be developed during Phase II of the project. Commercial applications of this technology include high-speed telecommunications and optical data processing.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
Fiber sensor networks are robust, and can survive extremely hostile environments such as those found in aerospace applications. Despite the small size of optical fiber, it has demonstrated excellent mechanical durability and corrosion resistance. Unlike conventional electronic-based technology, optical fibers are extremely secure from outside interference. Additionally, the small size and low weight of the proposed wavelength detector, and optical sensors and photonic crystal devices in general, are ideal for aerospace applications, as they exhibit minimal impact on the vehicle payload. This allows for the possibility of in-flight monitoring systems with negligible vehicle performance degradation.
| PROPOSAL NUMBER: | 02- H6.01-8515 (For NASA Use Only - Chron: 023484 ) |
| SUBTOPIC TITLE: | Crew Training and On-Board Crew Support |
| PROPOSAL TITLE: | Interactive Electronic Procedure Management System |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Sapien Systems
3510 Ingraham St. Suite 200
San Diego , CA 92109 - 6797
(858 ) 775 - 9755
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Jessica Baldis
jessica@sapiensystems.com
3510 Ingraham St. Suite 200
San Diego , CA 92109 - 6797
(858 ) 272 - 5586
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Electronic Procedure Management System (EPMS) is an innovative computer-based system for electronically presenting ?intelligent? procedures. Currently, NASA crews use paper-based procedures, Flight Data Files (FDFs) that contain brief, text-based instructions for completing a task. FDFs provide static information that can be cumbersome to navigate. In addition, carrying large quantities of paper procedures on long duration and long distance missions is not practical. By providing procedural data electronically EPMS offers several benefits and innovations relevant to the need identified in this SBIR proposal. Specifically, EPMS will provide an ?intelligent? method for navigating procedures with multimedia information tailored specifically to the expertise of the user. Presenting and storing the procedures electronically reduces the need to take bulky paper FDFs on missions. In addition, EPMS will integrate training, just-in-time training, and execution into one system. By providing several levels of data, users can access the specific amount and type of data necessary. User and procedure tracking functionality will facilitate identification of strengths and weaknesses throughout every step of a procedure, allowing for continued evaluation and improvement of training and materials and procedures.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
Advances in wearable computing are facilitating the growth of computing solutions in non-traditional computing environments. Many workers (Ex. aircraft, submarine, automotive, and shipboard maintenance personnel) in these non-traditional computing environments rely heavily on paper-based procedures similar to the FDF procedures NASA crews currently use. Sapien System?s proposed EPMS could revolutionize the work process for these workers offering access to electronic procedures on wearable computers ? saving organizations both time and money. Leveraging the initial work Sapien completed for NASA, Sapien has been funded to explore the use of electronic procedure management systems in both the aircraft maintenance and law enforcement communities. Sapien is working with the Office of Naval Research (ONR) and the National Institute of Justice (NIJ) on information display systems for repair and maintenance, ground troops, and Crime Scene Investigation (CSI) communities.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
Astronauts carry out most space flight operations via paper based procedures. An Electronic Procedure Management System (EPMS) will allow efficient operations with procedures. A procedure navigation system will ultimately allow users to hold all procedures on a wearable computer and quickly and efficiently navigate to the appropriate actions. Advanced interaction methods such as custom designed interfaces will allow input and rapid interaction with data, telemetry and other information. Tracking methods will allow monitoring of procedure execution in real-time and in training. Advanced content features in the system will allow repetitive and just-in-time training. The procedure management will be run on multiple computing platforms: EVA and IVA wearables, desk-top monitors and system servers. It will thus be useful not only inflight, but during ground training. Further, the procedure management system will be useful in non-spaceflight operations, such as vehicle processing, inspection and maintenance and scientific experiments.
| PROPOSAL NUMBER: | 02- H6.02-8697 (For NASA Use Only - Chron: 023302 ) |
| SUBTOPIC TITLE: | Distributed/International Ground Operations |
| PROPOSAL TITLE: | Remote On-demand Networked Distributed Operations (RONDO) |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
mobileFOUNDATIONS, Inc.
103 W. Broad Street, Suite 600
Falls Church , VA 22046 - 4237
(703 ) 532 - 9615
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Neil Baitinger
mick@mobilefoundations.com
103 W. Broad Street, Suite 600
Falls Church , VA 22046 - 4237
(703 ) 532 - 9615
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Mission operations for the International Space Station are based on the traditional concept of a primary fixed facility where most of the mission operations tasks are performed, supported by backroom staff of hundreds of engineers. This approach is resource intensive and expensive. The goal of this SBIR is to develop and deploy the technologies necessary to enable on-demand mission operations support. Our approach involves two key components: 1) creating advanced automation that will autonomously monitor the ground system for critical events and wirelessly alert on-call personnel when necessary and 2) developing and integrating the software and hardware to provide wireless access to necessary data, tools, and people (i.e., through videoconferencing) to immediately start resolving the event. Since automation must not significantly increase the risk of operations in Human Exploration and Development of Space (HEDS), our approach will minimize risk and ensure reliability by: 1) building our new technologies on top of state-of-the-art proven technologies and 2) leveraging our extensive knowledge of mission operations, advanced automation, and wireless communications. Thus, our innovative approach to operations will help NASA meet the objectives in the NASA Strategic Plan 2000 of reducing the costs of HEDS through operations automation and consolidation.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
We anticipate building new commercial applications on top of the new technologies, as well as incorporating them into our commercial IncidentPortal? product. One field that will receive the greatest benefit from this SBIR?s technologies is public safety/homeland defense. IncidentPortal provides incident management and wireless interoperability for the first responder community (i.e., police, fire). IncidentPortal has already been used for several major counter-terrorism exercises post 9-11. Public safety shares many of the needs addressed in the SBIR. By incorporating the new capabilities, we project capturing a 25% market share by 2005. We have already incorporated technologies from our Air Force SBIR into IncidentPortal, generating significant recognition for our AF sponsor. Other applications include network monitoring and the remote monitoring of assets or infrastructure. For example, our system could be used by the oil industry for monitoring thousands of miles pipelines and improving the response to anomalous conditions in the lines.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
The culmination of this research will result in an advanced wireless solution to enable the distribution and sharing of information over wireless devices. The resultant technology will be of tremendous value to all of the space operations communities: Federal (civilian and military) and commercial. Upon completion of the SBIR process, mFI plans to incorporate any new technologies into our commercial space offerings. The monitoring and alerting technologies that will be developed for ISS operations can also be applied to monitoring other NASA assets via telemetry streams, such as its networks and facilities. For example, the system that we are developing could easily be applied to monitoring intrusion detection systems, firewalls, etc. in order to protect NASA?s networks. Likewise, this system could be interfaced in the fire and HVAC systems at NASA centers in order to improve the response times of maintenance and first responders.
| PROPOSAL NUMBER: | 02- H6.02-9139 (For NASA Use Only - Chron: 022860 ) |
| SUBTOPIC TITLE: | Distributed/International Ground Operations |
| PROPOSAL TITLE: | Distributed Operations Software for Wireless Handheld Computers |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
TenXsys Inc.
4068 Wisteria Way
Boise , ID 83713 - 0000
(208 ) 250 - 0211
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Layne Simmons
layne@tenxsys.com
4068 Wisteria Way
Boise , ID 83713 - 0000
(208 ) 250 - 0211
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
?Anytime, anywhere information? is a powerful philosophy to improve the capabilities of integrated, international operators and the effectiveness of teams. As National Aeronautics and Space Administration (NASA) has moved into international programs, payload operations, manned and unmanned operations have all become much more complex, with real-time information being transmitted from various NASA operations centers to operators and scientists around the world. To realize the ?anywhere, anytime? philosophy new techniques and tools must be employed. The objective of this proposal is to demonstrate the feasibility of distributed architecture for operations using handheld devices that can be used for real-time operations and training of spacecraft. Previous research by TenXsys has developed the definition of an Adaptive Data Retrieval and Optimized, Intelligent Transfer (ADROIT) system that works in conjunction with one or more applications on a personal digital assistant (PDA) to deliver mission-essential information to distributed operators over a wireless communications infrastructure. The proposed research will extend this work to integrate voice, video, and more complex 3-D image displays and manipulation into the design. Additional advantages with this technology are the innovations on the central server side, which will enable more efficient and effective techniques for processing large volumes of data.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
The commercial market for wireless PDA based applications is virtually untapped. Tools that allow information to be automatically transmitted to people to allow training and operations, ?anywhere, anytime? have applications in many fields. Mobile professionals, educators, students, and individuals all stand to benefit from useful applications. Finance, business, transport operations, construction, health care, law enforcement (including homeland defense), emergency response and natural disaster management are all examples of areas where these tools could be highly leveraged thereby enhancing the information flow and coordination of activities. Many of the problems solved by the proposed operations application in this solicitation lend themselves to adaptation and augmentation that will provide a powerful tool to effectively link virtual teams from across the globe. Once the problems of data delivery and presentation have been solved, they are adaptable to virtually any application that requires collaboration.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
The TenXsys ADROIT solution will enable NASA mission planning, operations, training activities as well as design and engineering collaboration to be more effective. By developing central server techniques for processing large volumes of data into useful information, operations and information transfer will become more effective. As the operations for the space systems evolve, the ADROIT technology will allow mission responsibilities to be re-distributed across the globe, instead of being centrally located in Operations Centers. Handheld devices will become ubiquitous, and voice, video and data can be transmitted in areas with transient connectivity, in real-time. Additionally, large international engineering efforts will require less travel, as virtual teams become more effective.
| PROPOSAL NUMBER: | 02- H7.01-7917 (For NASA Use Only - Chron: 024082 ) |
| SUBTOPIC TITLE: | High Power Electric Propulsion For Human Missions |
| PROPOSAL TITLE: | Improved Operation and Lifetime of High-Power Hall Thrusters |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Ultramet
12173 Montague St
Pacoima , CA 91331 - 2210
(818 ) 899 - 0236
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Brian E. Williams
brian.williams@ultramet.com
12173 Montague St
Pacoima , CA 91331 - 2210
(818 ) 899 - 0236
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
One of the primary factors inhibiting the practical use of next-generation electromagnetic electric propulsion (EP) engines at high power levels (50-100 kW) is the current lack of thermally and mechanically stable insulators. Insulator materials for high-power Hall thrusters can erode rapidly as a result of use in high power density plasma environments and/or fail as a result of mechanical or thermal shock. Boron nitride (BN), currently the material of choice for EP engines, is presently fabricated from pressed and sintered powder that is unreinforced and, in the sizes required for high-power engines, is highly susceptible to failure due to thermal and mechanical shock. In addition, powder-derived BN is very difficult to fabricate in complex, thin-section components, and scaleup of part size and the required mass remains a significant problem. Substantial improvements in these areas can potentially be achieved by fabrication of fiber-reinforced BN via chemical vapor infiltration (CVI). Composite ceramics produced by CVI exhibit higher density, smaller grain size, higher purity, and far greater strength and toughness than unreinforced ceramics produced from powder. In this project, Ultramet proposes to fabricate erosion-resistant, mechanically stable, carbon fiber-reinforced pyrolytic BN (Cf/PBN) insulators for use in Hall thrusters. CVI Cf/PBN composite performance will be demonstrated through testing in a plasma environment.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
Improved high temperature insulating materials are directly applicable to commercial satellites. This EP technology improvement will lead to enhanced satellite capability via increased performance and lifetime and reduced system mass, which combine to greatly reduce mission cost. The automotive industry and engine manufacturers also have near-term applications for toughened ceramics in areas such as low heat rejection diesel engines. High temperature ceramic heating element performance will also be enhanced.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
Spacecraft propulsion technology innovations are sought for upcoming deep space science missions. Propulsion system functions for these missions include primary propulsion, maneuvering, planetary injection, and planetary descent/ascent. Innovations are needed to reduce spacecraft propulsion system mass, volume, and/or cost. Applicable propulsion technologies include nuclear and solar electric propulsion. One area of emphasis pertains to high-performance propulsion systems capable of delivering specific impulse (Isp) greater than 6000 seconds, while utilizing 50 to 100 kilowatts or more of electrical power from a nuclear energy source. Another area applies to propulsion technologies capable of delivering Isp greater than 3500 seconds, using electrical power from radioisotope or solar energy sources. Significant improvements are sought in in spacecraft capability, longevity, mass, volume and/or cost.
| PROPOSAL NUMBER: | 02- H7.02-8007 (For NASA Use Only - Chron: 023992 ) |
| SUBTOPIC TITLE: | Unmanned Autonomous Rendezvous Systems |
| PROPOSAL TITLE: | Autonomous Rendezvous and Docking Techniques |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Cybernet Systems Corporation
727 Airport Boulevard
Ann Arbor , MI 48108 - 1639
(734 ) 668 - 2567
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Joseph Tesar
jtesar@cybernet.com
727 Airport Boulevard
Ann Arbor , MI 48108 - 1639
(734 ) 668 - 2567
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Ongoing logistical repair, maintenance, and resupply of space platforms will become a costly and potentially dangerous activity in the post Space Station era. This is primarily driven by the need for more frequent missions, and as the number of missions increases, so does the cumulative probably of failure in the launch, docking, and return phases of the mission. The best defense will be to make substantially larger use of unmanned resupply vehicles that can automatically rendezvous, dock, and lock-up with said platforms without manned intervention. Over the past 20 years, Cybernet engineers have participated in the development of a variety of alternative rendezvous and docking sensor concepts. During this time, we have evaluated many alternative technologies which include 3D computer vision, Ladar, active and passive beacons, GPS, and INS systems. In this effort, we propose to leverage this expertise into demonstrating that 3D computer vision can solve the short-range docking problem. After feasibility is shown with space-acquired imagery, we will design an embedded system that can operate the 3D vision algorithms.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
Commercial applications include transportation and cooperative robots.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
This technology can be used by NASA to automate manned and routing rendezvous and docking.
| PROPOSAL NUMBER: | 02- H7.02-9616 (For NASA Use Only - Chron: 022383 ) |
| SUBTOPIC TITLE: | Unmanned Autonomous Rendezvous Systems |
| PROPOSAL TITLE: | Rendezvous and Docking Sensor Suite |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Advanced Optical Systems Inc
6767 Old Madison Pike, Suite 410
Huntsville , AL 35806 - 2181
(256 ) 971 - 0036
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Keith B. Farr
farr@aos-inc.com
6767 Old Madison Pike, Suite 410
Huntsville , AL 35806 - 2181
(256 ) 971 - 0036
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
NASA wants to develop new relative navigation methods and sensors for autonomous rendezvous and docking, with a minimum relative navigation sensor suite addressing spacecraft-to-spacecraft ranges of 100 kilometers through docking, including relative attitude control during the final 100 meters of the approach. This proposal represents an opportunity to leverage an on-going program. The Video Guidance Sensor (VGS) has been proven on orbit and is the system of choice for rendezvous and docking guidance for both manned and unmanned flights. Advanced Optical Systems, Inc. (AOS) has been selected to develop the first prototypes and to support Orbital Sciences Corporation (OSC) in developing the flight hardware for the Advanced Video Guidance Sensor (AVGS) for the Demonstration of Autonomous Rendezvous Technology (DART) mission under the Space Launch Initiative (SLI). AOS proposes to combine a mid/short-range AVGS with a long range, time-of-flight laser radar in order to achieve a complete sensor suite that gives range and bearing at ranges of 100 kilometers through docking and 6 degrees-of-freedom information from 300 meters through docking. As an alternative, and depending upon NASA?s needs, we could develop a wide field-of-view, mid range (2 kilometer) laser radar.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
In addition to the ongoing AVGS activities under SLI, Advanced Optical Systems is currently in discussions with several aerospace corporations to supply AVGS units for NASA and non-NASA missions. The addition of a long-range or mid-range laser radar to the AVGS would expand the applicability and customer base. The Rendezvous and Docking Sensor Suite would also find application to Unmanned Aerial Vehicle recovery and may find application to other military and civilian aircraft landing. Robotic arm operation is another potential application.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
Use in the Space Shuttle, use in the Alternate Access to Station (AAS), and use in any other programs involving rendezvous and docking.
| PROPOSAL NUMBER: | 02- H7.02-9628 (For NASA Use Only - Chron: 022371 ) |
| SUBTOPIC TITLE: | Unmanned Autonomous Rendezvous Systems |
| PROPOSAL TITLE: | Integrated Multi-Range Rendezvous Control System |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Princeton Satellite Systems
33 Witherspoon St.
Princeton , NJ 08542 - 3207
(617 ) 879 - 0129
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Stephanie Thomas
sjthomas@psatellite.com
33 Witherspoon St.
Princeton , NJ 08542 - 3207
(609 ) 279 - 9606
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
PSS proposes an integrated multi-range rendezvous control system written in our ObjectAgent distributed software architecture. The control system will use different algorithms at different ranges from the rendezvous target. Rendezvous maneuvers are achieved using a Lambert planner with genetic algorithm optimization for large orbit changes and using a Simplex planner with path constraints for maneuvers at close range to the target. Orbit determination is achieved using a continuous discrete Kalman filter which uses different sensors depending on their availability. For relative sensing, these are: radar for long range; vision for intermediate and close range; intersatellite-link (ISL) when available. For absolute sensing, these are GPS and ground ranging. The vision system, a single camera system developed by PSS or a selected existing system, will provide relative attitude in addition to relative position at intermediate range. PSS has the capability to perform high-fidelity simulations using MultiSatSim, allowing this project to move quickly into software testing. ObjectAgent is an inherently modular software architecture, allowing the resulting control system to be easily adapted, even on-orbit.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
Autonomous rendezvous capability is required for satellite inspection and servicing. PSS has previously conducted economical analysis which indicates refueling satellites can be profitable in some cases. Additionally, elements of the rendezvous control system may be applied to more general problems in formation flying. An autonomous systems are key to keeping the costs of such complex systems in check. Commercial interest in these applications is widespread internationally judging from interest in PSS' new autonomous guidance, navigation and control toolbox module for MATLAB.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
NASA spacecraft, being very valuable, are particularly suited to autnomous rendezvous applications. Expensive spacecraft such as Hubble could prolong their useful life with on-orbit refueling. Inspection capability can help diagnose problems with malfunctioning spacecraft. In general, autonomous maneuver planning such as used in PSS' rendezvous control system saves money by reducing operations costs.
| PROPOSAL NUMBER: | 02- H7.03-9186 (For NASA Use Only - Chron: 022813 ) |
| SUBTOPIC TITLE: | Propulsion Systems Ground Test Operations |
| PROPOSAL TITLE: | Principal Component Analysis for Feature Extraction from One Dimensional Signals |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Intelligent Automation, Inc.
7519 Standish Place Suite 200
Rockville , MD 20855 - 2785
(301 ) 294 - 5238
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Chiman Kwan
ckwan@i-a-i.com
7519 Standish Place Suite 200
Rockville , MD 20855 - 2785
(301 ) 294 - 5200
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
This proposal responds to the solicitation for methods to capture features from one dimensional sensor signals. We exploit a combination of Principal Component Analysis (PCA) and Learning Vector Quantization (LVQ) to capture the required features. This can be used to diagnose a wide variety of systems using sensors which are monitoring the various parameters of the system. We will also describe an innovative one dimensional test probe we have developed that is synergistic with the PCA and LVQ algorithms to yield a very powerful diagnostic tool. The goal of this work is to develop a toolbox of PCA and LVQ implementations optimized for equipment diagnostics. The toolbox will also include software optimized for use with our innovative one dimensional test probe signal concept, but would be equally useful for interpretation of any one dimensional signal. We will also show examples later of the PCA and LVQ algorithms used for a wide range of other applications where the input data set has thousands of degrees of freedom so our toolbox will not be limited to one dimensional signals.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
Commercial customers for our toolset will be developers of advanced equipment which requires comprehensive diagnostic means for testing, for external maintenance tools, and for built-in diagnostics and prognostics. A first non-NASA application we are pursuing is hydraulic systems for the US Army Future Combat System.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
Our past success with the algorithms we will include in the toolbox suggest that with further optimization and generalization, this could be a very useful tool for engineers developing automated health monitoring, fault detection, and diagnosis capabilities, especially for interpretation of complex one dimensional signals. The one dimensional test probe concept described in the proposal offers new capability in structural health monitoring and the toolset will assist users in applying that innovative new technology as well. Engine diagnostics would be a good first NASA application.
| PROPOSAL NUMBER: | 02- H7.03-9809 (For NASA Use Only - Chron: 022190 ) |
| SUBTOPIC TITLE: | Propulsion Systems Ground Test Operations |
| PROPOSAL TITLE: | Design and Analyses of HTS Coils for the VASIMR Experiment |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Tai-Yang Research Corporation
31 Pierson Dr.
Hockessin , DE 19707 - 1029
(302 ) 494 - 4048
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Dr. Chris M. Rey
cmrey@reyresearch.com
31 Pierson Dr.
Hockessin , DE 19707 - 1029
(302 ) 494 - 4048
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
In the Phase I effort, Tai-Yang Research Corporation (TYRC) proposes to design and perform analyses on state-of-the-art High Temperature Superconducting (HTS) coils for the Variable Specific Impulse Magneto-Plasma Rocket (VASIMR) experiment. Using the design results obtained in the Phase I effort, TYRC proposes in Phase II to fabricate, test, and install HTS coils (VX-2 and VX-3) in the existing VASIMR experiment. Replacing the conventional copper coils with state-of-the-art HTS coils in the VASIMR experiment will allow for greater design flexibility, electrical power consumption and increased operational performance.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
Superconducting magnets have found commercial markets in various industrial applications. Industrial applications range from the practical such as MRI/NMR magnets to the high-tech such as high-energy particle accelerators. More common for superconducting applications are high-tech devices such as: magnetic levitation and transportation (MAGLEV), magneto-hydrodynamics (MHD), energy storage (SMES or flywheels), and power transmission/generation technology, etc.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
Anytime there is a need for lightweight, low power consumption, and high-magnetic field, superconductivity will be the logical choice. NASA is presently studying the feasibity of: a) superconducting magnetic energy storage (SMES), b)superconducting flywheels for energy storage, c) VASIMR plasma propulsions, d) MAG-LIFTER for low-cost boost to orbit, d) adiabatic demagnetization for cooling, etc. High-field superconducting magnets are even finding applications in Department of Defense (e.g. active denial non-lethal standoff weapons)
| PROPOSAL NUMBER: | 02- S1.02-7918 (For NASA Use Only - Chron: 024081 ) |
| SUBTOPIC TITLE: | Deep Space Propulsion |
| PROPOSAL TITLE: | LOX Olefin Rocket Propulsion for Deep Space |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Pioneer Astronautics
11111 W. 8th Ave., Unit A
Lakewood , CO 80215 - 5516
(303 ) 984 - 9653
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
K. Mark Caviezel
KMCaviezel@Pioneerastro.com
11111 W. 8th Ave., Unit A
Lakewood , CO 80215 - 5516
(303 ) 980 - 0890
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The LOX Olefin engine (LOXO or LOX/LC2H4 or LOX/LC3H6) is a proposed technology designed to provide interplanetary spacecraft with high specific impulse, space storable propulsion. With the LOXO engine, the combination of liquid oxygen with sub-cooled liquid ethylene or liquid propylene as a rocket propellant enables development of compact lightweight high performance stages with isothermal common bulkhead propellant tanks. This could enable energetic deep space delta-V maneuvers. Currently, space missions requiring energetic delta V maneuvers weeks or months after launch are limited to use of moderate Isp conventional stored hypergolic propellants, typically achieving performance of 310-320 seconds. The much more energetic LOX/LH2 combination has the decided disadvantage of low density, and is not considered suitable for long term storage in space because of thermal management issues with the extremely cold (~20K) LH2. The LOXO propulsion system represents an important midway step that combines the advantages and avoids the major flaws of both of these extremes. Theoretical Isp for this propellant combination over 390 seconds has been calculated using AFALS chemical equilibrium code. With an achievable in-space thermal management system, LOXO is a good candidate for deep space propulsion, with performance greatly surpassing current options for mission planners.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
Although primarily conceived of as an enabling technology for governmentally sponsored deep space exploration missions, LOXO space propulsion would have many other applications as well. A high specific impulse space storable stage would find many customers among commercial, military, and scientific satellites who would value it as a very cost-effective alternative to the current choices of low performance toxic hypergols or hard cryogenic LOX/H2 propulsion. Commercial applications would include the delivery of large geostationary and medium altitude satellites into orbit, apogee kick, and also for high efficiency re-assignment maneuvers and end of life superboosting for geostationary satellites. The LOXO could be used for onboard spacecraft propulsion or for dedicated upper and transfer stages supporting every type of mission.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
LOXO could have applications to interplanetary NASA spacecraft that require large delta-V maneuvers well into deep space by providing high Isp storable fuels. Such fuels could allow faster transit times to the outer planets by avoiding gravity-assist flybys of inner planets or allow larger payloads.
| PROPOSAL NUMBER: | 02- S1.02-8217 (For NASA Use Only - Chron: 023782 ) |
| SUBTOPIC TITLE: | Deep Space Propulsion |
| PROPOSAL TITLE: | Sputter-Resistant Materials for Electric Propulsion |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Energy Science Laboratories, Inc.
6888 Nancy Ridge Drive
San Diego , CA 92121 - 2232
(858 ) 552 - 2034
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Timothy Knowles
tknowles@esli.com
6888 Nancy Ridge Drive
San Diego , CA 92121 - 2232
(858 ) 552 - 2034
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
This SBIR Phase 1 project shall develop sputter-resistant materials for use in electric propulsion test facilities and for plume shields on spacecraft using electric thrusters. A critical need arises because NASA is developing higher impulse, higher power thrusters for deep space science missions. Such thrusters will erode chamber walls ten-times more aggressively than before and create unacceptably high levels of contamination in the life test facilities. Without new materials that are ten-times more resistant than graphite, the only alternative may be installation of larger vacuum test chambers at huge facility cost.
The proposed sputter-resistant materials are based on carbon fibers in a highly textured configuration that allows deep penetration of incident ions and trapping of sputtered secondary atoms. Preliminary analysis predicts low sputter yield and significantly reduced backflow suitable for extending the use of existing test facilities to the next generation of ion engines. Refractory, vacuum compatible materials are used. Phase 1 will assess requirements and analyze performance of the concept liner designs. Selected configurations will be fabricated and sputter tested for model validation. Sputter resistant materials designs and Phase 2 development will be reported.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
Sputter resistant materials are required for
* high-tech materials processing with sputter sources
* fusion reactor first wall
* pulsed power diodes
* ion spectroscopy housings
* ion collection instrumentation
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
Sputter-resistant Chamber Wall Liners are required in the ground test facilities to enable development and life testing of Ion Engines, Hall Effect Thrusters, and other electric propulsion components.
Lightweight high-T sputter-resistant plume shields are required for use in spacecraft to protect panels from ion beams.
| PROPOSAL NUMBER: | 02- S1.02-8639 (For NASA Use Only - Chron: 023360 ) |
| SUBTOPIC TITLE: | Deep Space Propulsion |
| PROPOSAL TITLE: | Inherently Stiff Membranes with Shape Memory |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
United Applied Technologies, Inc.
11506 Gilleland Rd
Huntsville , AL 35803 - 4327
(256 ) 655 - 5120
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Rodney Bradford
r.bradford@unitedappliedtech.com
11506 Gilleland Rd
Huntsville , AL 35803 - 4327
(256 ) 650 - 5120
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Solar sails that have the inherent stiffness to greatly reduce or eliminate the need for tensioning while retaining low areal densities and compact stowage offer enabling capability for multiple missions in the Sun-Earth Connection Space Science theme. Polyimide film materials that are resistant to the space environment will be used to demonstrate and quantify the effectiveness of novel structural design and manufacturing approaches to produce scalable solar sails with areal densities below 15 g/m2. The benefits of this scalable technology to different sail designs including square riggers, heliogyros, and disks will be analyzed and quantified in terms of mass reduction and performance improvement. Alternate polyimide materials with higher surface smoothness and lower coefficients of thermal expansion will be evaluated using the new design and manufacturing approaches.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
Commercial space applications include support structures for solar concentrators used in solar thermal propulsion systems and large communication satellite antennas. Ground commercial applications include emergency shelters in extreme environments and lightweight articles exposed to long-term weathering conditions.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
This membrane structures technology has propulsion applications in NASA near-earth and Mars-class missions. It can also be applied to support structures in high resolution earth science platforms, large light collectors for precision secondary optics, and solar concentrators for electric propulsion systems.
| PROPOSAL NUMBER: | 02- S1.03-9196 (For NASA Use Only - Chron: 022803 ) |
| SUBTOPIC TITLE: | Multifunctional Structure and Sensor Systems |
| PROPOSAL TITLE: | INSPECTION OF DEFORMABLE MIRRORS USING ARRAYS OF MICROFABRICATED INTERFEROMETERS |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
MetroMEMS
3075 Leafwood Drive
Decatur , GA 30033 - 4408
(678 ) 637 - 1634
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Ali Razavi
ali.razavi@metromems.com
3075 Leafwood Drive
Decatur , GA 30033 - 0000
(678 ) 637 - 1634
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
In this project, MetroMEMS determines the scientific, technical, and commercial merit and feasibility of an innovative, high performance inspection and calibration method for dynamic testing of microfabricated deformable mirrors. Deformable mirrors are a key component in most adaptive optics systems. They compensate for wavefront distortion introduced by the medium between the object and the image. Hence, precise inspection and calibration of deformable mirrors are required for optimal performance. This innovative approach utilizes an array of microfabricated position sensing grating interferometer (?PSGI) with electrostatically actuated flexible fingers. Each sensor is capable of measuring displacement with high resolution and bandwidth (MHz). A 4x4 array of ?PSGI will be fabricated to inspect a deformable reflective target (<=10 mm in diameter) at 500 kHz maximum sampling rate. The proposed technique is general and can be applied to inspect various types of microfabricated structures.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
For most MEMS, critical device dimensions (10-1000 mm ? 10%) fall between silicon IC (<10 mm ? 10 ?) and conventional machining (>1000 mm ? 10 mm). As a result most commercially available measurement solutions cannot be used for quality inspection of MEMS. The proposed technology converts a large-scale metrology system into a miniaturized scale using a patented technology. It can be customized to the inspection needs of MEMS manufacturers to reduce manufacturing costs, lead-time and waste of material, and to increase product reliability. Potential customers may include MEMS manufacturers such as Texas Instruments, Analog Devices, Hewlett Packard and Motorola.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
NASA and its partners are developing the Next Generation of Space Telescopes (NGST) to reveal distant structures of the universe in similar details at infrared wavelengths. The small cryogenic Deformable Mirror (DM) is an enabling technology for NGST scientific objectives. It allows eliminating the blurring of astronomical images due to turbulence in earth?s atmosphere. As a result ground base telescopes can create clear images as if they were in space. If successful, the proposed technique allows high speed deformation measurement/feedback, inspection, calibration and health monitoring of microfabricated deformable mirrors.
| PROPOSAL NUMBER: | 02- S1.03-9223 (For NASA Use Only - Chron: 022776 ) |
| SUBTOPIC TITLE: | Multifunctional Structure and Sensor Systems |
| PROPOSAL TITLE: | SensorLine: A Distributed Sensor System for Planetary Exploration |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Tethers Unlimited
19011 36th Ave W. Suite F
Lynnwood , WA 98036 - 5752
(425 ) 744 - 0400
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Jeffrey Slostad
slostad@tethers.com
19011 36th Ave W, Suite F
Lynnwood , WA 98036 - 5752
(425 ) 744 - 0400
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The SensorLine is a small, simple, low-cost system for deploying arrays of tethered microsensors for planetary, asteroid, and subsurface exploration. The SensorLine system integrates the microsensors into a thin, lightweight tether that provides both power and communication. In planetary exploration applications, the SensorLine?s novel deployment method permits these sensors to be distributed over long distances on a planetary surface, enabling planetary landers to obtain in situ thermal, chemical, seismic, and other measurements over a much wider area at a significantly lower cost, complexity, and technical risk than robotic rovers. In exploration of the lunar poles, the SensorLine could enable a probe placed on a sunlit hill to obtain in situ measurements of soil composition in a permanently shaded crater. In subsurface exploration applications such as the proposed Cryoscout experiment, the SensorLine system can provide power, communications, and distributed sensing capabilities for burrowing probes.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
The SensorLine System and its derivative technologies have numerous potential applications in the environmental, military, and consumer markets. In environmental testing and safety markets, this system will provide a low-cost means for rapidly deploying sensors into areas where it is unsafe or impossible for humans to collect measurements manually, such as in emergency response to chemical spills. In military markets, it will provide a means for troops in unsecured areas to rapidly deploy sensors to detect chemical or biological weapons and to detect intrusion by hostile forces.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
The SensorLine System will provide a low-cost, lightweight multifunctional sensor system that will enable NASA?s robotic missions to obtain in situ thermal, chemical, seismic, and other measurements in areas that currently are inaccessible or very difficult to reach with current robotic technologies. Enabled missions include lunar polar crater exploration, Mars surface and subsurface missions, and study of asteroid surfaces. The Lead Scientist for JPL's Geophysics and Planetary Geology division has expressed strong interest in the SensorLine technology for Mars exploration missions.
| PROPOSAL NUMBER: | 02- S1.03-9862 (For NASA Use Only - Chron: 022137 ) |
| SUBTOPIC TITLE: | Multifunctional Structure and Sensor Systems |
| PROPOSAL TITLE: | Radiation tolerant non volatile memory with Hard by Design Techniques |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
MeltroniX Inc.
4205 Ponderosa Drive
San Diego , CA 92123 - 1525
(858 ) 292 - 7000
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Dave Strobel
dstrobel@meltronix.com
4205 Ponderosa Drive
San Diego , CA 92123 - 1525
(858 ) 292 - 7000
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
MeltroniX Inc proposes to research and rapidly develop radiation hardened non volatile memory microelectronics, based on commercial ferroelectric technolgy. These FRAMs designed by Ramtron exhibit excellent radiation performance in the memory cell but are extrememly sensitive in the peripheral circuitry. We will apply hard-by-design techniques, with the support of Ramtron, to develop a rad hard version for space and military applications.In Phase II this design will be fabricated on one of Ramtron's licensees wafer fab. To address the high density needs, MeltroniX will design several MCM and stacked memory configurations using advanced packaging technology.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
A Radiation hardened high density non-volatile memory device is a key component for any commercial system in a radiation environment. These applications include commercial space platforms, both GEO and LEO. Telecommuncation satellites and sensing applications (NOAA)require this memory to store critical data and support on board data processing. Terrestial applications are nuclear power plants and research accelerators (Fermi Lab). A potentially large market are commercial aircraft avionics which are becoming increasingly sensitive to single event effects as commercial IC feature sizes and voltages decrease.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
Virtually all NASA space programs have a demand for dense, rad hard non-volatile memory. These applications range from shuttle, space station, earth sensing missions and deep space probes. The world's most common 1 megabit EEPROM just became obsolete, creating an immediate demand for radiation guaranteed non-volatile memory ICs. Some of the NASA missons which will benefit are Mars Surveyor missions, solar system exploration e.g. (Titan, Europa landers,comet nucleus return), New Discovery Program, and Living with a Star.
| PROPOSAL NUMBER: | 02- S1.04-7448 (For NASA Use Only - Chron: 024551 ) |
| SUBTOPIC TITLE: | Spacecraft Technology for Micro/Nanosats |
| PROPOSAL TITLE: | Reconfigurable Task Processor |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
PicoDyne Inc
1918 Forest Drive
Annapolis , MD 21401 - 4319
(410 ) 990 - 1890
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Brian Smith
Brian.Smith@PicoDyne.com
1918 Forest Drive
Annapolis , MD 21401 - 4319
(410 ) 990 - 1890
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The work proposed herein is the development of a Radiation Tolerant Processing node with built-in reconfigurable logic and standard interfaces.
Microelectronics for Nanosats require efficient architectures to make the best use of precious area, power, and mass allocations. PicoDyne is currently developing a Radiation Tolerant FPGA for space use, and separately, microcontrollers and processors. We propose combining the functions of a software-programmable processor with programmable hardware on a single chip. The FPGA architecture we are implementing as a stand-alone chip will be scaled down to allow insertion onto this Reconfigurable Task Processor(RTP). The same commercial design tools used for the larger device will be applicable here.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
This device is applicable to many consumer electronics, where microcontrollers and microprocessors control functionality. This ranges from hand-held games and PDAs, to cell-phones, to microwave ovens.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
Micro and Nanosat avionics, instruments, and communications circuitry. This is also applicable to standard spacecraft electronics, where the same benefits of smaller size and increased functionality are desired.
| PROPOSAL NUMBER: | 02- S1.04-8839 (For NASA Use Only - Chron: 023160 ) |
| SUBTOPIC TITLE: | Spacecraft Technology for Micro/Nanosats |
| PROPOSAL TITLE: | Ultra-small, low-cost Earth horizon sensor |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
SiWave, Inc.
400 E. Live Oak Avenue
Arcadia , CA 91006 - 5619
(626 ) 821 - 0570
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Tony Tang
t.tang@siwaveinc.com
400 E. Live Oak Avenue
Arcadia , CA 91006 - 5619
(626 ) 821 - 0570
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
SiWave proposes to develop a novel Earth horizon sensor that is made possible by recently developed MEMS (micro electro mechanical systems) processing techniques. SiWave?s MEMS devices enable a precise location of the Earth horizon with large angular range. A MEMS Earth horizon sensor, when compared with current state-of-the-art Earth horizon sensors provides for three orders-of-magnitude reductions in size, reduced power consumption, lower cost, and increased functionality and flexibility.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
The proposed horizon sensor has commercial applications in telecommunications, broadcasting, surveillance, Earth science satellites (such as weather), and high altitude aircraft and balloons. Markets for this technology include large satellite constellations, such as LEO One, Teledesic, ECCO, and E-Sat which alone total nearly 1000 sensors.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
NASA applications include navigation for next generation nano/micro-spacecraft, Earth orbiting satellites, and planetary missions to Mars and other solar system planets. The reduction in size and mass will reduce the cost of the spacecraft as well as the launch costs. Perhaps more importantly, the proposed horizon sensor will enable new science missions for NASA not previously possible due to cost, size, or mass constraints.
| PROPOSAL NUMBER: | 02- S1.04-9050 (For NASA Use Only - Chron: 022949 ) |
| SUBTOPIC TITLE: | Spacecraft Technology for Micro/Nanosats |
| PROPOSAL TITLE: | A Microsatellite Propulsion Module for Micro-spacecraft based on Gel-propellant |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
MICRO AEROSPACE SOLUTIONS, INC.
2280 Pineapple Avenue
Melbourne , FL 32935 - 6640
(321 ) 243 - 4633
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Donald Platt
dplatt@micro-a.net
2280 Pineapple Avenue
Melbourne , FL 32935 - 6640
(321 ) 243 - 4633
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
A gel propellant booster engine to provide delta-v orbital maneuvering to microspacecraft in the range of 25 to 100 kg is proposed. It offers significant innovation in that it has the same performance in terms of specific impulse (Isp) as a solid motor but with less mass and the ability to be throttled and restarted. It is also safe from detonation and will not leak like a liquid propellant system. Its propellants are also of low toxicity. It can be used to boost a microspacecraft into a final orbit for a number of NASA, commercial or military missions.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
Commercial microspacecraft missions for Earth resource observation, formation flying for communciations systems and large spacecraft health and status monitoring are enabled by this motor. Also, capbility to launch such payloads from the cargo bay of the shuttle orbiter is available due to the safety of the propellants.
Military missions include missile defense warning and propulsion for space-based interceptors.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
Microspacecraft with large propulsive capability enabled by this motor can perform NASA missions such as Earth's magnetic field or cometary nucleus and tail mapping armadas, observations of Earth's ocean temperature, air pollution and missions to asteroids. Also free-flying microspacecraft can be deployed from the shuttle or space station to perform microgravity missions such as biotechnology or materials processing and then return to the shuttle or station for retrieval.
| PROPOSAL NUMBER: | 02- S1.05-8338 (For NASA Use Only - Chron: 023661 ) |
| SUBTOPIC TITLE: | Spacecraft and Space Environment Interaction |
| PROPOSAL TITLE: | Electrically Conductive Thermal Control Coating |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
EIC Laboratories, Inc.
111 Downey Street
Norwood , MA 02062 - 2612
(781 ) 769 - 9450
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Trung Nguyen
Trunghn@eiclabs.com
111 Downey Street
Norwood , MA 02062 - 2612
(781 ) 769 - 9450
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The electrical conductivity of anodized aluminum thermal control coating will be enhanced by deposition of an electronically conductive metal oxide within the anodic oxide pores. The electrical charge that might otherwise accumulate on its surface in the ambient space plasma will leak off through the coating. This will prevent structural damage from sputtering of the alloy substrate at coating breaks, and minimize electrical noise. The improved coating is a nanocomposite, consisting of an optically transparent electronically conductive metal oxide deposited within the pores of the anodic alumina and on the coating surface. The filled pores result in low transverse resistivity and the surface coating provides efficient coupling between conductive pores and the space plasma. In Phase I, we will developed electrodeposition processes for nanocomposite coatings with resistivity and optical properties suitable for use as electrically conductive thermal control coatings. In Phase II the coating performance in space environment will be evaluated, process scale-up and engineering aspects of process development will be addressed, and basic studies in support of these efforts as well as to improve coating properties will be pursued.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
Conductive anodized coatings can be used as low cost thermal control coatings for commercial satellites, such as for communications, and will provide improved performance by reducing noise from arcing associated with accumulation and discharge of surface charge.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
Stable electrically conductive thermal control coatings are a core requirement of the NASA space program. For Space Station Freedom (SSF) the structure is grounded to the negative of the solar array and is about 140V below plasma potential. Discharge across discontinuities in the coating caused, for example, by impact with micrometeoroids, generates electromagnetic interference (EMI) and even sputtering of the underlying metal. To prevent EMI, grounding locations are distributed over a surface, which makes construction more complicated and expensive. With the development of an in-situ nanocomposite coating with high electronic coupling efficiency and good optical properties, the charge could leak off through the coating so that damage and interference from charge build-up would be prevented. Also, the nanocomposite coating will weight far less, cost less, and is much simpler to manufacture than alternative coatings such as inorganic paint or organic coating.
| PROPOSAL NUMBER: | 02- S1.05-9890 (For NASA Use Only - Chron: 022109 ) |
| SUBTOPIC TITLE: | Spacecraft and Space Environment Interaction |
| PROPOSAL TITLE: | SEE enhancement of advanced commercial microprocessors for Space Applications |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Space Micro
12872 Glen Circle Road
Poway , CA 92064 - 2029
(858 ) 487 - 9295
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
David R. Czajkowski
dczaj2000@yahoo.com
12872 Glen Circle Road
Poway , CA 92064 - 2029
(858 ) 487 - 9295
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Space Micro will research an innovative concept for enabling use of commercial microprocessors and system on a chip(SOC). The problem for these chips in space is Single event functional interrupt (SEFI),where the space radiation environment causes the chip to enter a hang or locked state. Our concept is for a SEFI reset chip which will automatically sense and restore funtionality via an intelligent sequence of instructions. This SEFI controller chip will be fabricated in a rad hard process and conceptually can be packaged with its companion processor IC.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
The same benefits as NASA missions apply to commercial space platforms, both for communications satellites and imaging. An average of 32 satellites per year are projected using over 15 complex ICs needing SEFI protection. Vastly increased performance over traditional rad hard processors enables cheaper systems plus enabling new capabilites. Programs such as Echostar, Spaceway, Galileo, Direct TV, XM Radio, and all GEO communication spacecraft will be users.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
Every NASA space mission uses microprocessors and complex ICs. There is a compelling reason to utilize the high performance COTS ICs, but single event effects such as SEFI dramatically limit their usage. The SEFI controller chip enables breakthrough computing performance without sacrificing reliability due to this severe radaition effect. Typical NASA satellite averages over 10 processors plus other complex devices for imaging. Both earth sensing, solar system, and deep space probe missions will benefit due to use of inexpensive COTS micrelectronics availability.
| PROPOSAL NUMBER: | 02- S1.06-8390 (For NASA Use Only - Chron: 023609 ) |
| SUBTOPIC TITLE: | UV and EUV Optics and Detectors |
| PROPOSAL TITLE: | Extreme Ultraviolet Interference Filters |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Luxel Corporation
P.O. Box 1879
Friday Harbor , WA 98250 - 1879
(360 ) 378 - 4137
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Chuck Gibson
chuck.gibson@luxel.com
P.O. Box 1879
Friday Harbor , WA 98250 - 1879
(360 ) 378 - 4137
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The proposed innovation combines advances in EUV multilayer coating technology with Luxel?s long established manufacturing techniques to produce thin foil EUV and X-ray transmission filters. Currently, EUV filter passbands are limited to those that can be created from combinations of the natural electronic absorptions of various elements. EUV Multilayer technology offers the design flexibility to build filters with much more optimized passbands. Multilayer techniques have been used for some time to fabricate normal incidence EUV mirrors. With adequate deposition control, similar materials can be used to fabricate multilayer foils and add the flexibility of interference technology to the suite of EUV filter designs. At Luxel, this is possible because of recent completion of a new deposition system that provides adequate control of individual layer thicknesses. These new multilayer foils will be transformed into EUV transmission filters using Luxel?s traditional filter manufacturing processes. The goal of Phase I will be to show feasibility by fabricating and delivering an evaluation filter that is relevant to a NASA science application. During Phase II, the new multilayer design capabilities will be integrated into Luxel?s manufacturing processes. Filters based on this new technology will provide exciting new options for EUV sensors and science.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
Outside the space science community, EUV filters find applications in fusion energy and other forms of plasma research, advanced microelectronic fabrication, photoemission microscopy, and laser research. All of these applications can benefit from technology advances that lead to enhanced filter performance. Of particular interest is the ability to enhance NOAA?s operational solar activity forecasts. These predictions of the impact of solar activity on plane earth depend on solar telescopes carried on the GOES weather satellites. These instruments currently utilize Luxel filters and it is clear that the proposed technology would improve these devices.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
Within NASA, EUV filters are a key enabling technology for solar physics and high energy astrophysics missions. They are needed to isolate diagnostic spectral features and to protect sensitive detectors from unwanted optical radiation. Enhanced EUV filter technology will have significant beneficial impacts on the scientific returns of future missions. Examples of these applications are found in the roadmaps of the various Space Science Themes.
| PROPOSAL NUMBER: | 02- S1.06-8796 (For NASA Use Only - Chron: 023203 ) |
| SUBTOPIC TITLE: | UV and EUV Optics and Detectors |
| PROPOSAL TITLE: | Order of magnitude enhancement of AlGaN UV photo-detector efficiency |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Zaubertek, Inc
12565 Research Parkway Suite 300
Orlando , FL 32826 - 3283
(407 ) 882 - 0224
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Stephen H. Kleckley
skleckley@zaubertek.com
12565 Research Parkway Suite 300
Orlando , FL 32826 - 3283
(407 ) 882 - 0224
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
This SBIR phase I project will substantially improve III-Nitride photovoltaic detector quantum efficiency by real-time control of fundamental material properties. Specifically, minority carrier diffusion length in (Al)GaN photodetectors will be manipulated to achieve up to 10-fold increase in photodetector efficiency in the range 20-300 nm. The innovation builds on recent discovery of increased minority-carrier diffusion length and lifetime following brief forward-bias electron injection into p-(Al)GaN in p-n junctions or Schottky barriers. Consistent long-term improvements were observed in the optoelectronic properties, including spectral and temporal photoresponse. Increased diffusion length improves minority-carrier collection and eliminates "dead space", where carriers recombine before collection. The practical significance of the innovation is a lasting (days), remarkable (10-fold) quantum-efficiency enhancement for (Al)GaN-based photovoltaic detectors achieved through short time (seconds) electron injection.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
UV photo-detector applications that may be impacted by the proposed innovation, include UV Curing and Drying Control, Arc Detection, Phototherapy Control, Spectroscopy, Combustion Monitoring, Solar Irradiance Measurement, Sterilization and Purification Control, Medical Engineering, Dermatology, Output check of UV-lamps and gas burner flames, Measurement and control of ecological parameters, Control of solar radiation, UV water purification facilities, Deep-UV laser-induced fluorescence detector for naturally fluorescent molecules, UV-based transceiver for covert non-line-of-sight communicaitons.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
The Zaubertek product concept consists of a proprietary biasing method and electronics package for commercial (Al)GaN UV photodetectors, which have a cutoff wavelengths near 300 nm. This innovation will significantly impact NASA relevant UV photodetector applications in the 20-300 nm range, such as remote imaging, spectroscopy, and polarimetry of the Sun-Earth environment.
| PROPOSAL NUMBER: | 02- S1.06-8899 (For NASA Use Only - Chron: 023100 ) |
| SUBTOPIC TITLE: | UV and EUV Optics and Detectors |
| PROPOSAL TITLE: | High Quality, Low-Scatter SiC Optics Suitable for Space-based UV & EUV Applicati |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
SSG Inc
65 Jonspin Road
Wilmington , MA 01887 - 1020
(978 ) 694 - 9991
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Jay Schwartz
jschwartz@ssginc.com
65 Jonspin Road
Wilmington , MA 01887 - 1020
(978 ) 694 - 9991
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
SSG Precision Optronics proposes the development of a novel optical manufacturing process that will allow the production of state-of-the-art Silicon Carbide (SiC) optics. The work proposed combines three different manufacturing technologies, a slip cast SiC mirror forming process and low temperature CVD SiC coating process, which have been developed by SSG, and Computer Controlled Optical Surfacing technology (CCOS) which has been developed by Tinsley, a subsidiary of SSG. The combination of these technologies will provide SiC optics with state-of-the-art surface figures (low frequency and mid-frequency errors will both be addressed) and low-scatter surface finishes. SiC optics offer a number of critical advantages for space-based optical systems. The superior material properties of SiC provide a high degree of lightweighting (70% - 90% of beryllium) and a superior thermal stability (1.5x ? 2.5x better than ULE). The manufacturing process proposed will allow the technical advantages associated with SiC materials to be realized, providing the capability to produce imaging mirrors which are capable of providing excellent accuracies (<0.01 waves RMS), low micro-roughness (< 10 Angstroms RMS), and very low areal densities (~10 kg/m2 at an aperture of 1 meter) while maintaining the thermal stability required for space-based imaging applications. The quality and micro-roughness of these optics will be good enough to address the stressing needs associated with visible, UV and EUV wavebands. In our Phase I work the process development proposed will be verified by the production of a lightweighted SiC aspheric mirror to a set of stressing figure and finish requirements.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
The work proposed will enable the production of low-scatter SiC aspheric optics which have commercial applications ranging from high energy x-ray optics to thermally stable aspherics for EUV lithography tools.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
The proposed optical manufacturing process will address high precision, low-scatter, state-of-theart optical system requirements for NASA. These applications include deployable optical systems such as NGST, EUV waveband applications like KRONOS and high quality imaing missions like LDCM.
| PROPOSAL NUMBER: | 02- S1.06-8922 (For NASA Use Only - Chron: 023077 ) |
| SUBTOPIC TITLE: | UV and EUV Optics and Detectors |
| PROPOSAL TITLE: | Pixelized Device Control |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
QorTek Inc
4121 Jacks Hollow Road
Williamsport , PA 17702 - 9539
(570 ) 745 - 3555
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Daniel Thomasson
dan@qortek.com
4121 Jacks Hollow Road
Williamsport , PA 17702 - 9539
(570 ) 745 - 3555
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
We are proposing a new technological solution to complex figure control architectures for Sun-Earth ultraviolet (UV) and extreme ultraviolet meter sized optical instruments and detectors. Retention of low mass distribution for large aperture optics means eliminating heavy complex wiring bus and controls for UV or EUV optics and detector instruments with large numbers of active adjustment or actuation mechanisms. Precise metering of charge in or out of array device elements accurately and with reduced mass and complexity is a further requirement. The proposed solution would enable both distributed control and distributed power distribution to a large array of contiguous devices to maintain figure accuracy through launch orbit. The new system introduces a high level of risk reduction in developing and assembling complex instruments and optics for future NASA small system (<4 meter) instrument and optical packages.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
The advent of MEMS and microdevices is leading to smaller and denser device arrays for many high-end production systems. The ability to provide low cost, thin and lightweight control and power feed to such systems improves their commercial viability to many (optical and non-optical) systems and products. The proposed technology has application as a low cost approach to extend and transfer adaptive optics technology to commercial telescopes and to cost sensitive non-commercial optical (military) systems.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
The new system introduces a high level of risk reduction in developing and assembling complex instruments and optics for future NASA small system (<4 meter) instrument and optical packages. This not only encompasses Sun-Earth UV and near UV missions but can be directly applied to critical secondary optics for large optical spacecraft for TPF, MIDEX, Explorer and others. The ability to control non-planar (but contiguous) arrays of even small devices such as MEMS with the thin lightweight pixelized device control technology makes is attractive for a number of deployable space systems such as Mars rover, sample collection and thermally compensated habitats.
| PROPOSAL NUMBER: | 02- S2.01-8727 (For NASA Use Only - Chron: 023272 ) |
| SUBTOPIC TITLE: | Sensors and Detectors for Astrophysics |
| PROPOSAL TITLE: | A Novel Transition Edge High Tc Superconducting Bolometer Using CCVD thin films |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
MicroCoating Technologies
5315 Peachtree Industrial Boulevard
Atlanta , GA 30341 - 2107
(678 ) 287 - 3940
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Yibin Xue
yxue@microcoating.com
5315 Peachtree Industrial Boulevard
Atlanta , GA 30341 - 2107
(678 ) 287 - 3940
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
For the proposed Phase I project, MicroCoating Technologies, Inc. (MCT) will explore the feasibility of fabricating a two-layer thin film composite on single crystal substrates that is composed of an epitaxial superconducting BKBO-class thin film of superior, sharp temperature transition edge and a ?super-?doped epitaxial thin film of the same material compound with large absorption of far-infrared wavelengths. This enabling materials platform is made possible by MCT's proprietary non-vacuum Combustion Chemical Vapor Deposition (CCVD) technology, which permits the deposition of complex epitaxial thin films and variation in material composition. Thus absorber and detector are made in the same process sequentially for the high Tc transition edge bolometers.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
Far-IR detectors can be used for spectroscopy with a Fourier transform spectrometer. Since the existing detectors offer only moderate performance in linearity and responding speed, an improvement in detector technology will greatly increase the precision and convenience of spectroscopic measurement. With the rapid development in the photonics industry, for which the targeted marketplace is estimated at $23 billion/year in 2005, the far-IR spectroscopic measurement devices will have large markets in the near future.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
Future instruments for NASA?s sensors and detectors for astrophysics will require increasingly sophisticated electromagnetic radiation detecting and sensing technology. The the radiation of cosmic microwave background (CMB), the remnant from the creation of the universe about 15 billion year ago, has been shifted to longer and longer wavelengths and its weak anisotropy was discovered recently. It is believed that this temperature anisotropy (varying by > 130 mK) contains information about the very beginning of the universe as well as about the parameters that govern its evolution. Therefore, only bolometric detectors with high sensitivity for infrared, especially far-infrared and submillimeter wavelengths, make it possible to precisely measure the CMB temperature anisotropy as to map the temperature anisotropy over the sky and develop cosmological models to study the beginning and evolution of the universe.
| PROPOSAL NUMBER: | 02- S2.02-7897 (For NASA Use Only - Chron: 024102 ) |
| SUBTOPIC TITLE: | Terrestrial and Extra-Terrestrial Balloons and Aerobots |
| PROPOSAL TITLE: | Lift Gas Cracker |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Pioneer Astronautics
11111 W. 8th Ave., Unit A
Lakewood , CO 80215 - 5516
(303 ) 980 - 0890
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Robert Zubrin
zubrin@aol.com
11111 W. 8th Ave., Unit A
Lakewood , CO 80215 - 5516
(303 ) 980 - 0890
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The Lift Gas Cracker (LGC) is new method for producing lift gas for balloons for both terrestrial and extra-terrestrial applications, eliminating the need for heavy, bulky gas bottles. The LGC produces a lift gas from the cracking of methanol, an easily obtained, easily stored liquid, to make either the hydrogen/carbon monoxide cracking product or a hydrogen-enriched product by using membrane separation. Combustion of about 10% of the methanol provides sufficient energy to crack the remainder. The LGC product gas can be converted back into methanol, allowing a balloon to maintain altitude during the daytime without having to vent lift gas. The methanol can then be converted back into lift gas at night to maintain altitude without dropping ballast. Thus, long duration balloon flights could be extended a factor of 20 or more compared to conventional means.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
In addition to supplying lift gas in remote locations, such as during military operations or worldwide weather balloon launch campaigns, LGC in the membrane separation mode could supply cheap, easily generated hydrogen for multiple fuel cell applications, including automobiles and remote power supply stations.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
NASA applications would include ultra-long duration balloon flights for earth observation, greatly extending the time aloft. Other applications would be the production of lift gas in remote areas, such as the Arctic and the Antarctic, where conventional gas bottles are difficult and costly to obtain. LGC could also be used for long-duration balloon flights on Mars and Venus, enabling much more time for data acquisition compared to conventional technologies.
| PROPOSAL NUMBER: | 02- S2.03-8238 (For NASA Use Only - Chron: 023761 ) |
| SUBTOPIC TITLE: | Multiple Coordinated Observatories |
| PROPOSAL TITLE: | MEMS ELECTROCHEMICAL POWER SUPPLY FOR MINIATURE SATELLITES |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
TPL Inc
3921 Academy Parkway North, NE
Albuquerque , NM 87109 - 4416
(505 ) 342 - 4471
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Charles D. E. Lakeman Ph.D
clakeman@tplinc.com
3921 Academy Parkway North, NE
Albuquerque , NM 87109 - 4416
(505 ) 344 - 6744
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
TPL proposes to develop a novel MEMS power supply employing volumetric lithium ion microbatteries and micro-supercapacitors for miniature satellites. This configuration will provide high energy density and rechargeability for longevity and high specific power capability for handling both steady state and transient high power demands in an electrochemical micro-power system. The proposed design is unique because it embodies volumetric energy storage in cells that are ~1mm3 in extent. Existing MEMS microbatteries are area/planar designs that require large footprints (tens of mm2) to achieve useful capacities. The proposed space power system is area conforming and can be integrated with minimum volume systems. No existing satellite power system can make this claim.
These innovative devices will exploit TPL?s novel soft lithography microcontact printing (?CP) fabrication process to construct components that have both high power and high energy densities in an electrochemical device.
The PI has pioneered the use of soft lithography ?CP as a novel microfabrication process for non-silicon materials for advanced packaging and has excellent capabilities to achieve the project objectives. The effort will build on ongoing relationships with space and defense OEMs to deliver a product suitable for immediate insertion into space-based defense systems.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
In the future, miniaturized power supplies will be incorporated into emerging microsystem technologies for use in medical, industrial, and defense applications to improve patient outcomes, improve control over industrial processes for improved efficiency, and for numerous discrete sensor applications. The potential impact of microsystems on daily life promises to be very exciting. New functionality is being integrated into chip structures enabling the chip to think, sense, act and communicate. These microscopic systems are finding application in surgical instruments, sensors for biological, medical, environmental and pollution monitoring, for storm tracking, and for disposable games.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
The proposed volumetric power supply will enhance the viability and capability of not only miniaturized satellites, but also numerous airborne and space based-vehicles where weight and size are of prime importance. Such platforms could include high altitude balloons, and even air-borne smart-dust sensors. The proposed small form factor devices, which weigh less than a gram, will be critical to realizing an integrated, small volume, small footprint power system. Furthermore, realization of small form-factor batteries that can be included in implantable or ingestible devices will enable remote monitoring and treatment of humans in space.
| PROPOSAL NUMBER: | 02- S2.04-8132 (For NASA Use Only - Chron: 023867 ) |
| SUBTOPIC TITLE: | Thermal Control and Management |
| PROPOSAL TITLE: | Lightweight Cryogenic Radiator |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Energy Science Laboratories, Inc.
6888 Nancy Ridge Drive
San Diego , CA 92121 - 2232
(858 ) 552 - 2039
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Christopher L. Seaman
cseaman@esli.com
6888 Nancy Ridge Drive
San Diego , CA 92121 - 2232
(858 ) 552 - 2034
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
This SBIR Phase 1 project shall develop lightweight materials with high emissivity for radiative cooling down to 30 K, as needed by NASA for advanced spacecraft including the NGST mission. The materials are based on carbon fibers in an engineered configuration that creates blackbody features as well as millimeter wave antenna absorber features. The carbon fiber approach is fundamentally lightweight, structurally robust, thermally conductive, and permits a broad range of configurations.
Phase 1 will assess requirements and analyze the concept radiator. Selected emitter materials configurations will be fabricated and tested for model validation. Lightweight cryogenic radiator designs and Phase 2 development will be reported.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
The approach has potential to generate a range of novel optical materials with applications in thermal control, far infrared and millimeter wave astronomy, and microwave communications hardware. Specific applications are
* Improved absorbers for thermal , radiometric, and optical instruments operating in IR, FIR, MMW and MW bands
* Absorber coatings for instruments such as bolometers, MMW radiometers, and cryogenic calorimeters
* Stray light suppression for improved signal-to-noise in IR and MMW astronomy
30?200 K radiators for sensor cooling in surveillance satellites
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
* 30 K Cryogenic radiators for passive cooling of instrument module on NGST
* 30?200 K radiators for sensor cooling in remote sensing satellites
* Stray light suppression for improved signal-to-noise in IR and MMW astronomy
| PROPOSAL NUMBER: | 02- S2.04-9575 (For NASA Use Only - Chron: 022424 ) |
| SUBTOPIC TITLE: | Thermal Control and Management |
| PROPOSAL TITLE: | Helium Loop Heat Pipe for Large Area Cryocooling |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
TTH Research
14625 Baltimore Avenue, #445
Laurel , MD 20743 - 3827
(301 ) 641 - 2954
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Triem Hoang
thoang@tthresearch.com
14625 Baltimore Avenue, #445
Laurel , MD 20743 - 3827
(301 ) 350 - 5092
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
To take full advantage of the space environment, Far Infrared (FIR)/Submillimeter (SMM) interferometers require cold mirrors (~4 K) and detectors (~0.1 K or colder). The collecting mirrors for the proposed FIR/SMM missions are large. The most difficult challenge will be the ~4K cryocooling of the entire telescope structure. Given long duration of the missions, stored cryogens do not present an attractive option. Hence, an active cryocooling system capable of removing 10-100mW at ~4K is absolutely essential for the mission success. The cryocooling system must provide continuous operation and not cause significant vibrations of the optical components. In addition, the cooling power will have to be distributed over large mirror surfaces.
To meet the challenging cryocooling requirements of the FIR/SMM missions mentioned above, TTH Research proposes the development of an advanced capillary pumped cryo-cooling transport system operating at ~4K. Despite the fact that the CPL/LHP technology has reached a high level of maturity, the proposed research effort will demand a host of technology innovations that do not exist at the present time. Among them are the use of Helium as the working fluid in CPLs/LHPs and cooling over large areas at cryogenic temperatures.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
With a simple design and proven fabrication techniques, the large area LHP cooling loop is probably more adapted to the electronic cooling applications. In this case, it uses working fluids like water, methanol, or butane to transport and spread out the electronics waste heat over a larger area. Small diameter transport lines can be embedded in or even etched onto a Silicon wafer to form an integrated micro-chip and cooling system. A few examples of its potential usage are: heat spreaders for solid state transistors with medium to moderately high heat fluxes (20-50W/cm2) and heat transport devices embedded in printed circuit boards.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
If the proposed He-LHP is successful as anticipated, then it will be the first-ever CPL or LHP to provide a passive cooling transport in the liquid Helium temperature range (~4K). But beyond that, the He-LHP will enable the exploitation of the FIR/SMM astronomy to explore the early universe, formation of galaxies, stars, and planets. FIR/SMM collecting mirrors are large. The entire telescope including the mirrors need to be cooled to ~4K to minimize background noise. The cryocooling system must be light in weight, integrate easily into the telescope, and not cause significant vibrations to the optical components. Furthermore, it will likely have to be flexible and deployable. The He-LHP will meet all aforementioned requirements offering a robust passive ~4K cryocooling transport over large areas.
| PROPOSAL NUMBER: | 02- S2.04-9700 (For NASA Use Only - Chron: 022299 ) |
| SUBTOPIC TITLE: | Thermal Control and Management |
| PROPOSAL TITLE: | Intelligent Variable Emittance Panels Using New, ?True? Solid Electrolyte |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Ashwin-Ushas Corp Inc
206 Ticonderoga Blvd
Freehold , NJ 07728 - 3028
(732 ) 462 - 1270
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Prasanna Chandrasekhar
ashwinusha@aol.com
206 Ticonderoga Blvd
Freehold , NJ 07728 - 3028
(732 ) 462 - 1270
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
This firm has, in ongoing work in collaboration with the Air Force, NASA and JPL, developed a unique Variable Emittance technology based on the electrochromism of unique Conducting Polymers. This comprises thin (< 0.5 mm), flexible, lightweight (0.16 g/cm^2), variable area (0.5 cm^2 to 0.5 m^2), very low cost flat panels. Delta Emittance (DE) of 0.33 in space-qualified devices, and 0.53 in vacuum-durable unsealed devices, has been demonstrated. All space durability tests e.g. thermal vacuum, gamma-radiation and solar wind have been passed. A 90 cm2 panel and Controller are scheduled to fly on NASA?s ST5 microsatellite mission in 2004. A key technical barrier of this technology has however been the need to encapsulate and hermetically seal devices in CsI windows, due to a semi-solid electrolyte that does not function when completely desiccated. This causes the DE of > 0.53 in unsealed devices to fall to < 0.35 in sealed devices. The use of a just-discovered, truly solid, room temperature molten salt electrolyte compatible with our electrochromic system will permit the use of unsealed devices, allowing DE of 0.53. Intelligent design, with embedded sensors reading Emittance directly, and coatings reducing Solar Absorptance to < 0.2, are also planned.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
With proven Delta Emittance > 0.5, this technology may displace mechanical louvers and loop heat pipes in the > 100 spacecraft/year the US alone launches, each with several m^2 of thermal control area. Terrestrial military uses include IR camouflage countermeasures for the entire armed forces (air/land craft, soldiers), a multi-billion dollar market this firm is actively pursuing. Commercial uses include displays/billboards.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
With proven Delta Emittance > 0.5, this technology may displace mechanical louvers and loop heat pipes in the > 100 spacecraft/year the US alone launches, each with several m^2 of thermal control area. This new Variable Emittance technology is thus applicable to all spacecraft launched by NASA, but especially micro- and nano- spacecraft where extant technologies may not work, and for niches like space-based radars.
| PROPOSAL NUMBER: | 02- S2.05-7486 (For NASA Use Only - Chron: 024513 ) |
| SUBTOPIC TITLE: | Optical Technologies |
| PROPOSAL TITLE: | Development of Ultra-smooth Diamond Tooling for Machining Lightweight Mirrors |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
DIAMOND MATERIALS INC.
120 Centennial Ave.
Piscataway , NJ 08854 - 3908
(732 ) 885 - 0805
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Dr. Oleg A. Voronov
ovoronov@aol.com
120 Centennial Ave.
Piscataway , NJ 08854 - 3908
(732 ) 885 - 0805
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
DMI has produced functionally-graded nanostructured diamond materials that are able to machine lightweight silicon carbide optics with high precision and with minimal wear of the cutting edge. The goal of this project is to increase the tool life of a diamond cutter and to develop a technique for ultra-smooth polishing of the cutting edge as well as ultra-smooth machining of curved silicon carbide mirrors. It will enable the optics industry to enhance the performance of large size telescopes and interferometers. In Phase I, we will design a special diamond cutting tool for silicon carbide, manufacture samples of such cutters, and conduct research on mirror machining. In Phase II, ultra-smooth diamond tooling and fabrication techniques will be developed. In Phase III, we will machine ultra-smooth silicon carbide mirrors and other lightweight parts by DMI-developed diamond tools according to NASA?s needs.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
Developed ultra-smooth diamond tooling and silicon carbide mirror techniques will also benefit the machining of other optical materials and increase the performance of optical devices.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
The developed fabrication techniques for diamond cutters and for optical parts machining will enable industry to increase optical performance, structural performance of large space telescope and interferometers and discover new details about the Universe.
| PROPOSAL NUMBER: | 02- S2.05-7639 (For NASA Use Only - Chron: 024360 ) |
| SUBTOPIC TITLE: | Optical Technologies |
| PROPOSAL TITLE: | Multiform SiC Structures for Lightweight Space-Based Mirrors |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Ceramic Composites, Inc.
133 Defense Highway, Suite 212
Annapolis , MD 21401 - 8907
(410 ) 224 - 3710
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Chris Duston
cduston@techassess.com
133 Defense Highway, Suite 212
Annapolis , MD 21401 - 8907
(410 ) 224 - 3710
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Ceramic Composites, Inc. will demonstrate the feasibility of constructing a lightweight, affordable and dimensionally stable SiC mirrors using an innovative process. The structure will combine rigorous thermal control as well as structural strength and stiffness. The proposed technology demonstration promises to produce a net shape SiC article at a lower cost that present SiC manufacturing technologies. The present state of the art SiC manufacturing technologies requires extensive high risk machining as the final processing step. The proposed innovative processing technology eliminates the need for any machining as a final processing. The proprietary SiC processing technology will create a net shape SiC article and accomplishes this task by a Chemical Vapor Infiltration and Densification Process.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
This approach is primarily focused at demonstrating a very lightweight DACS system for propellants but could in the future also be applied to monopropellants and solid DACS systems.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
NASA Space Based Mirrors
| PROPOSAL NUMBER: | 02- S2.05-7969 (For NASA Use Only - Chron: 024030 ) |
| SUBTOPIC TITLE: | Optical Technologies |
| PROPOSAL TITLE: | Lightweight Active Nanolaminate Mirror with Wireless Shape Control |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Xinetics Inc.
37 MacArthur Ave
Devens , MA 01432 - 5022
(978 ) 772 - 0352
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Maureen Mulvihill
mmulvihill@xinetics.com
37 MacArthur Ave
Devens , MA 01432 - 5022
(978 ) 772 - 0352
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
For future NASA Cosmic Journey missions to study the Structure and Evolution of the Universe, telescope mirror apertures from 10 to 100m are desired. To achieve the large apertures, standard telescope designs containing heavy optical components that are time consuming and expensive to fabricate are obsolete. The current thrust is the use of polymer membranes and PVDF piezoelectric films that offer the potential to build mirrors in excess of 10m with areal densities below 1-kg/m2. However, these programs offer a challenge to design, materials and optical engineers to achieve a mirror that holds the optical surface within the required tolerances. The membrane approach is subject to thermally induced distortions, does not provide the necessary in-plane stiffness to mitigate distortions, and still requires wires/cables for actuator addressing. Xinetics proposes the Lightweight Active Nanolaminate Mirror with E-beam Shape Control. The thick-film nanolaminate has a greater in-plane stiffness than the polymer membranes and thus can maintain greater optical tolerances. The active discrete actuator laminate will be driven by an e-beam flux; thus making it wireless. This technology will enable a new class of optical structures for space that are lightweight, dimensionally stable, resistant to space environmental effects, inexpensive and rapidly manufactured.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
>From the proposed technology, two routes to commercialization will be pursued. The first is the wireless micropositioners and the second is light weight optical systems. The wireless micropositioners can be used when lightweight or restricted spaces are necessary. Since the wires and power electronic are unnecessary, no space is required to house them. The wireless actuators can be also used to control the optical surface on large aperture lightweight mirrors for surveillance telescopes enabling large diameter apertures reaching 100m. The surveillance community needs ultra-lightweight, large aperture optical systems that will provide low scatter, diffraction limited imaging in a space environment. Telescopes designed as proposed will be low cost, rapid to manufacture and stowable.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
The proposed large active mirror technology is potentially the most innovative single advance that the space telescope community has seen since its inception in the early seventies. A wireless active mirror controlled by an electron beam has never been built. NASA will have technology that can be used on many Structures and Evolution of the Universe and Origins missions where large aperture 1- to 100m observatories while maintaing low areal densities 1.0 kg/m2. Active mirrors controlled using e-beam matrix addressing completely eliminates the need for individual addressing wires and cables, eliminates the need for high power electronics, and mitigates the power dissipation associated with electrical control. This technology will reduce the mirror weight while still providing low scatter, diffraction limited imaging in a space environment.
| PROPOSAL NUMBER: | 02- S2.05-8886 (For NASA Use Only - Chron: 023113 ) |
| SUBTOPIC TITLE: | Optical Technologies |
| PROPOSAL TITLE: | Lightweight High Spatial Frequency Active Mirror Using E Beam Control |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Xinetics Inc.
37 MacArthur Ave
Devens , MA 01432 - 5022
(978 ) 772 - 0352
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Michael Roche
mroche@xinetics.com
37 MacArthur Ave
Devens , MA 01432 - 5022
(978 ) 772 - 0352
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
NASA?s Structure and Evolution of the Universe program outlines several missions, such as Terrestrial Planet Finder (TPF) and the Space Interferometry Mission (SIM), that will require the construction and deployment of arrays of telescopes, each potentially 100 to 1000m in diameter, dictating areal densities less than 1kg/m2. Gossamer optics can meet this challenge of affordable, large, lightweight optics. However, due to the difficulties inherent in deploying large scale, thin optics, Gossamer optical systems will require significant technological advances in active wavefront correction. A breakthrough in density, complexity reduction, reliability, and reduced cost per actuator is required for Gossamer systems corrected with adaptive optics. The revolutionary Adaptive Tertiary concept proposed here involves the use of modules, single units of active ceramic with integral electrodes that contain an array of actuator posts with spacings ranging from 1mm to 5mm. The segmented deformable mirror, with up to 349 mirror actuators at 2.5mm spacing in each hexagonal segment, will allow not only the individual correction of errors in any section of the primary optic, but potentially allows a simpler, lighter and less expensive primary to be employed.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
In addition to the benefits of hexagonal modules for Gossamer optic system wavefront correction, a segmented deformable mirror would have applications in high energy laser beam cleanup and propagation. The hexagonal array spacing also offers several advantages in conventional adaptive optics applications. The hexagonal packing provides a higher actuator density in a given aperture size and access to influence functions that are not possible with square arrays. Other applications would be in the ophthalmic area. High density mirror arrays could be installed on Fundus cameras to aid ophthalmologists in diagnosing retinal disease and other problems which can be diagnosed through the study of the capillary structure in the eye. There would be applications in laser eye surgery by improving the beam quality of lasers used as scalpels.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
The Adaptive Tertiary mirror would allow the correction of wavefront errors in Gossamer optics, which are critical to the development of 100 meter and larger diameter telescopes in space. The adaptive tertiary potentially alleviates some of the tight manufacturing, assembly, and deployment tolerances that are anticipated in working with ultralightweight optics, reducing the complexity of the system and therefore the risk and cost. The adaptive tertiary concept can be applied whether the primary mirror is segmented, as in the case with NGST, or the more typical vision of a continuous gossamer membrane. Each segment of the adaptive tertiary, with independent tip-tilt functionality, can correct both the large errors anticipated during deployment, or the higher spatial frequency errors compensated in a conventional deformable mirror.
| PROPOSAL NUMBER: | 02- S2.05-8888 (For NASA Use Only - Chron: 023111 ) |
| SUBTOPIC TITLE: | Optical Technologies |
| PROPOSAL TITLE: | Computer Controlled Optical Surfacing of Bare Beryllium Aspheric Optics |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
SSG Inc
65 Jonspin Road
Wilmington , MA 01887 - 1020
(510 ) 222 - 8110
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
John Kincade
jkincade@ssginc.com
4040 Lakeside Drive
Richmond , CA 94806 - 1963
(978 ) 694 - 9991
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Tinsley Laboratories, a subsidiary of SSG Inc., has developed a deterministic Computer Controlled Optical Surfacing (CCOS) process. Over the last 25 years, this process has demonstrated the capability to produce state-of-the-art aspheric optics, including extensive work with bare Beryllium aspheric reflectors. The objective of the work proposed here is to optimize and improve this process for bare Beryllium optics, with a goal of reducing the aspheric optical polishing time by > 2x. Increased efficiency, and reduced costs, are key drivers as next generation astronomical and earth observing applications are being driven to larger and larger telescope apertures. Beryllium optics are a key technology for these large aperture system designs, due to the material?s high specific stiffness and aggressively lightweighting capabilities. The process optimization that we propose will make Beryllium optics more cost effective for these applications, in this way allowing system designs to benefit from the superior bulk material properties associated with the material. In the Phase I work proposed the CCOS process optimization will be demonstrated by the polishing of a number of bare Beryllium witness samples.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
The development of a time/cost effective process for producing bare Be optics has a number of commercial and military applications. Cost and time savings will enable the introduction of Be optics into smaller aperture Military systems for space-based EO sensor missions and tactical Be scan mirrors. Commercial applications include high speed scanning systems where Be superior specific stiffness and lightweighting capability make Be the material of choice.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
The reduction on time/cost facilitated by the processing changes proposed here will be critical for a number of future space based applications. The primary benefit will be to large aperture deployable telescope concepts such as NGST. These missions require Beryllium (from a weight standpoint) but need to find cost/time effective ways to produce state-of-the-art Be optics.
| PROPOSAL NUMBER: | 02- S2.05-9836 (For NASA Use Only - Chron: 022163 ) |
| SUBTOPIC TITLE: | Optical Technologies |
| PROPOSAL TITLE: | Polymeric Broadband Polarizing Beamsplitters |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Cornerstone Research Group Inc
2750 Indian Ripple Rd.
Dayton , OH 45440 - 3638
(937 ) 320 - 1877
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Alison Thomas
thomasam@crgrp.net
2750 Indian Ripple Rd.
Dayton , OH 45440 - 3638
(937 ) 320 - 1877
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The development of high-performance, broadband, polarizing beamsplitters is paramount to the evolution of future optical and communications systems that require the use of polarized light. Conventional polarizing beamsplitters are limited by small fields of view and narrow spectral regions. Cornerstone Research Group, Inc. (CRG) proposes to develop broadband, polarizing beamsplitters based on a proprietary combination of nematic and chiral liquid crystals materials. The unique materials and processing allow the films to be transferred from the substrate on which they are fabricated and to either remain free-standing or to be applied to another surface as a coating. In addition, by altering the composition of the materials, the wavelength regime can be tuned. The bandwidth can be increased by introducing a pitch gradient throughout the film thickness.
The proposed technology will directly address NASA's requirement for novel optical coatings for use in the EUV, UV, visible, IR and far IR for filters, beamsplitters, polarizers and reflectors. Subtopic S2.05 calls for broadband polarizing beamsplitters, which this proposal specifically addresses.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
The technology presented in this proposal has many applications in the field of optics. The reflective films could be utilized as reflectors for imaging applications, such as HMD visor coatings. The films also have applications in such areas as communications systems and liquid crystal projectors. By integrating two films integrated together, high-performance filters could be fabricated for laser eye protection as well as filters for delicate, high-cost optical devices, such as infrared detectors. In addition, the films are conformable to complex surfaces. Therefore, they could be laminated onto optical surfaces and used as polarized coatings or filters.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
The primary application for the chiral liquid crystal polymer films discussed in this proposal is broadband beamsplitting. The ability to split an incident beam into right- and left-circularly polarized beams (or S-and P-polarized beams) could, therefore, be utilized anywhere where polarization preservation is needed or desired, such as polarizing beamsplitters for shared-aperture laser radar applications.
The unique ability to make CLCP membranes opens up the possibility of utilizing such reflectors for lightweight, space-based mirrors. By integrating two membranes of opposite handedness, a high-performance reflector can be fabricated that reflects in excess of 95% of the incident light. Because the materials are polymerized, they possess an inherent structural integrity and a slight degree of shape memory characteristic of polymeric materials. Additionally, with such high reflectivities over a broad wavelength range, it is conceivable that the reflectors could utilized as a lightweight propulsion sail.
| PROPOSAL NUMBER: | 02- S2.06-8776 (For NASA Use Only - Chron: 023223 ) |
| SUBTOPIC TITLE: | Advanced Photon Detectors |
| PROPOSAL TITLE: | Gamma Detector Modular Assemblies for EXIST |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
AGUILA TECHNOLOGIES INC.
310 VIA VERA CRUZ, SUITE 107
SAN MARCOS , CA 92069 - 2631
(760 ) 752 - 1199
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
M. Albert Capote
macapote@aguilatech.com
310 VIA VERA CRUZ, SUITE 107
SAN MARCOS , CA 92069 - 2631
(760 ) 752 - 1192
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The Energetic X-ray Imaging Survey Telescope (EXIST) is a proposed mission that aims to detect faint high energy X-ray sources in the energy range 10 - 600 keV. The concept for EXIST relies on an X-ray telescope imaging the entire sky each 95 min orbit. The core of the X-ray imaging telescope comprises approximately 8 square meters of pixilated Cd-Zn-Te (CZT) detectors, a technical feat never before attempted. This enormous array requires development of a new packaging technology for CZT detector arrays, one that allows detectors to be abutted together into large arrays of CZT tiles, with minimal dead space in between detectors. Also required is a technology that can produce these detectors with a high interconnection yield, not currently achieved with indium bump technologies. We propose an innovative technique to assemble CZT X-ray sensors avoiding conventional direct indium bump hybridization used today. The novel scheme incorporates commercial off-the-shelf flip-chip and multichip module technologies, combined with new flip-chip bonding materials and proprietary processes developed at Aguila under previous NASA sponsorship. This will result in novel detector modules containing fully-integrated readout electronics that can be implemented into a large-array motherboard.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
The commercial market for CZT pixel detectors is in medical imaging, environmental monitoring, anti-terrorism and industrial processing. Once the CZT material technology improves to where large area arrays are readily producible, the market for using this technology will offer many opportunities. Furthermore, there is a great need for high interconnect densities in flip chip electronic assemblies with many applications in automotive products and wireless communications.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
Lack of access to good packaging technology is hindering NASA's ability to develop large area CZT focal plane detectors for hard x-ray missions on balloons and in space such as InFOCuS, Constellation-X, EXIST and HSI. The ideas presented here may also be solutions to the array hybridization challenges for cryogenic arrays with calorimeters and bolometers which have been proposed for Constellation-X and various sub-mm and IR instruments.
| PROPOSAL NUMBER: | 02- S3.02-7576 (For NASA Use Only - Chron: 024423 ) |
| SUBTOPIC TITLE: | Precision Constellations for Interferometry |
| PROPOSAL TITLE: | Autonomous Resource Allocation and Task Management for Multi-Spacecraft Formatio |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Scientific Systems Co Inc
500 West Cummings Park, Suite 3000
Woburn , MA 01801 - 6580
(781 ) 933 - 5355
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Ravi Prasanth / Raman K Mehra
prasanth@ssci.com
500 West Cummings Park Suite 3000
Woburn , MA 01801 - 6580
(781 ) 933 - 5355
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Autonomous multiple spacecraft represent a critical enabling technology for future space missions. Currently, significant pre-flight planning and ground tasking are needed to design operational sequences for single-spacecraft missions. Multiple-spacecraft missions (especially formation flying tasks) dramatically increase the complexity of planning, sequencing and tasking, rendering them possibly intractable for current mission design approaches. The overall goal of this effort is to develop an Autonomous Dynamic Formation Planner (ADFP) applicable to multi-spacecraft formation flying tasks, using systematic methodologies for model-based prediction, optimal resource allocation and task/activity sequencing and control. During the proposed effort, SSC will develop and demonstrate an ADFP system for selected multiple-spacecraft formation-flying tasks, using representative constraints for onboard and formation resources. ADFP technology will provide a general framework for implementation of onboard autonomy for future multiple spacecraft missions, which is both resource and constraint-aware. Our project team includes subcontract support from the Research Institute for Advanced Computer Sciences, RIACS (a division of the Universities Space Research Association), and the Colorado Space Grant College (University of Colorado, Boulder).
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
The proposed Autonomous Dynamic Formation Planner technology is generically applicable to other DOD and DARPA multiple spacecraft programs. AFRL is planning to operate autonomous satellite constellations for future strategic objectives in space-based remote sensing, global intelligence and C3I networks. (For instance, TechSat 21 will demonstrate on-orbit autonomous satellite constellation technologies.) As these programs become operational, the commercial market for multiple and distributed spacecraft onboard autonomy will become necessary as OEM technology suppliers. ADFP will be developed and marketed in concert with established aerospace platform and avionics suppliers.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
The proposed Autonomous Dynamic Formation Planner technology addresses an important need for spacecraft autonomy for future multiple-spacecraft missions. Future NASA missions which will directly benefit from this technology include multi-spacecraft constellations and Formation Flying space platforms within the NASA Space Science Enterprise (Origins, Sun-Earth and SEU themes), including the Terrestrial Planet Finder (TPF), Constellation-X, Magnetospheric Constellation (DRACO), Laser Interferometry Space Antenna (LISA) and others.Applications within the Earth Science Enterprise which propose distributed spacecraft constellations are also applicable.
| PROPOSAL NUMBER: | 02- S3.02-8020 (For NASA Use Only - Chron: 023979 ) |
| SUBTOPIC TITLE: | Precision Constellations for Interferometry |
| PROPOSAL TITLE: | Magnetically Enhanced Vacuum Arc Thruster |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Alameda Applied Sciences Corporation
2235 Polvorosa Avenue, Suite 230
San Leandro , CA 94577 - 2249
(510 ) 483 - 4156
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Jochen Schein
schein@aasc.net
2235 Polvorosa Avenue, Suite 230
San Leandro , CA 94577 - 2249
(510 ) 483 - 4156
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Alameda Applied Sciences Corporation proposes to develop a new type of electric propulsion device dubbed the Magnetically Enhanced Vacuum Arc Thruster (MVAT). This thruster is itself a variant on the Vacuum Arc Thruster that has been demonstrated via a recently concluded Phase I SBIR contracts from NASA. The VAT was verified to be a throttleable low mass (~150g) high efficiency (~10% measured), high Isp (1000-3000s) electric propulsion device that can be remotely adjusted to deliver individual impulse bits from 0.25?Ns to 50?Ns with repetition rates varying from 1?1000 Hz while all the time providing an Isp of >1000s. The MVAT proposed here is a pulsed device that uses the magnetic field produced by the inductor in the PPU to increase the ISP even further and hence improve thrust and efficiency. The pulsed magnetic field will also be used to confine expanding plasma plume thereby limiting contamination effects. The MVAT can provide a wide range of impulse bits and a variety of repetition rates, which could satisfy coarse and ultra-fine control demands integrated in the same simple system, while offering low mass (<300g including the PPU), simplicity (no moving parts), high efficiency (?15%) and low cost of manufacturing.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
This technology might also find other applications in research and industry, for example as a source of heavy ion beams for heavy ion fusion reactors, for materials surface characterization, and for thin film optical coatings. Application examples include coatings for energy efficient window, DWDMs, aircraft and automotive transparencies and solar cell surfaces.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
The primary application of the specific electric propulsion thruster to be developed in the proposed work will be for optical interferometry mission. However, beyond this immediate application, the thruster could find use for larger or smaller spacecraft used in optical communication.
| PROPOSAL NUMBER: | 02- S3.02-9356 (For NASA Use Only - Chron: 022643 ) |
| SUBTOPIC TITLE: | Precision Constellations for Interferometry |
| PROPOSAL TITLE: | Precision Ultrasensitive Micromotion Interferometer |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
PHYSICAL OPTICS CORPORATION
20600 Gramercy Place, Building 100
Torrance , CA 90501 - 1821
(310 ) 320 - 3088
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Russell Kurtz, Ph.D.
sutama@poc.com
20600 Gramercy Place, Building 100
Torrance , CA 90501 - 1821
(310 ) 320 - 3088
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
NASA needs hardware technologies to maintain hyper-precision spacecraft constellations at a level that will make separated spacecraft optical interferometry practical. To address this need, Physical Optics Corporation (POC) proposes to develop and test a novel Precision Ultrasensitive Micromotion Interferometer (PUMI) system based on the company's unique phase conjugate micromotion detection technology, which will measure motion at an accuracy three orders of magnitude greater than current techniques such as Doppler lidar. The illumination will cycle at 4 Hz for each micron per second of motion with respect to the other spacecraft. These cycles are detected to determine spacecraft micromotion. Phase conjugation eliminates optical path difference problems, and phase distortions that are due to any intervening media. In Phase I POC will determine the requirements and expected performance of phase conjugate micromotion detection (PCMD), identify design tradeoffs, and produce a proof-of-principle system to demonstrate the feasibility of the proposed PUMI approach for NASA applications. In Phase II the design will be optimized for the intended use, information processing will be added, and an optimized PCMD system applicable to PUMI will be demonstrated.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
The two main commercial markets for the PUMI are communication satellites and interferometry. The PUMI will ensure accurate relative positioning of satellites, which is necessary for phased array communication systems. In interferometery, the PUMI will enable drift correction during long exposures.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
The two main NASA applications for the PUMI are astronomy and satellite positioning. For space-based astronomy, the PUMI will enable satellite station-keeping with respect to each other, with an extremely high degree of precision. This is critical for the installation of very long baseline astronomical systems, and useful for all multiple-satellite positioning.
| PROPOSAL NUMBER: | 02- S3.03-8209 (For NASA Use Only - Chron: 023790 ) |
| SUBTOPIC TITLE: | Astronomical Instrumentation |
| PROPOSAL TITLE: | Omnidirectional Narrow Band Pass, band Pass and Band Blocking IR Filters |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Lake Shore Cryotronics Inc
575 McCorkle Blvd.
Westerville , OH 43082 - 8699
(614 ) 891 - 2243
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Vladimir Kochergin
vkochergin@lakeshore.com
575 McCorkle Blvd.
Westerville , OH 43082 - 8699
(614 ) 891 - 2243
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
This Small Business Innovation Research Phase I project will address the feasibility of narrow band pass, band pass and band blocking optical filters, with very wide acceptance angles, made from macroporous silicon. In currently available filters based on interference in a multilayer stack, the transmission spectra depend on angle of incidence. Omnidirectional filters are clearly needed to simplify optical alignment and allow simpler utilization of non-collimated light beams. A new type of optical filter is proposed as a basis for such filters. The proposed optical filter will be made of a three-dimensional, periodic structure in monocrystalline silicon. In Phase I, the feasibility of such filters will be demonstrated by fabricating a filter structure and measuring its physical and optical properties. The feasibility study will concentrate on the near infrared spectral range, although similar principles can be applied out to the mid-IR. In Phase II, filters for different wavelength ranges will be fabricated and their performance will be optimized to meet the designed bandwidth, insertion losses, and out-of-band transmission. Phase III will involve product design and fabrication of physically robust filter structures to meet customers? requirements, and will include the necessary marketing and sales investments.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
Filters are one of the most ubiquitous optical components. The proposed technique for making narrow band pass, band pass and band blocking IR optical filters will serve commercial needs in imaging, chemical and environmental monitoring, fiber optic and free space communications, defense and other industrial and research applications.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
The proposed technique for making narrow band pass, band pass and band blocking IR optical filters will serve NASA's needs in astronomy, imaging, space and earth spectroscopy, chemical and environmental monitoring, and other research applications.
| PROPOSAL NUMBER: | 02- S3.03-9297 (For NASA Use Only - Chron: 022702 ) |
| SUBTOPIC TITLE: | Astronomical Instrumentation |
| PROPOSAL TITLE: | Control Instrumentation for Advanced Adiabatic Demagnetization Refrigerators |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Lake Shore Cryotronics Inc
575 McCorkle Blvd.
Westerville , OH 43082 - 8699
(614 ) 891 - 2243
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Joe Yeager
jyeager@lakeshore.com
575 McCorkle Blvd.
Westerville , OH 43082 - 8699
(614 ) 891 - 8843
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Driven by research and development of advanced photon detectors--which require temperatures below 100mK-- there is considerable research into new ADR designs and techniques. These AADR have many advantages over other technique to achieve ultra-low temperature and there is considerable commercial potential. We propose to design control instrumentation for advanced adiabatic demagnetization refrigerators (AADR). The first step is to develop a thermal and electrical model of the basic operating parameters of various AADR. The next step is to split the design into hardware development and software development. Hardware development will take the results of the thermal-electrical model and design a circuit. This involves trade studies of different methods to measure and control temperature, magnets and heat switches. The software design focuses on optimizing the control of the multiple ADR stages and their timing sequence. This work will result in a control program and hardware design, which will be integrated together in Phase II
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
An AADR, and the Continuous ADR especially, is a disruptive technology that is a more efficient method to reach temperatures below 100mK than existing dilution refrigerators. With the control instrumentation that we will develop, the AADR will be able to meet a wide range of applications. This includes physics and material science studies at temperature below 100mK. There is also an industrial application of semiconductor material analysis. Using advanced x-ray detectors, cooled to 100mK, semiconductors can be probed for material defects and impurities. A reliable control instrument?taking the AADR from research labs to factory floor?is required to open this market.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
The major application is for better ground testing of advanced photon detectors for NASA. A complete control system for Advanced Adiabatic Demagnetization will make for more efficient testing of detectors and detector components. Additionally, there is a broader application for any material testing at temperature below 100mK. A controller for an AADR is an enabling technology that extends the utility of ADR beyond detector testing.
| PROPOSAL NUMBER: | 02- S3.03-9508 (For NASA Use Only - Chron: 022491 ) |
| SUBTOPIC TITLE: | Astronomical Instrumentation |
| PROPOSAL TITLE: | A 32x32 CTIA readout multiplexer for far IR detector arrays |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
TechnoScience Corporation
P.O. Box 60658
Palo Alto , CA 94306 - 0658
(650 ) 852 - 9932
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Jam Farhoomand
jfarhoomand@mail.arc.nasa.gov
P.O. Box 60658
Palo Alto , CA 94306 - 0658
(650 ) 852 - 9932
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
We propose to investigate the feasibility of developing a 32x32 multi-gain readout multiplexer with the following key design features:
1- Optimized for use with infrared detector arrays requiring low bias levels, such as Ge:Ga far IR photoconductors. The unit-cell design will maintain constant bias across the detector during the integration and, thereby, will eliminate non-linearity and detector debiasing. The design will also minimize the channel-to-channel DC variation which improves the bias uniformity across all pixels of the array.
2- Capable of operation at cryogenic temperatures down to 1.5K. Advanced monolithic cryo-CMOS technology will guarantee deep cryogenic operation with minimal impact on noise performance.
3- Offers the potential of being directly hybridized to IR detector arrays using indium-bump technology.
No two-dimensional readout multiplexer with these features is currently available or has been developed. This effort fits well within the scope of the SBIR Subtopic S3.03 and will be a benefit to many large and small NASA projects including NGST, SOFIA, and Astrobiology missions.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
The basic product resulting from the proposed project will be a 32x32, multi-gain CTIA readout multiplexer suitable for far IR detector arrays. Such a device can be interfaced with a 2D detector array that is assembled from linear arrays or hybridized directly to a 2D array designed for this purpose. Future products could include expansion of this design to larger formats and can be customized to have added features specifically required for a particular instrument. Being the critical components of many instruments in NASA's space program, the principle market for these readouts will be NASA. Aerospace companies -- such as Raytheon, Boeing, Rockwell, and Ball Aerospace -- that either directly participate in the space program or independently manufacture infrared detector arrays are our secondary customers. Other customers would be science groups at universities and national labs engaged in developing science instruments for observations at ground-based observatories and for basic research.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
Potential applications for NASA includes: space instruments developed under Origins Program, science instruments for SOFIA, upcoming projects under Astrobiology Program, balloon-borne instruments for atmospheric research, and laboratory science-instruments.
| PROPOSAL NUMBER: | 02- S3.03-9519 (For NASA Use Only - Chron: 022480 ) |
| SUBTOPIC TITLE: | Astronomical Instrumentation |
| PROPOSAL TITLE: | Microwave-pumped GaAs far infrared photoconductor |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
TechnoScience Corporation
P.O. Box 60658
Palo Alto , CA 94306 - 0658
(650 ) 852 - 9932
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Jam Farhoomand
jfarhoomand@mail.arc.nasa.gov
P.O. Box 60658
Palo Alto , CA 94306 - 0658
(650 ) 852 - 9932
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
This proposal introduces an innovative concept which significantly enhances the performance of a far-infrared GaAs photoconductor. This method employs a microwave source, in the range of 90 to 120 GHz, to assist the photoionization process by pumping the infrared-generated electrons from the excited states to the continuum. Since the microwave photons are low in energy, they are not available to directly ionize the ground state of the shallow donors. Therefore, the microwave pumping process is not expected to generate additional leakage current and the associated noise. This will allow us to cool the detector as low as necessary to reduce the thermal leakage current and improve the detector's noise performance. The proposed concept is not limited to GaAs and may be applied in a broader scope. Since the excited state response of a photoconductor lies at lower frequencies (longer wavelengths), an important use of this method would be to extend the detector's long-wavelength response. For a photoconductor, such as Ge:Ga, whose excited state response is non-existent at its optimum operating temperature due to insufficient thermal energy, microwave pumping can provide the additional energy and essentially extend its long-wavelength response.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
The basic product resulting from the proposed project will be a single-element (discrete) GaAs detector. Such a device can be used as a stand-alone detector or can be incorporated in a modular form in a number of different instruments such as radiometers and heterodyne receivers. Future products could include large format arrays suitable for high sensitivity instruments, preferential detection, interferometers, infrared spectrographs, etc. Being the critical components of many instruments in NASA's space program, the principle market for these detectors will be NASA. Aerospace companies -- such as Raytheon, Boeing, Rockwell, and Ball Aerospace -- that either directly participate in the space program or independently manufacture infrared detector arrays are our secondary customers. Other customers would be science groups at universities and national labs engaged in developing science instruments for observations at ground-based observatories and for basic research.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
Potential applications for NASA includes: space instruments developed under Origins Program, science instruments for SOFIA, upcoming projects under Astrobiology Program, balloon-borne instruments for atmospheric research, and laboratory science-instruments.
| PROPOSAL NUMBER: | 02- S3.03-9542 (For NASA Use Only - Chron: 022457 ) |
| SUBTOPIC TITLE: | Astronomical Instrumentation |
| PROPOSAL TITLE: | Superconducting Digital Multiplexers for Sensor Arrays |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
HYPRES Inc
175 Clearbrook Rd
Elmsford , NY 10523 - 1109
(914 ) 592 - 1190
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Alan M. Kadin
kadin@hypres.com
175 Clearbrook Rd
Elmsford , NY 10523 - 1109
(914 ) 592 - 1190
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Large arrays of cryogenic microbolometers and other cryogenic detectors will be used for infrared imaging in future space observatories. If the signal from the sensors is amplified, multiplexed, and digitized using superconducting electronics, then this data can be efficiently read out to room temperature with a minimum of noise and thermal load. HYPRES will develop an integrated system based on SQUID amplifiers, a high-resolution analog-to-digital converter (ADC) based on RSFQ (rapid single flux quantum) logic, and a clocked RSFQ multiplexer. The ADC and SQUIDs have already been developed for other projects, so this work will focus on demonstrating the perfomance of the digital multiplexer, starting with a 3x3 prototype for Phase I.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
The ability to multiplex, digitize, and perform further signal processing with a low-power cryogenic readout chip will be invaluable to the cryogenic detector community. It may also have applications in wireless communications and radar. The flexibility of the architecture to adapt to user-specified requirements of speed and resolution should make this system adaptable to a diverse range of commercial and military applications, as well as those of NASA and others in the astrophysics community.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
Improved cryogenic readout electronics is needed for cryogenic detector arrays in proposed space observatories. Low-power A/D converters and digital signal processing that can be located near these detectors will enhance the effiency and performance of these imaging systems.
| PROPOSAL NUMBER: | 02- S3.04-7955 (For NASA Use Only - Chron: 024044 ) |
| SUBTOPIC TITLE: | High Contrast Astrophysical Imaging |
| PROPOSAL TITLE: | High Actuated Primary Mirror to Enable Prime Focus Coronograph Telescope |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Xinetics Inc.
37 MacArthur Ave
Devens , MA 01432 - 5022
(978 ) 772 - 0352
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Roland Plante
rplante@xinetics.com
37 MacArthur Ave
Devens , MA 01432 - 5022
(978 ) 772 - 0352
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The Highly Actuated Primary Mirror is an evolutionary advance that will form the basis of coronagraphic telescopes such as the Terrestrial Planet Finder to direct image planets planets orbiting nearby stars. Used in a Prime Focus coronagraph, it completely eliminates optics between the Primary and coronagraphic occulter. This mirror has the stroke and spatial frequency bandwidth to completely control the mid spatial frequency scatter from the primary mirror, giving high contrast performance. It features a lightweight mirror structure fabricated from silicon carbide, which is compatible with both ambient and cryogenic environments. Actuators with angstrom level precision are used for mirror shape control and optical replication is used to form the mirror surface. The mirror will advance primary mirror technology in terms of channel count (941 to 4,317), spatial resolution (100-mm to 10-mm), and dimensional stability (l/10 to l/100). From a NASA perspective, the highly actuated design is applicable to both earth observing and space imaging surveillance. From a commercial perspective, it enables the cost-effective, volume production of high precision aspheres, which will be in big demand for 0.1-mm lithography systems. Rapid response replication of the optical surface, the mirror substrate, and the control actuators form a new paradigm in mirror manufacture.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
The Highly Actuated Primary Mirror will enable the volume production of precision aspheres using programmable optical replication techniques. Instead of being used as a precision optic, the Highly Actuated Primary Mirror will be used as a programmable agile mandrel onto which nanolaminate foils will be deposited to replicate the optical surface. The optical foils can be made with varying optical prescriptions by using the shape control function of the agile mandrel. Recent advances in nanolaminate materials have resulted in low scatter, stress free foils having optical quality comparable to glass. Using a fugitive layer the optical foils can then be removed from the mandrel and bonded to a strong back. The result is an optic without the cost of aspheric polishing. The will form the basis for the cost-effective, volume production of high precision aspheres, which will be in big demand for 0.1-mm lithography systems.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
The Terrestrial Planet Finder is beginning the design of a Coronagraphic Telescope capable of directly imaging planets orbiting nearby stars. Such a coronagraph depends on suppression of scattered light to achieve high contrast performance. The primary source of scattered light is mid-spatial frequency figure errors on the optics of the coronagraphic telescope. Previous approaches used small, highly actuated deformable mirrors located at a pupil conjugate to the primary mirror. Phase aberrations of the primary are compensated, but require several intervening optics. Since the intervening optics are not conjugate to the PM or DM, errors result at the telescope exit pupil, degrading coronagraphic sensitivity. A Highly Actuated Primary Mirror can be used in a Prime Focus coronagraph that completely eliminates optics between the Primary and coronagraphic occulter. This mirror has the stroke and spatial frequency bandwidth to completely control the mid spatial frequency scatter from the PM, giving high contrast performance.
| PROPOSAL NUMBER: | 02- S4.01-7704 (For NASA Use Only - Chron: 024295 ) |
| SUBTOPIC TITLE: | Science Instruments for Conducting Solar System Exploration |
| PROPOSAL TITLE: | Vertical Interconnects for 3D CMOS Imager |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
NanoSciences Corporation/NanoSystems Inc
115 Hurley Road, Building #1B
Oxford , CT 06478 - 1037
(203 ) 267 - 4440
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Charles P. Beetz
cbeetz@nanosciences.com
115 Hurley Road, Building #1B
Oxford , CT 06478 - 1037
(203 ) 267 - 4440
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
NanoSciences proposes to develop a vertical interconnect structure base on a novel high rate through wafer micromachining process for application to a novel massively parallel high-performance smart 3D CMOS imaging technology under development at JPL. The smart imager will exhibit ultra high contrast handling capacity and high speed readout for defense and reconnaissance applications with special emphasis on anti-blinding, fast tracking, and high speed object identification and acquisition. Large format 2D focal plane arrays have been built in both CCD and CMOS technology although imaging performance continues to improve, it comes at the cost of reduced dynamic range, reduced speed, and increased power dissipation. Reduced speed is of particular concern for space based tracking, reconnaissance and robotic applications, that require faster than real-time imaging for high-speed closed loop control systems. The above-mentioned problems can be solved by processing data closer to the imager sense elements employing vertically interconnected structures. Vertical stacking solves the problem of interconnectivity leading to the development of smart focal planes without sacrificing imaging performance. The development of a reliable vertical interconnection presents a significant technical challenge, if successful, it will revolutionize new imager architectures and circuits, enabling smart imager development.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
Commercial applications of the vertical interconnection technology include generic interface chips for integrating CMOS circuitry to MEMS based sensor technology. Such applications include; precision mounts for MEMS based inertial sensors that will enable direct orthogonal mounting of sensors, compact 3D-integrated millimeter wave circuits for military and civilian telecommunications applications as well as novel vertical readout structures for staring focal plane array detectors, fluidic components for chemical analysis, medical diagnostic equipment and inkjet printheads.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
NASA applications of the vertical interconnect technology include a massively parallel high-performance smart 3D CMOS imaging technology under development at JPL, generic interconnection technology for vertical space conserving interfaces between CMOS circuitry and MEMS based sensor technology used for example in inertial guidance navigation systems, integrating micromachined instrumentation to control and communication electronics. The proposed vertical interconnect will enable space conserving interfaces critical for space missions.
| PROPOSAL NUMBER: | 02- S4.01-7884 ( |