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NASA 2007 SBIR Phase 2 Solicitation

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)
Andrea Hoyt Haight
adherenttech@comcast.net
9621 Camino del Sol NE
Albuquerque,  NM 87111-1522
(505) 346-1685

Expected Technology Readiness Level (TRL) upon completion of contract: 5 to 6

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Aging and durability of aircraft in both the military and civilian sectors are becoming major issues as the existing fleet continues to age. Additionally, the increased use of composite structures in the civilian fleet, such as in the Boeing 787 Dreamliner and the Airbus A380, make the understanding and/or improvement of composite durability, particularly durability of repairs, even more critical. Several areas have been identified as targets for improvement in composite aircraft repair. These include the development of rapid, low temperature repair methods and associated materials as well as development of the quality of repairs when they are made. Adhesion of bonded repairs is one area that needs to be addressed. In the Phase I program Adherent Technologies, Inc. demonstrated a novel moisture-resistant primer system for use in repairs of standard carbon/epoxy composites used in many subsonic aircraft. Our proprietary chemistry comprised of a reactive coupling agent and a carrier resin compatible with standard aerospace epoxy resins bonds directly to the prepared aircraft composite surface while retaining residual functionality that can be cured directly into the matrix of the repair leading to a covalently bound repair, thereby strengthening the repair interface. An increase in bond strength for primed samples relative to unprimed control specimens was noted; the improvement in the fracture toughness of the bonds was particularly of note. The Phase II effort will focus on the optimization of these primer systems and associated application and activation methods. Water-based systems will also be developed and demonstrated.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
This system is being designed to support the need for improvements in durability of repairs for subsonic aircraft.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The proposed primer technology, which will improve the quality of composite bonded repairs as well as composite bonding in general, will used throughout the aerospace composite materials market as well as having potential applications in civilian infrastructure (e.g. CFRP bridge decks and the like). The civilian aircraft market is projected to be a particularly significant consumer.

TECHNOLOGY TAXONOMY MAPPING
Airframe
Composites

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
ThinKom Solutions, Inc.
3825 Del Amo Blvd., Suite 200
Torrance, CA 90503-2168
(310) 371-5486

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
William Henderson
billh@thin-kom.com
3825 Del Amo Blvd., Suite 200
Torrance,  CA 90503-2168
(310) 802-4517

Expected Technology Readiness Level (TRL) upon completion of contract: 8 to 9

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The proposed Phase II project includes the design, fabrication, and testing of a fully-functional 320 element X-band antenna which will serve dual-roles as both the proof-of-design (POD) and the proof-of-manufacturability (POM) prototype of ThinKom's innovative low-cost electronically scanned array (ESA) antenna technology. Simultaneously emphasizing affordability and performance, this antenna subsystem will uniquely enable near-term wide deployment of airborne hazard detection and avoidance radar systems with greatly enhanced performance and functionality relative to currently fielded systems. This technology comprises a proprietary integrated "quasi-monolithic" feed/phase-shifter/radiator topology exclusively realized using low-risk low-cost flight-proven, manufacturing materials, components, and processes. In addition, this architecture is ideally-suited for simplified compact integration with a highly reliable, low-cost, low-power consumption beam steering controller (BSC) utilizing pre-existing COTS components. The expected RF loss through the feed, phase shifter, and radiator of this low-cost/high-performance topology is less than 1 dB at X-Band, which is no greater than (and in most cases less than) that of "traditional" (much) higher cost ESA implementations. Building upon the Phase I preliminary antenna subsystem design and highly successful phase-shifter risk-reduction verification testing accomplished in Phase I, the Phase II program will directly demonstrate and prove both the performance and revolutionary cost reduction potential of this new "no compromise" ESA architecture and technology. In addition to the targeted aviation hazard detection radar/sensor application, other benefiting applications would include ground mapping, atmospheric studies, and launch range surveillance radars and sensors as well as communication applications for which an agile highly directional beam is required such as high-gain LOS and NLOS (SATCOM) Data Links.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The technology is useful for a broad variety of radar and communication applications that are of interest to NASA. In addition to aviation hazard detection, other relevant radar applications include ground mapping, atmospheric studies, and launch range surveillance.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The technology is useful for a broad variety of commerical radar and communication applications similar to those useful to NASA. In addition to aviation hazard detection, other relevant applications include RF communication, as the technology is potentially useful whenever a highly directional steerable beam is required. This includes many distinct "on-the-move" communication systems.

TECHNOLOGY TAXONOMY MAPPING
Airport Infrastructure and Safety
Guidance, Navigation, and Control
RF

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Optimal Synthesis, Inc.
95 First Street, Suite 240
Los Altos, CA 94022-2777
(650) 210-8282

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
P. K. Menon
menon@optisyn.com
95 First Street, Suite 240
Los Altos,  CA 94022-2777
(650) 559-8585

Expected Technology Readiness Level (TRL) upon completion of contract: 6

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The problem of estimating the aerodynamic models for flight control of damaged aircraft using an innovative differential vortex lattice method tightly coupled with an extended Kalman filter was investigated during the Phase I research. The approach exploited prior knowledge about the undamaged aircraft to reduce the order of the estimation problem. Probing maneuvers were designed to improve the observability of the system dynamics. The derived performance model was then be used to determine the aircraft flight envelope, performance parameters and the maneuver limits. The estimated data can be used as the basis for designing safe landing guidance laws for damaged aircraft. Phase II research will refine the algorithms developed during the Phase I research and create a standalone software implementation. Structural dynamic computations and control power estimation will be included in the software. Operation of the software will then be demonstrated at near real-time speeds. All the algorithms and software developed under the proposed research will be supplied to NASA at the end of Phase II. Human-in-the-loop simulations and flight test evaluation of the system will be undertaken during the Phase III work.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The proposed research will contribute towards NASA's Integrated Resilient Aircraft Control program.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The proposed research will provide the information essential for designing safe landing guidance laws for damaged aircraft. Algorithms and software developed under the proposed SBIR work will contribute towards improving the safety of future commercial, military and general aviation aircraft operations.

TECHNOLOGY TAXONOMY MAPPING
Intelligence
Controls-Structures Interaction (CSI)
Guidance, Navigation, and Control
On-Board Computing and Data Management
Pilot Support Systems
Autonomous Reasoning/Artificial Intelligence
Computer System Architectures
Expert Systems

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Michigan Aerospace Corporation
1777 Highland Drive, Suite B
Ann Arbor, MI 48108-2285
(734) 975-8777

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
John Trenkle
jtrenkle@michiganaerospace.com
1777 Highland Drive, Suite B
Ann Arbor,  MI 48108-2285
(734) 975-8777

Expected Technology Readiness Level (TRL) upon completion of contract: 5 to 6

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
In a successful Phase 1 project for NASA SBIR topic A1.05, "Data Mining for Integrated Vehicle Health Management," Michigan Aerospace Corporation (MAC) demonstrated its SPADE anomaly detection software to key personnel in NASA's Intelligent Systems Division (ISD) and with data from our partners at Boeing, SpaceX and GMV Space Systems. The feedback from these demonstrations was used to establish future development directions for Phase 2. Phase 2 will consist of three major efforts: 1) the design and implementation of the Taiga system, a next-generation enhancement of the SPADE software, 2) an investigation into combining complementary functionality of Taiga with existing code at ISD including the Inductive Modeling System, Mariana and others, and 3) the implementation of a prototype automatic parallelizer, in cooperation with subcontractor Optillel Solutions, for a subset of C++ useful for hardware acceleration of machine learning applications. The scope of the interaction with researchers in NASA ISD will be to explore the relationships between IMS and Taiga and gauge benefits such a Data Handling, Feature Reduction, Visualization and Explainability. We will also investigate heterogeneous ensemble methods by analyzing the Mariana system. Optillel's C++ Parallelizer will reduce MAC's development costs for parallelizing C++ code for multi-core chips and clusters. This effort will build on Optillel's existing body of work that supports graphical programming languages, and will extend their technology to the analysis and parallelization of C++ code. Both the Taiga system and Optillel's prototype have significant commercialization potential in industries as diverse as Chemical, Pharmaceutical, Manufacturing and Aerospace.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
MAC's Taiga data mining platform has a variety of important applications at NASA. The need for next-generation data mining tools to aid in lifecycle support for aircraft, spacecraft, satellites and ships is widely recognized, as exemplified by the scope of the solicitation for this program. The Intelligent Data Understanding (IDU) Group at NASA Ames Research Center is a prime candidate for collaboration in developing and using Taiga. Through productive Phase 1 discussions with IDU, MAC determined that the most relevant area for Taiga at IDU is Discovery and Systems Health (DaSH), whose mission includes monitoring, data analysis, prognostics, diagnostics, and diagnostic decision aids. In this arena NASA will benefit from MAC's experience with Threat Assessment for satellites with the Air Force Research Lab. The Taiga system can be directly applied to problems being examined at DaSH, and it is highly complementary to existing software already being used and tested within IDU, including but not limited to Dave Iverson's Inductive Monitoring System (IMS) and Pat Castle's Mariana. There is important synergy between Tiaga and these packages; with IMS Taiga complements feature reduction, cluster visualization, explainability, fusion and data synthesis for validation, and with Mariana it complements data fusion and parallelization.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Products for discovering novel events and detecting anomalies are quickly becoming indispensable for the proper operation and maintenance of the complex systems employed by modern industry, medical providers and the military. Factories, health monitors, aircraft and other vehicles regularly produce hundreds or thousands of channels of telemetry in real time, which must be monitored for possible indications of failure. These data resources present an extremely diverse market opportunity for Taiga, which will detect events of interest in high-volume data streams of large dimensionality, independent of the raw data source. This diversity is confirmed by the variety of customers who have already expressed interest in MAC's anomaly detection software, including Dow Chemical, Boeing and Space-X. The "Write Once Deploy Anywhere" (WODA) component of Taiga represents another major commercial opportunity. The emerging trend in hardware from single to multi-core systems is exposing a fast-growing requirement in the software industry for intelligent development tools to aid programmers in converting existing non-parallel algorithms to parallel algorithms. After Phase 2, Optillel will be positioned to license its technology for C++ on any Integrated Development Environment and leverage an enormous pre-existing market. MAC will benefit by being the first partner to use Optillel's WODA technology and reduce development costs for multicore-enabled anomaly detection products.

TECHNOLOGY TAXONOMY MAPPING
Operations Concepts and Requirements
Telemetry, Tracking and Control
Autonomous Control and Monitoring
Autonomous Reasoning/Artificial Intelligence
Portable Data Acquisition or Analysis Tools

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Picometrix, LLC
2925 Boardwalk Drive
Ann Arbor, MI 48104-6765
(734) 864-5600

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
David Zimdars
dzimdars@picometrix.com
2925 Boardwalk Drive
Ann Arbor,  MI 48104-6765
(734) 864-5639

Expected Technology Readiness Level (TRL) upon completion of contract: 6 to 7

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
In this Phase 2 project, we propose to develop, construct, and deliver to NASA a computed axial tomography time-domain terahertz (CT TD-THz) non destructive evaluation (NDE) system which will provide true three dimensional images of aerospace polymer, ceramic, and composite structures. Traditional time domain terahertz reflection tomographic imaging captures only a single view of an object, generating images of laminar structure similar to an ultrasound "B-Scan". This reflection tomographic imaging is limited, however, in revealing only the laminar structure which presents a clear specular reflection from each interface. Furthermore, traditional time domain terahertz reflection tomographic imaging has substantial difficulty in determining the layer index of refraction an absorption properties without ambiguity. In Phase 1 we demonstrated the feasibility TD-THz axial computed tomography to generate cross-sectional slices of aerospace materials. This method acquires not one view, but many radial axial views, generating a sinogram which can be used to reconstruct images using a derivative of standard X-Ray CT filtered back-projection. The sinogram can be generated by the transmission absorbance, transmission time of flight, and, in principle, reflection measurements. The reconstructed TD-THz CT images are 3D maps of the absorption coefficients and/or the index of refraction of the subsurface material.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The proposed TD-THz CT NDE imager will be valuable in characterizing the aging and durability of aircraft and spacecraft materials and components. Material examples include Kevlar, Zylon, and other non-conductive polymer matrix composites. Example NDE applications where these materials are used include inspection of soft shell fan containment, thermal protection systems, and composite overwrap pressure vessels. These materials are in systems in which the 3D internal examination of new construction for flaws (voids, disbonds, inclusions, improper geometry and dimensions, and incomplete curing) may be critical. It will be critical to periodically inspect systems for damage, fatigue and chemical degradation.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Polymer matrix composites are used in automobile and ships and many other consumer and industrial products. TD-THz CT 3D imaging applications can include inspection of automobile dashboards, imaging inspection for delamination of printed circuit boards, inspection of pipe insulation, as well as with manufactured parts such as pure plastic and paper products. TD-THz CT imaging benefits homeland security applications under development such as personnel and luggage inspection for concealed weapons and explosives (in luggage, shoes, etc.). TD-THz CT imaging and spectroscopy can inspect items in shipment such as mail, cardboards packages, and plastic and wood crates.

TECHNOLOGY TAXONOMY MAPPING
Propellant Storage
Ablatives
Airframe
Erectable
Inflatable
Launch and Flight Vehicle
Testing Requirements and Architectures
Thermal Insulating Materials
Microwave/Submillimeter
Photonics
Ceramics
Composites
Optical & Photonic Materials

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Zona Technology, Inc.
9489 E. Ironwood Square Drive
Scottsdale, AZ 85258-4578
(480) 945-9988

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Jie Zeng
jzeng@zonatech.com
9489 E. Ironwood Square Drive
Scottsdale,  AZ 85258-4578
(480) 945-9988

Expected Technology Readiness Level (TRL) upon completion of contract: 3 to 4

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
An Adaptive Feedforward and Feedback Control (AFFC) Framework is proposed to suppress the aircraft's structural vibrations and to increase the resilience of the flight control law, in the presence of AE/ASE interactions. Specifically, the adaptive feedforward controller is designed to reduce any atmospheric induced structural vibrations of the aircraft. The adaptive feedback controller is applied as an additive perturbation of the flight control system to suppress any undesired AE/ASE interactions, and prevent the onset of Flutter/Limit Cycle Oscillation (LCO) instabilities within the flight envelope of a flexible aircraft. The proposed research effort fits very well within the scope of the NASA Dryden Flight Research Center topic "A1.10 Adaptive Structural Mode Suppression," specifically within the Integrated Resilient Aircraft Control (IRAC) effort under the Aviation Safety Program. This research will help the original flight control system to robustly recover from or adjust easily to any unforeseen change during its normal operation due to AE/ASE interactions. In addition, practical concerns will deal with the minimal interference with the original rigid-body controller, as well as its feasible implementation using the standard controller's sampling rate frequency.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Being capable of on-line estimation/monitoring of the elastic modes of the aircraft, the proposed adaptive control technology can be automatically adjusted to attenuate any potential adverse aeroelastic/aeroservoelastic effects of an aircraft before a sustained limit cycle and vehicle damage are encountered. Hence, the proposed project will assist NASA in its goal to achieve an integrated flight control system resilient to failures, damage, and upset conditions unforeseen during the development of the aircraft's original control law. Once this adaptive control technology is developed, it can be readily adopted by NASA for a wide class aerospace vehicles ranging from current to the next-generation designs such as F/A-18 AAW, Hyper X, X-43 and oblique flying wing.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The proposed adaptive feedforward and feedback control framework will have extensive application in non-NASA commercial applications. Firstly, due to the potential Flight Control System (FCS) benefits from avoiding notch filters, the proposed methodology can be used by military and commercial aircraft manufacturers for new aircraft designs, modifications and upgrades. Secondly, it brings a variety of applications in other industries. Among others it can be mentioned: • Acoustic noise cancellation in headphone devices • Reduction of the noise level for rotating fans in computer servers • Suppression and/or attenuation of vibrations in large satellite structures • Cabin noise reduction for the next generation executive transport aircraft, such as the • Marcel Dassualt's Falcon 7X. The noise source can be associated with engine or gust noise. • Vibration suppression across the automotive industry, such as vehicle's engine vibration, adaptively tuning of the suspension in formula 1 racing cars, and so on.

TECHNOLOGY TAXONOMY MAPPING
Controls-Structures Interaction (CSI)
Simulation Modeling Environment
Guidance, Navigation, and Control

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Barron Associates, Inc.
1410 Sachem Place, Suite 202
Charlottesville, VA 22901-2559
(434) 973-1215

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Alec Bateman
bateman@bainet.com
1410 Sachem Place, Suite 202
Charlottesville,  VA 22901-2559
(434) 973-1215

Expected Technology Readiness Level (TRL) upon completion of contract: 4

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The potential benefits of advanced algorithms for diagnostics and prognostics, inner-loop control, and other flight critical systems have been demonstrated in a number of research efforts. Because many of the new algorithms differ significantly from the approaches used in most operational vehicles, and because of factors such as non-deterministic behavior due to adaptation, flight certification of the approaches has been challenging. Verification and validation (V&V) of advanced control laws has received significant research attention, and progress has been made in terms of tools, methods, and architectures for facilitating V&V. Building on this prior V&V work, the proposed research will develop innovative methods and tools for validation of diagnostic systems. The Phase I research demonstrated the value of probabilistic analysis in general, and generalized Polynomial Chaos techniques specifically for measuring diagnostic system performance. The Phase II research will further develop probabilistic methods, and will combine them with worst-case analysis techniques to assess traditional diagnostic system metrics, as well as interactions between diagnostic systems and inner-loop control approaches. Building on the CAESAR tool control law validation tool, a software package to facilitate validation of diagnostic systems will be implemented, and the tool will be demonstrated on a representative diagnostic system.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The proposed software tool will be a key enabling technology for flight certification of advanced diagnostic algorithms. Such diagnostic algorithms have significant potential in terms of improving safety of flight in a wide range of fixed-wing and rotary-wing air vehicles. Diagnostic systems are of particular interest in unmanned and autonomous vehicles, because there is limited or no human interaction to aid with fault recognition, or to identify failures and take appropriate corrective action. The proposed technology will be applicable to NASA research aircraft such as the AirSTAR both in terms of certifying diagnostic systems for these aircraft, and in reducing the risk associated with flight testing of new diagnostic approaches on these research platforms. The proposed technology will also aid in realizing the goals of the Aviation Safety Program by helping to transition diagnostic technologies developed by NASA and other to production aircraft.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Non-NASA aerospace applications of the diagnostic validation approaches include commercial and military fixed-wing and rotary-wing air vehicles, and particularly autonomous and unmanned aerial vehicles. Diagnostic systems play a particularly important role in autonomous systems, which lack human interaction to aid in fault detection and isolation. With growing interest in autonomous vehicles from both military and commercial users, this represents a large potential market. The diagnostic validation procedures will also be valuable for marine and ground vehicles, again, particularly autonomous and unmanned vehicles. Other applications include industrial machinery such as factory automation and power generation equipment. The Polynomial Chaos tools underlying the validation approach will have even broader potential application. For example, these tools are already being applied to analysis of uncertainty in aeroelastic systems, which could easily be extended to other systems involving mechanical structures or fluid flows. Clearly, this represents a huge potential market.

TECHNOLOGY TAXONOMY MAPPING
Simulation Modeling Environment
Testing Requirements and Architectures
Telemetry, Tracking and Control
Guidance, Navigation, and Control
Autonomous Reasoning/Artificial Intelligence
Portable Data Acquisition or Analysis Tools

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)
Todd Quackenbush
todd@continuum-dynamics.com
34 Lexington Avenue
Ewing,  NJ 08618-2302
(609) 538-0444

Expected Technology Readiness Level (TRL) upon completion of contract: 6 to 7

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Recent advances in propulsion, aerodynamic, and noise technologies have led to a revived interest in supersonic cruise aircraft; however, achieving economic viability for these vehicles requires dramatic improvements in cruise efficiency. Optimization of inlet performance offers a potent method for achieving this goal, and a range of conceptual flow control systems are available to address critical problems like blockage, boundary layer bleed, duct length, and flow distortion. By exploiting High Temperature Smart Memory Alloy (HTSMA) technologies, these concepts can be mechanized into robust, compact and lightweight devices, enabling actuators suitable integration into the inlets of supersonic aircraft. The proposed effort leverages prior successful development of solid state smart structures by the investigators in developing of small scale surface-mounted flow control devices as well as large scale actuation systems for inlet ramp mechanisms actuated via HTSMA technology. The proposed Phase II will build upon the Phase I proof of concept study to further develop a fully integrated active supersonic inlet system, including active inlet ramp and deployable flow control devices, as well as the aero/thermo/structural analysis models required to design such systems and subcomponents. In addition, Phase II will be the continued refinement and characterization of actuator-ready HTSMAs.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
By providing foundational research on innovative concepts for propulsion system components for supersonic transport aircraft, the proposed effort will directly support a wide range of fundamental NASA goals in aeronautics. One key result of the effort will be extended development and characterization of highly promising HTSMA materials, a resource of great potential for high speed and/or high temperature applications in subsonic, supersonic, and hypersonic aircraft. In addition, the Phase I effort will lay the groundwork for enabling technology to provide integrated inlet/engine control to ensure safe, stable, and efficient operation for continuous flight above Mach 2. Also, the projected integrated aero/thermo/elastic models of actuator performance to be assembled and validated will assist the development of concurrent engineering tools for analysis and design of smart-materials-based propulsion flow control systems.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
A successful Phase II effort will open the door to prototype testing and eventual implementation of a HTSMA-driven adaptive flow control system. The most direct beneficiary would be next-generation supersonic aircraft that could incorporate these robust, low-profile, low-power flow control devices to permit an optimal balance of improved engine/inlet performance and enhanced engine safety. Successful implementation in this application would also lead to spin-off developments in a number of actuation tasks, including follow-on control concepts for compressor and turbine stages in subsonic or supersonic engines that would directly benefit both civil and military systems. Supersonic cruise technology is also of interest to U.S. Department of Defense agencies, and the developments projected here would directly benefit numerous missile designs as well as both manned and unmanned aircraft systems. Finally, spin-off applications of this technology for control of subsonic engine noise emissions of interest to commercial engine manufacturers, and commercialization of derivatives of the technology to be developed in Phase II for this application will be undertaken in partnership with commercial aircraft engine manufacturers.

TECHNOLOGY TAXONOMY MAPPING
Controls-Structures Interaction (CSI)
Kinematic-Deployable
Simulation Modeling Environment
Testing Facilities
Structural Modeling and Tools
Computational Materials
Metallics
Multifunctional/Smart Materials
Aircraft Engines

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Aspen Aerogels, Inc.
30 Forbes Road
Northborough, MA 01532-2501
(508) 481-5058

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Wendell Rhine
wrhine@aerogel.com
30 Forbes Road, Building B
Northborough,  MA 01532-2501
(508) 466-3130

Expected Technology Readiness Level (TRL) upon completion of contract: 5

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The overall objective of the Phase II project is to develop lightweight reinforced aerogel materials for use as the core structural insulation material in multifunctional thermal protection systems for next generation hypersonic vehicles. During this Phase II SBIR project, we will build on the successful results of the Phase I effort by optimizing the aerogel preparation methods and conducting a complete study of aerogel properties and capabilities. During the Phase II effort, the aerogel thermal conductivities and mechanical properties will be optimized for use as multifunctional TPS materials for hypersonic vehicles including the capability of withstanding very high heating rates. We will prepare these aerogels by methods that can be scaled-up and manufactured economically. Any issues associated with scaling-up production of the rigid aerogel panels will be determined, and a prototype thermal protection system will be fabricated and tested. Successful completion a Phase II program will result in an optimized formulation for the aerogel component of multifunctional TPS, and performance data will be available for further commercialization efforts specific to the aerospace industry. We believe the Phase II Program will advance the state of the art for the development of the next generation thermal protection system materials.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The material developed in the Phase II effort could have a variety of applications in the aerospace industry and within NASA. Aerogels are the most efficient thermal insulation known, and NASA has several applications that would benefit from the low density, high strength and low thermal conductivity of aerogels. Structural/insulative composite aerogels would have applications in hypersonic vehicles, crew exploration vehicles, and reusable launch vehicles. Aerogels could also be applied to NASA spacesuit applications, and insulation for cryogenic fuel tanks, cryogenic fuel transfer lines, and internal insulation applications on re-usable launch vehicles.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The resulting insulation system from this program will also have far reaching benefits for both military and commercial applications. The materials would also be of interest to DoD for their hypersonic global strike vehicles. The potential also exist for insulating weapons, fuel tanks, electronics, and landing gear bays of military aircraft. There are also numerous and far-ranging applications for durable and reliable insulation systems that would improve the energy efficiency of high temperature industrial processes. Finally, the product will have a commercial impact in areas such as: appliance insulation, airliner fuselages, and industrial furnaces and could also be used as a cryogenic insulation for LNG fuel storage tanks where structural insulation materials are required.

TECHNOLOGY TAXONOMY MAPPING
Reuseable
Thermal Insulating Materials
Multifunctional/Smart Materials

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Energy Plus Ltd.
23342 South Pointe Drive, Suite E
Laguna Hills, CA 92653-1422
(949) 583-1197

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Vincent McDonell
mcdonell@erc-ltd.com
23342 South Pointe Drive, Suite E
Laguna Hills,  CA 92653-1422
(949) 583-1197

Expected Technology Readiness Level (TRL) upon completion of contract: 5

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
For many applications involving liquid injection, the ability to predict the details of the breakup process is often limited due to the complexity of the two-phase phenomena. Likewise, the ability to experimentally characterize these phenomena is also limited due in part to the need to rely upon visualization tools which are inherently qualitative. As a result, the ability to validate predictions using these diagnostic tools is also limited. In recent years, visualization diagnostics have evolved substantially in terms of spatial and temporal resolution. The advancements, coupled with a tool to conveniently quantify the results obtained relative to the breakup process offer the potential for a marked increase in understanding of this phenomenon. The proposed effort will develop such a tool that will be applied to the problems of pressure swirl injectors and liquid injection into a crossflow. The typical characteristics associated with this type of liquid breakup, such as column/sheet flattening, bending, fracture point, dynamics, etc. will be automatically quantified using the tool proposed. The project will utilize existing results obtained with state-of-the-art high speed imaging, but will acquire limited data as well to validate the tools developed. Comparisons with advanced CFD modeling will be made to demonstrate the application of the software developed.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The project will result in a novel experimental technique that can be applied to existing and new imaging based diagnostic available at NASA. As applied to various two-phase flow problems, the tool developed will facilitate CFD validation as well as increased understanding of the breakup of liquids for a variety of applications. The tool is particularly well suited for quantitative comparison of experimental results with predictions from advanced simulation techniques such as LES and/or VOF or other high fidelity phase interface tracking methods. ERC will work closely with NASA to focus the Phase II efforts on areas/imaging problems of immediate interest to NASA.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The software developed will be of interest to imaging system providers to help improve the utility of their products. Likewise, any owner of such equipment applying it to problems involving sprays or multiphase flows can potentially make use of the software developed. Additional development for other specific applications will further expand the potential use.

TECHNOLOGY TAXONOMY MAPPING
Simulation Modeling Environment
Testing Facilities
Feed System Components
Optical
Combustion
Liquid-Liquid Interfaces
Aircraft Engines

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Energy Plus Ltd.
23342 South Pointe Drive, Suite E
Laguna Hills, CA 92653-1422
(949) 583-1197

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Vincent McDonell
mcdonell@erc-ltd.com
23342 South Pointe Drive, Suite E
Laguna Hills,  CA 92653-1422
(949) 583-1197

Expected Technology Readiness Level (TRL) upon completion of contract: 4

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
As air-breathing combustion applications advance, increased use of fuel for cooling, combined with cycle advancements, leads to a situation where the fuel can become superheated. While this can lead to potential benefit in terms of the eventual fuel injection process, with enhanced atomization and evaporation, it creates a significant challenge relative design of a system to successfully exploit this behavior. Further, existing computational design tools have not be sufficiently validated to predict the behavior of superheated liquids. Dealing with the superheat behavior in the injection of a liquid fuel requires substantially more physical phenomena to be accounted for compared to a subcooled system. As a result, detailed data and models for this behavior as encountered in practical fuels are needed in order to validate and evolve the models needed. In the work proposed, emphasis will be given to the injection of a plain liquid jet under superheated conditions. Building from the successful Phase I effort, the behavior of internal liquid and external spray in both quiescent and heated crossflow environments will be studied. The models evolved will be incorporated into an existing simulation environment developed by ERC for atomization of liquid jets. In addition, data will be available for CFD validation.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
For Aerospace applications, development of fuel injection schemes that involve fuel superheat will be enhanced by model construction and validation resulting from the proposed project. Both standalone modeling tools and models for incorporation into a CFD environment will result from the project. NASA design tools will be enhanced in general and any simulation platforms needing to incorporate superheated fuel behavior will benefit in particular.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Any application with fuel injection systems involving the potential for superheated liquid will benefit from the proposed work. Examples include automotive applications as well as boiler/furnace applications.

TECHNOLOGY TAXONOMY MAPPING
Simulation Modeling Environment
Testing Facilities
Feed System Components
Aircraft Engines

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
ATA Engineering, Inc.
11995 El Camino Real
San Diego, CA 92130-2566
(858) 480-2000

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Parthiv Shah
parthiv.shah@ata-e.com
11995 El Camino Real, Suite 200
San Diego,  CA 92130-2566
(858) 480-2101

Expected Technology Readiness Level (TRL) upon completion of contract: 4 to 5

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
A novel quiet engine air-brake (EAB) is proposed in response to NASA's solicitation for active and passive noise control concepts for conventional and advanced aircraft. The EAB concept is applicable to 1) next-generation, conventional tube and wing aircraft (current generation +1) and 2) advanced integrated airframe/propulsion system configurations (current generation +2, +3). Potential retrofit opportunities are also envisioned. Phase 1 analysis on NASA's Source Diagnostic Test (SDT) fan stage suggests that an EAB could realize three to four decibels overall noise reduction under the approach flight path by generating a swirling exhaust with drag equivalent to one to two turbofan-sized bluff bodies per powerplant. Such drag generation could enable slower and/or steeper and/or aero-acoustically cleaner approach trajectories. A Phase II development program is proposed to 1) perform aerodynamic designs of dual-stream, swirling bypass flow nozzles and experimentally assess their performance and noise, 2) develop conceptual aero-designs that address current engine architecture issues such as pylon duct bifurcations, and 3) develop a prototype design of an EAB for validation in a model-scale rig. The final deliverable to NASA will be a written report presenting design, analysis and experimental results from blown nozzle testing, plus a prototype EAB design.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The proposed technology can assist NASA in the development of next generation quiet aircraft, including tube and wing (current generation +1) and integrated airframe propulsion system configuration (current generation +2). These aircraft are likely to have noise sources from the engine and airframe that have comparable levels. A quiet air-brake device will allow noise reduction by creating drag without the associated unsteady flow structures of devices such as flaps, slats, and undercarriage. In addition, these devices will enable steep approaches, thereby locating the noise source further from the affected communities. An additional application for swirling exhaust flows is in the area of wake vortex avoidance and induced drag management. For example, swirling outflow devices placed on wing tips could be used to counter- or co-swirl relative to the bound vortex that is shed by a finite wing, resulting in potential induced drag reduction or increase (possibly of value in a quiet drag sense).

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The commercial potential for this system extends beyond NASA's development programs related to next-generation quiet aircraft. The larger, shorter-term market potential relates to the retrofitting of existing engines so that they can meet future noise standards and/or allow steeper glideslopes without increased noise. The midterm opportunity relates to engines which are currently being developed for commercial deployment in the next seven to ten years by the large engine manufacturers where there is potentially still an opportunity to incorporate features of this concept into the final design. ATA will explore both of these opportunities with Rolls Royce, Pratt and Whitney, and other engine manufacturers more stringently as part of Phase II.

TECHNOLOGY TAXONOMY MAPPING
Kinematic-Deployable
Aircraft Engines
Aerobrake

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Mechanical Solutions, Inc.
11 Apollo Drive
Whippany, NJ 07981-1423
(973) 326-9920

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Michael Platt
mjp@mechsol.com
11 Apollo Drive
Whippany,  NJ 07981-1423
(973) 326-9920

Expected Technology Readiness Level (TRL) upon completion of contract: 7

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The Phase I project successfully demonstrated that the advanced non-contacting stress measurement system (NSMS) was able to address closely spaced modes and blade-to-blade variations (mistuning). MSI's advanced NSMS method uses a radar-based blade vibration measurement system with the following capabilities: • Provides a continuous time series of blade displacement data over a portion of a revolution (solving the under sampling problem). • Includes data reduction algorithms to directly calculate the blade vibration frequency, modal displacement, and vibratory stress (solving the mode inference problem). • Uses a single sensor per stage to monitor all of the blades on the stage. The Phase II work begins by confirming the sensor calibration process, modifying the sensor module so it is compatible as an upgrade to existing NSMS system, and improving and finalizing the NSMS software. The result will be a stand-alone radar/tip timing radar module for current conventional NSMS users (as an upgrade) and new users. The hybrid system will use frequency data and relative mode vibration levels from the radar sensor to provide substantially superior capabilities over current blade vibration technology. This frequency data, coupled with a reduced number of tip timing probes, will result in a system capable of detecting complex blade vibrations which would confound traditional NSMS systems. The hardware and software package will be validated on an existing compressor rig at MSI. Finally, the hybrid radar/tip timing NSMS software package and associated sensor hardware will be installed for use in the NASA GRC spin pit test facility. MSI will also supply the stand-alone radar module to a major engine prime.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Based on the Phase I progress and Phase II plans, Phase II will conclude with the delivery of the system to NASA, GRC (software and radar hardware) and the stand-alone radar module to an engine prime. Improvements in blade vibration measurement capability will significantly reduce the cost and risk of development and operation of gas turbine engines. Customers include any government or engine test facility that currently uses an NSMS system and wants to upgrade or a facility that is considering the use of NSMS. The potential applications include any turbine engine ranging from gas turbine propulsion engines to industrial steam turbines used for power generation. The costs associated with maintenance, downtime, and readiness are already well established and understood by both military and industrial users, so an improved NSMS would be attractive to many types of customers.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Applicable to DOD/commercial engine primes and government test facilities, as well industrial gas turbine and steam turbine manufacturers in the power generation and oil/gas markets. These industrial vendors are striving for improved stage performance and are beginning to more seriously address mistuning issues. With further development a variation of the system has a role in Predictive Health Management (PHM) for aerospace and industrial machines.

TECHNOLOGY TAXONOMY MAPPING
Testing Facilities
Feed System Components
Portable Data Acquisition or Analysis Tools
Aircraft Engines

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
M4 Engineering, Inc.
2161 Gundry Avenue
Signal Hill, CA 90755-3517
(562) 981-7797

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Kevin Roughen
kevin.roughen@m4-engineering.com
2161 Gundry Avenue
Signal Hill,  CA 90755-3517
(562) 981-7797

Expected Technology Readiness Level (TRL) upon completion of contract: 6

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
M4 Engineering proposes to develop a generalized reduced order model generation method. This method will allow for creation of reduced order aeroservoelastic state space models that can be interpolated across a range of flight conditions. This development will be a significant advance to the process of control law development, especially in the design of control systems required to provide flutter suppression, gust load alleviation, and ride quality enhancement. The proposed technique will be an excellent compliment to modern linear and nonlinear aeroservoelastic analysis methods.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The first NASA application is the S4T program, which is currently a subject of ASE control law development at M4 Engineering. It is also expected that this technology will be directly applicable to the research projects planned in the Aeronautics Research Mission Directorate (ARMD). The multidisciplinary nature of the technology makes it an ideal candidate for use any time a very high performance vehicle is designed, where interactions between components, disciplines, and the control system are important. Examples include future high efficiency subsonic aircraft, quiet supersonic aircraft, high-altitude, long-endurance aircraft, hypersonic aircraft, and next-generation launch vehicles (either airbreathing or rocket powered).

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
M4 Engineering has active relationships with several prime contractors who are likely users of this technology. These include Boeing Phantom Works, Northrop Grumman, and Raytheon. These provide excellent commercialization opportunities for the technology. Active marketing to prime contractors and other specialty airframers (e.g., Aerovironment, General Atomics, etc.) will follow these applications. The application of these new reduced-order modeling techniques is expected to find wide application to many aerospace and non-aerospace products. Model reduction for control system development is a widely applicable concept. Examples include the medical engineering field, automotive, aerospace/defense, and alternative energy applications.

TECHNOLOGY TAXONOMY MAPPING
Airframe
Controls-Structures Interaction (CSI)
Launch and Flight Vehicle
Simulation Modeling Environment
Structural Modeling and Tools
Guidance, Navigation, and Control
On-Board Computing and Data Management

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Zona Technology, Inc.
9489 E. Ironwood Square Drive
Scottsdale, AZ 85258-4578
(480) 945-9988

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Danny Liu
danny@zonatech.com
9489 E. Ironwood Square Drive
Scottsdale,  AZ 85258-4578
(480) 945-9988

Expected Technology Readiness Level (TRL) upon completion of contract: 3 to 4

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
ZONA proposes a phase II effort to fully develop a comprehensive methodology for aeroelastic predictions of the nonlinear aerodynamic/aerothermodynamic - structure interaction (NANSI) on ballutes during hypersonic atmospheric entry, including potential surface wrinkling. A time-accurate Boltzmann aerodynamic flow solver, called BGKX, will first be extended to 3D geometries for inviscid /viscous hypersonic flows. BGKX is a robust, unified-Mach-number, all-altitude, viscous flow solver; it provides pressure and heat flux solutions in one step. To handle the complex geometry of wrinkling ballutes, an advanced cartesian grid system, called gridless boundary condition cartesian (GBCC), will be implemented within BGKX. Next, generalized reduced order models (ROM) of the BGKX aerodynamics and nonlinear structures will be established to handle ballute wrinkling and the complex flow. In addition to Direct physical coupling of the aerodynamics and structures, an aerodynamic ROM - structures ROM coupling procedure will be fully developed for efficient aeroelastic applications to wrinkled ballutes. Lastly, we will evaluate the sensitivity of the ballute aeroelastic behavior in specific structural features: the pre-tensioning of the ballute, its inflation, and the existence of structural properties variations around its circumference. ZONA will work closely with the NASA monitor in phase II should an additional ballute configuration be considered.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
ZONA's phase II methodology:nonlinear aerodynamics-nonlinear structures interaction (NANSI)can be used by NASA for: - Inflatable/Ballute design for CEV, space-access/atmospheric-entry vehicles, space station designs, weather balloons,etc. - BGKX, a unified-Mach-number, all-altitude, viscous flow solver, is a robust method for aerothermodynamic applications. - ZONA nonlinear structural ROM (ELSTEP) for efficient handling of the nonlinear structural applications. - Aerodynamic ROM-Structural ROM coupling procedure for efficient aeroelastic/aerothermoelastic applications. - The NANSI software framework can house ZONA and NASA codes (Volterra, LAURA,FUN3D,CFL3D,nasa.ELSTEP) alike for above applications. - NANSI is applicable to NASA aeroelastic projects: transonic/supersonic transports, morphing, launch vehicles, CEV, TPS, TDT activities in Langley, flight testing in Dryden , turbomechinery in Glenn, etc.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
ZONA's NANSI methodlogy can be used by DoD and private sectors for: - Aerospace/Defence sectors: Inflatable for DoD such FASM/Navy ,HARV/Army (ISR airship), Sensorcraft/AF, OFW,Rapid Eye, HALE of Darpa, SSC/store clearance/AF ,Morphing vehicles/AF, MAV/AF/Army etc. - Boeing/Airbus transports and General aviation sectors: NANSI and ROM-ROM will serve as an efficient CFD-based aeroelastic tool for transport and civil/private aircraft design and analysis.

TECHNOLOGY TAXONOMY MAPPING
Airframe
Inflatable
Kinematic-Deployable
Launch and Flight Vehicle
Cooling
Reuseable
Structural Modeling and Tools
Metallics
Multifunctional/Smart Materials
Aerobrake

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Advanced Fluidics, LLC
4217 Red Bandana Way
Ellicott City, MD 21042-5928
(410) 499-9237

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
SURYA RAGHU
sraghu@advancedfluidics.com
4217 Red Bandana Way
Ellicott City,  MD 21042-5928
(410) 499-9237

Expected Technology Readiness Level (TRL) upon completion of contract: 6 to 7

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The overall objective of the proposed research is to design, develop and demonstrate fluidic actuator arrays for aerodynamic separation control and drag reduction. These actuators are based on a compact design of low mass-flow fluidic oscillators that produce high frequency (1-5 kHz) sweeping jets. Preliminary experiments on separation control over a trailing edge flap on a NACA 0015 airfoil, V-22 wing section for download reduction, cavity tones and jet thrust vectoring have shown encouraging results for these actuators. Based on the results from Phase I, and the commercial interest from a leading aircraft manufacturer, we propose to conduct a systematic study of the scaling parameters of the fluidic actuator arrays in relation to the geometric and aerodynamic parameters of the wing using wind tunnel tests on a specially designed airfoil model. This will include the effects of actuator spacing, array location, pressure gradient and wing sweep on the actuator effectiveness. Failure Modes and Effects Analysis (FMEA) will be undertaken to estimate the risk of the proposed technology. A rapid inspection technique will be developed for conducting quick, in situ testing of the fluidic arrays. Projecting to the future, a synchronous array of actuators will also be developed.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The proposed work would be of interest to the ARMD for the aerodynamic flow control needs of the Next Generation Air Transportation System (NextGen), subsonic fixed wing and rotary wing programs and transonic flow control programs. The fluidic actuators would also be of interest to the Active Combustion Control, Active Stall Control and Active Inlet Control and Jet Noise Control Programs at NASA. Such arrays can also be used for de-icing systems using either hot air or de-icing liquids since the fluidic jets work with both liquids and gases.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Aerodynamic flow control has a large number of applications in the commercial and military aerospace industry. We foresee applications of our technology to separation control over leading and trailing edge of airfoils to achieve high lift and minimum-drag configuration for aircraft wings, control of jet exhaust noise in aircraft engines, intake flow control, and internal flows in gas turbines. One other area of application we are exploring is the flow control and de-icing over wind turbine blades.

TECHNOLOGY TAXONOMY MAPPING
Renewable Energy
Aircraft Engines

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Combustion Research and Flow Technology
6210 Keller's Church Road
Pipersville, PA 18947-2010
(215) 766-1520

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Richard Wilmoth
wilmoth@craft-tech.com
6210 Keller's Church Rd.
Pipersville,  PA 18947-2010
(215) 766-1520

Expected Technology Readiness Level (TRL) upon completion of contract: 2 to 3

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
A new chemical kinetics model and database will be developed for aerothermodynamic analyses on entry vehicles. Unique features of this model include (1) the ability to model chemical kinetics in highly nonequilibrium flows at high altitudes, (2) the ability to predict nonequilibrium dissociation without reliance on traditional continuum kinetic rate equations, and (3) the ability to model complex reactions from fundamental molecular quantum models. The model will permit analyzing high-speed, nonequilibrium flows about entry and aeroassist vehicles based on extensions to Direct Simulation Monte Carlo (DSMC) codes, and a new database will be developed for these extensions. The new approach offers potential for treating other complex nonequilibrium flow physics including ionization and radiation in a more direct manner than has been previously used and therefore offers potential improvements in accuracy. These tools will provide essential data for assessing the aerothermodynamic performance for a wide range of vehicle designs over a wide range of vehicle attitudes and flight conditions. The improved accuracy offered by our proposed chemical kinetic modeling approach offers significant benefits in the design of vehicles for both unmanned planetary missions and manned missions to the Moon and Mars.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The proposed chemical kinetics model software and database has substantive market potential for NASA return-to-space related activities, in terms of its broad-based applicability to vehicle design for both high-altitude continuum (60-85km) and rarefied flights. The new software developed directly supports the design of aeroassist and planetary entry vehicle systems, providing improved accuracy and ease of usage over existing software, thus reducing design costs and producing more reliable designs. NASA programs supported include Constellation, which involves LEO and Lunar return missions based on CEV, COTS which provides manned / unmanned service to and from ISS, and New Millennium which involves a number of planetary entry and sample return missions. The chemical kinetics model will be implemented in existing DSMC software (DAC) used by NASA and its contractors and will have overall features which will facilitate its widespread usage, as ascertained in discussions with key NASA personnel.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Varied DOD groups are extremely interested in this software and programs are in place facilitating widespread usage. We are involved in DOD programs where such high-altitude chemical kinetics is of interest for RV discrimination (MDA), for plume/divert jet signature predictions (AFRL/MDA), and for sensor/seeker window blinding/contamination by divert jets on interceptor missiles at rarefied altitudes (Army). The new model will greatly improve upon calculations at higher continuum altitudes which is of interest to DoD for: (1) RV applications where the wake (with charged species and/or ablation products) provides observable data used for detection and tracking; (2) plume/divert jet observable studies where local rarefaction effects occur and embedded DSMC is needed for accuracy; and (3) multi-body and flux interaction studies at high altitudes where the dense plume/blast interacting with the vehicle must be treated by local continuum methods with the vehicle itself being embedded in a rarefied, high-altitude flow.

TECHNOLOGY TAXONOMY MAPPING
Chemical
Fundamental Propulsion Physics
Micro Thrusters
Ablatives
Simulation Modeling Environment
Cooling
Reuseable
Aerobrake

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
MetroLaser, Inc.
8 Chrysler
Irvine, CA 92618-2008
(949) 553-0688

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Drew L'Esperance MetroLaser, Inc.
dlesperance@metrolaserinc.com
8 Chrysler
Irvine,  CA 92618-2008
(949) 553-0688

Expected Technology Readiness Level (TRL) upon completion of contract: 6

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Visualization of turbulence and shock phenomena by schlieren imaging has led to important discoveries in aerodynamics, and there has been much interest in applying schlieren methods for aircraft in flight. The goal of this project is to develop the next generation of Schlieren for Aircraft in Flight (SAF) systems. SAF is a technique for obtaining schlieren images of aircraft as they fly past the edge of the sun. In its original form, images were recorded with a time delay and integration (TDI) camera using slit masks that conformed to the edge of the sun. Problems arise if the cutoff mask is not precisely aligned with edge of the sun, or if the TDI camera is not aligned and synchronized with the aircraft flight path. These problems can be solved using the synthetic TDI method, where the aircraft transit of the sun is recorded on high-speed video, and then the TDI process is carried out computationally using programmable masks. Synthetic, TDI-based SAF systems are less sensitive to movement of the observation platform, and can be used with non-cooperative targets whose flight paths and velocities are not known in advance.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Flight testing is often used as a final critical check of aerodynamic designs developed by computational and wind tunnel methods because the information obtainable in wind tunnels is subject to interference. Outdoor schlieren systems using the sun and moon make it possible to examine shock waves and other phenomena from aircraft in flight. Applications exist in all forms of research and development associated with turbulent flow fields, including aero optics, flow control, drag, boundary layer transition, and flow separation. The proposed developments will be extremely important in flight-testing, where few such instruments can perform in a flight environment.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Potential commercial applications include aero-optics, flow diagnostics, flow-control, free-space laser communication, active laser imaging, high bandwidth video transmission, spectroscopy, and high-resolution imaging.

TECHNOLOGY TAXONOMY MAPPING
Optical

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Materials Technologies Corporation
57 Maryanne Drive
Monroe, CT 06468-3209
(203) 874-3100

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Yogesh Mehrotra
ymehrotra@aboutmtc.com
57 Maryanne Drive
Monroe,  CT 06468-3209
(203) 874-3100

Expected Technology Readiness Level (TRL) upon completion of contract: 5 to 6

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Lead-lag motions of rotor blades in helicopters require damping to stabilize them. In practice, this has necessitated the use of external hydraulic dampers which suffer from high maintenance costs. High operational (lifecycle) cost has prompted rotorcraft industry to use elastomeric lead-lag dampers that result in "dry'' rotors. However, complex behavior of elastomers provides challenges for modeling such devices, as noted by rotorcraft airframers. Currently used analytical models oversimplify the complexity of operational environment and make radical assumptions about operating parameters that, at best, lead to excessively simplistic, and often unreal, device models. These first order linear device models require costly and time consuming experiments to construct them; moreover, they do not directly relate to either the material characteristics or the geometric configuration. In Phase-I SBIR, MTC team pursued a fundamentally radical approach wherein elastomeric dampers are derived from first-principle-based modeling rather than device model-based analyses. Our Phase-I program was tailored towards successfully demonstrating closed loop simulation, i.e. a finite element based modeling of elastomeric materials integrated into a multibody dynamics framework for rotorcraft analysis. During Phase-II, comprehensive and sophisticated material models will be implemented and streamlined into a single comprehensive analysis framework. These implementations will be fully validated against bench and flight test data of Bell M429 elastomeric dampers. These program objectives will be accomplished via collaborative tripartite partnership with Bell Helicopter and Georgia Tech.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
TBF

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
-Robust Vehicle Design Practices -All Rotorcraft Manufacturers will benefit from first principles-based designing of complex products -Automotive, tracked vehicle industry

TECHNOLOGY TAXONOMY MAPPING
Airframe
Simulation Modeling Environment
Testing Facilities
Structural Modeling and Tools
In-situ Resource Utilization
Ceramics
Composites
Computational Materials
Metallics
Organics/Bio-Materials
Multifunctional/Smart Materials
Tribology

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Sukra Helitek, Inc.
3146 Greenwood Road
Ames, IA 50014-4504
(515) 292-9646

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Angela Lestari
nappi@sukra-helitek.com
3146, Greenwood Road
Ames,  IA 50014-4504
(515) 292-9646

Expected Technology Readiness Level (TRL) upon completion of contract: 7 to 8

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
During initial design studies, parametric variation of vehicle geometry is routine. In addition, rotorcraft engineers traditionally use the wind tunnel to evaluate and finalize designs. Estimation of rotor tunnel blockage is significantly more complex than bluff body corrections as the correction depends on operational characteristics such as rotor RPM and thrust produced. This proposal offers to develop an Integrated Design Environment (IDE) which can simulate a complete rotorcraft with or without wind tunnel walls including all the facility effects. At the heart of the innovation are: 1. An automated hybrid grid generator (viscous grids near the bodies and unstructured Cartesian grid everywhere else). 2. A robust and economical incompressible flow solver for the entire system of grids. 3. Momentum source based rotor model that is suitable and economical for simulating configurations with multiple rotors. In Phase I, the proof-of-concept developed used unstructured Cartesian grid for the model and wind tunnel. In phase II, the tool will be extended to hybrid grid with viscous grid near solid surfaces and will include several tools including a simple CAD like geometry manipulation tool and pre- and post-processing tools all integrated in one environment to facilitate ease of use.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
NASA's interest in civil rotorcraft research prompts for a computational tool which has an Integrated Design Environment that is easy to learn and be robust and computationally efficient. The proposed design tool accomplishes this goal, especially in areas where geometric design changes are being considered and wind tunnel testing is integral to the design study. The tool can be effectively used for rotorcraft and V/STOL aircrafts where quantification of parametric variation in the design is essential for success.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The integrated Design Environment with a simple module for geometry manipulation and tools for pre-processing and post-processing CFD simulation will be an asset to any organization with a need to analyze a rotorcraft design or develop a new design. Incidentally the tool acting as a computational wind tunnel will be an asset to other government agencies including ARMY, NAVY and AIR FORCE where wind tunnel testing of rotorcraft and V/STOL aircrafts is routine. In the rotorcraft industry, the proposed tool can be used to assist during the design process. The tool will be designed to be versatile and enable the user to easily vary design parameters. In the educational institutions the tool will help the students to gain insight on different flow phenomena, the effect of geometric variation and wind tunnel walls on the performance and flow field of a rotorcraft.

TECHNOLOGY TAXONOMY MAPPING
Portable Data Acquisition or Analysis Tools

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Lawrie Technology, Inc.
227 Hathaway E
Girard, PA 16417-1552
(814) 746-4125

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Duncan Lawrie
duncan@lawrietechnology.com
227 Hathaway E
Girard,  PA 16417-1552
(814) 746-4125

Expected Technology Readiness Level (TRL) upon completion of contract: 6 to 7

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
An all-composite driveshaft incorporating integral flexible diaphragms is described and proposed for phase II prime conractor testing. The approach obsoletes the split lines required to attach metallic flex elements and either metallic or composite spacing tubes in current solutions. Sub-critical driveshaft weights half that of incumbent technology are achievable for typical rotary wing shaft lengths. Spacing tubes are described, which comprise an integral part of the initial tooling but which remain part of the finished shaft and control natural frequencies and torsional stability. A concurrently engineered manufacturing process and design for performance is described which competes with incumbent solutions at significantly lower weight and with the probability of improved damage tolerance and fatigue life. This phase II proposal seeks to produce additional fatigue test articles to supplement the pair of shafts provided during phase I for static evelauation. The phase II effort will also support the prime contractor test program designed to raise Technology Readiness Level to 6-7.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The rotary wing subtopic 2.10 includes both materials & structures and propulsion components requiring lower weight and higher performance in power transmission components. These include tail rotor drives, tilt-rotor cross-over drives, and tandem rotor connection shafts. Current technology has not changed in decades as it concerns motion accomodating, high torque density driveshafts. Enhanced mission availability and cost reduction can be obtained via the reduced part count and improved fatigue performance already established by this fully integral, all-composite driveshaft technology. Further refinement and preparation of flight qualification test articles is proposed and, once fielded, NASA and NASA partners will also benefit from increased payload.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
In addition to both military and commercial rotary wing programs other extremely weight sensitive driveshaft applications include JSF lift fan flxible shafts and Navy hovercraft/air cushion landing craft. General industrial applications likely to benefit most include very high speed turbomachinery relying on long titanium spacing tubes to stay sub-critical.

TECHNOLOGY TAXONOMY MAPPING
Airframe
Controls-Structures Interaction (CSI)
Structural Modeling and Tools
Waste Processing and Reclamation
Fluid Storage and Handling
Composites
Energy Storage
Aircraft Engines

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
NanoSonic, Inc.
1485 South Main Street
Blacksburg, VA 24060-5556
(540) 953-1785

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Mike Bortner
mbortner@nanosonic.com
1485 South Main Street
Blacksburg,  VA 24060-0618
(540) 953-1785

Expected Technology Readiness Level (TRL) upon completion of contract: 7

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The overall objective of this NASA SBIR program is to develop technology enablers for NASA's rotorcraft vision to facilitate rotorcraft operation in all weather environments. Specifically, NanoSonic will build on its successful completion of Phase I objectives and first generation test article demonstration to optimize, scale up, and qualify high performance, multifunctional, nanostructured, icephobic appliqués with enhanced erosion resistance for rotorblade leading edges. Reliable all-weather service has specifically been identified as one of the barriers to achieving NASA's rotorcraft vision. To truly revolutionize air transportation mobility, rotorcraft must be able to operate in similar environments to current fixed wing vehicles – including environmental conditions in which icing may occur. NanoSonic's multifunctional appliqués will help to enable NASA's rotorcraft vision by completely preventing ice buildup on rotorblades. Implementation of NanoSonic's erosion resistant hydrophobic appliqués will facilitate mission critical operations in icing conditions and mitigate concerns of vibration transmission and shudder that are associated with ice buildup. NanoSonic's appliqués integrate erosion resistant nanocomposites, enhancing rotorcraft operation in high erosion environments. Maintenance and associated costs are reduced, as a new appliqué can be readily placed on the rotorblade leading edge when the existing appliqué has exhausted its functionality.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Of immediate interest to enabling NASA's rotorcraft vision, as the proposed technology is matured and qualified throughout the proposed effort, multiple manufacturers and customers will integrate this technology within their rotorcraft designs to help enable all-weather rotorcraft operation. In addition to rotorcraft, the proposed nanocomposite appliqués will be useful for a wide range of NASA applications where water repellency, minimization of water ingress, or reduced frictional drag is desired. The inherent water repellency provides anti-icing functionality useful in nearly any vehicle or structure for missions where icing or the risk of ice formation inhibits progress. Water repellency also suggests minimized water ingress, minimizing water uptake and potentially enhancing corrosion resistance. Minimization of corrosion on metallic surfaces would minimize maintenance and reduce concerns of potential structural integrity damage resulting from corrosion. Hydrophobic materials can also significantly reduce frictional drag, which may be particularly useful for operation of small exploratory vehicles.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The proposed multifunctional appliqués integrate high durability and hydrophobic functionality, which is marketable to an extremely broad range of applications outside of rotorcraft. Water repellency provides anti-icing functionality useful in nearly any vehicle or structure for missions where icing or the risk of ice formation inhibits progress. Water repellency also suggests minimized water ingress, which is a significant problem in nearly all applications where composites are used for metal replacement. For metallic materials, the proposed materials will minimize corrosion, reducing maintenance and concerns of potential structural integrity damage resulting from corrosion. Similar hydrophobic nanocomposites can also significantly reduce frictional drag, enhancing performance. Commercial applications are nearly limitless, including corrosion protection and frictional drag reduction for higher performance, cost and energy saving commercial aircraft and automobiles. Because of the dynamic applicability of NanoSonic's nanocomposites, the potential market spans from military to civilian, opening the door to endless possibilities in multiple industries.

TECHNOLOGY TAXONOMY MAPPING
Airframe
Ceramics
Composites
Multifunctional/Smart Materials

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Metron Aviation, Inc.
45300 Catalina Court, Suite 101
Dulles, VA 20166-2335
(703) 234-0819

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Jimmy Krozel
krozel@metronaviation.com
45300 Catalina Court, Suite 101
Dulles,  VA 20166-2335
(503) 274-8316

Expected Technology Readiness Level (TRL) upon completion of contract: 4

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
We design and develop a Decision Support Tool (DST) that supports On-Demand Special Use Airspace (SUA) scheduling and flight plan optimization around SUA between Airline Operations Control (AOC), Military, Air Traffic Control System Command Center (ATCSCC), and Air Route Traffic Control Center (ARTCC) personnel. The tool allows AOC and ARTCC Traffic Management Unit (TMU) personnel to coordinate strategic and tactical plans, with a strategic look ahead time from days to less than 2 hours, and tactical plans up to the minute centered locally around an ARTCC airspace. The tool coordinates aircraft movement though vs around SUA. The tool allows for asynchronous communication of priorities associated with flight plans and flight plan amendments (contingency plans) between the AOC and ARTCC TMU specialist, allowing the ATCSCC and Military to view these priorities and TMU responses to them at any time. This technology will be developed to Technology Readiness Level (TRL) 2 at the end of Phase I, and TRL 4 prototype system by the end of Phase II.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The proposed tool has application in Air Traffic Management (ATM) Research to study Dynamic Airspace Configuration (DAC) changes due to SUA usage, and automated Traffic Flow Management (TFM) solutions. The tool may be included into NASA's FACET or ACES simulation environment for benefits studies, or in real-time simulations to study how the Military and Air Traffic Control may collaborate in the future.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The proposed tool has application to military operations for wartime and non-wartime activity. In wartime, the competition for airspace resources can be controlled in a collaborative solution by our tool. In non-wartime civilian airspace, the proposed tool has an application in the management of SUA activity in the NAS, allowing the military to coordinate the activation and de-activation of SUA in collaboration with the FAA.

TECHNOLOGY TAXONOMY MAPPING
Spaceport Infrastructure and Safety
Guidance, Navigation, and Control
Pilot Support Systems

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Optical Scientific, Inc.
2 Metropolitan Court, Suite 6
Gaithersburg, MD 20878-4003
(301) 963-3630

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Ting-i Wang
tingwang@opticalscientific.com
2 Metropolitan Ct, Suite 6
Gaithersburg,  MD 20878-4008
(301) 963-3630

Expected Technology Readiness Level (TRL) upon completion of contract: 6 to 7

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Feasibility study including analysis and experiment performed in Phase I indicated that several singled-ended optical scintillometer and retro-reflector pairs installed on towers or poles are able to develop a vertical profile of near ground atmospheric turbulence and wind measurements in airport environment. In Phase II, OSI proposes to design, fabricate and test a prototype optical vertical profile system for atmospheric turbulence and crosswind measurements to provide critical atmospheric parameters for wake vortex decaying forecasting modeling. Several scintillometers will be built with the goal to demonstrate their ability to meet performance, size, weight, and packaging requirements for airport operations. An analytical and field test program will be conducted for further performance improvement of a vertical profile vortex detection system using optical scintillometers to measure near ground level crosswind, turbulence, and wake vortex on an airfield. The results of near ground vortex measurements plus the ground vortex measurements by double-ended optical scintillometers will provide the necessary assessment to design a crosswind, turbulence, and vortex detection system as a decision support tool for NASA's Airspace Systems (AS) Program to improve airport capacity and safety. The vortex detection system could also measure downdraft on the runway. The instrument will provide real-time continuous measurements of convergence and divergence along the runway. Vertical winds, and hence the downdraft, can be derived from the measured divergence. The proposed vortex detection system will also be able to provide critical large area wind information. By incorporating this valuable information into the low-level wind shear modeling, it will greatly enhance the performance of the present airport low-level wind shear systems.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
NASA Airspace Systems (AS) Program has identified that advanced technologies to detect and avoid wake vortex hazards is critical for performing safe, closely spaced and converging approaches at closer distances than are currently allowed. One of the primary interests is Wake Vortex Hazard Solutions that include wake avoidance procedures for airports with closely spaced runways; characterization of wake vortex and atmospheric hazards to flight; and wake vortex alleviation/mitigation technologies. The proposed wake vortex detection system by several optical scintillometers will provide critical real-time vortex information that will increase throughput of an airport runway complex and achieve the highest possible efficiencies in the use of airportal resources. The detection of vortex will entail reduced aircraft wake vortex separation standards for super-density operations. The proposed effort will lead to the development of wake vortex detection system that provides critical information relevant to NASA's NGATS-Airportal effort.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The FAA may require the vortex detection system successfully developed in this SBIR to be incorporated in the NGATS. The vortex detection and avoidance system will improve airport throughput and efficiency. More tests may be required and system may further improved in Phase 3 with FAA that will lead the system to TRL level 9 -the Actual system (flight) proven through successful mission operations. A TRL-9 system certainly has many market opportunities in domestic and international airports. To further expose OSI's products, OSI may team up with a large airport equipments vendor, such as the one with Airport Surface Traffic Configuration Management System. The team-up will lead to the large scale deployment of wake vortex detection systems at airports around the globe.

TECHNOLOGY TAXONOMY MAPPING
Airport Infrastructure and Safety
Optical

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Mosaic ATM, Inc.
801 Sycolin Road, Suite 212
Leesburg, VA 20175-5686
(703) 737-7637

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Bryan Wood
wood@mosaicatm.com
801 Sycolin Road SE, Suite #212
Leesburg,  VA 20175-5686
(800) 405-8576

Expected Technology Readiness Level (TRL) upon completion of contract: 3 to 4

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Although a number of airportal surface models exist and have been successfully used for analysis of airportal operations, only recently has it become possible to conduct detailed validation of such models through the use of airport surface surveillance data. In this effort, we propose to go a step further than existing models, by actually incorporating empirically-derived airport surface control practices into NASA's overall airportal simulation modeling capability. This effort will produce tools to support fundamental research of the concept and requirements for airportal operations in the Next Generation Air Transportation System (NextGen) by providing microscopic airportal surface modeling components that provide higher fidelity and greater validity of modeling than previously available. Through this effort we will use the Surface Operations Data Analysis and Adaptation (SODAA) tool to conduct detailed analysis of airport surface operations using actual data.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
This Phase 2 SBIR supports the research of airport operations toward implement of NextGen operational improvements. Until recently detailed analyses of airport surface operations could only be conducted through visual observation of taxi routes, runway occupancy times, and sequencing decisions whereas now it is possible to analyze such details using airport surface surveillance data through the use of the SODAA tool. We expect that the research and development components of this Phase 2 effort will be of greatest value to NASA and to the FAA to enable such analyses to be conducted more efficiently and effectively. The most likely commercialization and Phase 3 activities involve further development of the airport surface analysis capabilities begun in Phases 1 and 2. These capabilities will be used by NASA and other research organizations to further study operations on the airport surface.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The FAA requires detailed collection of operational metrics to support measurement of operational performance and investment analysis for new systems. The SODAA tool is already being used to support FAA programs in the conduct of Concept and Requirements Development. We expect that this use of SODAA and the analysis capabilities to be developed in this Phase 2 effort will be expanded further. The airport operations analyses that are enabled through the SODAA tool and the enhancements to be created through this Phase 2 effort also provide valuable analysis capabilities for airlines, fleet operators, airports, and other organizations in the aviation industry. Through the use of these microscopic analysis tools, airlines can refine their schedules and procedures to optimize their operation on the airport surface.

TECHNOLOGY TAXONOMY MAPPING
Simulation Modeling Environment
Airport Infrastructure and Safety
Expert Systems
Software Tools for Distributed Analysis and Simulation

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Waddan Systems
8801 Encino Avenue
Northridge, CA 91325-3228
(661) 257-4172

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Mahendra Singh
mahendra@waddansystems.com
8801 Encino Avenue
Northridge,  CA 91325-3228
(661) 257-4172

Expected Technology Readiness Level (TRL) upon completion of contract: 7

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Development of an Aircraft Nodal Data Acquisition System (ANDAS) based upon the short haul Zigbee networking standard is proposed. It employs a very thin (135 um) hybrid microminiature sensor assembly (MSA) and a host module with USB interface. At several nodes on the aircarft, MSAs are cemented for measurement. They transmit the measured data to the host module plugged into a PC. The MSA incorporates an integrated sensor (capable of measuring pressure, temperature, acceleration and surface strains), a microcontroller, a Zigbee transceiver and a battery for power. The host module incorporates a microcontroller and a Zigbee transceiver. In Phase I these modules were designed after trade-off analyses and experimental evaluation of the sensors and networking hardware. Based upon the design, the PCB packages for the MSA and the host module were built for initial characterization and testing during Phase II. In this phase the MSA design would be refined as a cement-and-forget-device (except for the battery).

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Test and measurement of airplanes during flight as well as on ground with various simulated loading scenario. Devices cab used in hard to reach remote locations and locations to which hardwired instrumentation is not possible. The low cost MSAs are designed for cement-and-forget applications with long battery life. By adding real time aircraft dynamic modal assessment software, real-time correlation and control algorithms, the MSA could be utilized in light weight, flexible and unstable aircraft structures.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The resulting technology can be employed many commercial test applications. It can also be used in hard to access or remotely located nodes on any structural test and measuremnt scenario. Examples of these applications include monitoring of power plants, vehicle engines, medically implanted devices for monitoring of human body etc.

TECHNOLOGY TAXONOMY MAPPING
Integrated Robotic Concepts and Systems
Airframe
Controls-Structures Interaction (CSI)
Launch and Flight Vehicle
Simulation Modeling Environment
Testing Facilities
Testing Requirements and Architectures
Structural Modeling and Tools
On-Board Computing and Data Management
Pilot Support Systems
Biomedical and Life Support
Architectures and Networks
Autonomous Control and Monitoring
RF
Instrumentation
Data Acquisition and End-to-End-Management
Data Input/Output Devices
Portable Data Acquisition or Analysis Tools
Portable Life Support
Highly-Reconfigurable

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Research Support Instruments, Inc.
4325-B Forbes Blvd.
Lanham, MD 20706-4854
(301) 306-0010

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
(978) 689-0003

Expected Technology Readiness Level (TRL) upon completion of contract: 4 to 5

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Research Support Instruments, Inc. (RSI) proposes to develop the Friction-Sensing Reflector Array Patches (FRAP), a technology that will measure the shear stress distribution on aerodynamic surfaces in ground test facilities with high resolution, sensitivity, and bandwidth. Unlike the oil-film interference method, FRAP patches will not be thinned as a function of time during a test. No knowledge of the streamlines of the flow will be needed in order to calculate the local stress distribution; this will avoid the tracers needed with the oil-film interference approach. Flexible patches of FRAP arrays, inexpensive due to simple, mass-production-compatible microfabrication techniques, will be interrogated using a light source and camera. FRAP will be independent of the flow species and applied as a very thin, flexible, adhesive material. The Phase II goals will be to improve the design and fabrication of the sensors, fully calibrate taking into account competing effects such as normal forces and temperature, demonstrate feasibility in a wide range of test environments from subsonic to heated and cold supersonic, and provide prototype units to NASA. The result will be a product that will address a critical NASA instrumentation need.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
RSI will use its experience in microfabricated structures and sensors to employ a highly innovative technology – a sheer-stress-sensing reflecting array – in order to non-intrusively measure skin friction in NASA ground test facilities. The FRAP technology will avoid the use of a depleted fluid and tracer elements that are inherent to the existing oil film interferometry method, and will address a key NASA need for non-instrusive diagnostics as well as flight test diagnostics and vehicle monitoring.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Several non-Government applications are possible. Flow sensors have a lucrative commercial market in manufacturing (for process monitoring) and medical diagnostics, as well a healthy market in scientific applications. Commercialized flow sensors are used in applications ranging from industrial processing and medical diagnostics to high-speed shock testing in chemical explosions. It is expected that the newly developed FRAP arrays will compete aggressively in these existing markets. In addition to NASA, target U.S. government customers will be the Air Force (for ground testing, flight tests, and vehicle monitoring) and the Navy (for similar applications).

TECHNOLOGY TAXONOMY MAPPING
Testing Facilities
Telemetry, Tracking and Control
Instrumentation
Optical
Sensor Webs/Distributed Sensors
Composites
Multifunctional/Smart Materials

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Traclabs, Inc.
8620 N. New Braunfels Avenue, Suite 603
San Antonio, TX 78217-3856
(210) 637-7819

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Russell Bonasso
r.p.bonasso@nasa.gov
8610 N. New Braunfels, Suite 110
San Antonio,  TX 78217-0000
(281) 483-2738

Expected Technology Readiness Level (TRL) upon completion of contract: 3 to 4

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Automation and autonomy are key elements in realizing the vision for space exploration. The NASA Exploration Technology Development Program (ETDP) has been developing several core autonomy capabilities, one of which is called a procedure representation language (PRL). PRL can be automatically translated into code that can be executed by NASA-developed autonomous executives. Another type of automation being developed by ETDP is automated planning aids. These will be needed to increase the number of missions that existing levels of flight personnel must be able to handle. But PRL has few constructs to enable automated planners and schedulers to take advantage of the procedures resulting from PRL. In Phase 1 we developed extensions to PRL to add planning information – resource, constraints and sub-procedural information – so as to produce code useable by automated planning software. In this project, we propose to develop an interactive planning aid for flight controllers to show that such an aid can process our enhanced PRL files to generate mission plans and to test their feasibility via an execution system. Besides refining our previous modeling efforts, this work will show that the availability of computer-useable planning information can lead to practical applications of NASA's automated planning efforts.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Procedures are at the core of all NASA missions, especially human space missions. Mission planning is also at the core of all space missions due to the high cost of space assets such as astronauts, equipment and communication links. Our technologies will have applications across many NASA programs, from Mission Control to on-board NASA vehicles and outposts. We expect applications of our technology to immediately impact NASA's Exploration Technology Development Program (ETDP). Two areas of ETDP will be immediate beneficiaries of this technology. First, the Centaur robot at NASA JSC is already using a preliminary version of PRL and a simple user interface to allow a remote supervisor to command the Centaur over a communication link. Our work will provide connection to automated planning technologies. Second, the Automation for Operations (A4O) project run out of NASA ARC is using PRL to enhance spacecraft operations. Our PRL extensions and planning technology would also be immediately applicable to spacecraft operations. We will work closely with representatives of both of these projects (Dr. Robert Ambrose at NASA JSC and Dr. Jeremy Frank at NASA ARC respectively) during Phase 1 to ensure our relevance to these two projects.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The military is currently a large customer for unmanned vehicle operations. Unmanned vehicles, both air and ground, are becoming more common in battlefield situations. In addition, Congress has mandated that one-third of all military vehicles must be unmanned by 2015. As these unmanned vehicles are increasingly deployed in tandem with dismounted forces coordinating software will be necessary to ensure successful operations. Procedures and mission planning play a large role in these kinds of operations. We also see a need for procedures and planning in operations such as refineries, chemical plants, nuclear and other power plants and any installation that has established standard operating procedures that must be carefully followed under often stressful situations, but whose procedures are currently paper, just like NASA's. Moving these industries to electronic procedures tied to system telemetry and integrated with planning will allow for more efficient and safer operations. We expect to tailor PRL and our PRL-related software to these industries and team with existing operators to evaluate and embed our software. Thousands of such facilities exist in the United States alone. Even with a small market penetration, TRACLabs Inc. will have significant revenues to invest in new products and services.

TECHNOLOGY TAXONOMY MAPPING
Autonomous Reasoning/Artificial Intelligence
Database Development and Interfacing
Human-Computer Interfaces
Software Development Environments

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
S&K Aerospace
63066 Old Hwy 93
St Ignatius, MT 59865-9008
(406) 745-7500

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Arthur Molin
amolin@ska-corp.com
63066 Old Hwy 93
St Ignatius,  MT 59865-9008
(281) 480-1453

Expected Technology Readiness Level (TRL) upon completion of contract: 7 to 8

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
NASA captures and distributes operational knowledge in the form of procedures. These procedures are created and accessed by a range of people performing many different jobs. These people have different needs for procedure data and different ways of interacting with procedures. We propose an Procedure Integrated Development Environment which will present different editing modes and different views depending on the users and tasks, but will use a consistent data representation for all users. We propose to connect the editing environment to other tools and systems that are useful to procedure development, including recon databases and verification tools. We propose to build this environment on the basis of an existing prototype, PRIDE, which was developed for the Engineering Directorate of Johnson Space Center.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
An integrated development environment for procedures would improve the efficiency of the procedure authors by allowing them to concentrate on the fields in which they are expert, without worrying about details of editing and formatting. It would present each user with a procedure view that is most useful for the job at hand. It would connect up to the needed data sources and other related tools, such as workflow tools. It would provide a direct interface to simulation tools, which allow users to work out problems with procedures at the desktop, instead of requiring expensive high-fidelity simulations to be run to find minor problems.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
A procedure development environment would be potentially useful to a wide range of commercial and industrial interests that use a large number of procedures in their business. The electronic procedures that are proposed here would be of considerable interest to those industries that rely on procedures that could be automated, due to the availability of data sources. These industries include oil and chemical processing, power plants, and robotic assembly plants.

TECHNOLOGY TAXONOMY MAPPING
Human-Robotic Interfaces
Operations Concepts and Requirements
Autonomous Reasoning/Artificial Intelligence
Data Acquisition and End-to-End-Management
Human-Computer Interfaces
Software Development Environments
Software Tools for Distributed Analysis and Simulation

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Aries Design Automation, LLC
6157 N Sheridan Road, Suite 16M
Chicago, IL 60660-5818
(773) 856-6633

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Miroslav Velev
miroslav.velev@aries-da.com
6157 N Sheridan Road, Suite 16M
Chicago,  IL 60660-5818
(773) 856-6633

Expected Technology Readiness Level (TRL) upon completion of contract: 6 to 7

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
We will develop an efficient tool for formal verification of PowerPC 750 executables. The PowerPC 750 architecture is used in the radiation-hardened RAD750 flight-control computers that are utilized in many space missions. The resulting tool will be capable of formally checking: 1) the equivalence of two instruction sequences; and 2) properties of a given instruction sequence. The tool will automatically introduce symbolic state for state variables that are not initialized and for external inputs. We bring a tremendous expertise in formal verification of complex microprocessors, formal definition of instruction semantics, and efficient translation of formulas from formal verification to Boolean Satisfiability (SAT). We will also produce formally verified definitions of the PowerPC 750 instructions used in the project, expressed in synthesizable Verilog; these definitions could be utilized for formal verification and testing of PowerPC 750 compatible processors, for FPGA-based emulation of PowerPC 750 executables, as well as in other formal verification tools to be implemented in the future.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The benefits to NASA will include state-of-the-art SAT-based technology for formal verification of PowerPC 750 executables. The PowerPC 750 architecture is used in the radiation-hardened RAD750 flight-control computers that are utilized in many space missions, including Deep Impact, the Mars Reconnaissance Orbiter, the Mars Rovers, and is planned to be used in the Crew Exploration Vehicle that will become operational in 2011. NASA will benefit from such a tool by being able to: 1) ensure that compiler optimizations have not introduced bugs in an executable; 2) formally verify properties of code sequences that are written directly in assembly language for performance reasons; and 3) formally verify properties of executables provided by other organizations that do not supply the source code. After Phase 2, our technology will become applicable to any microprocessor architecture to be adapted by NASA in the future, as the tool that we will develop will allow to automatically generate a symbolic simulator for any instruction set architecture, given a formal definition of its semantics. As another deliverable, NASA will get synthesizable Verilog definitions of the PowerPC 750 instructions used in the project; these definitions could be utilized for formal verification and testing of PowerPC 750 compatible processors, for FPGA-based emulation of PowerPC 750 executables, and for implementation of internal formal verification tools in the future.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The capability to automatically generate a symbolic simulator for an ISA, given a formal definition of its semantics, will dramatically increase the potential for commercialization of the proposed technology. All companies that either manufacture microprocessors or develop IP of microprocessors, as well as all their clients, will be potential users. As embedded microprocessors are increasingly used in safety critical applications, it will become the norm to formally verify the executables for such applications. The immediate non-NASA commercialization will target the members of Power.org, an organization whose purpose is to develop, enable, and promote PowerPC Architecture technology. Power.org has over 40 member companies. The PowerPC architecture is used in many safety-critical embedded systems. Non-NASA customers of this technology will similarly be able to use the tool to formally verify the equivalence of two instruction sequences, and to formally check properties for a given executable. Furthermore, non-NASA customers will be able to use the tool to detect security vulnerabilities in programs, thus ensuring their robustness to security attacks, as well as to detect malicious intent in executables. The last application will allow the technology to be used in sophisticated virus scanners, utilizing formal reasoning to ensure robustness to software obfuscations of malicious intent.

TECHNOLOGY TAXONOMY MAPPING
Operations Concepts and Requirements
Simulation Modeling Environment
Testing Facilities
Testing Requirements and Architectures
Spaceport Infrastructure and Safety
Guidance, Navigation, and Control
On-Board Computing and Data Management
Pilot Support Systems
Architectures and Networks
Autonomous Control and Monitoring
Autonomous Reasoning/Artificial Intelligence
Computer System Architectures
Expert Systems
Human-Computer Interfaces
Software Development Environments
General Public Outreach
Highly-Reconfigurable
Radiation-Hard/Resistant Electronics

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Structured Materials Industries, Inc.
201 Circle Drive N., Suite 102-103
Piscataway, NJ 08854-3723
(732) 302-9274

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Gary Tompa
gstompa@aol.com
201 Circle Drive North, Suite 102/103
Piscataway,  NJ 08854-3723
(732) 302-9274

Expected Technology Readiness Level (TRL) upon completion of contract: 4

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Field Programmable Gate Arrays are a widely used technology; however, they are generally limited in reprogrammability. Radiation hard, low power and high density ReProgrammable FPGAs (RP-FPGAs) would be a tremendous asset in long duration missions. The ability to adapt to changing mission profiles and on board capabilities is highly desirable. We are developing a RP-FPGA technology for flight use. In Phase I we have proven basic device concepts—increasing temperature stability, demonstrating scalable production process, and developing refining Phase II tasks. We have achieved this success by working with a leading FPGA manufacturer, and the enabling materials technology inventor and others. The range of technical interactions has also been increased as a result of the Phase I effort. In Phase II we will develop a viable demonstration prototype that will enable routine Phase III device manufacture. Present work has shown the desired end should be well achievable.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Long duration missions often must adapt to changes in mission capabilities and mission profiles. This project will provide NASA mission planners (and prime contractor builders) with a significant enhancement in device programming capability. The ReProgrammable FPGA will serve (1) near- and far-Earth orbit missions, (2) return to moon mission, (3) go to Mars missions, and (4) other interplanetary missions. The technology developed will further NASA's contributions to the nation's needs as a whole

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
FPGAs serve a wide range of applications as an alternative to ASICs. Highly desirable is a reprogrammable FPGA. Product revisions / upgrades are often constrained by past programmed logic or suffer from extra cost as programmed arrays must be replaced. A reprogrammable gate array would be a significant benefit to product designers and enable a new form of product upgrade to be easily carried out - hence offering opportunity to gain a significant market share. Radiation resistant applications span DoD, DoE, and civilian space use. Non-hardened devices are useful to commercial consumers in general.

TECHNOLOGY TAXONOMY MAPPING
Ultra-High Density/Low Power
Highly-Reconfigurable
Radiation-Hard/Resistant Electronics

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Acellent Technologies, Inc.
835 Stewart Drive
Sunnyvale, CA 94085-4514
(408) 745-1188

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Shawn Beard
sjb@acellent.com
835 Stewart Drive
Sunnyvale,  CA 94085-4514
(408) 745-1188

Expected Technology Readiness Level (TRL) upon completion of contract: 5 to 6

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Under Project Constellation, NASA is developing a new generation of spacecraft for human spaceflight. A significant percentage of the structures used in these spacecraft will be made of composite materials, and the Ares V payload shroud will be one of the largest composite structures ever built. This offers many challenges, not only for design and manufacturing, but also for inspection and maintenance. Inspection of large composite structures using traditional NDE methods is time consuming, expensive, and often not possible when access is limited (e.g. covered by a thermal protection system), resulting in a conservative (higher weight) design. Acellent proposes to develop a robust, state-of-the-art structural health monitoring (SHM) system to overcome these concerns. The Phase II will optimize the design and quantify the benefits for SHM on the Ares V payload shroud, and then expand the results to include other Ares V components such as the Altair Lunar Lander Structure, Earth Departure Stage (EDS) payload adapter, forward skirt and intertank, and the Core-to-EDS interstage. The proposed solution will be capable of detecting and quantifying damage with a high probability of detection (POD), accurately predicting the residual strength and remaining life of the structures with confidence, and providing information that will allow appropriate preventative actions on the monitored structure.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The proposed system directly addresses the need for structural inspection of the new generation of spacecraft being developed in Project Constellation. The system is specifically being designed for large composite structures such as the Ares V payload shroud, and can be applied to other Ares V components such as the Altair Lunar Lander Structure, Earth Departure Stage (EDS) payload adapter, forward skirt and intertank, and the Core-to-EDS interstage. It is expected that once developed, the proposed system will provide the following advantages over current inspection techniques: Low-cost built-in reliable damage detection system for monitoring of structure integrity; Improved personnel safety; Improvement of composite bonded joint reliability; Ease of installation; Reduction of labor time; Real-time convenience and automation of inspection during service. With the proposed system, the structural monitoring and functionality evaluation can be performed while the structure remains in service.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The technology developed under the project together with Acellent's current SMART Layer technology offers the potential to provide a complete solution for a wide range of structural analysis, evaluation, and maintenance requirements. The resulting products will enable a number of high value economic benefits to the Federal Government including: Increase in service life for manned and unmanned aircraft; Reduced life-cycle costs from improved maintenance scheduling; Reduced structure or vehicle downtime for inspection; Reduced costs for structural analysis and evaluation; Increased structural reliability. The work will be conducted in close collaboration with the U.S. Army, U.S. Air Force, U.S. Navy and industrial partners such as The Boeing Company, ATK-Thiokol, and Lockheed Martin to ensure that this research will be directly beneficial to them.

TECHNOLOGY TAXONOMY MAPPING
Airframe
Modular Interconnects
Structural Modeling and Tools
Tankage
Autonomous Control and Monitoring
Instrumentation
Data Acquisition and End-to-End-Management
Portable Data Acquisition or Analysis Tools
Sensor Webs/Distributed Sensors
Ceramics
Composites
Metallics
Multifunctional/Smart Materials

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Advanced Scientific Concepts, Inc.
135 E. Ortega Street
Santa Barbara, CA 93101-1674
(805) 966-3331

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Bradley Short
bshort@ASC3d.com
135 E. Ortega Street
Santa Barbara ,  CA 93101-1674
(805) 966-3331

Expected Technology Readiness Level (TRL) upon completion of contract: 7 to 8

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
With NASA's exploration initiative to return to Lunar Exploration and eventual human exploration of Mars, NASA has an increased need for an Autonomous Rendezvous and Docking (AR&D) solution. First generation rendezvous sensors used video guidance and required extensive human intervention and ground control. Data latency in these systems is problematic and has uncovered the need for an autonomous rendezvous and docking system. Scanning Ladar and stereo video have significant shortcoming and have not proven they can provide a solution to reduce the reliance on human interaction during proximity operations. ASC's Flash Ladar video cameras can provide the 6 Degree-of-freedom data in real time, not available in any other video system. Advanced Scientific Concepts Inc. (ASC) is a small business that has developed a number of 3D flash LADAR systems. Flash Ladar Video Cameras (FLVC) are 3D vision systems that return range and intensity information for each pixel in real time. The ASC camera with its 128x128 3D array is the equivalent of 16000 range finders on one chip. This allows the sensor to act as a 3D video camera with functionality well beyond just range finding. Its small size, low power and fast range data frame rate (30Hz) allows the sensor to be configured for a variety of rendezvous and proximity missions.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
ASC is working with SpaceX to deploy a 3D FLVC system for rendezvous and docking on one of their space missions. This Phase II will be the first step in developing a commercial AR&D product. ASC will work with SpaceX to launch and increase the TRL of this sensor. Flash Ladar can meet NASA's requirements for a sensor that will increase the success of EDL operations for Mars Landed Exploration, Exploration of Moons (ALHAT, Jupiter Icy Moons), Asteroid and comet rendezvous and sample return. Flash Ladar will have may other space applications. This sensor will increase the success of NASA operations such as: • Rover Mobility and Navigation • Topographical Mapping • Mars Landed Exploration • Exploration of Moons (ALHAT, Jupiter Icy Moons) • Asteroid and Comet Rendezvous and Sample Return • ISS Rendezvous and Docking • Space Situational Awareness • Rock Abundance and Distribution Maps

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
ASC is pursuing many non-NASA applications. Collision avoidance to save pedestrians and prevent vehicle damage, Helicopter landing in BrownOut conditions, Surveillance, Terrain Mapping, Autonomous Navigation for UGVs, unmanned surface vehicles (USVs) and UAV, Smart intersection, Ladar brakes, Robotics, Machine Vision, Hazard Material Detection and Handling, Underwater 3D Imaging, Sub Nanosecond Dynamic Imaging and data transmission, consumer electronics.

TECHNOLOGY TAXONOMY MAPPING
Perception/Sensing
Spaceport Infrastructure and Safety
Telemetry, Tracking and Control
Guidance, Navigation, and Control
Autonomous Control and Monitoring
Optical

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)
Fred Roe
roe@aos-inc.com
6767 Old Madison Pike Suite 410
Huntsville,  AL 35806-2181
(256) 971-0036

Expected Technology Readiness Level (TRL) upon completion of contract: 5

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
This Phase II SBIR project will provide real time, relative six Degree of Freedom (6DoF) information to the crew of the ORION for docking. Our technical innovation performs optimized correlation (ULTOR<SUP>REG</SUP>), using video from the centerline (boresight) camera, to accurately locate features of interest, and marry that with a passive pose and position algorithm (ULTOR<SUP>REG</SUP> P3E) to accurately measure relative position and pose. In Phase II this ULTOR<SUP>REG</SUP> P3E process will be ported to an ORION VPU emulator, integrated with a centerline camera emulator, and demonstrated in a hardware in the loop (HWIL) docking experiment. The benefits of this program include: • No additional weight or volume added to the weight constrained ORION baseline design. • A backup docking sensor capability using different physics. • The sensor output data will serve as an astronaut aid, working with the same imagery the astronaut views, and providing calibrated measurements. • The sensor can work with Star Tracker imagery for long range relative navigation. • The sensor data can be used directly with the Orion control system, allowing the astronaut to serve a supervisory role, relieving workload. • Supports Lunar orbit docking (uncrewed Orion). • Compatible with future robotic missions and robotic systems.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The proposed system supports the Exploration initiative and has the following NASA applications: • Orion crew aid and backup system for docking • COTS station keeping/berthing to resupply the ISS • Future Hubble deorbit or servicing missions • Earth orbit rendezvous for lunar transfer • Lunar orbit rendezvous for return to Earth • Lunar landing (georegistration with landing site maps) • MARS rendezvous, landing and return

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The proposed system has the following Non-NASA applications: • Satellite servicing • Commercial Space • Georegistration • Robotic Assembly • Security systems • DOD-Operationally Responsive Space (ORS) • DOD black programs

TECHNOLOGY TAXONOMY MAPPING
Testing Requirements and Architectures
Telemetry, Tracking and Control
Attitude Determination and Control
Guidance, Navigation, and Control
Pilot Support Systems
Optical

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Advanced Scientific Concepts, Inc.
135 E. Ortega Street
Santa Barbara, CA 93101-1674
(805) 966-3331

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Howard Bailey
hbailey@asc3d.com
135 E. Ortega Street
Santa Barbarta ,  CA 93101-1674
(805) 966-3331

Expected Technology Readiness Level (TRL) upon completion of contract: 5 to 6

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
With NASA's exploration initiative to return to Lunar Exploration and eventual human exploration of Mars, NASA has an increased need for advanced Autonomous Precision Landing and Hazard Detection and Avoidance solutions. Scanning LADAR and stereo video have significant shortcoming while ASC's Flash LADAR 3D video cameras can provide frames of 3D data in real time at video rates. The proposed high-sensitivity unit cell and ROIC enhances the sensitivity of ASC's standard ROIC by a very large factor as well as decreasing the associated unit cell area by a large factor. This enhancement reduces required laser power, reduces focal plane array power, allows PIN diode arrays to compete with APD detector arrays and increases the number of pixels possible in a given ROIC area. Advanced Scientific Concepts Inc. (ASC) is a small business that has developed a number of 3D flash LADAR systems. Flash Ladar Video Cameras (FLVC) are 3D vision systems that return range and intensity information for each pixel in real time. The ASC camera with its 128x128 3D array is the equivalent of 16000 range finders on one chip. This allows the sensor to act as a 3D video camera with functionality well beyond just range finding. Its small size, low power and fast range data frame rate (30Hz) provides an ideal Landing and Hazard Detection and Avoidance sensor

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Flash Ladar can meet NASA's requirements for a sensor that will increase the success of EDL operations for Mars Landed Exploration, Exploration of Moons (ALHAT, Jupiter Icy Moons), Asteroid and comet rendezvous and sample return. Flash Ladar will have may other space applications. This sensor will increase the success of NASA operations such as: • Rover Mobility and Navigation • Topographical Mapping • Mars Landed Exploration • Exploration of Moons (ALHAT, Jupiter Icy Moons) • Asteroid and Comet Rendezvous and Sample Return • ISS Rendezvous and Docking • Space Situational Awareness • Rock Abundance and Distribution Maps

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
ASC is pursuing many non-NASA applications. Collision avoidance to save pedestrians and prevent vehicle damage, Helicopter landing in BrownOut conditions, Surveillance, Terrain Mapping, Autonomous Navigation for UGVs, unmanned surface vehicles (USVs) and UAV, Smart intersection, Ladar brakes, Robotics, Machine Vision, Hazard Material Detection and Handling, Underwater 3D Imaging, Sub Nanosecond Dynamic Imaging, and consumer electronics.

TECHNOLOGY TAXONOMY MAPPING
Human-Robotic Interfaces
Integrated Robotic Concepts and Systems
Perception/Sensing
Teleoperation
Telemetry, Tracking and Control
Attitude Determination and Control
Guidance, Navigation, and Control
Optical

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
nLight Photonics
5408 NE 88th Street, Building E
Vancouver, WA 98665-0990
(360) 566-4471

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Steve Patterson
steve.patterson@nlight.net
5408 NE 88th Street, Building E
Vancouver,  WA 98665-0990
(360) 566-4460

Expected Technology Readiness Level (TRL) upon completion of contract: 6

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
nLight has demonstrated highly-uniform APD arrays based on the highly sensitive InGaAs/InP material system. These results provide great promise for achieving the performance and uniformity requirements necessary to enable 3D LIDAR applications such as autonomous precision landing and hazard detection avoidance. The high degree of uniformity demonstrated offers the potential for biasing the entire APD FPA at a single bias point. This is expected to lead to a dramatic reduction in the complexity of the integrated circuit driver, and allow for scaling to arrays of 256x256 elements and larger. Combined with reduced transmitter power requirements due to high detector sensitivity and low noise, this will ultimately lead to improved compactness, low mass, improved resolution, and low power consumption – all of which are of concern in NASA applications such as the un-manned Lunar or Mars landing vehicles. In the proposed Phase 2 program, nLight will optimize the performance and demonstrate manufacturability of the highly uniform epitaxy demonstrated in the first phase. These InGaAs APDs are expected to show gains in excess of 10, with very low dark current and noise factors, making them well suited for LIDAR detection. Highly-uniform dense focal plane arrays of various sizes up to 256x256 elements will be fabricated and tested. These arrays will be flip-chip bonded to read-out integrated circuitry for testing in 3D flash LIDAR cameras.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
1. Autonomous precision landing including hazard detection and avoidance 2. Spacecraft docking 3. Terrestrial and space-based atmospheric sensing

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
1. Military - Eyesafe rangefinders 2. Military - Covert, eyesafe surveillance through obfuscated conditions such as smoke, fog, rain 3. Military - Covert, eyesafe surveillance in MOUT (military operations urban terrain) and dense canopy/foliage settings 4. Military - Unmanned autonomous ground and airborne vehicles 5. Consumer - Adaptive cruise control, unmanned parking 6. Medical - Medical imaging

TECHNOLOGY TAXONOMY MAPPING
Perception/Sensing
Guidance, Navigation, and Control
Autonomous Control and Monitoring
Optical
Photonics
Optical & Photonic Materials
Semi-Conductors/Solid State Device Materials

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Q-Peak, Inc.
135 South Road
Bedford, MA 01730-2307
(781) 275-9535

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Glen Rines
grines@qpeak.com
135 South Road
Bedford,  MA 01730-2307
(781) 275-9535

Expected Technology Readiness Level (TRL) upon completion of contract: 4 to 5

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
In the Phase I program we demonstrated the efficacy of the proposed innovation by experimentally demonstrating an improvement in slope efficiency of ~11% by changing the pump wavelength from 806-nm to the 863-nm, which directly pumps the upper laser level of the 1047-nm laser transition in Nd:YLF. This level of improvement in efficiency is significant for space-based systems where overall efficiency is of great value. In addition to the optical-to-optical efficiency improvement, there is a lower heat load in the gain medium reducing the cooling requirements. In this work we take advantage of our broad experience with Nd:YLF and the unique advantages of the MPS(TM) design to develop an all-solid-state, compact, conductively-cooled laser system operating in 1-&#956;m region with an output energy of nominally 30 mJ and a pulse repetition frequency (PRF) of 30 Hz. The specific goal of this project will be to produce a laser design that is suitable for use in 3-D flash ladar systems housed in spacecraft and used for automated landing and hazard avoidance in difficult terrain and to deliver to NASA LaRC a working prototype of this laser design that is suitable for use in terrestrial testing of flash ladar systems when it is integrated with a suitable ladar receiver.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The proposed work has direct application to NASA programs for entry, descent and landing (EDL) systems in future lunar and planetary exploration missions. In particular, flash ladar systems that can provide real-time, three-dimensional terrain mapping capability would be useful for automation of terminal descent of unmanned vehicles. For this application the emphasis must be placed on compactness, reliability, efficiency, low weight, and high performance. The system concept we propose provides improved performance, due to higher efficiency, scalability, and modularity and the potential for improvement in overall system efficiency and the reduction in the required number of diode pump lasers.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The proposed high-efficiency, high-energy MPS technology to be developed in this Phase II program would be an extension of our existing diode-pumped product line and would offer a step-up in efficiency and energy from our existing products. A MPS Nd:YLF laser with 10 to 100 mJ/pulse fundamental energy, and high beam quality, with the addition of harmonic generation for some systems, 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.

TECHNOLOGY TAXONOMY MAPPING
Telemetry, Tracking and Control
Attitude Determination and Control
Guidance, Navigation, and Control
Optical

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Seldon Laboratories, LLC
PO Box 710
Windsor, VT 05089-0710
(802) 674-2444

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Beatrice Iliescu
biliescu@seldontech.com
PO Box 710, 7 Everett Lane
Windsor,  VT 05089-0710
(802) 674-2444

Expected Technology Readiness Level (TRL) upon completion of contract: 3 to 4

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Seldon Technologies will further test and develop its patented carbon nanotube filtration technology to NASA's Lunar Exploration challenges. This project focuses on the problem of efficient removal of nanoscale (10-100nm) and larger lunar dust particulates from air using a nanostructured fiber media containing carbon nanotubes. Lunar dust presents an important challenge to Lunar exploration and habitation, nonetheless it has some unique properties that can be taken advantage of in designing specialized filtration media capable of achieving efficient removal from air. As demonstrated in Phase I, rough surface shape combined with the electrically and magnetically charged nature of the dust means that rough, electrically activated filtration media will be effective tools for filtration. Seldon's work with its proprietary fused carbon nanotube media offers a unique path to significant new purification applications that meet important needs for NASA's Lunar Exploratory Initiatives. The unique physical properties of the carbon nanotubes will be capitalized upon to create a filtration media with high efficiency and low pressure drop that can be electrically powered to enhance filtration of charged lunar dust particles.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
There are important applications for this product throughout NASA's operations from protecting human life on lunar explorations, to cleaning the air of clean rooms, to reducing emissions from its vehicle fleet. The potential health and environmental impacts of airborne ultrafine particles are now known to be significant. Typical filtration solutions struggle to remove these very small contaminants. As a result, energy is wasted and, because of cost, some filtration applications are just not pursued. Products based on this technology will protect astronauts and sensitive equipment from lunar dust in the air handling systems of spacecraft and even in personal breathing apparatus. They will efficiently remove very small particulates from the air in NASA's clean rooms. Finally, filters will help to clean the emissions from the many earthbound diesel and other engines NASA operates to help reduce NASA's carbon footprint and improve the health of its employees and communities.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
According to the Centers for Disease Control the inhalation of fine particles is now estimated to be the ninth leading cause of death in the US. In the past, the best, most expensive filters have typically been used in clean rooms where the quality of products are dependent on the lack of contaminants in the environment. The market size for clean room air filters is estimated to be approximately $0.5 billion worldwide. As the production of sensitive equipment increases and employers acknowledge the health risks of their employees' exposure to some ultrafine particles, the market for such filters will continue to rise dramatically. The estimated global market size for air purification equipment is estimated to be about $2.5 billion. The tremendous surface area of Seldon's media and its ability to effectively capture and/or destroy pathogens with a relatively open structure gives the product an extended life making it a more effective barrier than available technology. Further, the material's high electrical conductivity offers an additional means for enhancing the purification efficiency by adding electrostatic attraction capabilities. Other product opportunities include incorporating the media into facemasks, gas masks, vehicle cabin air filters, and filters in building HVAC systems.

TECHNOLOGY TAXONOMY MAPPING
Air Revitalization and Conditioning
Sterilization/Pathogen and Microbial Control
Composites

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
MicroCell Technologies
2 Park Drive, Unit 4
Westford, MA 01886-3525
(978) 692-2613

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Michael Kimble
mkimble@reactive-innovations.com
2 Park Drive, Unit 4
Westford,  MA 01886-3525
(978) 692-4664

Expected Technology Readiness Level (TRL) upon completion of contract: 4 to 5

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
NASA desires to generate and store gases including oxygen and nitrogen at sub-critical conditions as a part of its lunar and spacecraft atmospheric systems. Oxygen at pressures up to 3000 psia is particularly desired for refilling storage tanks for lunar and in-flight applications including recharging high-pressure gas bottles for EVA/EMU, lunar rovers and surface hoppers. To address these needs, Reactive Innovations, LLC proposes to continue developing and delivering a compact high-pressure oxygen concentrator that can take low-pressure atmospheric gas and generate a separate stream of high-pressure pure oxygen. During a Phase I program, we applied our high-pressure reactor hardware to separate and compress oxygen from ambient pressure air and oxygen streams in both dry and saturated conditions. We used this information to develop a predictive performance model for the oxygen concentrator to aid in a conceptual design and to allow NASA mission planners to conduct trade studies on metrics including the generated oxygen rate per compressor mass and power requirements. For the Phase II program, we will produce operational prototype electrochemical concentrators that produce 3000 psia oxygen from ambient pressure sources of air or oxygen. These concentrators will be sized to produce 2 kg of oxygen at 3000 psia within a 24 hour time period. By the end of the Phase II effort, this concentrator will be at a Technology Readiness Level of 4-5.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Applications of this technology to NASA include generating oxygen for sub-critical storage on lunar habitats and within spacecraft environments. This technology will enable pressurized oxygen up to 3000 psia to be used for applications where cryogenic storage is not feasible or desired. Furthermore, NASA desires to use re-configurable modules that can function in dual-use or multi-use systems in these habitation environments. With our modular reactor technology, this process unit can be used for other atmospheric gas processing applications.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Non-NASA commercial applications of the proposed technology could find use in portable oxygen generators and concentrators for medical usage. This could be used in hospital and home therapy applications. Other applications of the oxygen compressor include on-site oxygen production for industrial and manufacturing needs, and on-board oxygen generation on aircraft.

TECHNOLOGY TAXONOMY MAPPING
Chemical
Propellant Storage
Air Revitalization and Conditioning
Biomedical and Life Support
Production
Portable Life Support
Energy Storage
Renewable Energy

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
NanoMaterials Company
15 North Bacton Hill Road
Malvern, PA 19355-1005
(610) 695-0081

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Nicholas V. Coppa
ncoppa@nanomaterialscompany.com
15 North Bacton Hill Road
Malvern,  PA 19355-1005
(610) 695-0081

Expected Technology Readiness Level (TRL) upon completion of contract: 5 to 6

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
This purpose of this project is to develop a spray drying prototype to for the recovery and recycle of water from concentrated waste water recovery system brine. Spray drying is a one step, continuous process where a solution, slurry, sludge or paste is transformed into a dry solid and clean water. The dry solids powder is easy to transfer and does not foul surfaces. The process is suitable for dewatering brine from the vapor compression distillation processor and other sources. It may serve as a backup processor for one or more existing water recovery systems unit processors. We will employ alternative heating methods and advanced process control.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Potential applications are brine dewatering, water recovery in life support systems for: the international space station, the Lunar surface, Mars transit and Mars surface missions. Additionally, spray drying can be used for the drying of high-solids-content moist matterSpray drying is well suited for the single step drying of liquid solutions or suspensions to a dry free solid while producing clean recovered water. A system of modest size can also serve as a backup unit or alternative for other water recovery processors.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Innovations in control and efficiency will be find applications in the production of pharmaceuticals. The focus on water recovery will draw interest from the chemical manufacturing and advanced materials industries. Spray drying is a promising technique allow for the optimization of precursor production to produce highest quality nanomaterials at the fraction of the current cost thus enabling many nanomaterial applications

TECHNOLOGY TAXONOMY MAPPING
Air Revitalization and Conditioning
Biomedical and Life Support
Waste Processing and Reclamation
Autonomous Reasoning/Artificial Intelligence
Microgravity
Ceramics
Composites
Optical & Photonic Materials
Multifunctional/Smart Materials
Superconductors and Magnetic

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
UMPQUA Research Company
PO Box 609
Myrtle Creek, OR 97457-0102
(541) 863-7770

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
James Akse, Ph.D.
akse@urcmail.net
PO Box 609
Myrtle Creek,  OR 97457-0102
(541) 863-2653

Expected Technology Readiness Level (TRL) upon completion of contract: 4

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
A nonhazardous urine pretreatment system prototype is proposed that will stabilize urine against biological growth or chemical instabilities without using hazardous chemicals. Untreated urine fosters biological growth, ammonia off-gassing, creation of bio-solids, and inorganic precipitates, which foul water and air reclamation hardware. The current Russian system employs hexavalent chromium, a strong oxidant and carcinogen, and sulfuric acid to stabilize urine (pH=1.8), while the future American system utilizes Oxone„¥, a strong oxidant, potassium hydrogen sulfate, and potassium benzoate to stabilize urine (pH=2.4). Urine stabilized by these methods requires triple and double containment, respectively. Chemical storage, handling, and delivery of pretreatment chemicals are also problematic due to their hazardous nature and low pH, which significantly increases Equivalent System Mass. The proposed prototype will utilize non-oxidizing biocides in combination with nontoxic and noncorrosive solid phase urine acidification to stabilize urine at much higher pHs (3.6-5.5). This approach has stabilized urine effectively for over 57 days during the Phase 1 program. The innovative prototype will fulfill an unmet need for safe, efficient, automated urine pretreatment for current and future NASA missions. The Phase 2 project will automate the nonhazardous urine pretreatment system, and deliver a fully functional Prototype suitable for testing at NASA facilities.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The NASA application of this innovative, safe, efficient and automated urine pretreatment hardware will be as Flight Hardware for deployment in support of future long duration missions such as the International Space Station, Lunar transit, and Lunar base. The primary application will be as a replacement for current urine pretreatment systems aboard the ISS. Secondarily, this device can be used to stabilize other waste streams, which are prone to microbial instability. It is anticipated that numerous other uses will be found for this system within NASA.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
This urine pretreatment technology may be employed in a variety of applications to provide a means for safe and stable urine storage. In the near term, this technology can be applied to storage onboard recreational vehicles, ships, airplanes, or in conjunction with portable restroom facilities. The capability to effectively store urine can be the basis for a new technology, in which, urine is collected in bulk, stored, and treated to reduce the environmental impact of treatment facilities and improve treatment efficiency. Solid phase acidification may also be used for control of pH in analytical instrumentation and industrial processes.

TECHNOLOGY TAXONOMY MAPPING
Biomedical and Life Support
Sterilization/Pathogen and Microbial Control
Waste Processing and Reclamation

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Aerodyne Research, Inc.
45 Manning Road
Billerica, MA 01821-3976
(978) 663-9500

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Andrew Freedman
af@aerodyne.com
45 Manning Road
Billerica,  MA 01821-3976
(978) 663-9500

Expected Technology Readiness Level (TRL) upon completion of contract: 5 to 6

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
We have built and tested an optical extinction monitor for the detection of spacecraft cabin particulates. This sensor sensitive to particle sizes ranging from a few nanometer to tens of micrometers in diameter. Designed to utilize commercial off- the-shelf components, the monitor, once calibrated, requires minimal recalibration and only periodic baseline determinations, a process which can be automated as part of the operation of the instrument. It employs no consumables. This monitor employs cavity attenuation phase shift technology and involves the use a light emitting diode coupled to a low-loss optical cavity. The Phase I project involved a proof-of-principle demonstration that demonstrated a sensitivity of less than 0.1 micrograms per cubic meter. During the Phase II project, a prototype sensor will be delivered to NASA for the purpose of laboratory and field measurements. A major goal will be to miniaturize the monitor.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
This sensor can be deployed on board spacecraft cabins for the purpose of monitoring the presence of airborne particulates. It can also be used for the same purpose in climate change studies where particulate concentrations and their optical extinction are key parameters in determining the amount of radiation forcing attributable to the presence of particles in the atmosphere. The low cost of this sensor will allow the deployment of far more sensors of this type than are currently used.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
There are two large commercial markets for this technology. The first is as a direct competitor to 'smoke nunber' measurement devices which are used to measure the opacity of combustion plumes from aircraft engines and smokestacks. The other involves in situ monitoring of engine exhaust emissions with respect to the presence of PM2.5, a newly designated criteria pollutant.

TECHNOLOGY TAXONOMY MAPPING
Optical

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Lynntech, Inc.
7610 Eastmark Drive
College Station, TX 77840-4023
(979) 639-0017

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Roger van Boeyen
roger.vanboeyen@lynntech.com
7610 Eastmark Drive
College Station,  TX 77840-4066
(979) 693-0017

Expected Technology Readiness Level (TRL) upon completion of contract: 4

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
With the increasing demands placed on extravehicular activity (EVA) for the International Space Station assembly and maintenance, along with planned lunar and Martian missions, the need for increased human productivity and capability becomes ever more critical. This is most readily achieved by reduction in space suit weight and volume, and increased hardware reliability, durability, and operating lifetime. Considerable progress has been made with each successive generation of space suit design; from the Apollo A7L suit, to the current Shuttle Extravehicular Mobile Unit (EMU) suit, and the next generation Constellation Space Suit Element (CSSE). However, one area of space suit design which has continued to lag is the fluid pump used to drive the water cooling loop of the Primary Life Support System (PLSS). Conventional electric motor-driven fluid pumps are heavy, bulky, inefficient, and prone to wear and water contaminants. A new pump type is needed. In Phase I, the feasibility of reducing the power consumption of Lynntech's electrochemically-driven fluid pump by employing high conductivity hydrocarbon-based electrochemical membranes was demonstrated. In Phase II, Lynntech will develop a fluid pump significantly more robust, and more efficient than the pumps currently used in space suit PLSSs.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
A rugged, long life, low power, compact fluid pump will have applications in the thermal subsystem of the Primary Life Support System (PLSS) of the next generation space suit. Lynntech's fluid pump will be more efficient, lighter, and more robust the centrifugal pump currently used in the Shuttle Extravehicular Mobile unit (EMU). Additionally, Lynntech's pump does not suffer from cavitation issues and is not susceptible to water impurities, like the Shuttle EMU pump.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
With the increasing power density of electronics, there is a growing market for miniature, low-power pumps for use in the thermal management of consumer electronics. In particular, the interest in a low-cost, lightweight, quiet, efficient liquid pump for laptop cooling is high. Another potentially large market is thermal management systems for small fuel cell power systems.

TECHNOLOGY TAXONOMY MAPPING
Cooling

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Paragon Space Development Corporation
3481 E. Michigan Street
Tucson, AZ 85714-2221
(520) 903-1000

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Christine Iacomini
ciacomini@paragonsdc.com
3481 E. Michigan Street
Tucson,  AR 85714-2221
(520) 382-4824

Expected Technology Readiness Level (TRL) upon completion of contract: 5 to 6

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
MTSA technology specifically addresses the thermal, CO2 and humidity control challenges faced by Portable Life Support Systems (PLSS) to be used in NASA's Constellation Program. Metabolically-produced CO2 present in the ventilation gas of a PLSS is collected using a CO2-selective adsorbent via temperature swing adsorption. The temperature swing is achieved through cooling to well below metabolic temperatures. The coolant can be water, liquid CO2 (LCO2), or any cryogenic fluid. Water or LCO2 is used as coolant by expanding the liquid to below sublimation temperatures when exposed to low pressure or vacuum environments. Subsequent super heated vapor, as well as additional coolant, is used to further cool the astronaut. The adsorbent is warmed using moist ventilation gas, producing condensation which is recycled at the habitat. The overall objective of the Phase 2 effort is to develop and test in a relevant environment a full-scale lunar PLSS MTSA subassembly Engineering Development Unit (EDU) comprised of a condensing ice heat exchanger (CIHX), a sorbent bed and a sublimation heat exchanger (HX). This will be achieved by developing high fidelity models and designs of the three functions, validated with test data available from previous work. At the completion of the effort, the EDU will have been manufactured and tested. The MTSA subassembly will be at TRL 5 and the EDU can be used for off-nominal operational testing as well as MTSA system integration tests.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
MTSA technology provides thermal, CO2 and humidity control for Portable Life Support Systems. Coolant flexibility enabled by the application of MTSA technology makes possible one PLSS design for use on the moon and on Mars. Given the multiple processes involved, there are several potential spin-offs of MTSA technology development for other NASA applications. For example, sublimation heat exchanger technology can be applied in surface habitats and small pressurized rovers (SPRs) where forced sublimated convection minimizes dust contamination. The entire MTSA concept can be possibly applied at the vehicle level. For example, habitat air revitalization could be performed by means of water recycling (rather than rejection and loss) as well as CO2 collection for oxygen regeneration or coolant production.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Non-NASA applications include a wide variety of portable life support systems for the Department of Defense and Home Land defense in chemical warfare agent shelters. We also anticipate interest from the fire fighter community as the sublimation heat exchanger concept emplolyed by MTSA is a powerful means for safe thermal control that exhausts non-flammable, spent coolant. Spin-offs of MTSA component development can be applied to cabin atmosphere maintenance concepts for emerging commercial orbital flight vehicles such as Bigelow's space hotels, and Commercial Orbital Transportation Services (COTS) vehicles where cryogenic breathing supplies may be available as coolant to drive CO2 and humidity control systems.

TECHNOLOGY TAXONOMY MAPPING
Cooling
Air Revitalization and Conditioning
Biomedical and Life Support
Portable Life Support

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Luminit, LLC
20600 Gramercy Place, Suite 203
Torrance, CA 90501-1821
(310) 320-1066

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Dmitry Voloschenko
kyu@luminitco.com
20600 Gramercy Place, Suite 203
Torrance,  CA 90501-1821
(310) 320-1066

Expected Technology Readiness Level (TRL) upon completion of contract: 6

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
To address the NASA need for lightweight, space suit-mounted displays, Luminit proposes a novel Holographic Waveguided See-Through Display. Our proposed Holographic Waveguided See-Through Display (HoWSD) will integrate highly selective waveguiding Bragg holograms into a helmet-mounted display (HMD) that will provide easy-to-access clearly visible information to astronauts during extravehicular activity (EVA). The proposed HoWSD incorporates a unique design and Luminit novel Holographic Optical Elements into a functional HMD, which enables us to meet NASA goals for a functional, unobtrusive display device that can be incorporated into NASA EVA helmets. HoWSD offers a compact, low-profile display with high brightness and contrast, which is fully see-through and high resolution. In Phase I Luminit demonstrated the feasibility of a see-through helmet-mounted display which prepared us for Phase II. In Phase II, Luminit plans to develop a fully-functional rugged prototype HoWSD that can operate under various illumination levels and demonstrate its functionality. The demonstrated results will offer NASA the capability of incorporating a non-obtrusive, rugged, wide field-of-view display into a space suit helmet designed for EVAs.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
If successful in Phase II, the HoWSD system, integrated into a space suit helmet, will enable astronauts to see important mission information, such as updates from the Primary Life Support System (PLSS), warnings and checklists, during EVA.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The HoWSD system will find applications in mobile devices, avionics, combat vehicle crew and soldiers' integrated protective ensembles, logistics and training, fire fighting, and in other areas where rugged helmet-mounted displays are needed. HMD technology advances made possible by the successful development of the proposed HoWSD visor optics system will lead to cost-effective commercialization. In particular, the new HMD system will find real-time 3D virtual reality applications. Medicine, avionics, education, CAD, mobile computing and communication, law-enforcement, fire fighting, and video games represent markets for compact, low-cost HMDs in the private sector.

TECHNOLOGY TAXONOMY MAPPING
Simulation Modeling Environment
Training Concepts and Architectures
Guidance, Navigation, and Control
Autonomous Control and Monitoring
Data Input/Output Devices
Human-Computer Interfaces
Portable Data Acquisition or Analysis Tools
Optical
Suits
Tools
Optical & Photonic Materials

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Vista Photonics, Inc.
67 Condesa Road
Santa Fe, NM 87508-8136
(505) 466-3953

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Jeffrey Pilgrim
jpilgrim@vistaphotonics.com
67 Condesa Road
Santa Fe,  NM 87508-8136
(505) 466-3953

Expected Technology Readiness Level (TRL) upon completion of contract: 4 to 5

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Breath respiratory species measurement during extravehicular activity (EVA) or intravehicular activity (IVA) is a demanding application for optical sensing techniques. Yet optical techniques offer many advantages including high-precision, fast response, and strong species selectivity. Accommodation within spacesuits demands that optical sensors meet stringent size, weight and power requirements. The next generation of emerging NASA Constellation spacesuits requires a new generation of CO2 sensing technology with performance beyond that presently in use on the Shuttle/ISS extravehicular mobility unit (EMU). Vista Photonics proposes to develop rugged, compact, low-power optical sensor prototypes capable of selectively determining carbon dioxide at EVA-relevant concentrations suitable for Constellation Configuration Two Spacesuits. Design variations include dual CO2 sensors for feeding into astronaut metabolic rate determination and simultaneous humidity measurement for automated suit thermal control. The enabling technology for meeting stringent NASA mission requirements is a new low power infrared optical source that provides the high-sensitivity of established optical absorption detection techniques.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The immediate targeted application for NASA is respiratory species monitoring during EVA and IVA. Phase II prototypes will be capable of selectively detecting carbon dioxide and humidity. The integrated sensors will be suitable for variable pressure EVA operation in diverse environments like the Moon, Mars and ISS. The sensors will allow real-time metabolic rate determination and automated suit thermal control. Unmanned planetary exploration missions in substantial atmospheres like Titan's are likewise contemplated. The emerging technology will also be suitable for use on both manned and unmanned terrestrial atmospheric research craft. Other applications include fire detection on aircraft and high-value installations, gas sensing in air revitalization and water recovery processes on spacecraft, and leak detection during spacecraft launch operations.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Phase III commercial applications abound for sensors whose performance and physical characteristics are suitable for spaceflight. Two specifically targeted applications are high-performance medical capnographs for measuring real-time end-tidal breath carbon dioxide in patients and carbon dioxide leak detection at power plant carbon capture & sequestration sites. Other examples include contaminant monitoring in process gas streams in the chemical and microelectronics industries, medical diagnosis through detection of biogenic gases in human breath that correlate to specific pathologies, and environmental monitoring and regulatory compliance in agriculture, power production, and occupational safety. The fully-developed Phase II instruments shall offer a compelling and desirable blend of performance, affordability, compactness, simplicity and ease-of-use relative to present commercial product offerings in these applications.

TECHNOLOGY TAXONOMY MAPPING
Biomedical and Life Support
Biomolecular Sensors
Optical
Sensor Webs/Distributed Sensors
Portable Life Support
Suits
Biophysical Utilization

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Advanced Cooling Technologies, Inc.
1046 New Holland Avenue
Lancaster, PA 17601-5688
(717) 296-6058

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
John Hartenstine
john.hartenstine@1-ACT.com
1046 New Holland Avenue
Lancaster,  PA 17601-5688
(717) 295-6061

Expected Technology Readiness Level (TRL) upon completion of contract: 6

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Researchers have determined that lunar soil contains approximately 43% oxygen in the lunar soil oxides, which could be extracted to provide breathable oxygen for consumption by astronauts. The proposed program will develop a solar receiver for the hydrogen reduction process that uses sodium heat pipes in the 1050<SUP>o</SUP>C temperature range. The heat pipe solar receiver is accepts the non-uniform solar thermal energy, and deliver the energy to the lunar regolith with a uniform heat flux and temperature. This increases throughput and efficiency. The principal Phase II program objective is to design, fabricate, and demonstrate a heat pipe solar receiver in a relevant environment and near optimum configuration. While the Phase I program focused on a single heat pipe solar receiver and regolith reactor, the Phase II program will examine variable-conductance or pressure-controlled heat pipes to supply the heat supplied from a single receiver to multiple reactors. The program will examine control schemes to vary the heat supplied to each reactor, hydrogen permeation, and evaluation of the heat pipe wall materials.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The immediate application is the development of a heat pipe solar receiver for oxygen production from lunar regolith. A lunar oxygen production plant is projected to provide breathable oxygen for astronauts a well as oxygen for rocket propulsion. In the current requirement, lunar regolith is processed to generate 1 metric ton of oxygen per year. This may be accomplished passively using a single heat pipe solar receiver/regolith reactor system or with multiple reactors using an active control scheme. The receiver could also be used for materials processing, processing lunar resources into materials such as concrete, fiberglass, and aluminum.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
One commercial application is VCHP heat exchangers in fuel cell reformers. In a fuel cell reformer, diesel fuel and air pass through a series of high temperature reactors to generate hydrogen. The operating temperature of the reactors must be closely controlled to maintain their chemical equilibrium. The current scheme uses a bypass valve, which has several drawbacks: it requires active control, requires power, and has a large pressure drop. ACT believes that VCHP heat exchangers can replace the current heat exchanger and control system with a passive system that automatically maintains the output stream from the heat exchanger at a constant temperature. The second application is adding pressure control to ACT's current line of commercial isothermal furnace liners, which are annular alkali metal heat pipes that provide nearly isothermal temperature uniformity. Adding pressure control will allow the temperature to be controlled within millikelvins, adding in isothermal processing of materials, thermophysical properties characterization, and calibration of temperature references.

TECHNOLOGY TAXONOMY MAPPING
In-situ Resource Utilization

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Pioneer Astronautics
11111 W. 8th Avenue, Unit A
Lakewood, CO 80215-5516
(303) 980-0890

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Mark Berggren
mberggren@pioneerastro.com
11111 W. 8th Ave Unit A
Lakewood,  CO 80215-5516
(303) 980-0231

Expected Technology Readiness Level (TRL) upon completion of contract: 3 to 4

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The Lunar Sulfur Capture System (LSCS) is an innovative method to capture greater than 90 percent of sulfur gases evolved during thermal treatment of lunar soils. LSCS sorbents are based on lunar soil iron compounds that trap sulfur contained in hot in-situ resource utilization (ISRU) product gases. Small amounts of polishing sorbents are used as needed to reduce equilibrium sulfur concentrations to the ppm or sub-ppm level. The LSCS is an effective technology for protecting in-situ resource utilization (ISRU) hardware from damage caused by the corrosive effects of hydrogen sulfide (H2S) and other sulfur-containing gases. Saturated sorbents can be regenerated for reuse, and desorbed sulfur can be converted to elemental sulfur. Key process steps include bulk H2S capture on lunar soil, further capture of H2S on polishing sorbent, regeneration of soil sorbent for re-use, recovery of high-purity H2S, and conversion of H2S to elemental sulfur. The LSCS reduces the risk of using Earth-based sorbents for primary sulfur capture by ensuring a ready supply of sorbent in the event of poor regeneration performance or process upset. The LSCS primary sulfur sorbent can be used as a non-regenerable sorbent if necessary without significant consequence to the ISRU process.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The primary initial application of the LSCS is for lunar sulfur capture and recovery. The LSCS has direct use to both protect ISRU hardware and catalysts and to produce useful amounts of sulfur for other lunar ISRU applications. The LSCS is directed at reducing the mass penalty and risk associated with the use of Earth-based sorbents for hydrogen reduction and other lunar oxygen production processes.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The LSCS has direct commercialization potential for thermal-catalytic synthesis processes that require sulfur removal from reducing gases derived from coal, biomass, or other impure hydrocarbon feeds in support of fuels and chemicals manufacture. The closed-loop aspect of the LSCS sulfur recovery system is particularly attractive as a potential zero-emission sulfur recovery system for terrestrial applications.

TECHNOLOGY TAXONOMY MAPPING
In-situ Resource Utilization

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Grainflow Dynamics, Inc.
1141 Catalina Drive, PMB #270
Livermore, CA 94550-5928
(925) 447-4293

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Otis Walton
walton@grainflow.com
1141 Catalina Drive, PMB #270
Livermore,  CA 94550-5928
(925) 447-4293

Expected Technology Readiness Level (TRL) upon completion of contract: 3 to 4

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
NASA has serious unmet needs for simulation tools capable of predicting the behavior of lunar regolith in proposed excavation, transport and handling systems. Existing discrete element method (DEM) or finite element (FE) models lack adequate fidelity for fine cohesive powders comprised of friable particles with irregular shapes and exhibiting substantial bulk dilation upon initial excavation. As such, they are inadequate for assessing the reliability of regolith excavation and handling systems, and even less so for evaluation of engineering trade-offs between total system mass, power and energy consumption. Also, current simulation tools do not include the effects of triboelectric and photo-ionization-induced charges on regolith particles. Building on the successful Phase-1development of a new charge-patch electrostatic model and a comprehensive cohesive particle interaction model for DEM, Grainflow Dynamics proposes to develop a high-fidelity predictive calculational tool, in the form of a DEM module with calibrated interparticle-interaction relationships, coupled with a FE module utilizing enhanced, calibrated, constitutive models which, together, are capable of mimicking both large deformations and the flow behavior of regolith simulants and lunar regolith under conditions anticipated in ISRU operations. This will not only provide unparalleled fidelity but also will leverage the computational efficiency of the continuum FE codes to drastically reduce the simulation time and resources necessary to perform engineering analyses on regolith systems. In addition, the modules will be parallelized to maximize their usefulness in multi-core and cluster computing environments. This work will lead to an improved engineering design tool that can be used by NASA engineers and contractors developing designs for ISRU equipment to evaluate both the reliability of various configurations as well as the trade-offs of system designs.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The pharmaceutical industry has a large number of applications, which would benefit from significantly improved simulation capabilities for cohesive powders in a variety of pharmaceutical material manufacturing, transport and handling operations, including micronization, granulation, coating, blending, tableting, dosating and capsule or blister-pack filling – especially powders designed for pulmonary delivery. The FDA's Process Analytical Technology (PAT) initiative emphasizes the need for pharmaceutical makers to understand the processes they use and to design the processes for quality, reliability, robustness and consistency. These goals overlap significantly with NASA's needs to better understand the processing of bulk cohesive granular material. Reliable tools to predict powder deformation and flow behavior would greatly facilitate the attainment of such goals.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The pharmaceutical industry has a large number of applications, which would benefit from significantly improved simulation capabilities for cohesive powders in a variety of pharmaceutical material manufacturing, transport and handling operations, including micronization, granulation, coating, blending, tableting, dosating and capsule or blister-pack filling especially powders designed for pulmonary delivery. The FDA's Process Analytical Technology (PAT) initiative emphasizes the need for pharmaceutical makers to understand the processes they use and to design the processes for quality, reliability, robustness and consistency. These goals overlap significantly with NASA's needs to better understand the processing of bulk cohesive granular material. Reliable tools to predict powder deformation and flow behavior would greatly facilitate the attainment of such goals. In addition, the xerographic industry (e.g., laser printers and copiers) could benefit from a predictive tool to assist in design improvements for powdered toner tribocharging, transfer, and fusing. Despite 50 years of R&D, many details of the overall xerographic process are only poorly understood, and fierce competition provides motivation to seek design improvements.

TECHNOLOGY TAXONOMY MAPPING
Tools
In-situ Resource Utilization

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)
Andrea Hoyt Haight
adherenttech@comcast.net
9621 Camino del Sol NE
Albuquerque,  NM 87111-1522
(505) 346-1685

Expected Technology Readiness Level (TRL) upon completion of contract: 5 to 6

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Any manned missions to extraterrestrial locations will require shelter structures for a variety of purposes ranging from habitat usage to biomass production. Such shelters need to be constructed in such a way to minimize stowed volume and payload weight. The structures must also be very durable and have the ability to survive punctures without collapsing. Ways of increasing available crew-load volume without greatly increasing launch weight or volume are also sought. Inflatable structures are ideal candidates for habitat structures for several reasons: (1) they feature the low stowage volume and payload weight required, (2) deployed volume can be easily increased without large increases in launch weight or volume, (3) they offer unique opportunities for incorporating intelligent and/or multifunctional systems such as self-healing capability, power generation and storage, sensor systems, and radiation protection. Adherent Technologies, Inc. is proposing an inflatable, rigidizable shelter system based on our Rigidization on Command<SUP>TM</SUP> (ROC) technology. The proposed shelter system features not only the required low stowage volume and lightweight character, but also feature a self-healing foam system incorporated into the final structure to minimize the damage caused by any potential punctures to the structure. The Phase I program successfully demonstrated the self-healing foam concept. This system will be optimized in Phase II and incorporated into a fully functional subscale prototype habitat utilizing ROC composite outer layers, self-healing layers, thermal and micrometeoroid protective layers, integrated lighting, and power systems.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
This system is being designed to support the need for structures on future manned space missions to the moon and Mars. Applications are seen as shelters for equipment with the potential for expansion into habitats and airlock structures.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
These rigidizable shelters will find application in military and disaster relief scenarios where transport of large numbers of structures into difficult areas is paramount. Individually, the ROC composite and self-healing foam materials will find applications in space-based communications structures, structural repair tapes, advanced fuel tanks, and hazardous material transport cars.

TECHNOLOGY TAXONOMY MAPPING
Inflatable
Kinematic-Deployable
Spaceport Infrastructure and Safety
Composites

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Dynamic Structures and Materials, LLC
205 Williamson Square
Franklin, TN 37064-1321
(615) 595-6665

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Jeffrey Paine
jpaine@dynamic-structures.com
205 Williamson Square
Franklin,  TN 37064-1321
(615) 595-6665

Expected Technology Readiness Level (TRL) upon completion of contract: 4 to 5

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Piezoelectric motors operate on the principal of converting the high-frequency oscillation of high-force, precision ceramic elements into useful continuous motion. High-power oscillations are converted to rotary motion through novel transmission mechanisms to produce high-torque, precision motion. Dynamic Structures and Materials (DSM) focused the Phase I innovation on the development and design of a precision rotary motor mechanism that employs piezoelectric oscillatory power and produces rotary motion for operation at cryogenic and extreme environments. The successful design of a high-torque prototype mechanism and the subsequent Phase I demonstration of the prototype under vacuum conditions lays the groundwork for the technology to reach product status and commercialization success in both NASA and non-NASA applications. Phase II efforts will refine the innovation with additional focus on developing the fundamental understanding of rotary piezoelectric motor design and implementation. The Phase II prototypes will be fully characterized over a temperature range of approximately 25K to 400 K in hard vacuum. The construction materials of this type of mechanism are inherently vacuum compatible and will be selected to provide very low or no outgassing. DSM has already demonstrated operation of its high-force linear piezoelectric motors for environments as low as 77 K.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The solid-state, vacuum-compatible nature of piezoelectric mechanisms lends itself well to the environmental conditions of lunar and Martian applications. In addition to the lunar and Martian surface applications discussed in the solicitation topic, a number of cryogenic space vehicle propulsion systems currently rely on large and heavy electromagnetic or pneumatic actuators, most of which are linear actuators driving a rack and pinion to provide rotary motion. The proposed technology would enable a reduced geometry and mass relative to these traditional technologies. The piezoelectric rotary motor technology is proposed for applications in the area of precision instruments, rover control, operational equipment, and space mechanisms.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Terrestrial applications are continuously looking for new rotary actuators, and the proposed concept's advantages in size and weight will make the piezo motor technology a competitive player in the rotary actuator market. DSM has been approached in the past by researchers interested in new rotary actuators for platforms related to robotic battlefield medical equipment. In addition, DSM has been introduced to a variety of applications requiring optical adjustments that could benefit from the characteristics of the rotary piezo motor including the power off hold feature for "set-and-forget" adjustments. All-electric vehicles and platforms looking to eliminate pneumatic and hydraulic actuation technologies will benefit from the piezoelectric actuator technology.

TECHNOLOGY TAXONOMY MAPPING
Mobility
Manipulation
Kinematic-Deployable
Tools
Multifunctional/Smart Materials

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
International Scientific Technologies, Inc.
P.O. Box 757
Dublin, VA 24084-0757
(540) 633-1424

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Russell Churchill
intlsci@earthlink.net
P.O. Box 757
Radford,  VA 24141-0757
(540) 633-1424

Expected Technology Readiness Level (TRL) upon completion of contract: 4 to 5

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
NASA has identified the need for development of technologies to support Lunar Lander and Lunar Habitats programs and for transfer of relevant technology to Crew Exploration Vehicle and Crew Launch Vehicle programs, including revolutionary advances in shielding materials to protect humans from the hazards of space radiation. To address this need and in response to NASA Subtopic X6.03, International Scientific Technologies, Inc. in conjunction with the College of William and Mary, proposed in Phase I the development of hydrogen-rich monomers for high performance polymers, such as aromatic polyimides, and the incorporation of metallic nanoparticles into nanocomposite materials to achieve multifunctional properties. The Phase II Technical Objectives include synthesis and characterization of hydrogen-rich monomers, fabrication and tailoring of high performance nanocomposite materials, acquisition of test data to determine key parameters of hydrogen-rich, multifunctional nanocomposite materials, and optimization of prototype hydrogen-rich, multifunctional materials. The Phase I program demonstrated that hydrogen-rich monomers can be prepared and polymerized with metallic nanoparticles. The feasibility established in Phase I will be realized in Phase II through development of polymeric nanocomposite materials consisting of hydrogen-rich monomers and metallic nanoparticles. The nancomposite materials will have multifunctional properties, including radiation shielding against galactic cosmic radiation, neutrons and electromagnetic radiation, structural integrity for flexible and rigid structures and habitats, and electrical conductivity for electrostatic control for dust mitigation during lunar missions.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The proposed multifunctional nanocomposites will find application in the Exploration Systems mission in protecting astronauts and sensitive optical, electronic, thermal and acoustic components from environmental hazards including radiation, dust and thermal transients, while, at the same time, providing lightweight structural functions. It is expected that nanocomposite systems will provide a high-performance-to-weight radiation shield that can be used within human habitats, spacecraft and protective apparel. Other missions supported by NASA could also make use of the nanocomposite materials in low earth orbit or in other orbital paths traversing high radiation regions of space.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Lightweight multifunctional radiation shielding will find application in the commercial (e.g., hospitals and nuclear power plants) and defense (e.g., nuclear-powered ships and surveillance satellites) sectors. The shields will provide protection for homeland security first responders employed by law enforcement agencies, fire departments and hospitals. It is also expected that the shielding can be fabricated into temporary shelters used by defense personnel and considered for use in the protection of individuals in case of a nuclear or radiological events. The radiation-shielding material will be suitable for fabrication into protective clothing for healthcare professionals involved in X-ray and nuclear medicine.

TECHNOLOGY TAXONOMY MAPPING
Erectable
Inflatable
Launch and Flight Vehicle
Thermal Insulating Materials
Suits
Composites
Radiation Shielding Materials
Multifunctional/Smart Materials

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
San Diego Composites, Inc.
9550 Ridgehaven Court, Suite A
San Diego, CA 92123-5607
(858) 751-0450

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Gary Wonacott
gwonacott@sdcomposites.com
9550 Ridgehaven Court, Suite A
San Diego,  CA 92123-5607
(858) 751-0450

Expected Technology Readiness Level (TRL) upon completion of contract: 5 to 6

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The process known as double bag vacuum assisted resin transfer molding (DBVARTM) was developed by NASA to help deplete by products. To date, the NASA DBVARTM process has reduced void content to approximately four to five percent. This number has fallen short of the goal of two percent. During the Phase I effort, San Diego Composites (SDC) was able to reduce the void content to 0.8 percent to 1.5 percent. There are three primary technical objectives to the Phase II effort. The first objective is to perform a trade study to evaluate and optimize the effect of stitched performs. Stitching has had a large effect on the void content in the laminate and several different stitching variables will be evaluated. The second objective is to transition the work done in Phase I to larger components. These components will consist of larger plates and structures will be evaluated using non destructive testing along with mechanical testing. At the end of the Phase II effort, a full scale component will be fabricated, evaluated using non destructive testing, and then the component will be tested. The final objective is to transition the technology to Boeing Phantom Works. This objective will demonstrate that the process developed in a laboratory can be reproduced at any facility. By the end of the Phase II program, the Technology Readiness Level (TRL) is expected to be 5-6.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
There are many different applications that may come from the development of low cost high temperature composite processing. Programs such as Mission to Mars could have benefited from such composite processing, and all future deep space explorations programs. Specific components include airframes, large antennas and telescopes, launch and flight vehicle structures, and components that require power management and thermal protection systems.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Potential non-NASA commercial applications include commercial aircraft and Integrated Defense Systems such as advanced UAV's. Specific components that would benefit from this technology includes aircraft engines, control structures, fluid storage and handling containers, fan blades, engine ducts, supersonic engine cowlings, high speed missile bodies and nose tips, and rocket motor cases. Additional applications could include the transportation industry such as automobile and rail components.

TECHNOLOGY TAXONOMY MAPPING
Airframe
Launch and Flight Vehicle
Composites
Aircraft Engines

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Rapid Imaging Software, Inc.
1318 Ridgecrest Place SE
Albuquerque, NM 87108-5136
(505) 265-7020

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
MICHAEL ABERNATHY
mikea@landform.com
1318 RIDGECREST PLACE SE
ALBUQUERQUE,  NM 87108-5136
(505) 265-7020

Expected Technology Readiness Level (TRL) upon completion of contract: 6 to 7

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Advanced Situation Awareness Technologies (ASAT) will facilitate exploration of the moon surface, and other planetary bodies. ASAT will create an Advanced Situation Awareness Technology by creating an integrated display from disparate data sources including video, telemetry, and geographic databases which in addition to topographic data can provide ortho-imagery, meteorological, hazard, and cultural data. This new augmented reality display will fuse multiple information streams into a high information density, three dimensional display with a common temporal context.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
ASAT will support: - safe lunar lander vehicle operation - safe planetary exploration vehicle operation - manned exploration of extratrestrial bodies ASAT will provide enhanced situation awareness to explorers (either present or telepresent) by providing and information rich augmented reality display running on a handheld appliance.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
ASAT will be commercialized for use in many applications but starting with the operation and teleoperation of optical sensors in a geographic context. Other applications may include aircrew situation awareness, and recreational multiplayer gaming.

TECHNOLOGY TAXONOMY MAPPING
Human-Robotic Interfaces
Integrated Robotic Concepts and Systems
Perception/Sensing
Teleoperation
Spaceport Infrastructure and Safety
Telemetry, Tracking and Control
Airport Infrastructure and Safety
Guidance, Navigation, and Control
On-Board Computing and Data Management
Pilot Support Systems
Human-Computer Interfaces
Sensor Webs/Distributed Sensors
Manned-Manuvering Units
General Public Outreach
K-12 Outreach
Mission Training

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Honeybee Robotics Ltd.
460 W 34th Street
New York, NY 10001-2320
(212) 966-0661

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Michael Rutberg
rutberg@honeybeerobotics.com
460 West 34th Street
New York,  NY 10001-2320
(646) 459-7830

Expected Technology Readiness Level (TRL) upon completion of contract: 4 to 5

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Future lunar site operations will benefit from mobile robots, both autonomous and tele-operated, that complement or replace human extravehicular activity. Three-dimensional sensing technology is at the heart of such functionality, enabling reliable navigation in complex, dynamic environments, and serving as a valuable tool for inspection and site survey. Honeybee Robotics is therefore developing a small-envelope, high-performance scanning LIDAR system, geared primarily towards robotic navigation and secondarily to site inspection and survey. The proposed Phase II will draw on the results of a DARPA-funded design study and Phase I of this effort, which resulted in successful proof-of-concept, as well as testbeds and proprietary software tools. The Honeybee 3D Miniature LIDAR (3DML) uses a novel scanning mechanism in conjunction with a pulse-time-of-flight optical rangefinding subsystem. The 3DML architecture, developed with expert input from Sensor Designs, an electro-optical systems consultancy, achieves wide field of view and high resolution while maintaining ultra-compact package size. The proposed Phase II will include development of a functional brassboard system prototype and its integration and test on a K10 research rover. Phase III will pursue a multi-pronged commercialization effort, including preflight development, production of a unit for terrestrial research, and incorporation of 3DML into a flight program.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The Honeybee 3DML is ideally suited to mobile robotic platform navigation, thanks to the wide field of view and high angular resolution. A key long-term goal is to produce flight units for NASA's Lunar Surface Systems, to facilitate robotic site operations support. In addition to rover navigation, a flight 3DML could be employed as a sensor for lunar vehicle and structure inspection. Adding long-range survey capability would result in an all-in-one navigation/inspection/survey sensor. Whether autonomous, teleoperated, or even manned, lunar mobile platforms will require 3D sensing to perform safely and effectively. Rover missions for Mars exploration could also make use of a compact, robust 3D LIDAR system. Future Mars rovers, including the AFL, the Mid-size Rovers, and the MSR rover, will be developed to increasingly sophisticated levels of automation, and will demand sophisticated sensor facilities. In the much nearer term, terrestrial 3DML units can be used for robotic research at NASA centers. The functional brassboard resulting from this Phase II effort will be delivered to Ames Research Center's Intelligent Robotics Group for continued use on their K10 test rovers. An 3DML trial on a K10 at a Moses Lake field test has also been discussed. Following a short development iteration, similar units for terrestrial research will be ready for sale to robotics labs in NASA and academia.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
This technology enjoys broad commercialization potential due to the very basic need for 3D vision that it satisfies. An immediately targeted market is military robotics, where 3DML will be an enabling technology for greater autonomy and easier navigation and operations. Given the high performance and relatively low cost of the sensor, this technology is also more broadly applicable to general ground robotics. This includes hazmat response and search-and-rescue, but also mining, agricultural and industrial automation, such as sensors for unmanned forklifts on a factory floor. The primary competitor to the 3DML technology is solid state "flash" LIDAR systems. While attractive for certain applications, flash LIDAR lacks the high resolution and flexibility of 3DML. Compared to the current and projected state of the art of flash systems, 3DML promises to achieve higher performance at lower cost. The 3DML architecture can be scaled down to a much lower-cost version by reducing the demands on the optomechanical and electro-optical subsystems, permitting incorporation into many consumer and commercial devices. For automotoves, a low-resolution version of 3DML could be used for blind-spot or guardrail warning systems. Home automation systems, smart appliances, and domestic robots like iRobot's Roomba and Scooba cleaners, could all benefit from low-cost, low-resolution 3D vision provided by 3DML.

TECHNOLOGY TAXONOMY MAPPING
Human-Robotic Interfaces
Integrated Robotic Concepts and Systems
Mobility
Perception/Sensing
Optical

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Honeybee Robotics Ltd.
460 W 34th Street
New York, NY 10001-2320
(212) 966-0661

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Jason Herman
herman@honeybeerobotics.com
460 West 34th Street
New York,  NY 10001-2320
(646) 459-7819

Expected Technology Readiness Level (TRL) upon completion of contract: 6

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Lunar dust has been identified as a significant and present challenge in future exploration missions. Significant development is called for in the area of devices and structures that tolerate or mitigate the presence of Lunar dust. Honeybee Robotics Spacecraft Mechanisms Corporation (SMC) seeks to develop methods for mitigating dust accumulation on reusable connection mechanisms, such as will be necessary for Lunar extra-vehicular activity and surface systems equipment. Honeybee has heritage in developing mechanisms for extreme, dusty environments. Near-term applications of such a connector include the utility and electrical connections that will be used on the next-generation Lunar EVA suit being developed for NASA JSC by Oceaneering Space Systems, as well as cryogenic utility connections that will be used to pass liquid hydrogen and liquid oxygen during in-situ¬ resource utilization (ISRU) activities. The Phase 1 research has resulted in the development of a dust-tolerant, manual electrical connector for the battery recharge circuit of the Portable Life Support Backpack (PLSB) being developed for the Constellation configuration two (Lunar EVA) suit. Phase 1 breadboard testing showed 53 successful mate/de-mate cycles in the presence of JSC-1AF simulant prior to failure. In addition, this failure appears to be the result of a late addition to the mechanical configuration that can be revised for even better performance. In Phase II, Honeybee will revise the design of the dust-tolerant connector, investigate design configurations for utility connections for ISRU activities, and test a connector brassboard in a chamber capable of closely reproducing conditions on the Lunar surface. This effort will lead to the development of a dust-tolerant electrical connector with a focused application to the Constellation configuration two (Lunar EVA) suits. This will result in a TRL 6 Lunar dust-tolerant electrical connector.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The dust-tolerant reusable connection mechanisms to be developed through this project will be an enabling technology for extended Lunar operations in that they will allow several cycles of utility connection and disconnection for EVA and surface operations. Future mission scenarios involving erectable structures, diverse EVA-compliant tools, Extravehicular Mobility Unit (EMU)-to-rover or EMU-to-robot interfaces, and other in-situ assembly or interconnection activities will all call for dust-tolerant reusable connectors. In particular, the Constellation configuration two (Lunar EVA) suit being developed by Oceaneering Space Systems (OSS) has many connectors on it that require dust-tolerant technology. Initial discussions with personnel from OSS have already begun, and OSS has signed-on to the Phase 2 effort as a consultant. The will provide data, requirements, and technical criticism of the connector developed during the Phase 2 effort. The technology developed here is also applicable to the exploration of Mars (where frequent global dust stomrms occur) and asteroids, but is driven by the especially abrasive characteristics of Lunar dust.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Military and homeland security operations are often conducted in uncontrolled environments. An increasing use of high-technology tools provides for improved performance, but also introduces new risks. The incorporation of dust-tolerant reusable connection mechanisms in military couplings will allow greater reliability and flexibility for modular electronics in operational scenarios, especially in dusty, dirty, sandy environments. Incorporation of dust-tolerant connectors would also reduce maintenance, repair, and overhaul costs by reducing select component failures due to degradation by dust and sand. Current connectors meet stringent mil-spec environmental requirements when connected, but the connection itself must be made under relatively clean conditions. We expect that adding a tolerance to making and breaking connections under off-nominal conditions will result in an increased service life for modular electronics for use in military and homeland security applications. There is also broad commercial potential for dust-tolerant reusable connectors in several commercial applications requiring the reliable performance of modular electronics in uncontrolled environments, including oil and gas exploration, first responders and emergency services, heavy and highway construction, and mining. By employing dust-tolerant connectors, rather than attempting to seal dust intolerant connectors against the environment, the connectors used in these applications may be truly ruggedized.

TECHNOLOGY TAXONOMY MAPPING
Human-Robotic Interfaces
Integrated Robotic Concepts and Systems
Airlocks/Environmental Interfaces
Testing Facilities
Modular Interconnects
Fluid Storage and Handling
Manned-Manuvering Units
Portable Life Support
Suits
Tools
Earth-Supplied Resource Utilization
In-situ Resource Utilization
Liquid-Liquid Interfaces

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Orbital Technologies Corporation
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 Gustafson
gustafsonr@orbitec.com
Space Center, 1212 Fourier Drive
Madison,  WI 53717-1961
(608) 827-5000

Expected Technology Readiness Level (TRL) upon completion of contract: 6

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The severity of the lunar dust problems encountered during the Apollo missions were consistently underestimated by ground tests, illustrating the need to develop significantly better lunar dust simulants and simulation facilities. ORBITEC is proposing to continue developing high-fidelity lunar dust simulants that better match the unique properties of lunar dust than existing regolith simulants (such as JSC-1AF). Current lunar regolith simulants do not have enough of the very fine particles, most lack the agglutinitic glass and complex surface textures that dominate lunar dust, and none of them have nanophase iron (Fe0). High-fidelity lunar dust simulants approximate the size, morphology, composition, and other important properties of lunar dust (including nanophase Fe0). High-fidelity lunar dust simulants are required to physically evaluate the effects of lunar dust on the operation of all Exploration Surface Systems and to verify the effectiveness of dust mitigation strategies and technologies. During Phase 1, several prototype lunar dust simulants were created, samples of the prototype lunar dust simulants were delivered to NASA for characterization (TRL 4). The proposed Phase 2 effort will refine and demonstrate the production process for lunar dust simulants that will be characterized and delivered to NASA for a variety of applications (TRL 6).

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
High-fidelity lunar dust simulants are required to evaluate the effects of lunar dust and verify the effectiveness of dust mitigation strategies and technologies for all Exploration Surface Systems, including: extravehicular mobility suit material composition and cleaning operations, lunar habitat construction design, mechanical performance (radiators, seals, valves), electrical performance (tools and equipment), landing operations (vision systems), and all manners of surface operations. Since there is strong evidence that the prototype lunar dust simulants contain the critical metallic iron component (including nanophase Fe0) along with the morphologies of lunar dust particles, it will also be applicable to human health and toxicity studies.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
High-fidelity lunar dust simulants are being developed to support the needs of the NASA lunar exploration program. However, industry and research institutions that are developing any EVA equipment for use on the lunar surface will also require high-fidelity lunar dust simulants to physically evaluate the effects of lunar dust on the operation of all Exploration Surface Systems and to verify the effectiveness of dust mitigation strategies and technologies. Much of this work in the near future will be under NASA contracts. Longer term, private industry plans to develop a variety of EVA equipment for use on the lunar surface.

TECHNOLOGY TAXONOMY MAPPING
Testing Facilities
Testing Requirements and Architectures
Manned-Manuvering Units
Portable Life Support
Suits
Tools

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
ElectroChem, Inc.
400 West Cummings Park
Woburn, MA 01801-6519
(781) 938-5300

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Michael Pien
mpien@fuelcell.com
400 West Cummings Park
Woburn,  MA 01801-6519
(781) 938-5300

Expected Technology Readiness Level (TRL) upon completion of contract: 1

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
ElectroChem proposes a Phase II program to advance its very successful SBIR Phase I technology effort to the point of minimum hydrogen loss through the electrolyzer membrane, while the high proton conductivity necessary for high efficiency water electrolysis is maintained. In Phase I, ElectroChem demonstrated that its concept of adding clay to a Nafion proton conductive membrane would significantly reduce the penetration of hydrogen gas through the membrane. In Phase II, a comprehensive technology effort (aimed at optimization) will be carried out which uncovers the microscopic changes that occur within the membrane as a result of the clay addition. The objective of this effort is first to correlate the microscopic morphology that occur within the Nafion-clay nanocomposite membranes with the reduction in hydrogen penetration produced by the clay addition. A second objective is to control the microscopic morphology and establish a process to develop the most effective Nafion-clay nanocomposite membranes, leading to advanced MEAs. The final objective is to evaluate the Nafion-clay nanocomposite membranes under high pressure Commercial Electrolyzer conditions. Successful completion of this effort will enable NASA to meet its requirement for an electrolyzer that will operate very efficiently both at low current densities and at high pressures.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
ElectroChem's Innovative Development of Nafion/Clay nanocomposite membranes, which reduce hydrogen penetration through the membrane, will be incorporated into its unique PEM IFF Water Electrolyzer design. Successful completion of ElectroChem's Phase II technology effort will enable NASA to meet its requirement for a RFC electrolyzer that will operate very efficiently both at low current densities and at high pressures (Lunar surface energy storage application). Operating the RFC electrolyzer at high-pressure eliminates the need for external gas compression prior to reactant storage, which reduces total system weight and volume. The drawback of high- pressure operation, however, has been the increased diffusion of hydrogen across the electrolyzer membrane, which effectively decreases the efficiency. ElectroChem's Nafion-clay nanocomposite membranes advance will overcome this drawback. ElectroChem's Advanced IFF PEM Electrolyzer will also produce a more stable and passive RFC for providing power for missions at remote locations, and for providing UPS backup power for NASA needs.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
For terrestrial applications, ElectroChem's IFF PEM Electrolyzer is ideal for supplying hydrogen fuel for future auto refueling stations. Also, IFF PEM RFCs, containing the advanced electrolyzer design, will be strong candidates for supplying power to remote sites with solar and/or off-peak utility power as sources of electrolyzer input power. Because of difficult maintenance problems, ElectroChem's reliable, long life IFF PEM RFC will be an excellent replacement for the lead acid batteries used in Navy Overseas Bases. In the Transportation area, advanced RFC systems are being considered for a wide range of vehicles. For the UPS industry, ElectroChem's Advanced RFC has many unique characteristics that are very attractive to hospitals, telecommunications, and other business activities where down time is critical. Unlike battery power storage systems, the RFC's power and cycle duration are independent, which provides the designer much more freedom in meeting the specific needs of the UPS application.

TECHNOLOGY TAXONOMY MAPPING
High Energy Propellents (Recombinant Energy & Metallic Hydrogen)
Renewable Energy

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Giner Electrochemical Systems, LLC
89 Rumford Avenue
Newton, MA 02466-1311
(781) 529-0500

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Cortney Mittelsteadt
cmittelsteadt@ginerinc.com
89 Rumford Avenue
Newton,  MA 02466-1311
(781) 529-0529

Expected Technology Readiness Level (TRL) upon completion of contract: 5

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Utilizing high strength polymers with controlled pore dimensions as a support, a customized membrane electrode assembly (MEA) can be generated for NASA's electrolyzer and fuel cell stacks that has optimized electrochemical performance with greatly improved mechanical properties enabling high pressure (>1000 psi) operation. The overall objective is to optimize DSM-based MEAs for a NASA lunar application. This will be accomplished through six tasks; 1. Extending GES's gas crossover and chemical degradation mitigation strategies to DSMs 2. Improving DSM with better ionomer; 3. Optimize the anode; 4. Optimize DSM MEAs for H2/O2 fuel cells. 5. Update GES model for electrolyzer and fuel cell performance. 6. Use model to select optimal DSM for lunar electrolyzer application and generate MEAs for full-size stack.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Lunar and space stations, satellites, high altitude aircraft

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Fuel cell vehicles, hydrogen filling stations, chlor-alkali process

TECHNOLOGY TAXONOMY MAPPING
Composites
Energy Storage

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Giner Electrochemical Systems, LLC
89 Rumford Avenue
Newton, MA 02466-1311
(781) 529-0500

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Timothy Norman
tnorman@ginerinc.com
89 Rumford Avenue
Newton,  MA 02466-1311
(781) 529-0556

Expected Technology Readiness Level (TRL) upon completion of contract: 5

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Water electrolyzer stacks are a key component of regenerative fuel cells, designed to replace batteries as a means of storing electric energy on the lunar surface. The delivery of a 2,000 psi balanced pressure, lightweight prototype electrolyzer is proposed. The cell design will be significantly smaller and lighter, and capable of higher pressure operation than previous aerospace electrolyzers designed and built by Giner Electrochemical Systems, LLC. The successful completion of Phase I yielded test data, trade studies, a thin frame design, and model enhancements that would provide the basis of stack sizing. In a Phase II program, an enhanced, 2,000 psi test stand will be created by upgrading the existing 1,200 psi stand. It will then be used to demonstrate thin frame designs, the robustness of internal components, and the innovative prototypical compression hardware at realistic conditions. Further advances in thin frame technology will be investigated, and additional analyses of a new thermoplastic material will be conducted with the prospect of using them in the deliverable if these technologies are ready.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
NASA is charged with returning humans to the moon in a permanently occupied lunar station. This station will require electric power during both the daylight hours, and the nighttime. The lunar day/night cycle is twenty-eight (28) earth days long. This necessitates commensurately larger quantities of stored product/reactant gases for the regenerative fuel cell. A very high-pressure water electrolyzer, as a component of a closed-loop regenerative fuel cell, will permit smaller launch volumes, saving space aboard the Orion crew exploration vehicle. The electrolyzer might also be useful for the production of hydrogen and oxygen for space vehicle propulsion, enabling missions to Mars. Other electrolyzers may be used to produce oxygen for life support systems both during flight and on the lunar and Martian surfaces.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Closed-loop regenerative fuel cells are potential battery substitutes for applications that require high power density. Several agencies of the U.S. Government and several private businesses are engaged in development of long-endurance aircraft and airships. The high-pressure electrolyzer developed under this proposed program would be directly applicable to these vehicles. Large-scale power storage via regenerative fuel cells may have terrestrial applications in telecommunications and other industries that require uninterruptible power supplies.

TECHNOLOGY TAXONOMY MAPPING
Energy Storage
Photovoltaic Conversion
Thermodynamic Conversion

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Ultramet
12173 Montague Street
Pacoima, CA 91331-2210
(818) 899-0236

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Brian Williams
brian.williams@ultramet.com
Ultramet
Pacoima,  CA 91331-2210
(818) 899-0236

Expected Technology Readiness Level (TRL) upon completion of contract: 5

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Fission-based power systems with power levels of 30 to &#8805;100 kWe will be needed for planetary surface bases. Development of high temperature, high efficiency heat exchangers is critical for next-generation nuclear power and space propulsion systems. In Phase I, Ultramet and Sandia National Laboratories demonstrated the feasibility of using high surface area foam core heat exchanger technology to substantially improve the power conversion efficiency of liquid metal-to-gas high temperature heat exchangers for fission surface power systems. Preliminary design and modeling suggested a substantial improvement in the efficiency of a liquid lithium-to-helium component relative to conventional plate-fin heat exchangers, and hardware fabrication and testing demonstrated the manufacturability, performance, and simplicity of the foam-based design. Open-cell foam is a natural coolant channel that does not require extensive, expensive machining of intricate coolant passages and eliminates the need for braze-bonding or welding of numerous individual sections. Initial testing showed the ability of textured, vapor-deposited lithium-compatible coatings to be uniformly wetted by liquid lithium at low temperature. The technology has the potential to best minimize the temperature difference between the maximum lithium reactor coolant and helium working fluid temperatures, as well as to reduce system mass and volume through the use of high surface area, low density open-cell foam, and increase safety and reliability by minimizing the number of piece parts and associated joints. In Phase II, Ultramet will team with Sandia to expand on the Phase I success by performing comprehensive design and stress analysis, determining physical properties, and establishing performance through high temperature (1000 K) thermal response and flow testing of coaxial heat exchangers using the Helium Flow Loop and Liquid Metal Integrated Test System at Sandia's Plasma Materials Test Facility.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Lunar bases and colonies would be strategic assets for effective utilization of abundant lunar resources and development and testing of space technologies required for further exploration and colonization of favorable places in the solar system. A reliable power system is required to supply energy demands for life support, science, and operation. The proposed fission power system has the potential to provide the necessary high power conversion to meet surface power requirements.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
In addition to compact, high efficiency space reactors, the proposed technology could contribute to a new Department of Energy Generation IV power system that significantly lowers cost, improves passive safety, has no carbon dioxide emissions, uses an advanced, proliferation-resistant fuel cycle, and reduces nuclear waste. The foam core heat exchanger technology could also be used in ground-based power or in portable power systems for military or surveillance applications and remote deployment. Brayton components, Sterling converters, and heat pipes can all benefit from this refractory materials development effort.

TECHNOLOGY TAXONOMY MAPPING
Composites
Metallics
Nuclear Conversion

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Payload Systems, Inc.
1 Broadway
Cambridge, MA 02142-1189
(617) 868-8086

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
John Merk
jmerk@aurora.aero
1 Broadway 12h Floor
Cambridge,  MA 02142-1189
(617) 500-0281

Expected Technology Readiness Level (TRL) upon completion of contract: 6

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Nuclear reactors to support future robotic and manned missions impose new and innovative technological requirements for their control and protection instrumentation. Long duration surface missions necessitate reliable autonomous operation, and manned missions impose added requirements for fail-safe reactor protection. There is a need for an advanced instrumentation and control system for space-nuclear reactors that addresses both aspects of autonomous operation and safety. Highly reliable, earth-based reactor instrumentation systems can provide an excellent reference for space-based designs, however there is currently no earth-based reactor control system that is practical for use in space. In Phase I, we established the feasibility of adapting proven terrestrial reactor instrumentation for space application, and developed a preliminary architecture on which to base a flight system. This Phase II will result in a complete detailed design for a space-based Reactor Instrumentation and Control System (RICS), including fabrication and testing of a ground-based prototype for system evaluation. Additionally, we will leverage existing neutron detection technology developed under a previous NASA contract, and optimized for the space environment. This Wide Range Neutron Detector (WRND), in conjunction with the proposed RICS, will provide a complete solution for autonomous operation of space reactors from hundreds of watts to multi-megawatts.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
NASA foresees numerous applications of nuclear power reactors, with anticipated power needs that might range from a few kilowatts to the megawatt level. Illustrative examples of these applications are: deep-space missions, orbiting power stations, weather stations, habitats, surface mobility for robotic and piloted rovers; excavating and mining equipment, and science payloads in general. All of these applications will require autonomous systems for control, safety and monitoring of the reactor. Space-qualified reactor instrumentation and control systems will be a useful COTS product for manufacturers of space-qualified nuclear reactors. The predicted total demand is subject to the development of space-based nuclear reactors but it is not unthinkable to forecast demand on the order of a dozen a year.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The primary non-NASA customer is likely the DoD, as part of future space-based surveillance or missile defense systems. Given the energy levels, mission durations, and reliability requirements necessary to carry out the DoD's mission over the next two decades, it's very likely that space-nuclear reactors will be needed in the future. Other potential customers include government, military and university run research reactors where autonomous control and protection would be financially beneficial and/or safer by minimizing the need for human interaction in the vicinity of the reactor. In its most basic form, the RICS is a ruggedized, compact data-acquisition and control system that could be adapted to support a wide variety of harsh environments. As such, the RICS could be a useful instrument outside the scope of a nuclear reactor. This includes military applications where fail-safe data acquisition and control is required with stringent size, weight and power constraints.

TECHNOLOGY TAXONOMY MAPPING
Particle and Fields
Autonomous Control and Monitoring
Data Acquisition and End-to-End-Management
Data Input/Output Devices
Highly-Reconfigurable
Radiation-Hard/Resistant Electronics
Power Management and Distribution

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Creare, Inc.
P.O. Box 71
Hanover, NH 03755-3116
(603) 643-3800

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Mark Zagarola
mvz@creare.com
P.O. Box 71
Hanover,  NH 03755-0071
(603) 643-3800

Expected Technology Readiness Level (TRL) upon completion of contract: 4

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Long-life, high-capacity cryocoolers are a critical need for future space systems utilizing stored cryogens. The cooling requirements for planetary and extraterrestrial exploration missions, Crew Exploration Vehicles, extended-life orbital transfer vehicles, and space depots will range from 10 to 50 W at temperatures between 20 and 120 K. Turbo-Brayton cryocoolers are ideal for these systems because they are lightweight, compact and very efficient at high cooling loads, in addition to their inherent attributes of high reliability; negligible vibration; long, maintenance-free lifetimes; and flexibility in integrating with spacecraft systems and payloads. To date, space-borne turbo-Brayton technology has been developed for modest cooling loads. During the proposed program, Creare will develop an advanced, high efficiency turbine optimized for a high-capacity cryocooler. The advanced turbine will enable a landmark reduction in cryocooler input power and overall cooling system mass. In Phase I, we defined the cryocooler requirements for a particular mission class, developed the conceptual design of a multistage cryocooler to meet the requirements, developed the preliminary design of the advanced turbine and successfully performed proof-of-concept tests on the turbine. During Phase II, we will fabricate the turbine optimized to provide 5-20 W of net refrigeration at 20 K and demonstrate its performance at prototypical operating conditions.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Advanced turbines will enable high-capacity turbo-Brayton cryocoolers that are compact, lightweight, and consume minimal power. Space applications include cryogen storage for planetary and extraterrestrial exploration missions, Crew Exploration Vehicles, extended-life orbital transfer vehicles, long-term geosynchronous missions, in-space propellant depots and extraterrestrial bases, and cooling systems for observation platforms requiring large arrays of infrared and X-ray detectors. Terrestrial applications include cooling for spaceport cryogen storage and cryogen transportation systems.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Non-NASA commercial applications include cooling for laboratory-scale and industrial-scale gas separation; liquefaction; cryogen storage and transportation systems; high-temperature superconducting magnets in motors and magnetic resonance imaging systems; liquid hydrogen storage for automotive fuel cells; and commercial orbital transfer vehicles and satellites.

TECHNOLOGY TAXONOMY MAPPING
Fluid Storage and Handling

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Firestar Engineering, LLC
557 Burbank Street, Unit J
Broomfield, CO 80020-7160
(303) 439-2698

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
David Fisher
David@firestar-engineering.com
557 Burbank St., Unit J
Broomfield,  CO 80020-7160
(303) 439-2698

Expected Technology Readiness Level (TRL) upon completion of contract: 4 to 5

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Firestar Engineering has developed a set of Nitrous Oxide Fuel Blend monopropellants that are: 1) Non-toxic, 2) Specific Impulse> 310 s, 3) Freezing point < -77 C, 4) Self Pressurizing, and 5) Highly throttleable. A monopropellant with these characteristics and with bipropellant performance has the power to revolutionize both private and government space initiatives. Applications which will benefit from these monopropellant blends are wide spread and system level studies have indicated competitive overall performance with everything except cryogenic bipropellants. Phase II efforts will concentrate on thruster development and monopropellant UN/DOT transportation classification. Thruster development will concentrate on a 25 lbf RCS thruster and performing a number of tests required for flight certification.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Firestar has explored NOFB monopropellant use for a number of future NASA applications. We are currently exploring alternative architectures for the Altair Lunar Lander (as part of the Odyssey/Space X team) which uses a NOFB monopropellant ascent stage. Additionally, we have submitted a white paper on NOFB use for the Mars Science Orbiter. We believe that NOFB monopropellants can realistically compete with all non-cryogenic in propulsion alternatives for both manned and un-manned applications.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
A non-toxic monopropellant with bipropellant performance has the power to revolutionize in space propulsion. We believe that our NOFB monopropulsion systems will drastically reduce costs associated with in space propulsion. The toxicity of hydrazine, MMH, and NTO require high levels of recurring costs to qualify and maintain hardware. Additionally, contingency planning, containment, cleaning, and safety monitoring is a continual large overhead cost associated with hydrazine testing activities. In contrast, with NOFB monopropulsion systems we are able to rapidly test a large number of concepts with minimal ground support hardware which reduces costs in developing new hardware. A significant number of commercial aerospace companies have expressed an immediate interest in the development and flight qualification of NOFB monopropellant option s.

TECHNOLOGY TAXONOMY MAPPING
Chemical
High Energy Propellents (Recombinant Energy & Metallic Hydrogen)
Monopropellants
Propellant Storage
Cooling
Reuseable
Feed System Components
Energy Storage

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Plasma Processes, Inc.
4914 Moores Mill Road
Huntsville, AL 35811-1558
(256) 851-7653

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Daniel Butts
dbutts@plasmapros.com
4914 Moores Mill Road
Huntsville,  AL 35811-1558
(256) 851-7653

Expected Technology Readiness Level (TRL) upon completion of contract: 5 to 6

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The ARES J-2X requires a large nozzle extension. Currently, a metallic nozzle extension is being considered with carbon-carbon composite as a backup. In Phase 1, Plasma Processes Inc. (PPI), with the support from subcontractor ATK Launch Systems, fabricated, coated and test fired Haynes 230 and domestically produced 2-D carbon-carbon nozzle extensions. The test results show coated carbon-carbon intact and Haynes 230 in need of film cooling and emissivity and, or thermal barrier coatings. Oxide emissivity coating reduced the Haynes 230 wall temperature by 500F. In Phase 2, the primary goal will be to develop the optimum thermal solution for a metallic J2X nozzle extension. Working with Pratt & Whitney Rocketdyne, high emissivity and thermal barrier solutions will be demonstrated on successively larger components until full size capability is demonstrated. A secondary goal is to continue the demonstration of domestically produced 2-D C/C composite nozzle extension materials and oxygen protective liners for use on liquid rocket engines. The team of Plasma Processes, Inc., Pratt & Whitney Rocketdyne and ATK Launch Systems offers the state of the art skill set that is uniquely suited to the Phase 2 program.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
J2X Nozzle Extension LSAM Ascent and Descent Engines Leading edges and control surfaces for hypersonic aircraft Propulsion components for space access and space return vehicles Propulsion components for Moon/Mars landing vehicles Common Extensible Cryogenic Engine (CECE)

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Nosetips , rocket nozzles and control vanes for strategic and tactical missiles Thermal control components for nuclear power, power generation, internal combustion, and jet engine applications. Crucibles High Power X-Ray Targets

TECHNOLOGY TAXONOMY MAPPING
Chemical
High Energy Propellents (Recombinant Energy & Metallic Hydrogen)
Micro Thrusters
Monopropellants
Nuclear (Adv Fission, Fusion, Anti-Matter, Exotic Nuclear)
Cooling
Reuseable
Thermal Insulating Materials
Earth-Supplied Resource Utilization
Ceramics
Composites
Metallics
Multifunctional/Smart Materials
Biochemical Conversion
Nuclear Conversion
Thermodynamic Conversion
Aircraft Engines

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Eltron Research, Inc.
4600 Nautilus Court South
Boulder, CO 80301-3241
(303) 530-0263

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Richard Bley
eltron@eltronresearch.com
4600 Nautilus Court South
Boulder,  CO 80301-3241
(303) 530-0263

Expected Technology Readiness Level (TRL) upon completion of contract: 6

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The goal of this work is to develop new thermoelectric materials for use in fabricating solid state cooling devices and electrical power generators, which are 200 to 300% more efficient than current thermoelectric materials and can operate in temperatures ranging from cryogenic to 700 C. The results of our Phase I definitely indicate that we will be able to reach this goal. These materials are being made from new nano-composites, using fabrication techniques developed at Eltron. The thermoelectric composite's matrix had already demonstrated exceptional ability for functioning in the environment of space. Used in a cooling system, these materials will provide an effective means for controlling the temperature of surfaces subject to the rapidly changing temperatures encountered in space. We have proven that this matrix works exceptionally well at providing support and allowing for convenient (and therefore economical) deposition of our materials. We have also demonstrated that the thermal conductivity in these new nano-materials has been reduced by well over an order of magnitude! In addition we have shown that we get an increase in the Seebeck Coefficient for materials we tested as well. These new thermoelectric materials can be used to prevent development of large temperature gradients and thereby prevent the mechanical stresses that accompany them. Used for power-generation, these new materials will be very efficient because of the properties that both the nano-phase materials and its matrix bring to the thermoelectric material. Because of the difficulties presented in the harsh environment of space, thermal management and power generation is most easily provided through devices that do not have any moving parts, are very durable, do not require maintenance, and operate efficiently over a wide range of temperatures. The proposed materials meet all these requirements.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
In the past, NASA's interest in thermoelectric systems has stemmed both from the need for an effective means of temperature control via the Peltier effect for surfaces exposed to the rapidly changing temperatures that occur in space, and for use in generating electrical power via the Seebeck effect for space vehicles too distant from the sun for effective use of solar panels. The new materials being developed here will be capable of withstanding both high and low temperatures and so they can be used to prevent development of large temperature gradients and the mechanical stresses that accompany them on missions such as the upcoming Mars and Venus trips. This is particularly true of the Venus landing, where materials will need to withstand up to 500 C temperatures. The improvement in efficiency possible from these materials as demonstrated during the Phase I could make them competitive with solar cells as a power source for space missions.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Development of this technology will result in considerable improvement in efficiency over currently used evaporative systems used in consumer and industrial refrigeration. This technology will also be of great value to the electronics industry. Systems incorporating this new technology will run more quietly and will produce much less pollution than current refrigeration and air conditioning systems. They will not be subject to the maintenance problems common in the compressors used today. An efficient, solid state electrical power generator that uses heat as its energy source would also result from successful development of this technology. The Boeing Company is very excited about our Phase I results and will be acting as a subcontractor in this Phase II. They will also continue to participate in this project in an advisory and reviewer capacity, as stated in their letter of support.

TECHNOLOGY TAXONOMY MAPPING
Cooling
Composites
Semi-Conductors/Solid State Device Materials
Thermoelectric Conversion

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Advanced Cooling Technologies, Inc.
1046 New Holland Avenue
Lancaster, PA 17601-5688
(717) 296-6058

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
William Anderson
bill.anderson@1-ACT.com
1046 New Holland Avenue
Lancaster,  PA 17601-5606
(717) 295-6061

Expected Technology Readiness Level (TRL) upon completion of contract: 6

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Long-term Lunar and Martian systems present challenges to thermal systems, including changes in thermal load, and large changes in the thermal environment between day and night. The innovation in the program is the development of a variable conductance heat pipe (VCHP) that passively accommodates the changing thermal load and environment. This allows the heat pipe evaporators (and any attached heat exchanger) to remain at an almost constant temperature. In addition to passively controlling the thermal load, the non condensable gas allows the fluid in the heat pipe to freeze in a controlled manner as the heat pipe is shut down, avoiding damage. The gas in the VCHP also helps with start-up from a frozen condition. The overall technical objective of the Phase I and Phase II programs is to develop a VCHP radiator that can passively adjust to changing temperatures/powers in the Lunar and Martian surface environments while maintaining the coolant outlet temperature in an acceptable range. During the Phase II program, a radiator panel and heat exchanger will be fabricated, then tested in a thermal vacuum chamber. Tests will include thermal cycling, as well as the ability of the radiator to startup from a frozen state.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The immediate NASA application is for Lunar and Martian radiators that can passively accommodate the large swings in environmental conditions between Lunar (or Martian) day and night, including long periods at very low temperatures. In addition, the VCHP can passively accommodate large changes in thermal load, and avoid damage during periods of low thermal load. Furthermore, the non-condensable gas in the VCHP will help with start-up during sudden increases in thermal load.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
A commercial application is VCHP heat exchangers in fuel cell reformers. In a fuel cell reformer, diesel fuel and air pass through a series of high temperature reactors to generate hydrogen. The operating temperature of the reactors must be closely controlled to maintain their chemical equilibrium. A typical system must maintain inlet and outlet temperatures within ±30<SUP>o</SUP>C despite a turndown ratio of 5:1 in reactant flow rate. The current scheme uses a bypass valve, which has several drawbacks: it requires active control and electrical power, and has a large pressure drop. A VCHP heat exchanger can replace the current heat exchanger and control system with a passive system that automatically maintains the output stream from the heat exchanger at a constant temperature.

TECHNOLOGY TAXONOMY MAPPING
Cooling

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Illuminex Corporation
1064 New Holland Avenue
Lancaster , PA 17601-5606
(717) 871-8971

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Youssef Habib
joe.habib@illuminex.biz
1064 New Holland Ave.
Lancaster,  PA 17601-5606
(717) 871-8971

Expected Technology Readiness Level (TRL) upon completion of contract: 8

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Heat pipes are widely used for passive, two-phase electronics cooling. As advanced high power, high performance electronics in space based and terrestrial applications produce ever increasing heat fluxes, heat pipes with improved thermal capacity are sought. Illuminex Corporation has demonstrated that using copper nanowire arrays as the wick in heat pipes increases the heat transfer capabilities. Phase I developed processing techniques to engineer copper nanowire arrays on copper sheet that were subsequently incorporated into vapor chamber style heat pipes as the wicking material at the evaporator region. In Phase II, the program will be advanced to manufacture large area copper sheets fully covered with nanowires on one side. This material will be used to construct the entire heat pipe, package and wick. This will enable the development of high performance, lightweight, low-profile (< 1 mm) heat pipes with enhanced thermal transfer properties. The decrease in weight and size is desirable for NASA space projects and will find commercial application in radar systems, servers, and portable electronic devices. The use of less material in heat pipe manufacture will result in lower production costs while the superior performance and smaller size will provide electronic system designers with greater flexibility in thermal management system design.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Heat pipes require no maintenance and consume no power, making them attractive components for cooling electronics in space vehicles, satellites, and astronaut support systems. Illuminex innovation results in size and weight reductions that are desirable for space applications. Currently, NASA is developing nuclear electric propulsion systems for long-duration space missions like the Jupiter Icy Moon Orbital mission. Heat pipes are proposed for the transfer of waste heat from the power generation systems and for use in the radiator systems used for the dissipation of the waste heat. Heat pipe thermal control technology has also been proposed for electric power generation for a lunar habitat, for the Space Solar Power Project, and spacecraft thermal control. Improved capillary pumping capabilities in zero gravity and under acceleration in nanowire heat pipes could prove valuable in space applications where gravity assisted systems are not functional.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The thermal characteristics of high-power-density CPUs in today's high-end computing applications are rapidly outpacing the cooling capabilities of commercially available strategies. The primary devices driving the market for nanowire heat pipes are high performance microprocessors. Technological advances in thermal control are needed to accommodate rising power densities in new electronic and optical devices and a steady replacement of traditional heat sinks by hybrid heat sinks with embedded heat pipes. The initial market for the nanowire array wick heat pipes will be the niche market of high end specialty heat pipes designed for military and aerospace applications including laser, radar and antenna systems. The next anticipated specialty market is thermal management in high end servers, followed by portable computers and other electronic consumer goods. Illuminex has partnered with Thermacore Inc., the largest North American manufacturer and distributor of heat pipes to bring the advanced nanowire heat pipe technology to the market.

TECHNOLOGY TAXONOMY MAPPING
Cooling
Earth-Supplied Resource Utilization
Metallics

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Linea Research Corporation
1020 Corporation Way, Suite 216
Palo Alto, CA 94303-4317
(650) 325-9000

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Yong Jin Lee
lee@linearesearch.com
781 Rosewood Drive
Palo Alto,  CA 94303-3638
(650) 533-9546

Expected Technology Readiness Level (TRL) upon completion of contract: 6 to 7

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
A key component of NASA's human exploration programs is a system that monitors the health of the crew during space missions. The wearable beat-to-beat blood pressure monitor proposed by Linea Research Corporation can be used to continuously monitor the physiological effect of prolonged space missions (including exposure to reduced gravitational environments) and the effectiveness of its countermeasures. During Phase I of the program, we demonstrated the feasibility of a novel, non-invasive beat-to-beat blood pressure monitor using a lightweight (<40 g) and low-power (<100mA @ 5V) initial prototype. Measurement of beat-to-beat blood pressure was successfully verified during human studies (tilt table tests) using a cuff-based blood pressure monitor as reference. Measurement of the beat-to-beat blood pressure was also verified against an arterial line in animal (porcine) studies using epinephrine to induce blood pressure changes. During Phase II of the program, we will develop and fabricate a field-capable, light-weight, wearable beat-to-beat blood pressure monitor that will be ready for demonstration on space missions. In addition to supplying the blood pressure monitors for use by NASA, Linea plans to introduce the technology for use in ambulatory blood pressure monitors. Linea will subsequently introduce the technology for integration into high acuity as well as home based blood pressure monitors. One patent has been filed and three are currently being prepared to protect the intellectual property. A business plan has been prepared to address the commercialization opportunities.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Autonomous medical care for the crew during human exploration missions is critical in preventing degradation in health due to adverse physiological responses to space flight environments. A wearable physiological monitor that provides continuous blood pressure (and heart rate) measurements will be extremely valuable in providing proper medical support for both normal activities and medical emergencies. The device can be used to monitor the long-term physiological effects of hypogravity and the effects of the countermeasures against hypogravitational environments. The device can also be modified to monitor the health status of crew during extravehicular activities. The device will provide wireless connectivity to a monitor (e.g. laptop already onboard) to allow transfer of both real-time and historical physiological data. The system will be developed as a single-unit wearable device which necessitates low power consumption and compact and lightweight form factor. The size criterion is a key factor for space applications as launch costs are directly determined by the weight of the device.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The proposed device has the potential to fundamentally change the half-billion dollar blood pressure monitoring device market. The technologies developed under the NASA program are most immediately applicable to ambulatory blood pressure monitors, but can also be applied to high acuity (e.g. arterial line replacement) as well as home blood pressure monitoring devices. For the ambulatory and home blood pressure monitoring segment, the technology developed under this program will enable beat-to-beat blood pressure measurement which will allow continuous measurement of blood pressure. Another significant advantage of the proposed beat-to-beat technology is that it does not require the inflation of the cuff except for calibration measurements. The inflation of the cuff can be uncomfortable for many users and can result in complications such as petechiae on the arm. The key advantage of the proposed technology over arterial lines used for high-acuity applications is the non-invasive nature of the measurement. Blood pressure monitoring based on arterial lines involves invasive procedures requiring percutaneous insertion of catheters into the radial or brachial arteries. Cannulation of the artery requires a skilled health professional and can often take significant time. In addition, cannulation can result in a number of complications including bleeding, infection, and rarely but significantly, lack of blood flow to the tissue supplied by the artery.

TECHNOLOGY TAXONOMY MAPPING
Biomedical and Life Support

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Operational Technologies Corporation
4100 N.W. Loop 410
San Antonio, TX 78229-4253
(210) 731-0000

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
John Bruno
john.bruno@otcorp.com
4100 N.W. Loop 410, Ste. 230
San Antonio,  TX 78229-4253
(210) 731-0015

Expected Technology Readiness Level (TRL) upon completion of contract: 6 to 7

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Astronauts lose significant bone mass during lengthy spaceflights. Although, no effective treatments or prophylactics have yet been defined, it is important to monitor bone loss during missions. As such, the sensor must be compact and facile to operate in spacecraft. Operational Technologies Corp. (OpTech) proposes to complete development of its successful Phase I competitive fluorescence resonance energy transfer (FRET)-aptamer assays for several bone loss markers and calcidiol. In Phase I, OpTech developed several rapid (15 minutes) specific competitive polyclonal FRET-aptamer assays with low nanogram/ml sensitivity. OpTech also cloned and sequenced 110 bone marker and calcidiol aptamers which will be individually screened in Phase II for optimal FRET assay performance. During Phase II, OpTech will shift its FRET to emit in the red (> 600 nm) to avoid the intrinsic fluorescence of urine and serum. OpTech will also lyophilize and package optimized FRET-aptamer assays for use with a bubble-free plastic cuvette and body fluid collection system. The assay system will be coupled to a modified version of the commercial off-the-shelf (COTS) Picofluor[TM] handheld battery-operated fluorometer customized to detect bone markers and calcidiol in body fluids. OpTech will deliver the packaged assays, handheld reader and software to NASA for testing.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
NASA would use this technology as a portable means for astronauts to sensitively self-monitor their bone loss or bone preservation treatments with one-touch ease from urine or serum samples. Monitoring of other clinical analytes such as glucose and environmental microbe monitoring in water supplies by astronauts would also be possible, if appropriate FRET-assays were developed.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Women and the elderly could use this system as a rapid and facile point-of-care (POC) diagnostic system to monitor osteoporosis and the efficacy of therapeutic regimens. The system might also be used to monitor bone repair following severe fractures or skeletal procedures related to plastic or reconstructive surgeries. In a broader sense, OpTech is developing FRET-aptamer assays for a wide array of analytes on Earth including foodborne pathogens and other bacterial, viral and clinical analytes.

TECHNOLOGY TAXONOMY MAPPING
Biomedical and Life Support
Biophysical Utilization

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Valeo Human Performance, LLC
1235 Clear Lake City Blvd., Suite F
Houston, TX 77062-8105
(281) 488-5877

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Paul Colosky
pcolosky@valeopt.com
1235 Clear Lake City Blvd., Suite F
Houston,  TX 77062-8105
(281) 488-5877

Expected Technology Readiness Level (TRL) upon completion of contract: 5 to 6

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
NASA's vision for future exploration-class missions has made countermeasures for muscle atrophy, bone loss and cardiovascular deconditioning areas of major research design and development within the U.S. space program. Due to restricted volume and mass capabilities within the newly-developing Crew Exploration Vehicle (CEV) and Lunar Surface Access Module (LSAM), there is a need for a multi-functional, compact exercise machine that can incorporate both resistive and aerobic exercise capabilities during lunar sortie missions. The proposed innovation is an exercise device, the multi-functional Constant Force Resistive Exercise Unit (CFREU), that can provide a whole-body workout for aerobic exercise and resistive exercise. The device provides constant force eccentrically and concentrically during multiple exercise configurations, allows resistance selection in 2.5kg increments, requires no power to operate, requires no on-orbit maintenance, and can be stowed in an area of 1 cubic foot. During the Phase II performance period, we propose to develop a fully-functional CFREU, as well as to perform a usability study.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Valeo's competitive advantage lies within the CFREU design. The unit is compact, easy to use, requires no power to operate, and requires no on-orbit maintenance or calibration. There is an evident need for a gravity-independent exercise unit that can provide a constant force for resistive exercise with integrated aerobic capability fashioned in a compact and lightweight design that offers familiarity, safety, and comfort during exercise.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Rehabilitation institutions would benefit from the multi-functional CFREU design. A portable exercise machine that can provide aerobic and constant force resistive capabilities in such a small volume is essential in clinical settings, and would prove especially beneficial in treating patients confined to bed rest. Physiologically, the constant force resistance provided by the CFREU is comparable to a traditional weight stack machine, but without the bulkiness and mass of weight plates. The personal home exercise equipment industry would also benefit from the multi-functional CFREU device. The compact force packs of the CFREU allow the overall unit to be small enough for easy use as a home gym. For the home gym design, future force packs can be designed such that they may be purchased individually by a consumer, and used as portable exercise devices when not in use with the full CFREU. Thus, the force packs replace the need for expensive, heavy, and bulky traditional weight plates, and allow portability.

TECHNOLOGY TAXONOMY MAPPING
Biomedical and Life Support

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
The DNA Medicine Institute
116 Charles Street, Suite 6
Boston, MA 02114-3217
(617) 233-7656

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Eugene Chan
echan@dnamedinstitute.com
116 Charles Street, Suite 6
Boston,  MA 02114-3217
(617) 233-7656

Expected Technology Readiness Level (TRL) upon completion of contract: 6

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The goal of the rHEALTH sensor is to provide rapid, low-cost, handheld complete blood count (CBC), cell differential counts, electrolyte measurements, and other lab tests based on a reusable, flow-based microfluidic platform. For Phase II, we will develop an rHEALTH prototype to be delivered to NASA for reusable CBC, cell differential counts, and electrolyte measurements. Each subassembly and individual assay will be tested individually prior to full integration into the system level prototype. The rHEALTH sensor is a compact, portable device that employs cutting-edge fluorescence detection optics, innovative microfluidics, and unique capabilities. Based on its streamlined design, the rHEALTH sensor is able to perform a suite of different assays using a single drop of blood. Furthermore, the entire system allows cost-effective operation because of its nanoliter operating volumes. This is in contrast to existing point-of-care diagnostics devices such as the iSTAT and Piccolo systems which only perform one panel of assays per disposable reagent cartridge. The result is a highly practical, cost-effective, and powerful sensor. The successful completion of the Phase II program is a significant milestone for our rHEALTH sensor. It means that we would have been successful in shrinking hospital-sized clinical laboratory into a portable device.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
(1) Real-time health monitoring. The proposed rHEALTH sensor is designed to monitor daily astronaut status so that adverse health events can be managed. (2) Real-time intervention. The ability to measure routine health status allows clinical intervention at appropriate times. (3) Electrolyte measurement on a daily basis for long space flight. (4) CBC measurements on a daily basis. (5) Measurement of cardiac biomarkers for chest pain to rule out myocardial infarction. (6) Measurement of CBC and electrolytes in response to astronaut illness. (7) Monitoring of astronaut renal function to assess volume status. (8) Tracking of bone biomarkers and calcium levels throughout duration of missions to assess intangible bone loss and remodeling.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
(1) Real-time health monitoring. Development of the rHEALTH allows monitoring of health status in real-time at the bedside or doctor's office. (2) Real-time intervention. Clinical intervention can be accomplished rapidly in acute situations with a handheld monitor. (3) Measurement of daily hematocrit for patients on coumadin or other anti-coagulation to diagnose early blood loss. (4) Detection of acute myocardial damage rapidly and outside the hospital so that life-saving therapy can be administered for heart attack patients. (5) Monitoring resolution of a patient's infection by tracking white blood cell counts throughout a prolonged antibiotic course. (6) Monitoring daily renal function of patients with kidney transplants or those with end-stage renal disease. (7) Measurement of athletes volume status during prolonged training for early diagnosis and dehydration. (8) Daily monitoring of electrolyte status for those individuals taking diuretics. Frequently, diuretics such as furosemide may cause hypokalemia and need to have their daily electrolyte status assessed.

TECHNOLOGY TAXONOMY MAPPING
Biomedical and Life Support
Biomolecular Sensors
Biochemical

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Design Interactive, Inc.
1221 E. Broadway, Suite 110
Oviedo, FL 32765-7829
(407) 706-0977

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Ali Ahmad
ali@designinteractive.net
1221 E. Broadway, Suite 110
Oviedo,  FL 32765-7829
(407) 706-0977

Expected Technology Readiness Level (TRL) upon completion of contract: 4 to 5

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The Cognitive Gauge (CogGauge) tool aims to develop a portable gaming application that assesses cognitive state of astronaut crew members with the goal of determining probable causes of observed cognitive deficits. CogGauge, while engaging astronauts in an entertaining experience, combines predictive tools for assessing cognitive workload with metrics that assess performance decrements. CogGauge uses a hybrid approach combining predictive workload values with behavioral/performance-based workload assessment across a number of task difficulty levels. This comprehensive approach takes into consideration learning effects across a number of cognitive tasks (i.e., mini-games in the gaming context) and derives assessment of performance decrements related to cognitive deficits to identify probable causes of cognitive decrement. Feedback from CogGauge may be provided to astronauts and/or flight surgeons to determine impact on space flight and missions.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
CogGauge, once developed, forms a foundation for several potential tools for use within NASA. For example, the underlying framework that utilizes a combination of predictive workload and performance/behavioral measures can be used to build several tools that could be integrated within shuttle (or its future replacements) controls to assess astronaut cognitive workload during a mission. Another possible expansion is to assess ground operations centers workload while monitoring a mission progress. In essence, the concepts/approach implemented in CogGauge could potentially expand to several applications within NASA that involve intense human-system integration.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
In terms of other government and commercial markets, CogGauge could be potentially tailored for use by aircraft pilots to assess their cognitive workload before/after long flying hours. In many situations, the approach/algorithms implemented in CogGauge could be used to model an operator interacting with a complex system, such as Command and Control, Power Plant Control Units, Nursing Stations, and so on. In today's net-centric work environment, operators are required to consume multiple streams of data simultaneously from several monitor stations, which can lead to issues of cognitive overload, decreased performance, and loss of situation awareness. CogGauge could be adapted to monitor operator workload in real-time and drive potential adaptations to displays/task demands to minimize times of overload. Such an extension of CogGauge may be useful in domains such as airport security checkpoints, customs, police stations, etc.

TECHNOLOGY TAXONOMY MAPPING
Biomedical and Life Support
Human-Computer Interfaces
Portable Data Acquisition or Analysis Tools

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
NTI, Inc.
1 1/2 S. Central Avenue
Fairborn, OH 45324-4716
(937) 253-4110

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Robert O'Donnell
odnova@aol.com
1 1/2 S. Central Avenue
Fairborn,  OH 45324-4716
(937) 879-0612

Expected Technology Readiness Level (TRL) upon completion of contract: 5

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Existing cognitive performance test batteries consist of synthetic tasks that, while they may probe isolated cognitive functions, provide an incomplete and unconvincing picture of an individual's true cognitive capacity within the total context of space missions. In essence, they are 'laboratory' measures that appear unrelated to the real-world environment. This leads to user non-compliance or rejection. The present proposal describes a technique for integrating traditional cognitive performance measures with assessment of the system and mission in which the individual must operate. This yields quantified measures of the person's cognitive ability to perform specific jobs in space. Specifically, an entertaining and scientifically rigorous assessment tool is integrated with a sleep/fatigue model and a quantified workload estimate for each task. This is accomplished by selecting tests based on task analyses of what the astronaut actually has to do, using the Fatigue Avoidance Scheduling Tool (FAST) to predict performance capacity as a function of sleep/rest, and integrating a mathematical vector to quantify the workload of specific tasks. The resulting "Person-System-Mission (PSM) index" provides a totally new and unique way not only to assess present cognitive capability, but to diagnose specific causes of decrement, and to suggest remedial actions.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Measurement and prediction of the cognitive effects of stressors such as fatigue and workload on specific tasks required of the astronaut are critical to NASA. The existence of a valid metric that is expressed in terms of the individual's ability to carry out specific tasks, rather than in terms of esoteric cognitive skills, will dramatically increase the value of an assessment tool to the individual, the commander, and the flight surgeon, thereby increasing user acceptance. This will lead to incorporation of such a metric on all spaceflights, especially those of long duration.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The principal non-NASA Government applications for the technology developed here will be in the Department of Defense and the Homeland Security Department. Mission- and safety-critical jobs frequently involve stressful conditions such as fatigue and high workload in both of these agencies. In DoD, for instance, the need to assess the combat readiness of the dismounted warrior has led to the establishment of the "Cog-Fit" program, which is attempting to model the effects of combat stresses on the person's ability to perform their job. The Air Force has similar programs. Homeland security, in addition to Coast Guard operations, requires personnel such as airport screeners to maintain high levels of cognitive alertness for long periods of time. It is expected that each of these agencies will have immediate applications for this technology. Non-NASA commercial applications will involve marketing the technology to transportation, shipping, and freight organizations that routinely carry out safety-sensitive operations, as well as to educational, industrial, and self-help organizations that will recognize the value of a scientifically well-grounded, entertaining cognitive assessment system.

TECHNOLOGY TAXONOMY MAPPING
Testing Requirements and Architectures
Autonomous Reasoning/Artificial Intelligence

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
PROVE IT, LLC
14514 Creek Crossing Drive
Orland Park, IL 60467-6046
(708) 441-9781

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
George Sadler
sadler@proveitllc.com
14514 Creek Crossing Drive
Orland Park,  IL 60467-6046
(708) 441-9781

Expected Technology Readiness Level (TRL) upon completion of contract: 3 to 4

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
NASA calculation that over a kg of packaging waste are generated per day for a 6 member crew. This represents over 1.5 metric tons of waste during a Mars mission. Currently, these wastes are considered a disposal burden. However, packaging can designed to have valuable secondary uses which can lighten other payloads. These include: Light generation, electricity generation, storage structures, building materials, and raw material for hardware items. These benefits are not readily available in NASA's foil laminate structures used for packaging. Other materials more amenable to secondary uses lack the moisture and oxygen barrier essential to achieve NASA's shelf life targets for foods. This project controls moisture electro-thermally and oxygen electrochemically in an overwrap container. Once oxygen and moisture are managed in the overwrap, individual packaging can be made of virtually any material and the broad potential of secondary packaging becomes available. Phase I developed the tools and mathematical equations necessary to construct and model the performance of the overwrap system. Phase II research will combine these tools to create a working overwrap system capable of achieving NASA's shelf life requirements and providing valuable secondary uses to packaging wastes. As a result of this research, spent packaging will no longer be a waste burden, but will become a valuable mission asset.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The overpack system with secondary applications parallels military needs. The US Navy seeks strategies for reducing packaging wastes and the Army has need for lightweight packages which are more adaptable to field preparation. The proposal explores space savings innovations such as magnetic induction heating and laser fabrication using spent packaging. These have broad application across the space program and throughout the military.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Proposed packaging innovations have commercial, military and environmental application. Strategies for imparting biochemical activity to packaging (including antimicrobial, oxygen scavenging, and antioxidant properties) have broad food and pharmaceutical applications. The military also relies on foil laminate containers. Innovations of this research would provide packaging to the military which are lighter in weight and which are more amenable to field preparation. Seeking strategies to build value into packaging waste is in itself environmentally responsible. However, as world environmental regulations become stricter, new markets will open for technologies which address packaging wastes.

TECHNOLOGY TAXONOMY MAPPING
Erectable
Tankage
Biomass Production and Storage
Sterilization/Pathogen and Microbial Control
Waste Processing and Reclamation
In-situ Resource Utilization
Radiation Shielding Materials
Photovoltaic Conversion
Renewable Energy
Thermoelectric Conversion

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Merril Corporation of Utah, dba MSI Photogenics
P.O. Box 511283
Salt Lake City, UT 84151-1283
(801) 773-7900

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
John Czirr
bart.czirr@missionsupport.us
515 East 1860 south
Provo,  UT 84606-7312
(801) 374-6722

Expected Technology Readiness Level (TRL) upon completion of contract: 5

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Analysis of Phase I test data demonstrates that the Photogenics Spectroscopic Dosimeter will detect neutron energies from 0.8 up to 600 MeV. The detector efficiencies in the energy region of interest to NASA of 0.5 to 150 MeV were predicted by MCNP-X models. These models were partially confirmed by the tests at the EAL and LANSCE, with a high confidence in the data for the 1-14 MeV range and a confirmation of the detector's spectroscopic capabilities between 15-150 MeV. Further analysis of the high energy data will be performed in Phase II. Using the detection efficiencies determined Phase I and the IRCP74 damage coefficients, doses have been calculated for the neutron fluxes encountered in the test facilities. During Phase II a full-scale working model of the spectroscopic dosimeter will be fabricated and tested.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
NASA is seeking improved neutron spectroscopy to enhance its characterization of the space environment and has also identified a need for improved accuracy in the estimate of neutron dose experienced by astronauts on long duration space missions.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The NASA version of the dosimeter can be redesigned for use in radiation safety monitoring at a wide variety of facilities concerned with potential radiation hazards, i.e. laboratories, university research facilities, and private nuclear power plants.

TECHNOLOGY TAXONOMY MAPPING
Particle and Fields

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Michigan Aerospace Corporation
1777 Highland Drive, Suite B
Ann Arbor, MI 48108-2285
(734) 975-8777

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
David Johnson
djohnson@michaero.com
1777 Highland Drive, Suite B
Ann Arbor,  MI 48108-2285
(734) 975-8777

Expected Technology Readiness Level (TRL) upon completion of contract: 5

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Michigan Aerospace Corporation (MAC) is pleased to present the following Phase II proposal for a Fabry-Perot Based Interferometer Receiver for the High Spectral Resolution Lidar (HSRL) System. Under the Phase I work, MAC successfully developed instrument models and created a conceptual design for an aircraft-qualified receiver that can be used with the current HSRL collection optics. This design is optimized to spectrally separate the aerosol and molecular backscatter for the calculation of the aerosol-to-total-scattering ratio and aerosol extinction coefficient. Additionally, wind and temperature data products can be produced with this system. The proposed Phase II efforts are directed at designing and building a bench-top HSRL 532nm receiver that is capable of taking accurate measurements of aerosol scattering ratio, extinction coefficients, molecular temperature and line-of-sight (LOS) velocity. This demonstration unit will verify a new adaptive interferometer measurement technique, called the Programmable Edge Technique (PET), which makes use of a Digital Micro-mirror Device (DMD) in conjunction with a Fabry-Perot interferometer and two photo-multiplier tubes (PMT). The completed bench-top receiver design will serve as the baseline for future aircraft mounted implementations.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
This research is directly applicable to the highly-modular HSRL system at NASA Langley Research Center. Subsequent development of this work will result in a system that can validate and extend the current HSRL system. A 532nm implementation of this work will allow cross-validation of the HSRL and PET techniques, as well as add extended capability for temperature, density, pressure and line-of-sight (vertical) wind velocity estimation.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The atmospheric measurement capabilities made possible through this research aids in military areas such as atmospheric mitigation for snipers, long-range gunnery and precision landing zones for manned and unmanned aircraft as well as meteorological monitoring to assist in Nuclear/Biological/Chemical (NBC) threat analysis and tracking. Non-military applications include clear-air turbulence sensing for commercial aircraft, meteorological monitoring of tropospheric and upper-atmosphere winds, and site selection and improved efficiency for wind farms.

TECHNOLOGY TAXONOMY MAPPING
Optical
Photonics

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Fibertek, Inc.
510 Herndon Parkway
Herndon, VA 20170-5225
(703) 471-7671

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Floyd Hovis
fhovis@fibertek.com
510 Herndon Pkwy
Herndon,  VA 20170-5225
(703) 471-7671

Expected Technology Readiness Level (TRL) upon completion of contract: 5

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Stable, single-frequency cw lasers operating at 2 µm and at 1064/532/355 nm are needed in a number of lidar systems that are being planned for NASA airborne and space-based lidar systems. These include the following. 1. Direct Detection Doppler Wind Lidar systems that operate at 355 nm. 2. Coherent Wind Lidar systems that operate at 2 µm. 3. High Spectral Resolution Lidar systems that operate at 1064/532/355/nm. 4. Ozone DIAL systems. At least two missions that have been recommended by the NRC Earth Science Decadal Survey will need the technology that we propose to develop. These are the 3D-Winds mission and the ACE (Aerosol/Clouds/Ecosystems) mission. In our Phase 1 SBIR we successfully completed proof of principle demonstrations of the desired cw single-frequency lasers. Our approach for the 2 µm source was a compact linear resonator that demonstrated 65 mW of single frequency output compared to a goal of 20 mW. Our approach for the 1064/532/355 nm source was intracavity second and third harmonic generation in a compact 1064 nm ring laser that demonstrated simultaneous single-frequency outputs of 520 mW at 1064 nm, 240 mW at 532 nm, and 1.9 mW at 355 nm. The goal was > 1 mW at 355 nm. For Phase 2 we propose to build more hardened engineering demonstration units of the lasers, to develop electronics that could be readily transitioned to radiation hardened designs, and to demonstrate a frequency locking module for the 1064/532/355 nm source. We expect both lasers to be at a TRL of 5 at the completion of the Phase 2 work.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Stable, single-frequency cw lasers operating at 2 µm and at 1064/532/355 nm are needed in a number of lidar systems that are being planned for NASA airborne and space-based lidar systems. These include the following. 1. Direct Detection Doppler Wind Lidar systems that operate at 355 nm. 2. Coherent Wind Lidar systems that operate at 2 µm. 3. High Spectral Resolution Lidar systems that operate at 1064/532/355/nm. 4. Ozone DIAL systems. At least two missions that have been recommended by the NRC Earth Science Decadal Survey will need the technology that we propose to develop. These are the 3D-Winds mission and the ACE (Aerosol/Clouds/Ecosystems) mission.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
We have identified the following three possible non-NASA commercial applications. 1) Fourier Transform Spectroscopy for remote sensing applications. A stable and robust single frequency 1064 nm source is needed to support these activities. 2) Direct Detection Wind Lidar development at a number of aerospace companies. We have identified at least four companies that are interested in using the technology we are proposing to develop as a part of wind lidar systems that they are developing for balloon-based, airborne, and space-based applications. 3) Development of an aircraft based water vapor lidar for atmospheric studies of the troposphere. A 1064 nm seed laser will be needed for the water vapor lidar we have jointly proposed to build.

TECHNOLOGY TAXONOMY MAPPING
Laser
Optical

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Q-Peak, Inc.
135 South Road
Bedford, MA 01730-2307
(781) 275-9535

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Alex Dergachev
dergachev@qpeak.com
135 South Road
Bedford,  MA 01730-2307
(781) 275-9535

Expected Technology Readiness Level (TRL) upon completion of contract: 4 to 5

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The primary objective of the proposed Phase II program is to develop and deliver a ruggedized, compact single-frequency 2050-nm-laser system suitable for coherent LIDAR applications. Such a system uses the latest Tm:silica heavily-doped fiber technology to provide as much as 3X efficiency improvement over existing systems. An all-amplifier technology provides flexibility and stability in the generation of coherent lidar waveforms. The hybrid fiber/bulk amplifier scheme allows to combine the advantage of high small-signal gain attainable in a fiber amplifier with the advantages of a bulk crystal amplifier such as high storage efficiency, immunity to various non-linear processes and damage-free operation for pulse generation.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The proposed work has direct application to NASA coherent, wind-sensing lidar programs based on the use of eyesafe, 2000-nm region lasers, as well as CO2 DIAL applications. The system concept we proposed provides improved performance, enhanced ruggedness and the potential for improvement in overall system efficiency. Other applications are as a pump source for mid-infrared-generating parametric oscillators, for application to DIAL sensors.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Commercial uses are for ground- and aircraft-based wind sensors in commercial aviation for wind shear and turbulence detection.

TECHNOLOGY TAXONOMY MAPPING
Optical

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
PolarOnyx, Inc.
470 Lakeside Drive, Suite F
Sunnyvale, CA 94085-4720
(408) 734-3048

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Jian Liu
jianliu@polaronyx.com
470 Lakeside Drive, Suite F
Sunnyvale,  CA 94085-4720
(408) 245-9588

Expected Technology Readiness Level (TRL) upon completion of contract: 5

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
This SBIR phase II project proposes a single frequency high energy fiber laser system operating at low repetition rate of 10 Hz to 1 kHz for coherent Lidar systems for remote sensing. Current state-of-art technologies can not provide all features of high energy and efficiency, compactness, narrow linewidth, super frequency and power stability, low noise, and high extinction ratio at the same time. PolarOnyx proposes, for the first time, a high energy (100 mJ) single frequency (< 1 KHz) PCF fiber laser transmitter to meet with the requirement of solicitation. This proposal is based on the spectral shaping sub-mJ fiber laser we have achieved in our labs. In the high power amplifier stage, PolarOnyx proposes an innovative PCF fiber based regenerative amplifier approach by employing our patent pending proprietary technologies in fiber lasers, that will be able to operate at low repetition rate (10 Hz to 1 kHz) and reach high energy level of 100 mJ. These will make the fiber laser transmitter system superior in terms of wall plug efficiency (over 30%), energy(100 mJ), noise, size, and cost. Proof of concept experiment has been demonstrated in Phase I time frame. A compact prototype will be delivered in Phase II.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Immediate applications include coherent lidars applications for atmospheric parameters measurement. It can also be used as a laser source for NASA's remote sensing system, and as a transmitter for optical communication systems between GEO, LEO, and earth.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
There are a number of potential applications for the proposed high power fiber laser transmitter system: • Medical equipment and biomedical instrumentation. The high power laser can be applied to ophthalmology, refractive surgery, photocoagulation, general surgery, therapeutic, imaging, and cosmetic applications. Biomedical instruments include those involved in cells or proteins, cytometry, and DNA sequencing; laser Raman spectroscopy, spectrofluorimetry, and ablation; and laser based microscopes. • Military / aerospace. The proposed fiber laser can be directly used in military applications, and space, aircraft, and satellite applications such as LIDAR systems, remote sensing system, illuminator system, and phase array antenna system. • Optical fiber communications. Tunable lasers represent the next generation of critical optical components needed to build the local optical networks of the future and cable TVs that will deliver increased communication bandwidth and improved Quality of Service (QoS) to local access users. The market for the application is growing and will be of great potential. RHK reported the tunable lasers will have a market potential of 800 millions dollars in 2009 as a result of applications of local optical networks and cable TVs. With successful development of the fiber lasers, the technology proposed by PolarOnyx will provide a vital tool to solve the existing and potential issues and merge with the huge market of optical fiber communications.

TECHNOLOGY TAXONOMY MAPPING
Laser
Optical
High-Energy
Photonics

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Intelligent Automation, Inc.
15400 Calhoun Drive, Suite 400
Rockville, MD 20855-2737
(301) 294-5200

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Arvind Bhat
abhat@i-a-i.com
15400 Calhoun Drive, Suite 400
Rockville,  MD 20855-2737
(301) 294-5254

Expected Technology Readiness Level (TRL) upon completion of contract: 6

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
This Phase II proposal, builds upon the extensive research and digital radar design that has been successfully completed during the Phase I contract. Key innovations of the proposed Phase II work will be • High update rate software configurable Direct Digital Synthesizer (DDS) design. The state-of-the-art DDS ICs can operate at 1 GHz update rates. IAI proposes to achieve the same or higher update rates, with increased flexibility (in frequency/ phase tuning) which arises from the software defined nature of the DDS implementation. • High-sampling rate (400 MHz and above), multi-channel digital receiver design. On-board signal processing capabilities will be integrated in the receiver. This includes digital implementation of commonly used radar receiver architectures (Digital down-up conversion, Digital filtering, Correlation, SAR imaging). • Digital implementation of direct RF generation techniques for L-Band frequencies. Flexible and scalable analog up-conversion techniques would be implemented to generate frequencies in the S-Band, X-Band, going up to the Ku band. • Scalable and modular hardware architecture to support multiple radar missions. Such a design approach would also address the issue of portability between different reconfigurable logic device families/ vendors. • Technology transition to adapt the radar design to meet space qualified standards.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The proposed technology is built upon the radar design and communications expertise of IAI, developed over several SBIR and non-SBIR contracts. Our innovation is the digital synthesis of critical radar blocks and reconfigurable design to support most commonly used radar modes. Our proposed technique can be used for a wide range of remote sensing applications for NASA including: • High bandwidth channel sounders • Weather surveillance radar for aircrafts • Earth science measurements like surface deformation, topography and soil moisture measurements • Space based radar missions • Non-cooperative target tracking radar in air space IAI has a long history of successfully designing custom radars for DoD and NASA, and most NASA applications could be supported by our reconfigurable radar design.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The most promising Non- NASA commercial applications are: • Reconfigurable radar for commercial applications • Cognitive Radios/ Radar for Defense related applications • High bandwidth arbitrary waveform generator • UAV based applications (due to the small form factor and plow power). This would include UAV based weather surveillance, target tracking and other commonly sought after UAV radar applications IAI has tremendous experience of designing customized radar assembly and packaging them as field-ready units.

TECHNOLOGY TAXONOMY MAPPING
RF
Portable Data Acquisition or Analysis Tools
Microwave/Submillimeter
Highly-Reconfigurable

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Dynamic Sensing Technologies
125 I Brittany Manor Drive
Amherst, MA 01002-3147
(520) 444-5622

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Luko Krnan
luko@dynamicst.com
125 I Brittany Manor Dr
Amherst,  MA 01002-3147
(520) 444-5622

Expected Technology Readiness Level (TRL) upon completion of contract: 6

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The proposed effort seeks to develop a digitally steered polarimetric phased array L-Band radar utilizing a novel, high performance architecture leveraging recent advances in radio frequency and digital signal processing components. The driving methodologies are: the minimization of costly and inflexible analog circuitry, adoption of standardized manufacturing processes, and inclusion of reconfigurable software/firmware architectures to facilitate fulfillment of varied sensing requirements. The Phase II effort will build upon the successful Phase I demonstration of the system concept through fabrication of a 2 Dimensional instrument and system validation in a relevant environment.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The conical scanning beamforming scatterometer leverages recently developed processing technology in order to enable collocated measurements of emission and backscatter in a compact aircraft instrument with no moving parts. These measurements are not currently available in NASA's L-Band radar systems. The measurements support Earth science applications and are an important step in the path to space for L-band scatterometer/radiometer systems. The short term goal of this work would be to enable collocated measurements with the 2-D Electronically Steerable Thinned Array Radiometer (ESTAR) instrument. In addition this work serves as validation for the Soil Moisture Active/Passive Mission (SMAP) mission which will carry a mechanically conical scanning radiometer/radar system. Also, the system is well-suited for high-resolution SAR measurements in planetary exploration, as well as GNSS backscatter measurements (CLARREO).

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The need for data produced by the proposed system is not limited to NASA. Within the government, agencies such as USDA, NOAA and DOE have needs for an accurate soil moisture product. Private corporations in the energy and hydrology services fields are also potential customers. The system concept is also applicable to other microwave frequencies, opening the possibility of instrument development to meet a growing demand for lower cost, agile, multi-mission phased array radar systems in fields such as atmospheric remote sensing and aviation.

TECHNOLOGY TAXONOMY MAPPING
Microwave/Submillimeter
Highly-Reconfigurable

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Virginia Diodes, Inc.
979 Second Street SE
Charlottesville, VA 22902-6172
(434) 297-3257

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Jeffrey Hesler
Hesler@VADiodes.com
979 Second Street SE, Suite 309
Charlottesville,  VA 22902-6172
(434) 297-3257

Expected Technology Readiness Level (TRL) upon completion of contract: 4

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
This proposal is responsive to NASA SBIR Subtopic S1.03: Passive Microwave Technology, specifically the fourth bullet item; "Low noise (<2000 K DSB), compactly designed (< 8 cm3), heterodyne mixers requiring low local oscillator drive power (<2 mW) with RF input frequency between 100 GHz to 1 THz." The proposed research is significant not only for the development of Schottky mixers that meet these requirements, but also for the creation of a receiver system, including the LO chain, that achieves the goals of high sensitivity, compact size, low total power requirement and operation across complete waveguide bands. The proposed receivers will meet all of the requirements for high resolution spectroscopic studies of planetary atmosphere's (including the Earth's) from spacecraft, as well as airborne and balloon platforms. The final contract deliverable will be a breadboard receiver module suitable for use on the proposed Vesper mission to probe the atmosphere of Venus. Perhaps more importantly, their exceptionally broadband performance, compactness and reliability will make them ideal for the broader range of scientific and commercial applications, which includes the extension of sophisticated test and measurement equipment to 1 THz and the development of low cost imaging systems for security applications and industrial process monitoring.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The technology developed through this research will enable the development of more power efficient and frequency agile heterodyne receivers to be used in NASA's submillimeter-wave missions that will not utilize cryogenically cooled systems. These include long term missions to planets that cannot afford the expense or are of too long duration for cryogenic systems and studies of planetary atmospheres that do not require the absolute lowest sensitivity but rather benefit from the frequency agility, robustness and stability of Schottky receivers. Primary examples of NASA missions are those to study planetary atmospheres, such as VESPER, MACO and MARVEL, and Earth observing satellites such as SIRICE and possibly Cameo. In addition, there are a host of balloon and aircraft projects that routinely use room temperature heterodyne receivers to study atmospheric chemistry that will benefit from the highly sensitive and more compact, power efficient and frequency agile receivers that will be developed.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Vector network analyzers (VNAs) and spectrum analyzers (SAs) are critical tools for any microwave laboratory. If terahertz technology is to reach its full potential, the functionality of VNAs and SAs must be extended to frequencies from 300 GHz through 3 THz with the same level of performance and ease of use that is achieved at lower frequencies. Today, several companies produce commercial extension kits for VNAs and SAs. However, most of these systems reach only to W-Band and/or are difficult to sweep across broad frequency bands. The few commercial systems that extend beyond W-Band tend to have reduced performance, specifically in terms of transmitter power and dynamic range. In fact the performance of these commercial systems is limited by the quality of the terahertz components, specifically the high frequency mixers and multipliers. Through this proposal VDI is developing the technology needed to achieve full waveguide band frequency mixers and their associated LO chains for frequencies up to at least 2 THz, with the performance necessary to achieve the same dynamic range that is today achieved at W-Band.

TECHNOLOGY TAXONOMY MAPPING
Microwave/Submillimeter

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
JJW Consulting, Inc.
1500 New Horizons Blvd.
North Amityvile, NY 11701-1130
(970) 392-2756

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
James whelehan
pingship@yahoo.com
1500 New Horizons Blvd.
North Amityvile,  NY 11701-1130
(631) 630-5320

Expected Technology Readiness Level (TRL) upon completion of contract: 4 to 5

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
A broadband G-Band low noise amplifier has been designed using a 50nm MHEMT. The MHEMT model that was used for the design was measured. With the use of this model, a single ended MMIC low noise amplifier was designed using various analysis tools. The single ended amplifier had a midband gain of 27.0dB with a noise figure of 3.7dB, a significant advance in the state-of-the-art. A balanced amplifier was also designed under this contract. It consisted of a waveguide to microstrip transition, an input coupler, the balanced amplifier, an output coupler, and a microstrip to waveguide transition. The MMIC chip that consisted of the input and output coupler and balanced amplifier was 1.4mm long by 1.23mm wide. The simulated performance demonstrated a gain of 25.6dB with a noise figure of 4.4dB midband. Since the MMIC process that will be used is fully space qualified and has been used on NASA's ATMS program, the design at the conclusion of the Phase II program should be ready for a space system insertion. The design would only be changed to meet specific program objectives.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The G-Band amplifier that will be developed under the Phase II program has significant NASA commercial applications. Many of NASA's remote sensing satellites for weather forecasting and tracking presently have water band sensors that operate at G-Band. However, these sensors have limited capability since low noise amplifiers are not available at the present time. These systems presently have mixer front ends with limited sensitivity. The G-Band low noise amplifier will greatly enchance the sensitivity of these systems as well as providing more accurate weather forecasting and tracking of storms such as hurricanes. The fact that the MMIC is based on a proven space process and can be inserted into space systems almost immediately is a unique advantage for this design.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The development of the low noise G-Band amplifier using the 50nm device is an advancement in the state-of-the-art for low noise amplifiers.The innovative design can then be used to advance the low noise performance of MMIC amplifiers down to the microwave region. They can also be used to enhance the sensitivity of commercial satellite communication systems. In addition, the emerging market for imaging systems in the submillimeter and THz region could use a MMIC amplifier with this performance. In fact, JJW Consulting has developed and shipped a 140GHz Imaging system that was to be used for an all-weather landing system. The system used a 140GHz LNA. The sensitivity of this system could be enhanced by the inclusion of these amplifiers.

TECHNOLOGY TAXONOMY MAPPING
Telemetry, Tracking and Control
Large Antennas and Telescopes
Airport Infrastructure and Safety
Pilot Support Systems
RF
Instrumentation
Microwave/Submillimeter
Radiation-Hard/Resistant Electronics

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Luxel Corporation
515 Tucker Avenue
Friday Harbor, WA 98250-1879
(360) 378-4137

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Jacob Betcher
jacob.betcher@luxel.com
PO Box 1879
Friday Harbor,  WA 98250-1879
(360) 378-4137

Expected Technology Readiness Level (TRL) upon completion of contract: 6

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
NASA will fly x-ray microcalorimeters on several mission payloads scheduled within the next 5 years: New and improved IR/Visible blocking filters are urgently needed to realize the full potential and throughput of these missions. The innovation proposed, high transmission polyimide support mesh, will replace the nickel mesh used in previous blocking filter designs. Polyimide's composition affords high transparency to x-rays, especially above 3 keV. Phase 1 prototypes demonstrated 11-15% higher transmission than comparable nickel mesh across the UV-Visible-NIR range. With development of the Phase 1 process in Phase 2, the mesh will be optimized for strength, transmission, integration with filter materials, and filter lifetime; it will include deicing capability as required. Lithographic production means adaptability to meet future mission-specific filter performance requirements. The Phase 2 project will achieve a flight readiness level of 5-6 for blocking filters using the new mesh. Phase 1 results show that with successful process development, the proposed high transmission polyimide mesh will significantly improve mission throughput and effective area for microcalorimeter payloads on proposed NASA missions such as Spectrum-X-Gamma and NeXT in the near term as well as Constellation –X.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Enhanced filter throughput is needed technology to meet NASA's Universe and Sun-Earth Connection program goals. The new high transmission mesh will find application in: • Blocking filters for x-ray microcalorimeter spectrometers proposed for Spectrum Roentgen Gamma, the New X-ray Telescope, Micro-X, and Constellation-X, particularly for observations at higher energies. • X-ray telescope entrance filters • Soft x-ray and EUV bandpass filters for heliophysics and astrophysics • Energetic particle detector filters • Thin foil filters for space-based astronomy that require robust, highly transmissive support mesh

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Extreme ultraviolet and x-ray filters for the GOES satellite series. Thermal barrier windows for laboratory-based astrophysics using x-ray microcalorimeters Windows for energy dispersive spectroscopy (EDS) systems used with scanning electron microscopy. New support mesh for zirconium pellicles used in extreme ultraviolet lithography (EUVL).

TECHNOLOGY TAXONOMY MAPPING
Optical
High-Energy
Optical & Photonic Materials

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Aymont Technology, Inc.
30 Saratoga Avenue, Suite 6H
Ballston Spa, NY 12020-1217
(518) 810-3294

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Larry Rowland
rowland@aymont.com
30 Saratoga Ave., Suite 6H
Ballston Spa,  NY 12020-1217
(518) 810-3294

Expected Technology Readiness Level (TRL) upon completion of contract: 5

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
In this Phase 2 SBIR program submitted to National Aeronautics and Space Administration (NASA) in response to Topic S1.05 (Detector Technologies for UV, X-Ray, Gamma-Ray and Cosmic-Ray Instruments), Aymont Technology, Inc. (Aymont) and GE Global Research will enable high-sensitivity ultraviolet imaging. We will build upon our Phase 1 result showing working SiC UV avalanche photodiodes with high quantum efficiency as well as GE's product expertise in SiC photodiodes. Our team will demonstrate 16 x 16 arrays of SiC photodiodes including electronics for visible-blind high-sensitivity ultraviolet (UV) detection. We will demonstrate imaging using these arrays at UV wavelengths. In order to enable large scale arrays needed for future NASA missions, we will also demonstrate a 3 x 3 array of SiC photodiodes and avalanche photodiodes without front side contacts. In Phase 3, this array will be scaled to VGA dimensions (640 x 480) and utilized by NASA and others as the best-performing choice for UV imaging in space, satellite, security, and other applications. Additionally, APD arrays will be enabled. These will give the capability of imaging where each pixel has the sensitivity of a PMT.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
High-sensitivity, large-area ultraviolet light detection is essential for detection of species that may indicate presence of organic processes such as sulfur oxides, hydrocarbons, hydrogen peroxide, hydroxyl radicals, ozone, and nitrogen oxides. Better, higher resolution ultraviolet detection than currently available is necessary for future missions. Arrays of SiC APDs will meet the imaging and analysis needs of TPF and subsequent possible missions such as Life Finder and the Large UV/Optical Telescope over the next two decades. Specific NASA missions using near ultraviolet detectors include Terrestrial Planet Finder, the Beyond Einstein program and NASA's Astronomical Search for Origins program. These missions require exceptional sensitivity for species detectable in the UV that may indicate organic processes, the presence of water, or perhaps life.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Potential commercial applications include machine vision, environmental monitoring, analysis of artifacts, medical imaging, and radiation detection.

TECHNOLOGY TAXONOMY MAPPING
Large Antennas and Telescopes
Particle and Fields
Optical
High-Energy
Radiation-Hard/Resistant Electronics
Semi-Conductors/Solid State Device Materials

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Black Forest Engineering, LLC
PO Box 8059
Colorado Springs, CO 80933-8059
(719) 593-9501

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Stephen Gaalema
sgaalema@bfe.com
1879 Austin Bluffs Parkway
Colorado Springs,  CO 80918-7857
(719) 593-9501

Expected Technology Readiness Level (TRL) upon completion of contract: 4 to 5

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The solid-state detector array is the primary technology to implement the current generation of space borne high-energy astronomy missions that are managed by NASA in partnership with the international community. Readout integrated circuitry (ROIC) specifically designed for photon resolving X-ray detection with solid-state detectors will create a new generation of high-performance X-ray imaging sensors. AC sensitive detector input circuitry, similar to that used by Black Forest Engineering (BFE) for laser detection and ranging (LADAR), is ideally suited to NASA X-ray astronomy imaging system requirements. BFE proposes on Phase II to produce and test 32x32 hybrid sensor arrays that can meet a wide range of NASA X-ray imaging applications. The arrays will provide single photon sensitivity, accurate X-ray energy determination, X-ray event time stamping, low power dissipation and ambient temperature operation.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The X-ray imaging technology developed on this SBIR will meet NASA's soft-to-hard energy requirements. One specific application is the Energetic X-ray Imaging Survey Telescope (EXIST); however, the design approach is applicable to a wide range of X-ray imaging systems and future systems such as Constellation-X. The readout approach is compatible with a wide variety of X-ray detectors for maximum utility. Power requirements are low to support space-based applications. The X-ray imager design and packaging approach is compact to allow 4-side abuttable imager assemblies to create large focal plane arrays.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Future medical high energy imaging systems (such as advanced PET scanners) may make use of this technology.

TECHNOLOGY TAXONOMY MAPPING
High-Energy
Photonics

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Physical Optics Corporation, EP Division
20600 Gramercy Place, Bldg. 100
Torrance, CA 90501-1821
(310) 320-3088

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Paul Shnitser
PSProposals@poc.com
20600 Gramercy Place, Building 100
Torrance,  CA 90501-1821
(310) 320-3088

Expected Technology Readiness Level (TRL) upon completion of contract: 5 to 6

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
To address the NASA need for high-quantum-efficiency, high-resolution, low-cost photodetectors for the far-UV spectral range, Physical Optics Corporation (POC) proposes to develop a new Silicon Microchannel Plate-based Large Area UV detector (UV-Si-MCP) with a highly efficient, negative electron affinity (NEA), solar-blind AlGaN photocathode fabricated directly on the surface of a silicon-based microchannel substrate. In Phase I, POC demonstrated the feasibility of fabrication of the AlGaN photocathode on the MCP structure, and developed the technology for fabrication of the entire device that meets NASA specifications for the area of sensitivity, quantum efficiency, and spatial resolution. In Phase II, POC will develop a fully functional prototype with a large number of channels and high quantum efficiency, assembled with NASA active pixel readout electronics. This efficient and radiation-hard UV photodetector with low background noise will offer NASA capabilities to improve sensitivity and spatial or spectral resolution of UV instruments for several missions devoted to a better understanding of the origin of the universe and its evolution to modern form.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Future NASA applications of Si-based Microchannel Plate photodetectors with AlGaN photocathodes fabricated directly on the entrance plate include several missions such as Terrestrial Planet Finder (TPF), SUFO, GALEX, and others. The highly sensitive, solar-blind, low noise, radiation-hard detectors for the FUV region (from 100 nm to 200 nm) will open new opportunities in the investigation of the evolution of the universe, planet finding, investigation of Sun-Earth interactions, etc.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Military applications for new detectors include missile plume detection, fire detection, and detection of biochemical agents. Silicon Microchannel Plate technology will be used in several commercial applications including microchannel chemical reactors with high surface area, beneficial for catalysis (efficient conversion of bio-products into diesel fuel, hydrogen production, and other reactions). This technology will be useful for high-density electronic devices where silicon wafers can be used both as a substrate for the fabrication of semiconductor devices and for creating micro-heatpipe systems. It is applicable to the fabrication of disposable microarrays with nanoliter volumes for fast testing tissue samples against thousands of pathogens.

TECHNOLOGY TAXONOMY MAPPING
Large Antennas and Telescopes
Particle and Fields
Optical
High-Energy

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Polatomic, Inc.
1810 N. Glenville Drive, #116
Richardson, TX 75081-1954
(972) 690-0099

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Robert Slocum
BobSlocum@polatomic.com
1810 N. Glenville Dr., #116
Richardson,  TX 75081-1954
(972) 690-0099

Expected Technology Readiness Level (TRL) upon completion of contract: 5

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
This Phase 2 SBIR proposal describes the design, fabrication and calibration of a brass-board Self-Calibrating Vector Helium Magnetometer (SVHM). The SVHM instrument is capable of making high accuracy vector component measurements of Earth and planetary magnetic fields. The major SVHM innovation is use of scalar field measurements made with the SVHM sensor to self-calibrate the vector measurements thereby eliminating the standard suite of three fluxgate vector magnetometers and the independent scalar magnetometer required to correct for fluxgate drifts and offsets. The SVHM bread-board conceptual design can achieve a dynamic range of ¡Ó65,000 nT, both vector and scalar accuracy with self-calibration of ¡Ó1 nT, and sensitivity of <10 pT /„©Hz. The SVHM bread-board will be miniaturized to meet volume, power and mass goals. The SVHM bread-board will utilize a fiber-coupled laser pump source and resonance drive, which permits reduction of helium cell volume by a factor of 10 and eliminates resonance drive coils and cables. The feasibility of designing a brass-board SVHM model using advanced laser and digital components was established in Phase 1. The SVHM bread-board will be calibrated and the self-calibration function demonstrated at a NASA coil facility during Phase 2.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The accurate measurement of the magnetic field components and their orientation in space is recognized as a basic requirement for space research. Conventional scalar and vector magnetometers measure the Earth¡¦s scalar field value in the range from 25,000 nT to 100,000 nT. The SVHM will be used to map near-Earth and distant-Earth magnetic fields in orbit and high-altitude aircraft. The major feature of the SVHM is its outstanding accuracy. This feature makes possible a major mapping project similar to MAGSAT with SVHM instruments on multiple satellites. On the Earth and other planets, the magnetic field provides unique information on the structure and dynamics of the planetary interior, fluid flow within and upon its surface, and the influence of the solar environment. The SVHM vector mode can provide high accuracy vector measurements of solar and planetary magnetic fields equal to or less than the Earth¡¦s field.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The SVHM characteristics of outstanding accuracy, omni-directionality (no dead zones), and high-frequency signal response will open up a variety of commercial and military applications. The SVHM will be used at the Earth's surface for geophysical airborne and surface magnetic prospecting as well as the new standard for geomagnetic observatories. A high-sensitivity version of the SVHM in a surface gradiometer configuration may be used for investigation of geopotential changes in the Earth¡¦s crust associated with earthquakes. The laser-pumped scalar helium magnetometer technology is currently being developed for high sensitivity magnetometers to be used by the US Navy for submarine detection and mine countermeasures applications. SVHM sensors in a gradiometer configuration may be useful for location of IEDs and buried sea mines. The miniaturized SVHM sensor using OSP technology will have applications in UAVs used for sea and land surveillance for submarines, tanks under trees, tunnels and underground facilities.

TECHNOLOGY TAXONOMY MAPPING
Particle and Fields

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
The Peregrine Falcon Corporation
1072 A Serpentine Lane
Pleasanton, CA 94566-4731
(925) 461-6800

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Robert Hardesty
rhardesty@peregrinecorp.com
1051 Serpentine Lane Suite 100
Pleasanton,  CA 94566-8451
(925) 461-6806

Expected Technology Readiness Level (TRL) upon completion of contract: 3 to 4

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Peregrines innovation will reduce the required input power, increase a coolers systems margin for a giving cooling load and reduce vibration accordingly for Cryocoolers. Our innovation will enhance the thermal conductivities of structures associated with the cryocooler, enable much more efficient heat removal and thereby produce a more efficient system. Effectively we will be increasing the thermal conductivities of the structures associated with the Cryocoolers by embedding Thermal Pyrolytic Graphite within a matrix of material to produce a thermal conductivity 5 times higher than current available materials. As cryocooler technologies attempt to cool components down around the 4<SUP>o</SUP>K level, waste heat and the management thereof becomes critical to the performance of the cryocooler. Thermal conductivity structures made from our innovation possessing a thermal conductivity of 700 W/mK will eliminate thermal loads more effectively and will lead to a more efficient and better performing cryocooler. Phase I has proven feasibility, Phase II will development and demonstrate our innovation resulting in a flight component for the MIRI cooling system for the James Webb Space Telescope.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
This innovation will have an enabling effect on Cryocoolers reducing their power requirements, size, mass and vibration. Beyond Cryocoolers, this product can provide an advanced solution for many thermal control applications like radiators, conduction bars and structural components. In some instances it will replace active cooling systems (heat pipes) with a passive solution based upon this high conductivity innovation.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Commercial satellites will use this technology for the same reasons NASA will to produce high thermal conductivity devices including conduction bars, radiators, and structural components. This technology can also be applied to provide tight thermal control for instruments, detectors and lasers. Commercial electronics can use the technology for laptop computers, ignition switches for automobiles, and heat sinks for power amplifiers.

TECHNOLOGY TAXONOMY MAPPING
Cooling
Metallics

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Tai-Yang Research Corporation
9112 Farrell Park Lane
Knoxville, TN 37922-8525
(302) 593-4777

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
David Hilton
dkhilton@tai-yang.com
2031 E. Paul Dirac Drive
Tallahassee,  FL 32310-3711
(865) 805-0220

Expected Technology Readiness Level (TRL) upon completion of contract: 4 to 5

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The Tai-Yang Research Company (TYRC) of Tallahassee, Florida, will design, build and test a superconducting magnet system optimized for low current space based applications. Adiabatic demagnetization refrigeration (ADR) for milli-Kelvin sensor cooling is enabled by the use of superconducting magnets to eliminate ohmic heating. Present systems use low temperature superconductors and require significant cooling system power to operate the magnets. TYRC's proposed superconducting magnet will operate at higher temperature and lower current than systems presently available, and will therefore reduce the total system burden. In Phase I, TYRC successfully demonstrated a method for producing a high temperature superconductor optimized for the low currents (< 10 amps) required for space based magnets. In Phase II, TYRC will produce several small test coils from the optimized conductor to develop the manufacturing technology. TYRC will design a demonstration magnet with input from NASA personnel to address mission requirements. TYRC will then manufacture and test the demonstration magnet to validate the design. At the conclusion of the project, TYRC will be positioned to supply low current superconducting magnets optimized for space based ADR systems identified for NASA missions.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
NASA missions requiring sensor cooling to < 1 Kelvin may be cooled by adiabatic demagnetization refrigeration (ADR) systems. These novel coolers are enabled by the use of superconducting magnets. Present ADR systems use low temperature superconducting magnets that must be cooled to 10 Kelvin. The superconducting magnets developed by TYRC will utilize a conductor technology that operates at 20 Kelvin, and will therefore reduce power consumption and cooling system mass. NASA low temperature sensor cooling applications for space based systems require current leads that minimize heat conduction and heat generation in a mechanically robust configuration. Unlike other superconductor current lead technologies presently used for NASA missions, TYRC's novel, proprietary conductor technology addresses the requirements for structural strength and low heat leak.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Low current high temperature superconducting magnets find application where weight savings and system power requirements are important. One such application is for magneto-optical imaging systems for studying low temperature material properties. TYRC has already produced a conceptual design for such a system using its novel, proprietary superconductor technology. The proposed coil technology is directly applicable to these systems, and may be introduced to this market during Phase II. NASA has licensed its ADR cooling system technology to a supplier interested in supplying such systems to research laboratories. TYRC's proposed coil technology may be used in these systems. Low current superconducting leads with higher temperature thermal intercepts may be of interest to cryogenic systems integrators seeking new methods of reducing heat leaks. TYRC's novel, proprietary conductor technology, now available, is directly applicable.

TECHNOLOGY TAXONOMY MAPPING
Electromagnetic Thrusters
Ultra-High Density/Low Power
Instrumentation
Superconductors and Magnetic
Power Management and Distribution

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Novawave Technologies
900 Island Drive, Suite 101
Redwood City, CA 94065-5176
(650) 610-0956

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Joshua Paul
jbpaul@novawavetech.com
900 Island Dr
Redwood City,  CA 94065-5176
(650) 610-0956

Expected Technology Readiness Level (TRL) upon completion of contract: 5 to 6

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The Small Business Innovative Research Phase II proposal seeks to develop a compact UV laser –based sensor for Earth science and planetary atmosphere exploration. The device will be capable of measuring formaldehyde in real-time at ultra-trace levels. The sensor is based on a revolutionary, single frequency tunable UV fiber laser that was successfully demonstrated for the first time during Phase I. This laser was mated with a detection cell and high fidelity formaldehyde spectra were obtained. The Phase II sensor will be compact and capable of detecting formaldehyde at ppt levels, and may be capable of simultaneously detecting NO2, an important pollutant.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
NASA applications for the instrument described in this proposal include the interrogation of extraterrestrial atmospheres for trace species, as well as in the study of Earth's atmosphere and the monitoring of cabin air in crewed exploration vehicles. The described instrument will have potential applications in atmospheric chemistry and satellite validation performed on umanned aerial systems (UAS).

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The worldwide market for gas sensors with the capabilities of the proposed system is significant. Numerous potential applications can be found in trace gas monitoring, pollution monitoring, and industrial process control.

TECHNOLOGY TAXONOMY MAPPING
Optical
Photonics

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Xiomas Technologies
1317 Skyway Drive
Ypsilanti, MI 48197-8952
(734) 646-6535

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
john green
johngreen@xiomas.com
1317 Skyway Drive
Ypsilanti,  MI 48197-8952
(734) 646-6535

Expected Technology Readiness Level (TRL) upon completion of contract: 6 to 7

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
An autonomous airborne imaging system for earth science research, disaster response, and fire detection is proposed. The primary goal is to improve information to researchers and operations personnel. By operating autonomously and with higher spatial resolution, the system will deliver a 3X to 4X reduction in operating costs compared to current systems. The system uses a two color Quantum Well Infrared Photo detector (QWIP) to improve the accuracy of energy release from wildfires, thereby improving our understanding of the carbon cycle. The system includes a multi-sensor step-stare imager, position and attitude sensor, data communications link, and a data processing system with; feature extraction (such as fire detection), image geo-coding, and image compression. The sensor head is an innovative design combining high resolution framing devices (cameras) with a step-stare scanning mirror. This configuration results in high spatial resolution imagery and wide area coverage. The design of the sensor head is flexible allowing for a variety of imagers including; visible and IR cameras and/or hyperspectral sensors. We envision several versions of the instrument, one weighing around 75 pounds and a smaller version weighing less than 15 pounds.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The project is aimed at advancing sensor development for Earth Science and Observation particularly with regards carbon cycle research, disaster response, fire research, autonomous systems operation, and reducing the size weight and power while increasing the operational efficiencies of remote sensing systems.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Several government and commercial entities have expressed a need for a system of this type including; 1) the U.S.F.S. for improved operational efficiencies in fire mapping, fuel loading, and burn area rehab, 2) DHS for border patrol, 3) FEMA for disaster response, 4) various entities for hydrology mapping of ground water, springs, and seeps, 5) commercial entities for heat loss from buildings, 6) National Nuclear Security Administration's (NNSA) Office of Nonproliferation Research and Development (NA-22) to improve national capabilities to detect the proliferation of nuclear weapons (ref solicitation no. DE-AR52-07NA28115)

TECHNOLOGY TAXONOMY MAPPING
Architectures and Networks
Autonomous Control and Monitoring
Autonomous Reasoning/Artificial Intelligence
Data Acquisition and End-to-End-Management
Data Input/Output Devices
Optical
Sensor Webs/Distributed Sensors

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Aerodyne Research, Inc.
45 Manning Road
Billerica, MA 01821-3976
(978) 663-9500

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Andrew Freedman
af@aerodyne.com
45 Manning Road
Billerica,  MA 01821-3976
(978) 663-9500

Expected Technology Readiness Level (TRL) upon completion of contract: 4 to 5

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
This Small Business Innovation Research Phase II project concerns the development of a multi-wavelength monitor that will provide rapid, real-time measurement of the average aerosol absorption coefficient in a parcel of sample air. This monitor will employ Aerodyne's patented Cavity Attenuated Phase Shift (CAPS) technology in order to produce a far simpler, smaller, lower cost alternative to more traditional instruments with no loss in sensitivity or accuracy. A unique property of the proposed instrument is that it requires little or no calibration. The Phase II project entails construction a field-ready prototype and deploying the sensor on various field missions undertaken by Aerodyne's particle measurement research group. Aerosol particles affect the radiative balance of the earth directly, by scattering and absorbing solar and terrestrial radiation, and indirectly, by acting as cloud condensation nuclei. The atmospheric loading of aerosols generated through human activities can exert an influence on the earth's radiation budget comparable in magnitude with greenhouse gases. The uncertainties in the current understanding of aerosol direct and indirect forcing limit the ability to quantify human influences on climate change.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Successful development of a low cost multispectral sensor would allow almost routine measurement of the scattering properties of atmospheric aerosols, something precluded by the cost and complexity of current instrumentation.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Quantification of the light absorbing properties of so-called "black carbon" could be readily achieved and could conceivably lead to the development of a monitor for combustor particulate emissions. Such an instrument would be of immediate benefit in at least two regulatory markets, that of stationary combustors (incinerators, power plants, etc.) and emissions certification for commercial aircraft engines.

TECHNOLOGY TAXONOMY MAPPING
Optical
Aircraft Engines

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Vista Photonics, Inc.
67 Condesa Road
Santa Fe, NM 87508-8136
(505) 466-3953

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Jeffrey Pilgrim
jpilgrim@vistaphotonics.com
67 Condesa Road
Santa Fe,  NM 87508-8136
(505) 466-3953

Expected Technology Readiness Level (TRL) upon completion of contract: 4 to 5

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Environmental species measurement on airborne atmospheric research craft is a demanding application for optical sensing techniques. Yet optical techniques offer many advantages including high-precision, fast response, and high species selectivity. Balloonsonde, kite, unmanned aerial vehicle (UAV), or glider deployment demands that sensors meet stringent size, weight and power requirements. Few measurements are as important, and none have entered into the public consciousness, like the need to quantify atmospheric carbon dioxide. Vista Photonics proposes to develop rugged, compact, power efficient prototype optical sensors capable of selectively measuring atmospheric carbon dioxide and water vapor with precision that rivals ground based instruments. The enabling technology for meeting stringent NASA mission requirements is a newly emergent infrared laser source that delivers the high-sensitivity of established optical absorption detection techniques with extreme compactness and low power draw.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The immediate targeted application for NASA is trace atmospheric species monitoring on unmanned terrestrial atmospheric research craft. Phase II prototypes will be capable of selectively detecting carbon dioxide and water vapor. The integrated sensors will be suitable for dynamic airborne environments on Earth and in planetary measurements as diverse as the Moon, Mars and Titan. Other applications include fire detection on aircraft and high-value installations, gas sensing in air revitalization and water recovery processes on spacecraft, and leak detection during spacecraft launch operations.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Phase III commercial applications abound for sensors whose performance and physical characteristics are suitable for unmanned airborne measurements. A prominent example includes leak monitoring at carbon capture and sequestration sites where greenhouse gases are stored underground. Other examples include contaminant monitoring in process gas streams in the chemical and microelectronics industries, medical diagnosis through detection of biogenic gases in human breath that correlate to specific pathologies, and environmental monitoring and regulatory compliance in agriculture, power production, and occupational safety. The fully-developed Phase II instruments shall offer a compelling and desirable blend of performance, affordability, compactness, simplicity and ease-of-use relative to present commercial product offerings in these applications.

TECHNOLOGY TAXONOMY MAPPING
Air Revitalization and Conditioning
Optical
Portable Life Support

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) 965-7780

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Hong Jiao
h.jiao@lgrinc.com
67 East Evelyn Avenue, Suite 3
Mountain View,  CA 94041-1518
(650) 965-7772

Expected Technology Readiness Level (TRL) upon completion of contract: 5 to 6

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Los Gatos Research proposes to develop a powerful new technology - next generation Micro-Capillary Electrochromatography - a high performance and low power consumption microfluidic sample separation device suitable for separating organic molecules as signatures as past and present life on Mars. In this Phase II effort, we will refine this enabling new microfluidic technology that we have successfully demonstrated in Phase I in order to integrate with NASA Mars Organic Detector. Specifically for the Phase II work, we will target two important classes of compounds: polycyclic aromatic hydrocarbons (PAHs) and amino acids. The overall objective is to integrate the micro-CEC devices with the existing micor-CE analyzers to form a dual micro-CE/micro-CEC system capable of separating all neutral and charged organic molecules targeted by Urey, thus significantly broaden NASA organic sample separation capability. In addition, this research work will also be performed in parallel with efforts to develop microfluidics devices for the commercial analytical markets.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The proposed micro-CEC technology has great potential to complement NASA's current efforts to find signature of life on Mars such as Urey Mars Organic Analyzer and Mars Organic Detector. The proposed technology has broad applications including on-chip biosensors, electrochemical sensors, wet-chemistry systems, as well as high pressure micropumps for fluid positioning, mixing, metering, storage, and filtering systems. In addition, our novel technology is naturally suited to such applications as planetary and small body surface chemistry studies, clinical diagnostics, spacecraft and biosphere environmental monitoring, and toxicology studies. Finally, the novel micro-CEC technology will also benefit NASA's other "Micro Laboratories" programs such as monitoring Space Station environment and in-situ explorations of Europa and Titan.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The next generation mciro-CEC technology described in this proposal possesses a myriad of potential commercial technologies and applications in markets ranging from specialty medical and aerospace industries to consumer electronics. The primary commercial products based on such CEC technology are components for DNA, protein and drug separation and analysis, biological and chemical analysis systems, and drug delivery systems in pharmaceutical and biotechnology industries. In addition, the EOF based technology is also well suited for MEMS actuator systems and embedded health monitoring systems. Our proprietary technology vastly improves robustness and reliability, thus clearing one of the last hurdles of a wider acceptance of CEC in the biotechnology and pharmaceutical industries

TECHNOLOGY TAXONOMY MAPPING
Biomedical and Life Support
Biomolecular Sensors
Biochemical

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Creare, Inc.
P.O. Box 71
Hanover, NH 03755-3116
(603) 643-3800

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Robert Kline-Schoder
rjk@creare.com
P.O. Box 71
Hanover,  NH 03755-0071
(603) 640-2468

Expected Technology Readiness Level (TRL) upon completion of contract: 5 to 6

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
NASA, the DoD, DHS, and commercial industry have a pressing need for miniaturized, rugged, low-cost, high vacuum systems. Recent advances in sensor technology at NASA and other government laboratories, in academia, and in industry have led to the development of very small mass spectrometer detectors, as well as other analytical instruments needing high vacuum, such as scanning electron microscopes. However, the vacuum systems to support these sensors remain large, heavy, and power hungry. To meet this need, Creare proposes to build a miniaturized vacuum system based on a very small, rugged, and inexpensive-to-manufacture, molecular drag pump (MDP). The MDP is enabled by the development of a miniature, very high-speed (200,000 RPM), rugged, low-power, brushless, DC motor which will be optimized for wide temperature operation and long life during this project. The vacuum pump has performance that is well matched to the needs of the new generation of miniature analytical instruments. The pump represents an order-of-magnitude reduction in mass, volume, and cost over current, commercially available, state-of-the-art vacuum pumps. The new pump will form the heart of a complete vacuum system optimized to support analytical instruments in terrestrial applications as well as on spacecraft and planetary landers. Furthermore, the miniature high-speed motor will be designed so that it can be used in a wide range of high vacuum pumps, including pure molecular drag, pure turbomolecular, and hybrid turbomolecular/molecular drag pumps that can be tailored to the requirements of specific missions and applications.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
A number of current NASA initiatives seek to reduce the size and power requirement of scientific instruments. Success in these efforts will lead to new generations of sensors that can be deployed on smaller, less expensive platforms, including Unmanned Aerial Vehicles (UAVs), balloons, microspacecraft, and miniature interplanetary probes. Our proposed rugged vacuum system directly supports these goals by reducing the size, weight and power consumption of vacuum systems required to run these instruments. In addition, the pump technology that we will develop under this program is currently baselined as a part of the MOMA instrument being developed (under NASA funding) by the Johns Hopkins Applied Physics Laboratory for a 2013 Mars mission as well as part of the development of a NASA/GSFC, next-generation laser desorption time-of-flight mass spectrometer that has significantly improved capabilities and robustness for in situ astrobiology missions which were recently selected for funding under the NASA ASTID program.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Numerous commercial applications exist for the proposed rugged, low-cost vacuum system, primarily to support portable analytical instruments such as mass spectrometers and leak detectors. Current-generation devices are limited by the size and mass of their high vacuum and rough pumps, or else use less capable absorption pumps. Building a small, lightweight, rugged, low-cost, and low power high vacuum system whose performance is tuned to the needs of miniature detectors is expected to greatly expand the market for such devices. The pump technology to be developed under this proposal will be used in instruments being developed by one of our partners in portable mass spectrometers for use by the Department of Homeland Security and the Defense Threat Reduction Agency.

TECHNOLOGY TAXONOMY MAPPING
Biochemical

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Vista Photonics, Inc.
67 Condesa Road
Santa Fe, NM 87508-8136
(505) 466-3953

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Jeffrey Pilgrim
jpilgrim@vistaphotonics.com
67 Condesa Road
Santa Fe,  NM 87508-8136
(505) 466-3953

Expected Technology Readiness Level (TRL) upon completion of contract: 4 to 5

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Trace species measurement on unmanned atmospheric research craft suitable for interplanetary travel is a demanding application for optical sensing techniques. Yet optical techniques offer many advantages including high-precision, fast response, and strong species selectivity. Balloonsonde, kite, unmanned aerial vehicle (UAV), or glider deployment demands that optical sensors meet stringent size, weight and power requirements. Vista Photonics proposes to construct rugged, compact, low-power optical sensor prototypes capable of selectively determining isotopic-resolved hydrocarbons at Titan-relevant concentrations. The sensor will be demonstrated in Phase II by airborne measurement of CO2 and water vapor on Earth. The enabling technology for meeting stringent NASA mission requirements is a new rugged, compact, and lightweight optical path length enhancement cell that recovers the established sensitivity of high-performance optical absorption detection techniques on a platform with no moving parts. The proposed spectrometer will be capable of detecting multiple species with little additional weight or power penalties.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The immediate targeted application for NASA is trace atmospheric species monitoring on planetary exploration probes. Phase II prototypes will be capable of selectively detecting isotopic-resolved concentrations of acetylene, ethylene and methane. The prototypes will also be proven for airborne measurement of atmospheric species on Earth, including carbon dioxide and water vapor. Other species can be included as required. The integrated sensors will be suitable for low pressure environments like the Moon and Mars and in substantial atmospheres like Titan's. The emerging technology will also be suitable for use on both manned and unmanned terrestrial atmospheric research craft. Other applications include fire detection on aircraft and high-value installations, gas sensing in air revitalization and water recovery processes on spacecraft, and leak detection during spacecraft launch operations.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Phase III commercial applications abound for sensors whose performance and physical characteristics are suitable for spaceflight. Two specifically targeted applications are high-performance unmanned airborne detection of carbon dioxide/water vapor and carbon dioxide leak detection at power plant carbon capture & sequestration sites. Other examples include contaminant monitoring in process gas streams in the chemical and microelectronics industries, medical diagnosis through detection of biogenic gases in human breath that correlate to specific pathologies, and environmental monitoring and regulatory compliance in agriculture, power production, and occupational safety. The fully-developed Phase II instruments shall offer a compelling and desirable blend of performance, affordability, compactness, simplicity and ease-of-use relative to present commercial product offerings in these applications.

TECHNOLOGY TAXONOMY MAPPING
Air Revitalization and Conditioning
Biomedical and Life Support
Optical
Photonics
In-situ Resource Utilization

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Busek Co., Inc.
11 Tech Circle
Natick, MA 01760-1023
(508) 655-5565

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Nathaniel Demmons
nate@busek.com
11 Tech Circle
Natick,  MA 01760-1023
(508) 655-5565

Expected Technology Readiness Level (TRL) upon completion of contract: 4

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Busek proposes to develop and deliver a complete engineering model colloid thruster system, capable of thrust levels and lifetimes required for spacecraft operational tasks such as tip-off de-tumbling and attitude control. The self contained thruster system shall be capable of delivering ~75µN with sufficient total impulse to de-tumble spacecraft such as LISA. The proposed Phase 2 work builds upon a highly successful Phase 1 effort where the key principals of the innovation, a propellant isolation membrane and a passive capillary feed system, were unequivocally demonstrated. The proposed system is completely passive with no moving parts and requires no valves to ensure its high reliability. In order to inhibit propellant contamination prior to operation in space, a unique isolation membrane will separate propellant from the emitter. Upon heating the isolation membrane dissolves, allowing propellant from a collocated reservoir to flow forward to the electrospray thruster without contamination. The thruster consists of an array of self adjusting emission sites that are activated by application of an electric field that initiates emission. The delivered thrust is modulated by varying the applied electric field. The significant innovations of the proposed colloid thruster include: a compact, low power, modular thruster system containing no moving parts, which is capable of delivering sufficient thrust for spacecraft tip-off control and ACS applications.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Busek has recently delivered two colloid thruster clusters with eight complete thruster systems to JPL for use on the LISA Pathfinder mission, a precursor to LISA. Both missions require very precise, low noise micro-thrusters that are specific to the science portion of the mission. Such thrusters are not well suited for the more general thrusting task of launch vehicle separation tip-off cancellation, which requires larger thrusts. Using the same thrusters for the science portion of the mission that are designed for the tip-off requirements compromises their achievable performance and limits lifetime, suggesting that a secondary thruster system is preferred to perform short term, higher thruster maneuvers. We believe that the simple colloid thruster proposed herein is capable of meeting the tip-off requirements for the LISA mission, thus allowing the primary colloid thrusters to be designed based solely on science mission requirements. The completely passive, compact, self contained tip-off colloid thruster system will have minimal impact on overall spacecraft system design. This thruster will also be useful for other missions where a compact, bolt-on propulsion system is necessary for short-duration, high-thrust maneuvers.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
There are ongoing trends toward miniaturization of spacecraft to very small sizes, however, developing an efficient miniaturized propulsion system is seen as a challenge to achieving widespread commercial, military and government application. While electronics and sensors have made great advances in miniaturization, studies have shown that micro-satellites are constrained by lack of suitable propulsion. This represents a significant market opportunity for colloid propulsion. The colloid thruster proposed here combines a small footprint, simple construction, and a strong technological heritage (e.g. ST7) that enables it to fulfill primary, ACS, and tip-off thrust operations for a wide range of micro/nano-satellites.

TECHNOLOGY TAXONOMY MAPPING
Micro Thrusters
Propellant Storage
Electrostatic Thrusters
Feed System Components

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Payload Systems, Inc.
1 Broadway 12th Floor
Cambridge, MA 02142-1189
(617) 868-8086

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Joe Parrish
jparrish@aurora.aero
1 Broadway, 12th Floor
Cambridge,  MA 02142-1189
(617) 500-0248

Expected Technology Readiness Level (TRL) upon completion of contract: 4

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Aurora Flight Sciences (AFS), in collaboration with the MIT Space Systems Laboratory (MIT-SSL), proposed the Synthetic Imaging Maneuver Optimization (SIMO) program to develop a methodology, calibrated through hardware-in-the-loop testing, to optimize S/C maneuvers to more efficiently synthesize images for missions such as Stellar Imager (SI). Time and fuel-optimal maneuvers are only a part of the optimization problem. Selecting the maneuver waypoints (number and location) determines the quality of the synthesized image. The number of S/C, the size of the sub-apertures, and the type of propulsion system used also impacts imaging rate, propellant mass, and mission cost. Capturing all of these mission aspects in an integrated mission optimization framework helps mission designers to select the most appropriate architecture for meeting the needs and constraints of missions such as SI.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The SIMO technology is directly applicable to, and motivated by, NASA GSFC's Stellar Imager mission. However, other NASA missions requiring staged control are the Space Interferometry Mission, Terrestrial Planet Finder Mission (Interferometer and Coronagraph), SPIRIT, and SPECS. In fact, the Terrestrial Planet Finder Mission – Interferometer requires both sub-aperture reconfiguration as well as staged control. Of particular interest may be the LISA mission. NASA and ESA are currently trying to validate the ability to free-float a proof mass, measure its motion to pico-meter accuracy relative to the encompassing spacecraft, measure range between spacecraft as well as capture and maintain this knowledge. This has proven to be a financially challenging endeavor. The capabilities being developed for SIMO, as well as the potential to transition it to the micro-gravity environment of ISS, creates an opportunity to test staged sensing and control in support of LISA at a fraction of the cost.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
We anticipate that there are other applications both within NASA and beyond, and in military and commercial sectors. The DARPA F6 program is creating a virtual satellite architecture where elements are flown in loose formation to enhance staged deployment, technology upgrade, payload reconfiguration, and survivability using the technologies of distributed communication/computing, power beaming, and cluster flight. The AFS-MIT team is a member of three of the four competing teams under DARPA's F6 program, providing a direct path for SIMO technology transfer. The DoD is also interested in robust and efficient multi-vehicle reconfiguration for satellite servicing, docking, inspection, and assembly of large apertures.

TECHNOLOGY TAXONOMY MAPPING
Simulation Modeling Environment
Testing Facilities
Testing Requirements and Architectures
Guidance, Navigation, and Control
On-Board Computing and Data Management

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Microscale, Inc.
800 West Cummings Park, Suite 3350
Woburn, MA 01801-6377
(781) 995-2245

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Xingtao Wu
wu@microscaleinc.com
800 West Cummings Park, Suite 3350
Woburn,  MA 01801-6377
(781) 995-2245

Expected Technology Readiness Level (TRL) upon completion of contract: 4 to 5

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
This Small Business Innovation Research (SBIR) Phase II project will research a novel deformable mirror design for NASA adaptive optics telescope applications. The innovation offers reliable mechanics for the strained architecture, thus facilitating dynamic modeling and the overall control of the DM system. A system-level finite element analysis and design optimization, in combination with proof-of-concept experimental verification methods, will be adopted to identify the most promising design for the future adaptive optics telescope systems. Focus will be given to improve the long time reliability and stability of the system while reducing thermal distortions. Phase II objectives are to (1)design and pragmatically build and integrate the monolithically integrated 100x100 Single Crystal Bimorph Array (SCBA) Deformable Mirror (DM) system onto VLSI substrate for VIS/NIR infrared operating range to demonstrate the monolithic proof-of-concept operating of the DM system, and (2) demonstrate a beam shaping system employing the SCBA DM chips to efficiently compensate rapidly changing aberrations and characterize the final integrated corrector system for phase modulation depth, framing speed, operating field of view, influence function, spatial uniformity, and scalability to millions of actuators.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The current SBIR research will use the proposed DM technology to address the high-end application requirements for astronomical telescope systems including (1) correction of aberrations in large-aperture, space-deployed optical interferometers and telescopes, (2) high-resolution imaging and communication through atmospheric turbulence, (3) laser beam steering, and (4) optical path alignment, (5) propagation of directed laser energy through atmospheric turbulence, will require deformable mirror (DM) wavefront correctors with several hundred to millions of elements.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Non-NASA applications include laser beam shaping, ophthalmology and other microscope applications. In particular, for the Department of Defense, if needed, the prototype adaptive optical systems based on the Phase II results can be applied to military seekers, FLIRs, optical communications, and other adaptive optics systems for military operations. For optical computing, the VLSI circuit could be combined with piston-only micromirror structure for a phase-only spatial light modulator. Commercial markets for these systems also include retinal imaging, supernormal human vision, and amateur telescopes. The research is also expected to lead to a family of compact, low-cost, high performance spatial light modulators for direct retinal display, head mount display, and large-screen projection display applications.

TECHNOLOGY TAXONOMY MAPPING
Autonomous Control and Monitoring
Optical
Substrate Transfer Technology
Photonics
Optical & Photonic Materials

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
TRS Ceramics, Inc.
2820 East College Avenue
State College, PA 16801-7548
(814) 238-7485

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Xiaoning Jiang
xiaoning@trstechnologies.com
2820 East College Ave, Suite J
State College,  PA 16801-7548
(814) 238-7485

Expected Technology Readiness Level (TRL) upon completion of contract: 3 to 4

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Single crystal piezoelectric deformable mirrors with high actuator density, fine pitch, large stroke and no floating wires will be developed for future NASA science and communications applications. Single crystal piezoelectric DMs share the fine pitch with co-fired electrostrictive or ceramic piezoelectric DMs and MEMS DMs, but with large stroke at relatively low voltages (< 150 V) and with a broader operation temperature range (< 20 K - > 300K). Specifically, a 32x32 actuator array with stroke > 2 um, pitch of < 1mm and a 8x8 actuator array with stroke > 12 um, pitch of < 2mm will be developed for fine and coarse DMs. Actuator driving electronics will be scaled up to a multi-channel actuator driver and optimization of the design, facesheet mounting process and characterizations for deformable mirrors will be investigated.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Single crystal microactutaors can be used for large stroke, high precision deformable mirrors in NASA coronagraphic instruments, interferometric telescopes, and space-based observatories. ORIGINS missions SUVO, SAFIR, and Planet Imager, Earth Science applications, such as LIDAR systems as well as Coastal Ocean Imaging systems will all benefit from this deformable mirror technology.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Large stroke, high precision actuator arrays based deformable mirrors are also attractive to DOD adaptive optics programs such as directed energy applications and medical adaptive optics such as retina imaging applications. Apart from adaptive optics applications, large stroke, high precision piezo actuators are also good candidates for active vibration control and structure morphing, RF communication tuning, bio-medical manipulators, photonic tooling, cryogenic microscopy tools, micro/nanofabrication and nanoassembly.

TECHNOLOGY TAXONOMY MAPPING
Large Antennas and Telescopes
Laser
Instrumentation
Photonics
Ceramics
Composites
Multifunctional/Smart Materials

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Nanohmics, Inc.
6201 East Oltorf Street, Suite 400
Austin, TX 78741-1222
(512) 389-9990

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Keith Jamison
kjamison@nanohmics.com
6201 East Oltorf, Suite 400
Austin,  TX 78741-7511
(512) 389-9990

Expected Technology Readiness Level (TRL) upon completion of contract: 6

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Next-generation space telescopes require advanced optical coatings to provide low-loss polarization-preserving transmission/reflection of light in a variety of spectral ranges. These coatings also need to protect optical components as well as the coatings themselves, from damage in a space environment. For example, one of the critical technologies identified in the NASA capabilities roadmap for advanced telescopes and observatories is advanced optical coating technology for cryogenic mirrors that is uniform and polarization preserving in the visible through far IR regions as well as improved dichroic, spectral and combiner coatings . To address this need Nanohmics is investigating us of sputter deposited amorphous nitrides and oxides as high quality, long lived radiation resistant coatings for production of anti-reflection and bandpass coatings on optical substrates including metals, PMMA, beryllium and other materials. Discussions with the contracting officer's technical representative indicated that the main Fresnel lens in the EUSO (Extreme Universe Space Observatory) may be a good candidate for amorphous nitride anti-reflective coatings. The Phase II effort will focus on coatings for PMMA based optics; however, this coating technology can be applied to many other optical systems.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The main benefit to NASA will be a robust wide-band anti-reflective or band-pass coating for optical components in space that can be applied at low substrate temperatures. This coating is radiation hard and ideal for space based applications. This coating system can be applied to a variety of optical components to provide radiation hard, flexible, scratch resistant coatings.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
High quality radiation and scratch resistant coating are useful in a wide variety of applications. The amorphous nitride / oxide coating system can be applied to standard optical components to produce hard scratch resistant coating for harsh environmental in a large number of civilian and military applications.

TECHNOLOGY TAXONOMY MAPPING
Large Antennas and Telescopes
Optical
Sensor Webs/Distributed Sensors
Optical & Photonic Materials

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Creare, Inc.
P.O. Box 71
Hanover, NH 03755-3116
(603) 643-3800

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Jay Rozzi
jcr@creare.com
P.O. Box 71
Hanover,  NH 03755-0071
(603) 643-3800

Expected Technology Readiness Level (TRL) upon completion of contract: 5

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Large aperture, lightweight optical mirror technologies are critical for the future of lightweight telescopes and their attendant missions to explore the planets in our solar system and beyond. Chemical vapor deposition (CVD) coated silicon carbide (SiC) has been shown to be a viable alternative for lightweight mirrors due to its thermal stability; however, cost-effective manufacturing techniques to pre-finish this material have not been sufficiently developed. During the Phase I project, we established the feasibility of the low-rate step of our hybrid machining approach by successfully completing ductile-regime machining (DRM) of CVD SiC. We were able to produce a surface that had a roughness of a near-optical quality. We established key partnerships that will enable the development of the high rate machining step and demonstrated that our hybrid machining approach will reduce the cost of fabricating a finished mirror by up to 46% when compared with the current state-of-the-art. During the Phase II project, we will work further to develop our hybrid machining process, demonstrate it on a large scale optic, and deliver it to NASA.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The government seeks a means to affordably produce lightweight aspheric optics from super-hard ceramic materials. Large aperture, lightweight, optical mirror technologies are critical for the future of telescopes to explore the solar system and beyond. Silicon carbide, silicon, and silicon nitride have been shown to be viable alternatives for lightweight mirrors; however, cost-effective manufacturing techniques to machine these materials have not been developed in parallel. The pre-finishing process prepares the net-shape blank for final optical finishing. Current processes, such as diamond grinding, reactive atom plasma processing, or standard laser micromachining have not demonstrated that they can produce damage-free surfaces of sufficient optical figure or form accuracy. The use of our innovation can substantially reduce the cost of these optics and enable the increased functionality of new and existing platforms. The results of our work would have far-reaching benefits for government aircraft and military systems.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Cost-effectively manufacturing super-hard ceramics has always been the primary barrier to commercial acceptance of this advanced material technology. For many applications, ceramic materials offer significant advantages over other options, but their cost precludes their consideration in design. Effective and affordable manufacturing processes are required to render ceramics as a viable design option. For silicon carbide, our innovation will enable the machining of this material to a high quality and with an intricate shape. Thus, we will enable a paradigm shift in the machining of super-hard optical ceramics, along with the concomitant decrease in processing costs. This will increase the market for such materials in commercial aircraft, automobiles, cutting tools, artificial joints, and various other applications.

TECHNOLOGY TAXONOMY MAPPING
Ceramics
Optical & Photonic Materials

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Coherent Logix, Inc.
1120 S. Capital of Texas Hwy, Bldg. 3, Suite 310
Austin, TX 78746-6460
(512) 382-8940

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
David Gibson
gibson@coherentlogix.com
1120 S. Capital of Texas Hwy., 3-310
Austin,  TX 78746-6446
(512) 382-8950

Expected Technology Readiness Level (TRL) upon completion of contract: 8 to 9

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
NASA's exploration, science, and space operations systems are critically dependent on the hardware technologies used in their implementation. Specifically, the performance and deployment of autonomous and computationally-intensive capabilities for space based observatories, orbiters, autonomous landing and hazard avoidance, autonomous rendezvous and capture, robotics, relative navigation, and command, control and communications systems are directly dependent on the availability of radiation-tolerant, high-performance, reconfigurable and adaptable, energy-efficient processor technology. Coherent Logix, Incorporated proposes to develop a radiation tolerant HyperX technology based processor to address these critical needs. This program will leverage more than $18M of previous investment by the Department of Defense. Building on the research done in Phase I, the Phase 2 program will develop the radiation hardened by design (RHBD) HyperX. This will be followed in Phase 3 by the completion and productization to a TRL 8/9 of a Radiation Tolerant HyperX Processor.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Potential NASA applications include processing for exploration, science, and space operations systems. Specific examples include space based observatories, orbiters, autonomous landing and hazard avoidance, autonomous rendezvous and capture, robotics, relative navigation, and command, control and communications systems.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Potential Non-NASA applications include high-reliability processing for automotive, aviation, and medical markets, among others.

TECHNOLOGY TAXONOMY MAPPING
Intelligence
Mobility
Manipulation
Telemetry, Tracking and Control
Ultra-High Density/Low Power
Guidance, Navigation, and Control
On-Board Computing and Data Management
Architectures and Networks
Autonomous Control and Monitoring
Autonomous Reasoning/Artificial Intelligence
Computer System Architectures
Expert Systems
Portable Data Acquisition or Analysis Tools
Software Development Environments
Software Tools for Distributed Analysis and Simulation
Highly-Reconfigurable
Radiation-Hard/Resistant Electronics

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Ashwin-Ushas Corp, Inc.
500 James Street, Suite 7
Lakewood, NJ 08701-4043
(732) 462-1270

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Prasanna Chandrasekhar
chandra.p2@ashwin-ushas.com
500 James Street, Suite 7
Lakewood,  NJ 08701-4043
(732) 901-9096

Expected Technology Readiness Level (TRL) upon completion of contract: 7 to 8

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
This work further developed a highly promising variable emissivity technology for spacecraft thermal control, based on unique conducting polymer (CP) electrochromics combined with ionic electrolytes, developed earlier by this firm (Air Force, JPL) with: Extremely thin (< 0.2 mm), flexible (plastic), lightweight (0.192 kg/m^2), variable area, "skin-like" construction; Delta-Emittance > 0.4, emittance range 0.15 to 0.90; power 40 micro-W/cm^2; proven space durability (thermal vacuum, atomic-O, VUV, solar wind), operating temperature (-)70 to (+)105 C); use of ionic electrolytes with zero vapor pressure needing no seal; low cost (est. $5K/m^2). A technical hurdle in the earlier-generation technology, of high solar absorptance (values up to 0.8) in the dark, high-emissivity state, remained, the sole hurdle hindering implementation of the technology. The Phase 1 introduced the new innovation of unique, proprietary IR-transparent coatings lowering the solar absorptance (Alpha(s)) of the variable emittance devices ("skins") drastically. In Phase 1, the best coatings yielded Alpha(s) of 0.306, emittance of 0.383 for the light state, and Alpha(s) 0.454, emittance 0.841 for the dark state (Delta emittance 0.458), with a calculated temperature under direct sunlight in space of < 60 C. Devices endured thermal vacuum > 110 days, VUV, atomic-O exposure, abrasion tests. Calorimetric emittance measurements under space vacuum were identical to emissometer measurements in air. In Phase 2, the primary objective will be ground space qualification and a TRL of 7 or higher, with an extensive series of tests to include: thermal vacuum, thermal cycling, solar wind, atomic-O, micrometeoroid, vibration, ESD. These will be done in our labs as well as at several partner labs, including two large aerospace companies who are Phase 2 commercial partners, and several outsourcing vendors. At least one firm spaceflight opportunity has been identified. Expected TRL at end of Phase 2 is 7-8.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
This technology may displace extant mechanical louvers, heat pipes, as well as newer technologies (MEMS louvers, electrostatics, reverse-electrochromics), on large as well as small spacecraft, deployed by NASA as well as commercial and military entities. Additionally, other technologies are difficult or impossible to adapt to micro- (< 100 kg) and nano- (<5 kg) spacecraft, the thrust of future aerospace development, which will allow launch of more spacecraft at lower cost, opening doors to profound new applications for communications, defense. The potential variable emittance market is estimated at several hundred m^2 per year, with a substantial portion for NASA craft.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Besides potentially replacing extant mechanical louvers and heat pipes in spacecraft, the technology is possibly the only one applicable to micro- and nano-spacecraft, the thrust of future aerospace development. Availability of the technology will allow for much greater design freedom in such spacecraft. Military uses include space-based radars and undetectable nano-satellites. Non-space uses of these IR electrochromics include battlefield IR camouflage countermeasures, sunglasses for older patients and displays/billboards.

TECHNOLOGY TAXONOMY MAPPING
Launch and Flight Vehicle
Cooling
Reuseable
Thermal Insulating Materials
Suits
Optical & Photonic Materials

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Rini Technologies, Inc.
582 South Econ Circle
Orlando, FL 32765-4303
(407) 359-7138

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Dan Rini
dan@rinitech.com
582 South Econ Circle
Orlando,  FL 32765-4303
(407) 359-7138

Expected Technology Readiness Level (TRL) upon completion of contract: 5

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Future Spacecraft from the JPL will require increasingly sophisticated thermal control technology. A need exists for efficient, lightweight Vapor Compression Cycle (VCC) systems, for medium-to-low cooling loads (less than 2kW). While conventional VCC technology is relatively compact and efficient for multi-kW loads, it is difficult to find a system that strikes a balance between coefficient of performance, weight and size within the sub-kW range. The particular system proposed will be a highly efficient Mini-Heat Pump featuring custom compressor and heat-exchanger technology. The compressor is a highly efficient, high power density, orientation independent rotary compressor designed for 500W of heat removal, a temperature lift of 50K and with a Coefficient of Performance (COP) of 2. In the Phase II effort RINI proposes to continue development of the Mini-Heat Pump to increase compressor performance, study long term reliability, and design, build and test a deliverable prototype. Detailed compressor analysis will be performed, and the results will be applied to a compressor that will be integrated with a motor identified in Phase I for use with the heat exchangers from the Phase I. The Phase II effort will result in delivery of an efficient, lightweight, orientation independent, reliable and compact prototype heat pump for NASA missions.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
This project will provide a compact prototype cooling unit through the utilization of a unique high power density rotary compressor. This system will provide a much needed "temperature lift" to increase radiator temperatures and reduce radiator sizes for high cooling loads. Such a unit will be useful to NASA for incorporation into future spacecraft and instruments for space missions, small compartment or micro-climate cooling, and possible portable applications.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Meso-scale heat pumping devices such as the one developed for this effort may also be used in an array of portable or confined space applications such as avionics cooling, electronics cooling, and portable personal cooling units. Potential medical applications also exist in enabling active, controlled cooling or heating for patients with body temperature control disabilities.

TECHNOLOGY TAXONOMY MAPPING
Ultra-High Density/Low Power
Cooling
Manned-Manuvering Units
Portable Life Support
Liquid-Liquid Interfaces
Thermodynamic Conversion

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)
James Maddocks
jmaddocks@atlasscientific.com
1339 Engineering
Madison,  WI 53706-1607
(608) 265-4246

Expected Technology Readiness Level (TRL) upon completion of contract: 5

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Future NASA missions require thermal control systems that can accommodate large changes in ambient temperature. The two essential aspects of an effective thermal interface material (TIM) are high compliance and high thermal conductivity. Thermal interface materials (TIM) are often used to fill the cavities between mating surfaces to increase the thermal conductance across the interface. Traditional TIMs are polymer based composites such as thermal grease or paste. The nature of polymer matrices makes them inapplicable under vacuum and in a cryogenic environment. The goal of the proposed research is to develop a flexible thermally-conductive tape. The proposed innovation forms a versatile, vacuum-proof, thermally conductive tape. The tape is pliable and should conform to the contours of the interface.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Thermal management is a critical aspect of various high power devices for future NASA missions. The energy generated by electronic devices dissipates into the ambient environment through heat sinks or heat spreaders. Effective heat conduction requires good thermal contact between heat sinks and electronic packages. Thermal contact resistance arises from the microscopic lack of planarity and micro-roughness of the mating surfaces. When two surfaces are brought into contact, the actual contact area is usually much smaller than the apparent contact area, resulting in a thermal barrier at the interface. The problem becomes even more severe in vacuum and low temperature environments. Therefore, high thermal conductivity and vacuum compatible thermal interface materials are crucial to thermal control of electronic devices in space applications.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The proposed thermal interface technology is believed to be applicable to many uses in thermal management. It may be used at the interface between electronic devices and heat spreaders, to attach thermometry, heaters, etc. Being electrically conductive to some extent, it could also be used to form electrical connections. Further, it could be used to quickly attach items without the use of adhesives and to attach items in locations that might otherwise be difficult or impossible to achieve. Avoiding adhesives also eliminates the outgassing of various vapors over time.

TECHNOLOGY TAXONOMY MAPPING
Cooling
Instrumentation
Multifunctional/Smart Materials

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
MicroLink Devices
6457 Howard Street
Niles, IL 60714-3301
(847) 588-3001

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Noren Pan
noren_pan@mindspring.com
6457 Howard Street
Niles,  IL 60714-2232
(847) 588-3001

Expected Technology Readiness Level (TRL) upon completion of contract: 4 to 5

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The innovation in this Phase II SBIR is the development of a technology which will enable the manufacture of a lightweight, low cost, high radiation resistance InP based solar cells with high efficiency suitable for space power systems. The key technological step is the application of a production-worthy epitaxial liftoff (ELO) process to a multijunction solar cell structure fabricated on a large area ( 3-inch and 4-inch)InP substrates. Our focus will be on the improvement of the efficiency of dual junction to greater than 23% and a pathway towards InP based triple junction. The number of substrate reusage will also be investigated to determine the impact of cost savings due to the high cost of InP substrates. Radiation testing of the ELO InP solar cells will be performed and compared to standard InP solar cells.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
This technology will be potentially applicable on many NASA space missions on which solar power is needed, particularly those utilizing solar electric propulsion (SEP). InP is particularly attractive if missions require a high efficiency at the end of life under high radiation environments. Low cost is another attractive feature of this technology since the InP substrate will be reused multiple times reducing the cost of InP based solar cells.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
InP based materials offer higher efficiency in the long wavelength region in comparison to other indirect semiconductor like Ge. The insertion of InP has been prohibitive due to the cost of InP substrate. The ELO technology offers a clear pathway towards a lower cost structure for InP based solar cells. A lower cost structure could permit the usage of InP solar cells in very high efficiency terrestrial requirements. This effort could also benefit high frequency electronic InP based devices since the removal of the substrate could provide a significant reduction in the thermal resistance of the device.

TECHNOLOGY TAXONOMY MAPPING
Photovoltaic Conversion

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Kopin Corporation
200 John Hancock Road
Taunton, MA 02780-7320
(508) 824-6696

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Roger Welser
rwelser@kopin.com
200 John Hancock Road
Taunton,  MA 02780-7320
(508) 824-6696

Expected Technology Readiness Level (TRL) upon completion of contract: 3 to 4

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Current matching constraints can severely limit the design and overall performance of conventional serially-connected multijunction solar cells. The goal of this SBIR program is to enhance the operating tolerance of high efficiency III-V solar cells by employing nanostructured materials in advanced device designs. A larger fraction of the solar spectrum can potentially be harnessed while maximizing the solar cell operating voltage by embedding thin layers of narrow band gap material in a higher band gap matrix. Nanostructured devices thus provide a means to decouple the usual dependence of short circuit current on open circuit voltage that limits conventional solar cell design. While previous experimental work on quantum well or quantum dot solar cell devices has typically employed GaAs as the wide band gap matrix, we take a different approach, instead employing InGaP as the barrier material. During the Phase I effort, we observed that thin InGaP layers can be extremely effective at reducing the dark current. A novel device structure resulted in over a 100 mV enhancement in the open circuit voltage of GaAs PIN diodes solar cells without any degradation in the short circuit current. The Phase II program will aim to further optimize single-junction nanostructured InGaP solar cells and then utilize these cells as building blocks to construct robust, multijunction photovoltaic devices with power conversion efficiencies approaching 40%. Ultimately, the technical approach employed in this program has the potential of achieving conversion efficiencies exceeding 50% with a single p-n junction device, enabling improved overall performance and lower manufacturing costs.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Future space exploration missions will require photovoltaic power systems capable of operating over a wide range of conditions, ranging from extreme environments with high temperatures and tremendous radiation exposures to low temperature, low intensity conditions. Conventional multijunction solar cells can provide high conversion efficiencies, but only under limited environmental conditions. The near term objective of this SBIR program is to build a solar cell using nanostructured wide band gap materials that matches the conversion efficiency of conventional multijunction technologies while performing over a much wider range of operating conditions. The technology developed during this program is expected to have immediate market opportunities as power systems for NASA science missions.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The SBIR project described here is part of a larger effort to realize the ultimate objective of third generation photovoltaics, namely ultra-high conversion efficiency at low costs. The wider operating conditions enabled by nanostructured InGaP solar cells would substantially enhance the overall performance of terrestrial concentrator photovoltaic systems. This technology could thus accelerate the adoption of photovoltaics into the renewable energy market to address the world's growing energy needs without degrading the environment. In addition to its potential commercial value and social benefits, this SBIR program will enhance the technical understanding of quantum well and quantum dot devices.

TECHNOLOGY TAXONOMY MAPPING
Solar
Radiation-Hard/Resistant Electronics
Semi-Conductors/Solid State Device Materials
Photovoltaic Conversion
Renewable Energy

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Quallion, LLC
12744 San Fernando Road
Sylmar, CA 91342-3728
(818) 833-2000

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Hisashi Tsukamoto
hisashi@quallion.com
12744 San Fernando Rd
Sylmar,  CA 91342-3278
(818) 833-2002

Expected Technology Readiness Level (TRL) upon completion of contract: 6 to 7

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Quallion's Phase II proposal calls for expanding the nominal operation range of its space rated lithium ion cells, while maintaining their long life capabilities. To expand this temperature range, Quallion will conduct analysis on a variety of materials. Based upon our results from Phase I, Quallion will further optimize the formulations and fabricate our large format satellite cells for cell level testing. Quallion is also proposing a "right sizing" of this production facility to allow for cost effective, low volume production with enhanced reliability, long-term supply guarantee and design flexibility that allows for future production for NASA missions.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Once the design is verified, Quallion will be able to provide the aerospace satellite community with a satellite cell with expanded operation temperature capabilities for specialty mission. As an option to NASA, this chemistry configuration can be incorporated into our existing production 15Ah and 72Ah lithium-ion satellite cell design, in which the validation of the cells performance will occur during the Phase II execution.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
If successful in Phase II, Qualllion can incorporate this developed technology for other applications requiring a wide operating temperature range. Such applications include military, automotive and aerospace.

TECHNOLOGY TAXONOMY MAPPING
Energy Storage

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Sun Innovations, Inc.
44166 Old Warm Springs Blvd.
Fremont, CA 94538-6144
(510) 651-1329

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
ted sun
ted@sun-innovations.com
44166 Old Warm Springs Blvd.
Fremont,  CA 94538-6144
(510) 651-1329

Expected Technology Readiness Level (TRL) upon completion of contract: 2 to 3

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Spacecrafts rely on arrays of solar cells to generate electrical power. It is an on-going challenge to maximize electrical power available to spacecraft while reducing overall stowage volume and mass of solar array, which requires developing more efficient solar cells with higher specific power density. The objective of this SBIR project is to develop a generic approach, based on novel functional nano-materials, to significantly increasing the solar cell efficiency (~10%), specific power density, radiation resistance and lifetime, without adding much cost or weight to the existing solar cells. The feasibility to synthesis such nano-materials has been explored and demonstrated in Phase I. Without optimizing, preliminary test on commercial solar cells show an efficiency gain approaching 5% after applying such nano-materials. Such nano-materials will be further improved for energy efficiency and environmental durability in Phase II, to reach the objective of at least 10% gain in energy efficiency on majority of commercial solar cells.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The novel nano-materials will find major applications in many NASA space programs. By significantly enhancing the efficiency and output of solar cells, with virtually no change on solar device volume or weight, it would be ideal addition to the solar panels used in space shuttles and other space vehicles. By enabling advanced solar cell with efficiency over 30% and specific power density over 550 W/Kg, the launch and operation cost of spacecraft can be lowered, which greatly benefit various NASA spacecraft programs.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The proposed technology can also be applied to most types of commercial solar cells. By enhancing the efficiency of commercial solar cell (e.g. Silicon cells), without incurring much cost, it will reduce the key "cost per watt" of solar cells in competing with other sources of electrical energy; hence it help promoting the market adoption of solar energy, which benefit the Nation's environment as well as energy independence from foreign oil.

TECHNOLOGY TAXONOMY MAPPING
Solar
Spaceport Infrastructure and Safety
Ceramics
Optical & Photonic Materials
Radiation Shielding Materials
Photovoltaic Conversion
Renewable Energy

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Sienna Technologies, Inc.
19501 144th Avenue NE, Suite F-500
Woodinville, WA 98072-4423
(425) 485-7272

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Ender Savrun
ender.savrun@siennatech.com
19501 144th Ave NE Ste F-500
Woodinville,  WA 98072-4423
(425) 485-7272

Expected Technology Readiness Level (TRL) upon completion of contract: 5 to 6

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The current state-of-the-art co-axial swaged tantalum (Ta) heaters use magnesium oxide (MgO) insulators, which limits their operation to temperatures well below 1300ºC to prevent undesirable chemical reactions between Mg and Ta and heater failure. This program will develop a new ceramic insulator that is chemically compatibility with Ta and has high thermal stability at temperatures of 1300ºC-1600ºC for swaged heaters for BaO-impregnated and LaB6 hollow cathodes. In Phase I, we demonstrated the new ceramic insulators can be used in swaged Ta heaters for BaO-impregnated cathodes that operate at 1100ºC-1300ºC. In Phase II, we will further develop the new ceramic insulator for use in LaB6 hollow cathode heaters that operate at 1600ºC. We will develop an extrusion process to fabricate ceramic insulators with high dimensional tolerances at low cost and fabricate a prototype swaged coaxial heaters in collaboration with a heater manufacturer. Performance mapping and heater testing will be carried out in collaboration with an end-user aerospace company.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Swaged coaxial heaters for hollow cathodes have applications in space as components of ion propulsion systems and spacecraft charging/charge-control systems, including ATS-6, SERT-II, SCATHA, and SCSR-1 flight experiments. Hollow cathodes have also been used on spacecraft, including an Agena vehicle, on communication satellites, on the space shuttle, the electrodynamic tether, and space station structure and other space environments that include those of low-earth orbits, sun-synchronous high inclination orbits, and geosynchronous orbits.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The United States Air Force has many missions in the design stage that would benefit from small, low-cost satellites operating either autonomously or as an element in a cluster of such vehicles flying in formation with carefully controlled distances and orientations to each other. The ion and Hall thrusters provide an enabling technology for microsatellites, which are proposed for many military and commercial applications. The commercial applications include communications and imaging satellites, companions to large satellites to provide surveillance and close-up inspection capabilities, such as to monitor and assure proper deployment of solar panels, antennae and other appendages.

TECHNOLOGY TAXONOMY MAPPING
Electromagnetic Thrusters
Electrostatic Thrusters
Ceramics

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
CU Aerospace, LLC
2100 South Oak Street, Suite 206
Champaign, IL 61820-0903
(217) 333-8274

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
DAVID CARROLL
carroll@cuaerospace.com
2100 S. Oak St. - Suite 206
Champaign,  IL 61820-0903
(217) 333-8274

Expected Technology Readiness Level (TRL) upon completion of contract: 5 to 6

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
A team of CU Aerospace, the University of Illinois, and ManTech SRS Technologies proposes Phase II development of a 3 kg CubeSat spacecraft for initial flight test of a 20 m2 UltraSail, a next-generation high-risk, high-payoff solar sail system for the launch, deployment, stabilization and control of very large (km2 class) solar sails, enabling very high payload mass fractions for interplanetary and deep space spacecraft. UltraSail is an innovative, non-traditional approach to propulsion technology achieved by combining propulsion and control systems developed for formation-flying microsatellites with an innovative solar sail architecture to achieve controllable sail areas approaching 1 km2, sail subsystem area densities less than 5 g/m2, and thrust levels many times those of ion thrusters used for comparable deep space missions. The primary innovation presented in Phase I was vacuum demonstration plus analysis of two modes of sail deployment. The Phase II effort will include fabrication of dual 1.5 kg CubeSats, vacuum and dynamic testing of the separation release unit, and simulation of spacecraft deployment to full film length, analysis of spacecraft dynamics and environmental effects, and formulation and analysis of mission objectives and groundstation requirements.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
UltraSail is potentially useful for a range of robotic missions ranging from Near-Earth to Sun-Earth Lagrange point L1 to Mars to the Kuiper Belt. The low development cost of CubeSat-based solar sails coupled with high thrust and payload mass fraction results in economical, high-performance missions. The use of CubeSats and MicroSats coupled with UltraSail permits low-cost mission development before committing to much larger systems.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
UltraSail has military applications for earth-observing missions at high orbit where stationary observing is useful e.g. pole-sitting missions. Also, NOAA and NSF have strong interests in the science that can be returned using sails in non-Keplerian orbits and at Lagrange points.

TECHNOLOGY TAXONOMY MAPPING
Solar
Kinematic-Deployable

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
sci_zone
17133 Inavale
Holland, MI 49424-5656
(505) 205-8315

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Andrew Santangelo
andrew_santangelo@mac.com
17133 Inavale
Holland,  MI 49424-5656
(505) 205-8315

Expected Technology Readiness Level (TRL) upon completion of contract: 7 to 8

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Satellite design encompasses a multitude of steps from concept to flight, which can take several years, depending on the scope, requirements and budget of the mission. The process also requires a wide range of design and management tools, with limited consistency and data interchange capability. Detailing the relationships between the satellite configuration (components and interrelationships), inventory control systems, life cycle management, design, analysis and test data is extremely difficult at best. No tool exists that meets these needs for the general satellite design, system engineering and integration process. Sci_Zone has begun development of our innovative Satellite Design Automation architecture QuickSAT<SUP>TM</SUP>, in conjunction with our step_SATdb open database architecture to meet this need. step_SATdb seamlessly integrates existing detail design tools with QuickSAT<SUP>TM</SUP>, as well as databases tracking requirements, hardware and software components and payloads in inventory, with the final configuration of the satellite. QuickSAT<SUP>TM</SUP>, provides for not only rapid design, via design wizards and integration to existing design tools, but will provide coherency between a range of applications and data sets. step_SATdb stores and distributes supporting satellite design, configuration, mission, support and test data from a centralized database server and can distribute the data across multiple platforms and via the internet.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Step_SATdb and QuickSAT allows for the rapid development, configuration management, and deployment of systems and satellites. NASA commercial applications include any Satellite or Subsystem development program, manned or unmanned mission - and any project requiring seamless integration between costing, performance, program and project life cycle support, and design processes. Once developed the product should be widely adopted within NASA due in part to QuickSAT, the open APIs, its ability to tie into NASA legacy systems and future environments such as NeXIOM and Step_SATdb's open architecture and platform independence, plus free cost.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Step_SATdb and QuickSAT allows for the rapid development, configuration management, and deployment of satellites while considering performance, risk and managing the process through out the program life cycle. Non-NASA applications include any aerospace related applications requiring seamless integration between costing, performance and design. Non-NASA commercial customers include our own customers, AFRL and SAIC, interested in implementing QuickSAT, and supporting Step_SATdb Environments. This will provide us the opportunity to expand our offering and market to new customers due in part to the architecture's open environment and platform independence. It is planned this project will set a standard for data exchange and design management. A market will then exist of step_SATdb certified applications, guaranteeing increased software sales and support services. This process has begun with the acceptance by AFRL of step_SATdb as the standard data architecture for the Operationally Responsive Space Program.

TECHNOLOGY TAXONOMY MAPPING
Simulation Modeling Environment
Training Concepts and Architectures
Testing Requirements and Architectures
Architectures and Networks
Autonomous Reasoning/Artificial Intelligence
Computer System Architectures
Data Acquisition and End-to-End-Management
Database Development and Interfacing
Expert Systems
Human-Computer Interfaces
Software Development Environments
Software Tools for Distributed Analysis and Simulation
General Public Outreach
K-12 Outreach
Mission Training

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Stellar Exploration, Inc.
174 Suburban Road Suite 120
San Luis Obispo, CA 93401-7518
(805) 549-8200

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Tomas Svitek
charles@stellar-exploration.com
174 Suburban Road, Suite 120
San Luis Obispo,  CA 93401-7518
(805) 549-8200

Expected Technology Readiness Level (TRL) upon completion of contract: 7

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
We are proposing to exploit (in an innovative way) existing, readily available, GNC sensors for the purpose of precision lunar landing. Majority of previous lunar lander concepts with the precision/pinpoint landing capability required expensive and risky development of new GNC and landing sensors (scanning lidars, multi-beam mm-ww radar, etc.). Our proposed alternative consists solely of existing and low-cost sensors that synergistically leverage each capability and compensate for individual sensor weaknesses. For example, we can use a simple single-beam low-frequency radar altimeter (available at low-cost off-the-shelf, and proven on several Mars lander missions). The low-frequency radar can meet the maximum slant range requirements much easier than the mm-wave sensor but it does not have the adequate multiple narrow beam capability of the Apollo LM or Viking lander radar. However, the optical descent imaging measurement (using DSMAC-type sensor) can supplement the single beam radar measurement and obtain the same information about the complete state vector. There are several similar concepts implemented in this sensor suite of complementing strengths and weakness of individual sensors.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The successful integration of low-cost GNC suite would open wide area for sales of that system for several other applications besides the lunar lander (Mars and asteroids mission, and proximity and rendezvous operations in LEO). The preliminary cost estimate for such integrated sensor suite is between $450K and $800K (depending on the software complexity and level of testing required). We anticipate that the first sale of the integrated sensor suite module would occur realistically within 24 months after the completion of Phase 2. Eventually, we estimate that flight rate of these integrated modules could approach 2-3 units per year (mostly in the US market, with minor potential in an international market). For the first ten years, the realistic (conservative) estimate of the total market potential is between 10-16 units, resulting in the total potential market of $5-7M.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Additional non-NASA (eg, privately funded) missions can use this technology.

TECHNOLOGY TAXONOMY MAPPING
Guidance, Navigation, and Control

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Microcosm, Inc.
4940 W. 147th Street
Hawthorne, CA 90250-6708
(310) 726-4100

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
James Wertz
jim@smad.com
4940 W. 147th St.
Hawthorne,  CA 90250-6708
(310) 219-2700

Expected Technology Readiness Level (TRL) upon completion of contract: 6

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Microcosm, with partners Space Micro and HRP Systems, will design, build, and test a plug-and play (PnP) star sensor for small satellites, achieving TRL 6 at the completion of Phase II. All three companies are very experienced in developing PnP systems. On a recent Phase II Air Force SBIR program, Microcosm built and tested a prototype miniature star sensor called MicroMak<SUP>TM</SUP>, and is building a prototype radiation hard star sensor under a new Phase II Air Force SBIR. The new star sensor proposed here will focus on PnP compatibility for NASA missions of interest, with a mass goal of 0.5 to 0.75 kg. Anticipated NASA applications necessitate a modified version of the baseline MicroMak<SUP>TM</SUP> sensor, including: 1) Interfaces compatible with a new PnP avionics architecture, 2) radiation-hardened CMOS focal plane arrays (FPAs), and 3) processing electronics to enable longer mission life. The baseline MicroMak<SUP>TM</SUP> sensor was designed with inherent radiation-tolerant features: FPAs with no direct view of space, and all-reflective optical elements. The PnP star sensor will leverage MicroMak<SUP>TM</SUP> heritage, providing a modular, PnP, long-life star sensor for NASA missions, providing a cost and mass reduction of a factor of 2 or more over existing star sensors.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The proposed star sensor will directly support NASA rapid spacecraft development efforts involving PnP architectures, and various classes of missions, including: longer-life missions, such as outer planets missions; long life libration point astronomy missions; and lunar and Mars exploration. This sensor can also support multiple applications, including spacecraft attitude determination, formation flying, and rendezvous and docking. The expected PnP compatibility and low mass, power, and cost will fill the near term need for improved, low cost attitude sensing technology with lower cost, complexity, mass, and power than traditional solutions. When combined with other sensors, such as an IMU, the new star sensor will have additional capabilities. Microcosm's precision navigation with integrated attitude determination sensor is directly applicable, providing an opportunity to enhance the new star sensor by adding a low-cost micro-electromechanical IMU and GPS receiver. This device can provide higher attitude output rates, up to 100 Hz, supporting additional applications.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The sensor will also have applications for other government systems with similar PnP, attitude accuracy, mission lifetime, and radiation tolerance requirements. Programs seeking rapid spacecraft integration cycles, employing PnP architectures, will also benefit from this new sensor. The Air Force Operationally Responsive Space (ORS) program may be a customer. Microcosm is currently selling components in the satellite attitude determination and control system market, and the MicroMak<SUP>TM</SUP> star sensor should be ready for market in the next two to three years. The proposed new PnP star sensor could be ready for operational flight status in this same time frame, if its development is pursued aggressively in parallel with the baseline MicroMak<SUP>TM</SUP> sensor. Both LEO and GEO satellites could take advantage of such a sensor as well, facilitating rapid, low-cost integration, and possible new applications, such as mounting directly to a communications antenna to get significantly improved determination of antenna pointing.

TECHNOLOGY TAXONOMY MAPPING
Attitude Determination and Control
Guidance, Navigation, and Control

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Stellar Exploration, Inc.
174 Suburban Road Suite 120
San Luis Obispo, CA 93401-7518
(805) 549-8200

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Tomas Svitek
charles@stellar-exploration.com
174 Suburban Road, Suite 120
San Luis Obispo,  CA 93401-7518
(805) 549-8200

Expected Technology Readiness Level (TRL) upon completion of contract: 7

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
We are proposing to leverage the Missile Defense Agency investments in high-performance propulsion systems for low-cost space missions with large Dv requirements, for example, a soft lunar lander. This design concept exploits a core set of hardware developed under past and current Department of Defense (DoD) investments. The propulsion system concepts under consideration are from the DoD's Missile Defense Kinetic Kill Vehicle programs such as EKV, THAAD, ASAT and LEAP. These are bipropellant, storable and hypergolic system that use high-performance propellants (MMH/NTO). This subtopic is seeking technologies with the superior performance for orbital control, for on-orbit applications including storage capability and propulsion. This propulsion system should allow transfers from LEO or GTO to lunar orbit or similar destinations. These missions have in common the substantial Dv propulsion requirements that cannot be met with the existing flown propulsion systems on current small spacecraft missions (for example, SNAP-1, Cubesats, Orbcomm or similar missions). Our proposed solutions offers that capability at an affordable but credible cost.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The successful adaptation and qualification of the KKV-derived propulsion system would offer unprecedented capability to the small spacecraft community. This capability can be used for multiple applications but from NASA viewpoint, primarily lunar, planetary and other deep-space missions. We envision that Stellar would team with the propulsion component providers (Aerojet and P&W Rocketdyne) and also NASA Ames and offer an integrated propulsion solution suitable for this class of missions.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Any small satellite missions with large propulsion requirements are potential market, including recent Google lunar X-prize efforts.

TECHNOLOGY TAXONOMY MAPPING
Chemical

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Whittnghill Aerospace, LLC
265 Durley Avenue, Suite 208
Camarillo, CA 93010-8544
(805) 901-2297

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
George Whittinghill
grw@whittinghillaerospace.com
265 Durley Avenue, Suite 208
Camarillo,  CA 93010-8544
(805) 901-2297

Expected Technology Readiness Level (TRL) upon completion of contract: 6

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
A Nitrous Oxide-fed Liquid Thrust Vector Control system is proposed as an efficient method for vehicle attitude control during powered flight. Pulled from a N2O main propulsion system oxidizer tank, it features system simplicity, no toxicity, room temperature storability, high system mass fraction and superior performance due to its exothermic decomposition characteristics, answering the need for innovative attitude control technologies. A continuing series of 1,000 lb thrust hybrid rocket motor tests are proposed to characterize N2O's Side Specific Impulse as a function of thrust vectoring angle, as well as a series of 4,000 lb thrust motor firings culminating in a closed-loop Guidance Navigation and Control Hardware-In-The-Loop test in a vertical stand. At the conclusion of Phase 2, the technology will be ready for development into an upper stage as an integrated main propulsion Thrust Vector Control (TVC) /Attitude Control System for a small launch vehicle, or as a separate TVC system for any solid, liquid or hybrid powered vehicle.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Potential NASA applications include Small Expendable Launch Vehicle upper stages, Orbit Transfer Vehicles, Spacecraft Buses, On-Orbit Kick Motor Stages and Descent Stages.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Potential Non-NASA applications include commercial solid, liquid and hybrid small satellite launchers and boosters.

TECHNOLOGY TAXONOMY MAPPING
Chemical
Monopropellants
Propellant Storage
Feed System Components

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Physical Sciences, Inc.
20 New England Business Center
Andover, MA 01810-1077
(978) 689-0003

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Mary DeLeo
deleo@psicorp.com
20 New England Business Center
Andover,  MA 01810-1077
(978) 738-8106

Expected Technology Readiness Level (TRL) upon completion of contract: 5 to 6

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
In the Phase I program we successfully demonstrated the feasibility of the Pulsed ElectroGasdynamic (PEG) thruster for attitude control and orbital maneuvering. In this thruster, propellant gas is introduced into the thrust nozzle through a fast acting gas valve where a short, high voltage pulse is applied to break down and heat the propellant gas. The heated gas expands in the nozzle generating a high impulse (~mN-s per pulse) at a high specific thrust (120 £gN-s/joule). The specific impulse (Isp) will be in the range of 500~1500 sec. This process can be repeated at a frequency to meet the spacecraft thrust requirements. The thrust generating mechanism of the proposed thruster is gasdynamic expansion, not magnetohydrodynamic interaction. The proposed thruster is different from the conventional pulsed electrothermal thruster in that the joule heating of the propellant takes place as the propellant gas expands through the divergent nozzle, thereby eliminating the heat and momentum losses at the nozzle throat. Our Phase II objectives are: (i) develop an engineering model; and (ii) develop a proto-flight model of the proposed thruster system.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The Pulsed ElectroGasdynamic (PEG) thruster, when developed to technical maturity, will be used for satellite mobility, such as rapidly changing position for rendezvous, attitude control, orbital maneuvering and controlled satellite constellation formation. These maneuvers require a relatively high thrust (mN ~ N) at a moderately high specific impulse (Isp „l 1000 sec) and a high electric efficiency (~60%). The PEG thruster will meet this requirement in a broad thrust range. For example, when operated at 1 Hz, the PEG thruster will generate a thrust of 1 mN with 10 W of electric power input. At higher pulse rates, 100 Hz for example, 100 mN of thrust will be generated with 1 kW of electric power. Higher thrust can be obtained by scaling up the thruster size. The PEG thruster in a low power mode will also be used for station keeping applications. To this end, a PEG thruster suite can be added to any spacecraft equipped with a N2H4/NTO Monopropellant/Bipropellant propulsion system without incurring a mass penalty for high precision ¡§digital¡¨ attitude corrections at a higher Isp than is obtained with the conventional monopropellant solution. Furthermore storable ¡§Green¡¨ propellants such as N2O and NH3 are very suitable as PEG thruster propellants. The PEG thruster will serve NASA¡¦s Science Mission Directorate needs in earth orbit, near-earth and in deep space.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The Pulsed ElectroGasdynamic (PEG) thruster will be very useful for military applications that require: (i) wide dynamic range in thrust; (ii) high Isp; and (iii) high electrical efficiency. For purely commercial applications, the PEG thruster will be useful for satellite station keeping, orbit raising, and attitude control. For such applications the following advantages of the PEG thruster can be fully exploited: (i) various kinds of propellant gas can be used; (ii) thrust level can be adjusted by changing pulse frequency over 2~3 orders of magnitude; (iii) the life time of the thruster hardware will be much longer than the other thrusters; and (iv) construction of the thruster is simple and can be scaled easily.

TECHNOLOGY TAXONOMY MAPPING
Micro Thrusters

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Advatech Pacific, Inc.
1849 North Wabash Avenue
Redlands, CA 92374-4970
(909) 307-6218

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Peter Rohl
peter.rohl@advatechpacific.com
1849 North Wabash Avenue
Redlands,  CA 92374-4970
(909) 307-6218

Expected Technology Readiness Level (TRL) upon completion of contract: 6 to 7

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
An integrated environment for rapid design studies of small satellite missions will be developed. This environment will be designed to streamline processes at the NASA Ames Mission Design Center. Several key concepts are introduced. The proposed environment introduces modern Product Data Management and Product Lifecycle Management (PDM/PLM) tools and processes to satellite mission design. Specifically, the notion of product structure, or bill of material (BOM), is expanded to a simulation BOM, or SBOM, with the capability to manage engineering analysis data, files and processes in the context of a product, in this case satellite mission. This approach constitutes a significant step beyond mere document management, which limits the traceability of which model of which analysis belongs to which version of the geometry or other analysis. It is a key enabler for model re-use. A Linked Model Environment (LME), i.e. an environment where all engineering analysis models are associatively linked, which was developed concurrently in the commercial aerospace and automotive industry, will extended to satellite mission design. This environment significantly reduces the amount of manual intervention engineers have to perform to translate information from one simulation tool to another. The concept of digital mockup (DMU), which typically addresses form and fit of components in an assembly, is expanded to include function, such that the inclusion of components in a satellite assembly that are functionally incompatible is rejected. Repetitive-iterative engineering tasks will be automated with the help of an integration framework tool which automates the execution of a sequence of codes and provides the capability to wrap drivers like optimizers or quality engineering tools around an automated analysis workflow.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The results of this research directly benefit the NASA Ames Mission Design Center in their activity of assembling Small Satellite missions. Currently, the Missions Design Center does not employ an integrated, PLM-based approach in their design activities. The Mission Design Center receives geometric information from component suppliers in a variety of formats. The current in-house CAD package is Solidworks. Analysis tools such as STK and disciplines such as structural and thermal analysis need subsets of the detailed CAD geometry in particular formats that they can process. Currently, much time is spent converting geometry from one format to another, and critical information can be lost in the process. The proposed work will directly address these issues. In addition, there are a number of additional potential applications of this technology. For example, JPL could use our tools in the design of exploratory space probes. The tools could also play a role in the development of micro and nano satellites all the way to manned space missions.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The proposed VSIE is directly applicable to the Plug&Play space vehicle design approach currently being investigated by the US Air Force at AFRL Kirtland AFB. The goal of the plug and play space vehicle design approach is to apply the proven capability of computer peripherals to integrate themselves with computers to space vehicle components. This will enable space vehicles to be assembled quickly enough to meet rapidly developing operational needs where time is the critical factor. Advatech Pacific is currently working with AFRL Kirtland AFB to develop the ISET tool which enables pre-conceptual/conceptual level design of space vehicles by both traditional approaches and utilizing standardized plug and play space vehicle components. The enhanced DMU and data management concepts suggested in the present proposal will be directly applicable to support this Plug&Play scenario. This type of technology will be a key enabler for the Responsive Space Launch program by the US Air Force. On the commercial side, any of the primes or first tier suppliers could benefit from the tools being developed, specifically on small satellite projects.

TECHNOLOGY TAXONOMY MAPPING
Launch and Flight Vehicle
Simulation Modeling Environment
Testing Requirements and Architectures
Modular Interconnects
Structural Modeling and Tools
Software Tools for Distributed Analysis and Simulation
Power Management and Distribution
Wireless Distribution

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Mobile Energy Products, Inc.
3820 S Hancock Expressway
Colorado Springs, CO 80911-1231
(719) 392-4266

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Za Johnson
zjohnson@electroenergyinc.com
3820 S Hancock Expressway
Colorado Springs,  CO 80911-1231
(719) 392-4266

Expected Technology Readiness Level (TRL) upon completion of contract: 6

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Development of energy storage capable of operational temperatures of 380ºC and 486<SUP>o</SUP>C with a specific capacity 200 Wh/kg for use as a power source on the Venusian surface and for planetary probes in similar high temperature atmospheres and where ambient pressures of 90 atmospheres are to be expected. This proposal provides for further research and development of the Li(Al)/CoS2 high temperature energy storage chemistry to develop high temperature space energy storage, which will enable the in situ exploration of the atmosphere of Venus and deep atmospheres of Jupiter or Saturn for future NASA missions. This energy storage will provide power for thermal control systems, high temperature electronics and sensors, and high temperature motors and actuators. The approach has a parallel path of evaluation of low melting point electrolyte for 380ºC operation and optimization of the 486ºC Venus energy storage chemistry. The final task is battery level characterization at various temperatures and discharge rates, with implementation of the previously completed design of a robust battery/cell container and ceramic to metal seals. The development includes the delivery of a prototype battery to JPL for testing.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Successful completion of this development of high temperature batteries will enable in situ planetary exploration for NASA missions, where energy storage must be occur at high temperatures due to environmental conditions. The energy storage will have a specific energy >200 Wh/kg based on Phase I development which demonstrated battery discharge profiles in excess of 7 days (173 hrs) at 475ºC temperature with background and burst (pulse) discharge currents. The cell specific energy demonstrated in Phase I was greater than 270 Wh/kg.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The R&D conducted under this program will have the potential to make improvements to thermal batteries, low temperature thermal batteries, high temperature energy storage for borehole and terrestrial applications, geothermal batteries and other specialty high temperature energy storage for space applications.

TECHNOLOGY TAXONOMY MAPPING
Teleoperation
Control Instrumentation
Telemetry, Tracking and Control
Ultra-High Density/Low Power
Attitude Determination and Control
Data Input/Output Devices
Portable Data Acquisition or Analysis Tools
Sensor Webs/Distributed Sensors
Tools
In-situ Resource Utilization
Energy Storage

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Advanced Scientific Concepts, Inc.
135 E. Ortega Street
Santa Barbara, CA 93101-1674
(805) 966-3331

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Steven Silverman
ssilverman@asc3d.com
135 E. Ortega Street
Santa Barbara ,  CA 93101-1674
(805) 966-3331

Expected Technology Readiness Level (TRL) upon completion of contract: 6 to 7

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Advanced Scientific Concepts Inc. (ASC) is a small business that has developed a number of 3D flash LADAR systems. Flash Ladar Video Cameras are 3D video cameras that return range and intensity information for each pixel in real time, and is functionally equivalent to 16000 range finders on one chip. Actual data collected, at the JPL mars yard, using ASC's compact Flash Ladar system demonstrated in a previous NASA phase I SBIR effort confirm that the ASC Flash LADAR Video Camera (FLVC) system can meet the requirements for Entry, Descent and Landing (EDL). The FLVC's small size, low power and very fast range data frame rate (30Hz) the sensor can be configured for a variety of EDL missions. An existing Phase two effort is fabricating a compact FLVC for delivery to NASA for field testing, however the system is not hardened. The proposed Phase 2 effort will produce a space qualified sensor engine which can be integrated with the system being delivered to NASA. The sensor engine is the break-though enabling technology for the FLVC. The sensor engine will be fabricated, tested and used to upgrade the camera JPL. As a result of these improvements, the TRL level of this sensor will be at 6-7. Flash Ladar is ideal for determining real-time spacecraft trajectory, speed and orientation to the planet surface, as well as evaluating potential hazards at the landing site is required for precision landing. Sloped ground, craters, rocks and surface composition are among the potential hazards. The "framing camera" nature, of Flash LADAR systems, makes them well suited as hazard avoidance sensors for EDL. Flash LADAR can provide a direct, real-time measurement of the altitude of the spacecraft during descent as well as surface relative velocity and orientation, while simultaneously mapping the topography of the terrain below to identify landing hazards and provide localization information.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
This sensor will increase the success of NASA operations such as: • Mars Landed Exploration • Exploration of Moons (ALHAT, Jupiter Icy Moons) • Asteroid and Comet Rendezvous and Sample Return • ISS Rendezvous and Docking • Space Situational Awareness • Rock Abundance and Distribution Maps • Topographical Mapping • Rover Mobility and Navigation NASA Langley Research Center has purchased two of ASC's existing FLVC systems for performing laboratory, field, and airborne test and evaluation of this technology for use on the ALHAT program. On system has been deployed for EDL helicopter experiments and has shown excellent results. ASC has developed unit cells that show 10x increase in detection threshold sensitivity (which implies 10X lower laser power requirements for a given return signal to noise ratio). NASA LaRC has offered to support ASC in defining requirements for advanced ROIC technology to increase device threshold sensitivity for a proposed Phase II effort. NASA LaRC's second camera is incorporating the automatic range calibration and higher sensitivity detector arrays that were investigated under the supporting SBIR. This system will be used for high altitude EDL testing for ALHAT.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
ASC is pursuing many non-NASA applications. Collision avoidance to save pedestrians and prevent vehicle damage, Helicopter landing in BrownOut conditions, Mid-Air Refueling, Surveillance, Terrain Mapping, Autonomous Navigation for UGVs, unmanned surface vehicles (USVs) and UAV, Smart intersection, Ladar brakes, Robotics, Machine Vision, Hazard Material Detection and Handling, Underwater 3D Imaging, Sub Nanosecond Dynamic Imaging, 3D Sports Imaging and data transmission, consumer electronics.

TECHNOLOGY TAXONOMY MAPPING
Perception/Sensing
Teleoperation
Optical
Photonics
Radiation-Hard/Resistant Electronics

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Honeybee Robotics Ltd.
460 W 34th Street
New York, NY 10001-2320
(212) 966-0661

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Kris Zacny
zacny@honeybeerobotics.com
460 W 34th Street
New York,  NY 10001-2320
(510) 207-4555

Expected Technology Readiness Level (TRL) upon completion of contract: 6

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Robotic planetary exploration missions will need to perform in-situ analysis of rock and/or regolith samples or returning samples back to earth. Obtaining and delivering a sample can be a complex engineering problem, especially if it's done autonomously thousands of miles away. To accommodate future missions, these subsurface access and sample handling technologies must be developed to meet a broad range of potential requirements, including a variety of rock or subsurface materials, rigorous sample preservation requirements, and the general problem of autonomous operation in the presence of dust and with limited resources. The one-to-three meter range has been identified as a critical regime for planetary exploration and while there has been some technology development in this regime, there is currently no proven flight-like approach to robotically achieving this depth through layers of challenging material from realistic roving or landed platforms. The Phase 1 research has resulted in proving the benefits of rotary-percussive drilling system as it pertains to breaking of formation and cuttings transport. The primary objective of the proposed effort is to develop, via testing in a simulated Mars environment, a breadboard one-meter sampling drilling system for acquiring a small volume of drilled cuttings and a core (if necessary) from a target depth on Mars. This project would build on the existing knowledge base of Mars drilling, and its particular strength lies with its capability of performing drilling tests under simulated Martian conditions of temperature and pressure and CO2 atmosphere. This is a component technology effort that includes the development of a rotary percussive drill head and a sampling lead drill string. Honeybee Robotics will leverage drill head development by utilizing voice coil percussive actuator technology developed by the Jet Propulsion Laboratory (JPL) for the Mars Science Laboratory Powder Drill.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The Mars Exploration Program Analysis Group has identified subsurface access as a major technology need for future Mars science missions - key to understanding conditions favorable to life including the presence and morphology of forms of water, as well as for geological investigations. Potentially relevant missions may include Astrobiology Field Laboratory, Mid-Size Rovers, Mars Scout, and Mars Sample Return. A subsurface access tool (robotic or astronaut-assisted) for the Moon be of scientific interest and also necessary for ground truth for resource mapping (including the presence, form, and concentration of potential polar cap water ice, potential in the 1-3 meter depth range) and regolith geotechnical properties assessment. A drill with sample acquisition and analysis, could identify regolith composition for the purposes of determining the presence and quantities of lunar resources for future in situ resource utilization. In addition, regolith geotechnical properties may also be roughly inferred from drill telemetry. This information is important for understanding excavability, load-bearing capacity and trafficability of lunar regolith for ISRU and lunar infrastructure development in preparation for lunar human bases. A 1m class drill could also be modified for Venus, comets, Europa and Near Earth Objects. In addition the lessons learned from this effort may be extrapolated to shallow surface drilling as well as deep drilling missions.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Low cost, low mass drills could be used to quickly assess hazardous areas (oil spill sites around the refineries, toxic waste disposal sites, volcanoes, etc.) without endangering human life. In addition, the Department of Defense could deploy such rovers in conflict zones to assess the road trafficability potential prior to deployment of rescue teams as well as for identifying buried items such as mines. The petroleum and mining industries have also shown interest in robotic sampling. Honeybee Robotics is currently leveraging our experience in this area by working with a major mining concern on developing the "Mine of the Future". There is also a great need for this type of drill for Arctic sampling and extreme biology studies to acquire uncontaminated samples.

TECHNOLOGY TAXONOMY MAPPING
Integrated Robotic Concepts and Systems
Manipulation
Perception/Sensing
Tools
In-situ Resource Utilization

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Honeybee Robotics Ltd.
460 W 34th Street
New York, NY 10001-2320
(212) 966-0661

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Kris Zacny
zacny@honeybeerobotics.com
460 West 34th Street
New York,  NY 10001-2320
(510) 207-4555

Expected Technology Readiness Level (TRL) upon completion of contract: 5 to 6

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Autonomous surface sampling systems are necessary, near term, to construct a historical view of planetary significant events; as well as allow for the identification of materials useful for ISRU activities. Paramount to this is exploration missions capable of in-situ analysis of core samples that deliver the stratigraphy of the target. These sample handling technologies must be developed to meet a broad range of potential requirements, including a variety of rock or subsurface materials, rigorous sample preservation requirements, and the general problem of autonomous operation in the presence of dust and with limited resources. Honeybee seeks to develop critical subsystems for a small, low-mass, low-power Rotary-Percussive Corer (RoPeC) capable of autonomous sample acquisition and delivery from a depth of 5 cm. Specific attention will be given to the tall-pole items including the core break-off, retention, delivery, rotary-percussive drive, and gas flushing subsystems. Near term applications include the Astrobiology Field Laboratory and Mars Sample Return missions. Previous coring tool development has focused on integration and far-horizon proof of concepts; resulting in complete systems designed around specific requirements. The path forward lies in maturing specific aspects of designs quickly. The Phase 1 research has resulted in a survey of existing sampling systems as well as a conceptual design of the RoPeC with a focus on modularity. In Phase 2, Honeybee will mature the design of RoPeC subsystems; including the integration of a percussive voice coil actuator developed by the Jet Propulsion Laboratory for the Mars Science Laboratory (MSL) Powder Acquisition Drill System. A focus on modularity will ensure that subsystems can be redesigned independently; enabling the acquisition of core samples in targets including MEPAG suggested rocks, MSL Mars analogs and Phoenix analogs. This will lead to the a TRL of 5-6.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Future robotic astrobiology missions such as Astrobiology Field Laboratory or Mars Sample Return will benefit greatly from the ability to capture rock and regolith cores. The drill could be also deployed during lunar sortie missions by astronauts (hand held coring drill) since it is desirable to bring a small core back as opposed to a large rock. From a science standpoint, core samples have a distinct advantage over collected drill cuttings in that the stratigraphy and morphology of the sample is preserved. This facilitates detection of localized organics and fossil biosignatures, as well as analysis of geochemistry and mineralogy. The need for a flight-ready surface coring tool has been evident in various NASA program reviews, mission concepts, and mission baselines. RoPeC, a low-mass, low-power drill, will reach a depth of 5cm in rock, regolith, and icy soil, and will be robotic-arm-mountable, enabling access to outcroppings and other non-horizontal target formations. Using a rotary-percussive drilling mechanism will enable penetration of strong basaltic or icy targets without unduly compromising tool life or power requirements. During phase 2, Honeybee will perform a comprehensive study to determine the mass/cost/schedule requirements to make RoPeC flight ready.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Rotary-percussive drilling has many terrestrial applications in industry, as well as in research and development. Scientists often use coring tools to acquire core samples for the study of everything between geological classification to ocean drilling and surveying. Traditionally, petroleum engineers will use large cores to extract information about boundaries between sandstone, limestone, and shale. This process is time consuming so smaller cores are sometimes taken. This method of sampling is called sidewall coring and provides more information to the petroleum engineering than simply logging data. Both rotary and percussive methods are currently utilized, but increased efficiency is likely possible through a combination such as utilized in the RoPeC design. Scientists studying earthquake mechanics could also benefit from the use of the RoPeC in a similar fashion. Automation of this process would save time and money; enabling the science goals of the research with reduced schedule and budget risk/impact. The RoPeC also has applications for the study of terrestrial biology, such as coring into rocks in the Arctic, Antarctic, or other desirable locations. Tullis Onstott of the Department of Geosciences from Princeton University has expressed interest in a coring tool for sampling tunnel face and biofilm-rock interfaces at the Deep Underground Science and Engineering Laboratory.

TECHNOLOGY TAXONOMY MAPPING
Integrated Robotic Concepts and Systems
Manipulation
Perception/Sensing
Teleoperation
Biochemical
Tools
In-situ Resource Utilization

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
SciberQuest, Inc.
Pacific Executive Plaza, 777 South Highway 101, Suite 108
Solana Beach, CA 92075-2623
(858) 793-7063

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Homa Karimabadi
homak@sciberquest.com
Pacific Executive Plaza 777 South Highway 101, Suite 108
Solana Beach,  CA 92075-2623
(858) 793-7063

Expected Technology Readiness Level (TRL) upon completion of contract: 7 to 8

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Existing scientific visualization tools have specific limitations for large scale scientific data sets. Of these four limitations can be seen as paramount: (i) memory management, (ii) remote visualization, (iii) interactivity, and (iv) specificity. In Phase I, we proposed and successfully developed a prototype of a collection of computer tools and libraries called SciViz that overcome these limitations and enable researchers to visualize large scale data sets (greater than 200 gigabytes) on HPC resources remotely from their workstations at interactive rates. A key element of our technology is the stack oriented rather than a framework driven approach which allows it to interoperate with common existing scientific visualization software thereby eliminating the need for the user to switch and learn new software. The result is a versatile 3D visualization capability that will significantly decrease the time to knowledge discovery from large, complex data sets. Typical visualization activity can be organized into a simple stack of steps that leads to the visualization result. These steps can broadly be classified into data retrieval, data analysis, visual representation, and rendering. Our approach will be to continue with the technique selected in Phase I of utilizing existing visualization tools at each point in the visualization stack and to develop specific tools that address the core limitations identified and seamlessly integrate them into the visualization stack. Specifically, we intend to complete technical objectives in four areas that will complete the development of visualization tools for interactive visualization of very large data sets in each layer of the visualization stack. These four areas are: Feature Objectives, C++ Conversion and Optimization, Testing Objectives, and Domain Specifics and Integration. The technology will be developed and tested at NASA and the San Diego Supercomputer Center.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
A natural choice is infusion of SciViz into NASA supercomputing operations. SciViz is expected to find rapid adoption among supercomputing user base since it circumvents the well known problems associated with visualization of large data sets with minimal interruption of existing visualization environments. The value proposition to NASA is increase in user productivity and broadening of NASA's supercomputing user base.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Supercomputer centers, national labs, data-centric private industries such as oil and gas. Diverse fields of science and industries are facing a tsunami of data and not surprisingly data visualization represents a US$2 billion worldwide market. We plan to fully leverage our initial deployment within NASA and SDSC supercomputer centers in order to gain market penetration and expand into other sectors. Any field that deals with large data sets is a potential market candidate for SciViz. This includes other computational centers such as national laboratories, military, the field of electron microscopy and oil companies.

TECHNOLOGY TAXONOMY MAPPING
Computer System Architectures
Software Development Environments
Software Tools for Distributed Analysis and Simulation

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Tech-X Corporation
5621 Arapahoe Avenue, Suite A
Boulder, CO 80303-1379
(303) 448-0727

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Michael Galloy
mgalloy@txcorp.com
5621 Arapahoe Ave Suite A
Boulder,  CO 80303-1379
(303) 996-2032

Expected Technology Readiness Level (TRL) upon completion of contract: 7

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
We propose to enable user-friendly interaction with multi-processor and multi-core resources,allowing users to seamlessly retrieve remote data with DAP and take advantage of parallelcomputing resources for analyzing that data. Where possible, we plan to make these featuresavailable in the open-source GDL (Gnu Data Language) version of IDL.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
IDL is widely used for analysis and visualization throughout NASA. DAP is also used by NASA; there are 72 NASA datasets listed on the OPeNDAP website including datasets at GES-DISC Data Holdings, CDAWeb Data Holdings, Physical Oceanography Distributed Active Archive Center (PODAAC), and Ocean Earth Science Information Partner (OceanESIP).

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
IDL is widely used in academia, industry, national labs. Data analysis in various areas can benefit from accessing remote data, e.g. astronomy, remote sensing, climate studies, medical imaging, chemical engineering. There are 28 non-NASA organizations with over 100 datasets listed on the OPeNDAP website.

TECHNOLOGY TAXONOMY MAPPING
Software Tools for Distributed Analysis and Simulation

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Toyon Research Corporation
6800 Cortona Drive
Goleta, CA 93117-3021
(805) 968-6787

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Kenan Ezal
kezal@toyon.com
6800 Cortona Drive
Goleta,  CA 93117-3021
(805) 968-6787

Expected Technology Readiness Level (TRL) upon completion of contract: 6 to 7

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Attitude determination of spin-stabilized platforms is especially challenging. Current low-cost gyroscope technology does not lend itself to attitude determination of platforms spinning in excess of one rotation per second. Traditional GPS-based attitude (GPS/A) sensors require three or more antenna elements separated by large baselines. Single-element designs require extensive calibration of the satellite signal-to-noise ratio (SNR) and are not very accurate. Toyon Research Corporation proposes to develop a small, single-aperture low-cost GPS/A sensor for space launch vehicles, and to demonstrate the sensor in an operational environment. The sensor determines the platform attitude with a single GPS antenna having a diameter of approximately 6.5 cm. The standalone performance of Toyon's GPS/A sensor on a spinning platform is better than 2.1 degrees for roll, and better than 1.2 degrees for yaw and pitch (one-sigma). The system performance can be further improved when integrated with accelerometers and/or magnetometers. Although current low-cost gyroscope technology does not allow their use on spinning platforms, non-spinning platforms may take advantage of gyro measurements for further improvements in attitude performance. During the proposed Phase II program Toyon will develop, build and test a prototype system that will be delivered for validation onboard an actual space launch vehicle.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Toyon's Miniature Integrated Direction-finding Attitude-determining Anti-jam System (MIDAAS(TM)) provides drift-free and temperature insensitive GPS-based attitude (GPS/A) measurements for small expendable launch vehicles and micro-satellites in a small package and at a lower cost than array-based GPS attitude systems. The stand-alone MIDAAS sensor performs equally well for spinning and non-spinning platforms, and can be integrated with alternative sensors such as accelerometers, magnetometers, and gyroscopes, when feasible. The MIDAAS technology has direct applications to any navigation system requiring 3-D attitude measurements including manned and unmanned vehicles and robots. When feasible, the integration of low-cost gyroscopes results in a ten-fold improvement in navigation accuracy without significant increases in cost: the MIDAAS sensor provides tactical-grade performance when integrated with a commercial-grade inertial measurement unit (IMU).

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The MIDAAS GPS-based attitude (GPS/A) sensor technology is applicable to a wide range of military and civilian applications including unmanned aerial vehicles (UAVs), micro air vehicles (MAVs), unattended ground sensors (UGS), handheld positioning units, recreational and military virtual- and mixed-reality orientation devices, radio-controlled (RC) vehicles, ground vehicles, and far-target locators, as well as military spin-stabilized munitions and platforms. The technology appeals to customers who desire robust position and attitude measurements for spinning and non-spinning platforms that have stringent cost and size, weight and power (SWAP) constraints.

TECHNOLOGY TAXONOMY MAPPING
Integrated Robotic Concepts and Systems
Perception/Sensing
Telemetry, Tracking and Control
Attitude Determination and Control
Guidance, Navigation, and Control

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Composite Technology Development, Inc.
2600 Campus Drive, Suite D
Lafayette, CO 80026-3359
(303) 664-0397

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Robert Taylor
robert.taylor@ctd-materials.com
2600 Campus Drive, Suite D
Lafayette,  CO 80026-3359
(303) 664-0394

Expected Technology Readiness Level (TRL) upon completion of contract: 5 to 6

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Under this and several other programs, CTD has developed TEMBO<SUP>REG</SUP> deployable solid-surface reflectors (TEMBO<SUP>REG</SUP> Reflectors) to provide future NASA and Air Force missions and commercial communications satellites with large RF apertures that can operate at very high operational frequencies (Ka band and above). TEMBO<SUP>REG</SUP> Reflectors incorporate non-tensioned graphite composite membranes that are formed using conventional construction techniques and stiffened using CTD's TEMBO<SUP>REG</SUP> shape-memory composite panels to allow practical packaging and deployment without complex mechanisms. The simplicity of the design provides a significant cost advantage when compared to existing deployable reflector technologies, (4-fold cost reduction over mesh antenna and 2-fold reduction in manufacturing time) and the continuous graphite surface enables high frequency antenna operations at Ka band and above. CTD can stow either a Cassegrainian (center-fed) or Gregorian (offset-fed) 5m TEMBO<SUP>REG</SUP> Reflectors in a Falcon 1e launch vehicle. To moderate cost and fabrication time, the TEMBO<SUP>REG</SUP> reflector is supported by a deployable backing structure. In the proposed Phase II effort, CTD will further refine innovative backing structure developed in Phase I as well as to develop additional precision capability to enable both the high frequency (Ka band and above), large aperture (5 to 8 meters) performance required for near-term and future NASA programs.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
NASA Earth surveying missions such as the Soil Moisture Active/Passive (SMAP) mission and DESDynI, are specific near-term NASA missions with needs for large aperture reflectors to provide L-band radar and radiometers. Although these missions are within the frequency capability of mesh reflectors, JPL has expressed concern that the poor side-lobe performance of mesh reflectors may significantly degrade the performance of the L-band radiometer. This poor side-lobe performance on the mesh reflectors is believed to be due to edge infringements inherent in the mesh reflector design. The TEMBO solid-surface deployable reflectors being developed by CTD, , exactly meet this need. Also, Space Science missions, such as the proposed Europa Lander CADMUS and a Venus Radar instrument being developed by JPL will need large aperture deployable antenna reflectors. CTD's TEMBO<SUP>REG</SUP> Reflector could also be key to the success of these missions by providing increased deployed aperture and high-frequency capability at low cost and risk.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
CTD has been working with the Air Force and the Missile Defense Agency to develop and implement components and subsystems based on CTD's Elastic Memory Composite materials. For example, CTD has delivered EMC hinge/actuators to MicroSat Systems, Inc. to deploy an experimental solar array on the Air Force's TacSat-2 mission, which is currently scheduled for launch in late 2006. Enhancements to CTD's Solid Surface TEMBO<SUP>REG</SUP> deployable reflectors are of interested to Operationally Responsive Space for lower frequency applications and in the future for other DoD applications. CTD has begun to identify several commercial terrestrial markets where nano-particle-reinforced TEMBO<SUP>REG</SUP> materials show great promise. In one case, we have received $325K of funding from a customer to develop a prototype product, which is planned for field-testing in 2007. This prototype represents the first of many possible applications for this customer, and we are currently negotiating development agreements for additional prototypes. Our customer is the leader in the target market of interest. Their 2002 sales of products that could incorporate some TEMBO<SUP>REG</SUP> products was $481M. If TEMBO<SUP>REG</SUP> materials were used on only 25 percent of these products, and CTD received only 5 percent of these revenues as sales of TEMBO<SUP>REG</SUP> materials, this would result in $6M in annual sales. We believe this is but the tip of the iceberg for the commercial potential for TEMBO<SUP>REG</SUP> polymers and composites.

TECHNOLOGY TAXONOMY MAPPING
Kinematic-Deployable
Operations Concepts and Requirements
Testing Requirements and Architectures
Large Antennas and Telescopes
RF
In-situ Resource Utilization
Composites
Multifunctional/Smart Materials

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Omega Optics, Inc.
10435 Burnet Road, Suite 108
Austin, TX 78758-4450
(512) 996-8833

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Maggie Chen
maggie.chen@omegaoptics.com
10435 Burnet Road, Suite 108
Austin,  TX 78758-4450
(512) 996-8833

Expected Technology Readiness Level (TRL) upon completion of contract: 6

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
NASA's future exploration missions focus on the manned exploration of the Moon, Mars and beyond, which will rely heavily on the development of a reliable communications infrastructure from planetary surface-to-surface, surface-to-orbit and back to Earth. Flexible antennas are highly desired in many scenarios, such as pressurized rovers, pressurized habitats, space suits, and any other applications that require conformal profiles. Existing flexible electronics has an intrinsic low switching frequency due to their low carrier mobility. The CNT network in solution we used has carrier mobility as high as 46770cm2/V•s and a large current-density carrying capacity of ~1000 mA/cm2, corresponding to a high carrying power of over 2000mW/cm2. Such high carrier mobility and large current carrying capacity allow us to achieve high-speed (>100GHz), high power flexible electronic circuits and antennas. A prototype of a fully printed S-band 4-bit 2D (4x4) 16-element PAA on flexible substrate such as Kapton, including FET based T/R module and phase shifters will be developed and optimized. For the FETs working as switches/amplifiers, the switch speed, on-off ration, the gain, noise figure, insertion loss and power consumption will be significantly improved through finding better gate dielectric material, increasing the CNT purity and the optimizing the FET geometry including the channel length and the channel width. Performance features of the printed PAA will be characterized including frequency/bandwidth, gain/efficiency, and power consumption. To survive NASA's stressing environment, the operating temperature range will be investigated and the performance under shock and vibration will be evaluated. The humidity test and aging tests will also be carried out. Radiation hard test will also be carried out in Phase II under the program manager's guidance.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The flexible PAAs can be used in lunar communication networks, space suits, large inflatable PAAs, high power electronics/antennas, and etc. (1) For Lunar local networks Lunar local networks are expected to provide coverage for short (~10m) to medium range (~5-10km) communications at UHF/S/C-band, with date rates not to exceed 19 Mbps. The S-band PAA is specially designed for the lunar local communications. (2) For space suits during EVA Compared with the ongoing research at JSC for EVA communications, our fully printed antenna can be "stick-on" directly on the outside of the space suit, while the wearable e-textile antenna is integrated into the clothing. It allows for optimal antenna placement for dynamic situations and can be easily peeled-off for exchange or repair.The printing process is much cheaper than weaving into space suite. (3) For large inflatable PAA Among all large active PAA issues, the most serious is its cost (an electronic phase shifter costs between $200 and $5,000). The printing technology will enable large-area inflatable active PAA deployment, due to the dramatically reduced cost (estimated cost/per element around $20 for large arrays). (4) High power electronics/antenna The CNT we used has a large current-density carrying capacity of ~1000 mA/cm2, corresponding to a high carrying power of 2000mW/cm2. Such a large power carrying capability allows this technology to be used in high power electronics/antenna applications.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The high operating frequency of the flexible nano-FET is particularly useful in many Non-NASA applications requiring ultra-sensitive and standalone, including: (1) RF identification tags Omega Optics, Inc. has teamed up with the world leading RFID company, Checkpoint, for collaboration in high frequency RFID development. A supporting letter is attached in the proposal. (2) Sensors; Omega Optics, Inc. has teamed up with the world leading sensor company, Sensortran, for collaboration in conformal sensor development. A supporting letter is attached in the proposal. (3) Smart cards; (4) Electronic papers; (5) large area flat panel displays;

TECHNOLOGY TAXONOMY MAPPING
Large Antennas and Telescopes
Ultra-High Density/Low Power
RF
Highly-Reconfigurable
Radiation-Hard/Resistant Electronics
Semi-Conductors/Solid State Device Materials

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Applied EM, Inc.
144 Research Drive
Hampton , VA 23666-1339
(757) 224-2035

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Thomas Campbell
tom_campbell@appliedem.com
144 Research Drive
Hampton,  VA 23666-1339
(757) 224-2035

Expected Technology Readiness Level (TRL) upon completion of contract: 4 to 5

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
As NASA prepares for the Constellation Space Missions and Extra-Vehicular Activity (EVA) on the moon by 2018, astronauts will be required to spend more time exposed to the hazards of EVA operations. Providing reliable communications is imperative during current EMU/ISS operations as well as future Constellation Missions. Communications during EVA is required to relay progress regarding the task and to monitor the health and ability of the astronaut to perform in hazardous environments. Therefore, in order to improve astronaut mobility and space communications, Applied EM, Inc. will apply the results of Phase I to develop and demonstrate a prototype multi-frequency design of a conformal, flexible, body-worn antenna that can be integrated into space suit designs to enhance UHF communications during EVA operations. In addition, the antenna design has multi-frequency capability that enables wireless bio-med telemetry for wearable computer applications during space operations. NASA's new Constellation Space Suit System (CSSS) will provide new space suit designs to improve the astronaut's mobility, efficiency, and safety while wearing the space suit during long periods of EVA operations. Therefore, the objectives for Phase II will consider antenna designs for both near term and far term space mission applications.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
This multi-disciplinary research project enables a wide range of products that include novel body-worn antenna designs, conformal helmet mounted antenna designs, antennas for wireless RF telemetry systems, fabric systems for accommodating body-worn antennas, and fabrication methods to produce flexible, integrated body-worn antenna systems. The body-worn UHF antenna and wireless designs for wearable computer applications can be used in the new space suit designs, that are currently being considered, as well as potential EVA communication systems for Constellation Program and the Crew Exploration Vehicle (CEV), ISS, and Lunar Surface Access Modules. The final antenna designs, electromagnetic simulations, and test data obtained during this project can be used in a wide range of NASA research programs and applications. In addition to improving EVA communications capability, the potential for wireless antenna nodes for wearable computers is extensive.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
This multi-disciplinary research project will produce a wide range of products that include novel body-worn antenna designs, conformal helmet mounted antenna designs, antennas for wireless RF telemetry systems, fabric systems for accommodating body-worn antennas, and fabrication methods to produce flexible, integrated body-worn antenna systems. These products will have much potential in a wide range of non-NASA applications commercially as well as government. Commercial applications would include body-worn antennas for health monitoring, communications, remote sensing, information transfer systems as well as in uniform designs using conductive coatings. Government applications would primarily be for DoD (military) and the Department of Homeland Security (DHS) as body-worn antennas can be used for Warfighter, Special Operations Forces, special uniforms requiring communications in severe environments such as chemical and biological threat situations.

TECHNOLOGY TAXONOMY MAPPING
RF
Sensor Webs/Distributed Sensors
Suits
Multifunctional/Smart Materials

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Eltron Research, Inc.
4600 Nautilus Court South
Boulder, CO 80301-3241
(303) 530-0263

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Christopher Marotta
eltron@eltronresearch.com
4600 Nautilus Court South
Boulder,  CO 80301-3241
(303) 530-0263

Expected Technology Readiness Level (TRL) upon completion of contract: 5

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
In this NASA Phase II SBIR Project, we will continue the development of graphitic nanosheets (GNS) for electrochemical capacitor (EC) electrode materials. In the Phase I project, treatments of the electrode materials resulted in increases of relative capacitance (2x), relative energy (4x), and relative power (25%). These results surpassed those of commercially available ECs for relative power and will fulfill NASA's need for energy storage materials for communications and navigation. We will address the following in the Phase II program: (1) Increase performance through exfoliation, activation, and other surface treatments; (2) Use these materials as supports for the deposition of pseudocapacitive species to form a nanocomposite electrode; (3) Improve the test cell fabrication to decrease equivalent series resistance (ESR) and passive layer formation; (4) Purify electrode materials and electrolyte to decrease leakage current and self-discharge; (5) Perform environmental testing including temperature, pressure, and vibration; (6) Fabricate, test, and deliver functional prototype cells to NASA at the end of the Phase II project. This technology is currently at a TRL of 3-4 and we expect to achieve a TRL of 5 with delivery of prototype cells to NASA for testing.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
NASA is interested in electrochemical capacitors for transient power demands that are capable of rapid discharges, typically on the order of milliseconds. Such demands shorten battery and fuel cell lifetime. ECs will be used to complement an energy storage system (load leveling), dramatically lengthening battery/fuel cell lifetimes while reducing the required sizes of the batteries/fuel cells. Specifically ECs can be used in burst communications systems that require high power transients on the order of millisecond durations with a short number of total pulses to avoid detection. Other NASA applications would be flash LIDAR for Object Detection and Avoidance (ODA) systems (for avoiding rocks when landing) and autonomous rover guidance on a planet surface. Finally, NASA is looking to replace hydraulic systems with electromechanical actuators that require high transient power delivery. These requirements can be fulfilled by ECs which store charge that can be quickly discharged without burdening batteries or fuel cells.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Other applications include maintenance-free power sources for microcomputer memories, backup power for actuator and solenoid valves, and power supplements for consumer electronic devices. The biggest potential market of ECs will be the automotive sector for launch assist and regenerative braking in electric vehicles. ECs with improved performance (greater relative energy and power, improved charge/discharge capacities) are generating increased interest among producers of battery operated equipment. ECs can have a prominent impact on hybrid electric vehicles, where their implementation will accelerate the development of this technology. Successful development of this technology will improve the fuel efficiency of these HEVs significantly since the need for large batteries is reduced. The economic impacts will also promote a greater demand for carbon nanomaterials, and lead to more competition among manufacturers, providing quality products at a lower price. This technology can also be adapted for battery and fuel cell electrodes.

TECHNOLOGY TAXONOMY MAPPING
Electromagnetic Thrusters
Launch Assist (Electromagnetic, Hot Gas and Pneumatic)
Micro Thrusters
Telemetry, Tracking and Control
Electrostatic Thrusters
Attitude Determination and Control
Guidance, Navigation, and Control
Architectures and Networks
Autonomous Control and Monitoring
Laser
Manned-Manuvering Units
Portable Life Support
Suits
Composites
Multifunctional/Smart Materials
Energy Storage

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Surface Optics Corporation
11555 Rancho Bernardo Road
San Diego, CA 92127-1441
(858) 675-7404

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
David Sheikh
dsheikh@surfaceoptics.com
11555 Rancho Bernardo Road
San Diego,  CA 92127-1441
(858) 675-7404

Expected Technology Readiness Level (TRL) upon completion of contract: 4

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Surface Optics Corporation (SOC) will develop a band pass filter comprised of a visible dielectric mirror and an induced transmission filter, applied to two sides of a cast polyimide membrane. The mirror/filter combination will block 95% of the incident solar radiation, while allowing a narrow pass-band for laser communication. The combination of a visible dielectric mirror constructed on one side of a membrane and a band-pass filter on the second surface, offers a means of creating a very efficient solar reflector with relatively few coatings layers. The exceptionally thin and flat optical substrate will minimize degradation of the laser signal. 2-meter membrane filters are sought by NASA to prevent over-heating of ground-based laser communication receivers operating during daylight hours. In Phase II, the designs will be scaled to large membrane substrates approximately 2-m in diameter.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
This research will benefit future NASA programs requiring interplanetary laser communication.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
High quality membranes coated with precision optical coatings may be useful for large ground-based, segmented telescopes such as TMT and Hobby-Eberly. Although the concept is still in its infancy, a coating transferred to a glass segment via a polymer membrane would be analogous to tinting an automobile car window. Preliminary evaluations indicate a membrane with less than lambda/6 PTV error, may be useful for segmented mirror systems with active correction. A coating transfer process would eliminate the need for a segment assembly containing motors, controllers, and actuators, from being placed in a vacuum chamber for periodic recoating.

TECHNOLOGY TAXONOMY MAPPING
Thermal Insulating Materials
Laser
Composites
Optical & Photonic Materials

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
SVT Associates
7620 Executive Drive
Eden Prairie, MN 55344-3677
(952) 934-2100

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Bentao Cui
bcui@svta.com
7620 Executive Dr
Eden Prairie,  MN 55344-3677
(952) 934-2100

Expected Technology Readiness Level (TRL) upon completion of contract: 3 to 4

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
High quality GaN epitaxial films are one of the keys to current efforts for development of both high-power/high-speed electronic devices and optoelectronic devices. In fact, solid state lighting, high-temperature and high-power electronics, microelectronic and mechanical sensors, and high-efficiency solar cells are all poised at a new level of development. This enormous market is waiting for low-cost, high quality substrates to achieve performance and fabrication economies of scale. After achieving dislocation densities below 1E7 cm-2 in the phase I work, this NASA SBIR phase II project addresses the development of a dislocation filter that can routinely prepare low-stress GaN thin films with threading dislocation densities below 1E6 cm-2. The method relies on using a low-angle ion beam to induce both nanofilter for defect reductions and to inhibit droplet formation at low growth temperatures. Dislocation densities have so far been determined by standard etch pit densities method. The goal the project to optimize the multiple defect nanofilter with smoothening by transition layers in between filters to reduce the TD to less than 1E6 cm-2 and process, fabricate high performance HEMT for solid state high power amplifier (SSPA) applications. To obtain a more practical evaluation of the effectiveness and commercial viability of the method, heterojunction field effect transistors with high electron mobility will be fabricated in these ultra-low defect density films. These high-quality material based high electron mobility transistors (HEMTs) will enable high linearity power amplifiers with excellent thermal stability and frequency response. The proposed method to grow on low-stress, low-dislocation density films will lead to the production of electronic devices of unparalleled performance.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
High speed and high power amplifiers, radiation-hard and ultra-low noise amplifiers, HEMT devices for radar and range finding, collision avoidance, and digital transmission, UV photo detectors for free-space optical communications, astrophysics, and biological agent detection, flame detection, and missile launch monitoring.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
HEMT device for RF and microwave mobile wireless communications. Blue lasers, high brightness visible LEDs, UV detectors for chemical and biological agent spectroscopy and threat detection, ozone detection and environmental monitoring.

TECHNOLOGY TAXONOMY MAPPING
Guidance, Navigation, and Control
Laser
RF
Biochemical
Photonics
Radiation-Hard/Resistant Electronics
Semi-Conductors/Solid State Device Materials

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Scientific Systems Company, Inc.
500 West Cummings Park, Suite 3000
Woburn, MA 01801-6503
(781) 933-5355

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Rajesh Krishnan
rajesh.krishnan@ssci.com
500 West Cummings Park Suite 3000
Woburn,  MA 01801-6562
(781) 933-5355

Expected Technology Readiness Level (TRL) upon completion of contract: 5 to 6

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The Lunar EVA network will exhibit a wide range of connectivity levels due to the challenging communications environment and mission dynamics. Disruption-Tolerant Networking (DTN) enables communications in environments where intermittent end-to-end connectivity occurs due to nodes moving temporarily out of range by taking advantage of persistent storage and mobility. DTN forwarding is a mature technology, but requires an adaptable routing algorithm that covers opportunistic and scheduled modes of operation under stable or disrupted connectivity. SSCI, in collaboration with Boston University and BBN Technologies proposes novel adaptive hybrid routing protocols and efficient data set reconciliation algorithms that will significantly enhance the scalability and performance of state-of-the-art DTN approaches. SSCI further proposes to develop the SELENE DTN system prototype using COTS hardware and demonstrate data muling capability in a 20-node network. SELENE technologies will provide the Lunar EVA network with the reliability necessary to support Lunar missions in the extreme network conditions on the Lunar surface. Through Phase II, SSCI will identify and secure commitments from industry and government transition partners to transition SELENE to commercial applications.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The technologies developed in SELENE are applicable to NASA lunar exploration missions. Furthermore, these technologies can also be used in manned or unmanned missions to Mars or other planets to maintain reliable communications. Disruption Tolerant Networking technologies were, in fact, originally developed for the InterPlaNetary Internet Project (IPN).

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Potential customers for the technologies are the United States Marine Corps, to whom we are proposing to develop a system for reliable, disruption-tolerant logistics data collection for condition-based maintenance. Another potential customer is ONR, which is developing Dynamic Tactical Communications Networks (DTCN). Other potential customers include those interested in reliable sensor data collection under harsh environments, such as the oil industry, or those interested in remote surveillance activities.

TECHNOLOGY TAXONOMY MAPPING
Teleoperation
Architectures and Networks
RF
Sensor Webs/Distributed Sensors

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
International Electronic Machines Corporation (IEM)
60 Fourth Avenue
Albany, NY 12202-1924
(518) 449-5504

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Zack Mian
zmian@iem.net
60 Fourth Avenue
Albany,  NY 12202-1924
(518) 449-5504

Expected Technology Readiness Level (TRL) upon completion of contract: 6 to 7

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Current hydrogen flame detection systems exhibit shortcomings ranging from limited detection range, to localization inaccuracy, limited sensitivity, false alarms, and inability to self-diagnose failures. During Phase I. International Electronic Machines Corporation IEM created and tested a prototype version of an Intelligent FlameFinder Detection and Alert System (IFDAS), demonstrating that IEM's system could accurately detect, track, and localize hydrogen flames and reliably discriminate between hydrogen flames and over two dozen sources of false alarms including reflections of flames or the sun, welding, other flame sources, etc., using a unique, innovative, and expandable Flame Detection Expert System design. In Phase II, IEM proposes to develop a full working prototype system employing multiple IFDAS sensor units, an enhanced flame detection expert system, and a comprehensive user interface including means for notifying emergency personnel when a fire is detected. This IFDAS Prototype will be demonstrated under real-world conditions at Stennis Space Center.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Launch vehicles used by NASA rely heavily upon use of hydrogen as a fuel. As such several NASA centers (Stennis, Marshall, and Kennedy, for example) use large quantities of hydrogen in conjunction with engine testing and rocket launches. At each of these facilities, there are existing devices in place for hydrogen flame detection ranging from Fire Wire and Hydrogen Gas Detectors to UV detectors and even Long Wave IR imaging systems. In discussions with engineers at each of these facilities, IEM has learned that they are actively investigating alternative hydrogen Flame detection systems for the Constellation Program. IEM continues to work with these engineers to better understand the specific needs for each of these programs but believes that IFDAS can perform an important role in improved flame detection and localization while at the same time eliminating a long list of potential false alarm conditions.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The primary non-NASA markets identified for include a variety of first responders including EMTs, fire and police departments, and fire brigades for large chemical manufacturers and refineries. Using an intelligent device to actually monitor and area where hydrogen was in use to detect flames early and to assist in guiding the first responders safely to the site of the fire has been identified as an important commercial objective. IEM has identified a partial list of potential commercial applications, including, but not limited to: • Hydrogen production, storage, and transmission industry • Chemical manufacturers • Refineries • Fuel cell industry • Hydrogen refueling industry With the emergence of hydrogen as an alternative fuel, the Hydrogen Economy is now beginning to build momentum towards greater market penetration in areas from consumer vehicles to commercial trucks and buses to hydrogen fueled railroad locomotives.

TECHNOLOGY TAXONOMY MAPPING
Propellant Storage
Intelligence
Perception/Sensing
Operations Concepts and Requirements
Testing Facilities
Optical
Sensor Webs/Distributed Sensors

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Mobitrum Corporation
8070 Georgia Avenue, Suite 209
Silver Spring, MD 20910-4973
(703) 989-8096

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Ray Wang
ray_wang@mobitrum.com
8070 Georgia Avenue, Suite 207
Silver Spring,  MD 20910-1707
(301) 585-4040

Expected Technology Readiness Level (TRL) upon completion of contract: 5 to 6

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The term Integrated Systems Health Management (ISHM) is used to describe a capability that focuses on determining the condition (health) of every element in a complex system (detect anomalies, diagnose causes, prognosis of future anomalies), and provide data, information, and knowledge (DIaK) to control systems for safe and effective operation. Therefore, ISHM capability is achieved by integrating DIaK that can be distributed throughout the system elements. DIaK must be available to any element of a system at right time and within a proper context. The implementations of the ISHM in the past have primarily focused on data access, and have not emphasized the integration of intelligence across all elements that make up a system. In order to distribute DIaK effectively, the integrated system must have the distributed capabilities and they require effective network functions across the whole system. Mobitrum proposes to develop a Sensor Area Network (SAN) for ISHM to bring the distributed intelligences together across all elements within ISHM system. The proposed SAN can be mixed of wireless and wired architecture. In order to implement credible ISHM functions, SAN must provide ISHM with effective communication mechanisms using distributed and/or hierarchical architectures to deliver intelligence across all elements.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
"Sensor Area Network for Integrated Systems Health Management" is a state-of-the-art technology offering wide ranges of capabilities for network-based data sensing, condition monitoring, and acquisitions. This implementation offers great opportunities to NASA for distributed sensor applications. The device, when integrates with intelligence, is powerful for remote sensing and monitoring control across many heterogeneous networks. The technology has many NASA applications: Test Facilities and Test Article; Integrated System Health management (ISHM); Integrated Vehicle Health Management (IVHM) for Aviation Safety Program; Advanced Control Technology - Fundamental Aeronautics Test Program; Earth science applications; Field communications device for spatial data input, manipulation and distribution: Intelligent Rocket Test Facilities (IRTF) with smart sensor elements, measurement, and field verification applications; Sensing and monitoring for Aircraft - icing on wings - data from heaters and sensors and Aircraft emissions - collection of data around airports; Verification and validation of equipment (e.g., RFID); System Diagnosis and Prognosis.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Sensor area network (SAN) and health-enabled smart sensor technology combine has a huge application for current and future RFID industry. It is applicable for the following areas: (1) tele-medicine utilizing medical sensor-RFID to treat patient remotely to save health care cost; (2) lower cost transponders offering multi-read and receiving voice and text-based messaging; (3) network-based read/write electronic storage; (4) identification and communication smart badge for voice and test messaging; (5) road transport and traffic telematics; (6) transport information and control systems; (7) home automation and control; (8) energy management for cost saving; (9) security (intruder detection); (10) safety (sensing); (11) utility remote meter reading; (12) building automation systems real-time monitoring and control of security and surveillance systems, alarms, HVAC, etc., (13) Manufacturing and distribution industrial automation using RFID; (14) Health care wireless monitoring.

TECHNOLOGY TAXONOMY MAPPING
Launch Assist (Electromagnetic, Hot Gas and Pneumatic)
Human-Robotic Interfaces
Integrated Robotic Concepts and Systems
Intelligence
Mobility
Manipulation
Perception/Sensing
Teleoperation
Control Instrumentation
Launch and Flight Vehicle
Operations Concepts and Requirements
Simulation Modeling Environment
Training Concepts and Architectures
Testing Facilities
Testing Requirements and Architectures
Spaceport Infrastructure and Safety
Telemetry, Tracking and Control
Ultra-High Density/Low Power
Reuseable
Airport Infrastructure and Safety
Attitude Determination and Control
Guidance, Navigation, and Control
On-Board Computing and Data Management
Pilot Support Systems
Air Revitalization and Conditioning
Biomass Production and Storage
Biomedical and Life Support
Biomolecular Sensors
Sterilization/Pathogen and Microbial Control
Waste Processing and Reclamation
Architectures and Networks
Autonomous Control and Monitoring
RF
Fluid Storage and Handling
Instrumentation
Production
Autonomous Reasoning/Artificial Intelligence
Computer System Architectures
Data Acquisition and End-to-End-Management
Data Input/Output Devices
Database Development and Interfacing
Expert Systems
Human-Computer Interfaces
Portable Data Acquisition or Analysis Tools
Software Development Environments
Software Tools for Distributed Analysis and Simulation
Biochemical
Gravitational
Sensor Webs/Distributed Sensors
High-Energy
Portable Life Support
Suits
Tools
General Public Outreach
K-12 Outreach
Mission Training
Highly-Reconfigurable
Earth-Supplied Resource Utilization
In-situ Resource Utilization
Computational Materials
Radiation Shielding Materials
Multifunctional/Smart Materials
Biophysical Utilization
Power Management and Distribution
Wireless Distribution

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
S&K Aerospace
63066 Old Hwy 93
St Ignatius, MT 59865-9008
(406) 745-7500

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Mary Beth Hudson
mhuson@ska-corp.com
16441 Space Center Blvd #C-200
Houston,  TX 77058-2015
(281) 480-1453

Expected Technology Readiness Level (TRL) upon completion of contract: 4 to 5

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Electronic procedures are currently being used to document the steps in performing medical operations for the Space Shuttle and/or the International Space Station (ISS). Capturing the data electronically makes is easier to manage, modify and query the contents of the procedures. For the ISS, NASA is currently transitioning to electronic procedures based on the eXtensible Markup Language (XML) standard. Modeling procedures electronically using XML has a number of benefits. Procedures can be quickly and effectively searched to determine which procedures are affected by software and hardware changes. Procedures are more easily shared by other computer-based systems. And procedure execution aids become possible, such as real time data capture and automatic book marking of the current procedure step. Such procedure models will be an important component of an integrated Medical Decision Support needed for future exploration missions. The primary purpose of this project is to continue to research and develop a Procedure Representation Language (PRL) and support tools that will benefit the creation, maintenance, and use of the medical procedures, and to develop them in such a way that new advances can be easily inserted, eventually leading to the Medical Decision Support system.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
NASA has been using checklists and procedures to support space operations since its beginnings. Recently there has been an effort to move away from paper documents to electronic documents. The ISS program is now in the process of converting their medical procedures documented in Micrsoft Word to an XML-based representation. We expect this work to continue under the Constellation program. We believe that our work and research in modeling procedures in XML will be applicable to both the ISS and the Constellation programs.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Recent news stories on NPR discuss a new initiative for hospitals to use medical checklist procedures before, during, and after operations to improve safety. The World Health Organization (WHO) is encouraging surgeons world-wide to use them. Our work on medical checklists for ISS can be easily moved to other medical settings such as hospitals. Hospitals in the Houston area that may be interested in our work include UTMB and the Medical Center. In addition, first responders such as EMT, Firefighters, and Park Rangers could benefit by using electronic checklists/procedures. Other industries, such as aviation and the military have been using electronic checklists, to the extent that many pilots use PDAs rather than paper to perform their preflight procedures. Software in aviation checklists are introducing hyperlinks associated with the steps in the checklist. These hyperlinks let them link a step in the procedure to another document for additional information. Our work in modeling checklist procedures for ISS and their ability to reference other procedures and documents can benefit the growing needs in this area.

TECHNOLOGY TAXONOMY MAPPING
Autonomous Reasoning/Artificial Intelligence
Data Acquisition and End-to-End-Management
Human-Computer Interfaces

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
WEVOICE, Inc.
9 Sylvan Drive
Bridgewater, NJ 08807-2235
(908) 575-8955

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Sherry Ye
sherryqye@gmail.com
9 Sylvan Drive
Bridgewater,  NJ 08807-2235
(908) 575-8955

Expected Technology Readiness Level (TRL) upon completion of contract: 7 to 8

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
For in-helmet voice communication, the currently used Communication-Cap-based Audio (CCA) systems have a number of recognized logistical issues and inconveniences that cannot be resolved with incremental improvements to the basic design of the CCA systems. The objective of this research project is to develop an Integrated Spacesuit Audio (ISA) system that can possess similar performance to a CCA while offering users inherent comfort and ease of use. In Phase I, the feasibility of using microphone array beamforming or multichannel noise reduction plus a single-channel postfilter to combat a variety of types of in-helmet noise was validated. Comparative simulations indicated that novel multichannel noise reduction is more practical and more effective than traditional microphone array beamforming for ISA systems. Phase II will pursue advanced development and prototype of the proposed technical solution for the ISA system. Directions for improvement that were established in Phase I will be carefully followed, subjective evaluation will be carried out, and the ISA designs will be further optimized. Finally a real-time demo system will be built using either DSP or FPGA. It should be ready for testing and use by NASA at the end of Phase II.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
- In-Helmet voice communication for the design of new spacesuits - Telecollaboration via multimedia telepresence - Human-machine interface for intelligent systems

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
- Hands-free in-car voice communication and processing - Mobile phone - Military voice communication and speech processing systems - Telemedicine and telehealth - Multi-party teleconferencing - Acoustic surveillance

TECHNOLOGY TAXONOMY MAPPING
Data Input/Output Devices
Human-Computer Interfaces
Portable Data Acquisition or Analysis Tools

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Luna Innovations Incorporated
1 Riverside Circle, Suite 400
Roanoke, VA 24016-4909
(540) 552-5128

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Shi-Hau Own
submissions302@lunainnovations.com
3157 State Street
Blacksburg,  VA 24060-6604
(540) 552-5128

Expected Technology Readiness Level (TRL) upon completion of contract: 5 to 6

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The total annual corrosion related costs in the US has been estimated at greater than $300 billion. Much of these costs are associated with scraping and repainting of metals such as steel structures in the NASA launch platform and related support equipment. Because of the staggering costs stemming from corrosion of steel infrastructure, there is a tremendous need to develop intelligent coatings that can perform numerous functions above those historically demanded of coatings. Luna is addressing the need to enhance the service life of NASA vehicles and equipment through a multifunctional coating system. This research program will develop robust, inexpensive coatings that are i) ultrahydrophobic as a first line of defense to repel water absorption and ii) self healing to replenish coating integrity after damage to yield long term corrosion resistance. The technology developed on this program will decrease life cycle costs, reduce maintenance, and increase readiness by limiting equipment down-time.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The technology developed on this program is relevant to any painted metal structures within the NASA program including buildings, vehicles, launch platform, etc. This novel paint system will reduce corrosion related costs, and increase the lifetime of NASA vehicles and support equipment.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
This proposed research is part of an overall larger effort and fits well into the strategic focus of Luna. The ability to form self healing ultrahydrophobic coatings on selected surfaces will have a huge effect on military and commercial applications such as anti-corrosion, chemical and biological warfare defense, marine vessels, and automotive applications.

TECHNOLOGY TAXONOMY MAPPING
Metallics

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Emergent Space Technologies, Inc.
6301 Ivy Lane, Suite 720
Greenbelt, MD 20770-6330
(301) 345-1535

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Timothy Esposito
timothy.esposito@emergentspace.com
6301 Ivy Lane, Suite 720
Greenbelt,  MD 20770-6333
(301) 345-1535

Expected Technology Readiness Level (TRL) upon completion of contract: 7 to 8

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Emergent Space Technologies Inc. proposes to develop the Ground Enterprise Management System (GEMS) for spacecraft ground systems. GEMS will provide situational awareness for distributed ground systems, and an understanding of how events and automated actions impact the system in real-time. Recent software advancements have improved sustainability, extensibility, fault tolerance, and ease of automation for ground systems. These traits are important for NASA's missions, from Exploration to Earth and Space Science, but can pose challenges, especially when the system has a high degree of interoperability and communications between components that isn't visible to the end-user. Operators can quickly become overwhelmed with the increased complexity of software components constantly exchanging data and the volumes of information being passed around behind-the-scenes. In fact, for largely distributed systems, as much "situational awareness" is needed for the ground system as for the spacecraft itself. GEMS will provide a centralized integration framework that is needed to provide operators with transparency into the ground system, its state, and its component interactions. GEMS will enhance plug-and-play integrations while providing information management and system coordination. The innovation that enables GEMS is the development of "data-driven" algorithms and software adapters that gather data from the various components of the ground system to construct a data model that captures the system state, organizes the data, and displays it to the mission operators.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
GEMS can support any NASA project that requires a ground system, including earth-orbiting satellites, lunar, deep-space, and interplanetary missions, as the key ground system technologies for these different classes of missions are inherently the same. The concepts we propose allow GEMS to adapt to existing ground systems as well as integrate with ground systems in development. A high percentage of NASA projects, especially the middleware-based projects, can benefit from the increased awareness of the ground system state and automation. As such, under a Phase II proposal, Emergent will demonstrate GEMS to candidate missions for early adoption. Emergent has had recent involvement integrating modern IT technologies with the SSMO Multi-Mission Operations Center, GMSEC, and TRMM. Emergent employees have also worked with the Earth Observing System (EOS) missions in the past. Current and future missions that could be targeted include the lunar missions such as LRO and exploration missions like Orion. Some potential NASA ARC missions for a GEMS implementation include GeneSat, PharmSat, LCROSS, LADEE, SMEX, and potentially others.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The GEMS system can be applied to commercial and other Government space industries directly. Sample commercial applications could include the OrbImage satellites or the replenished ORBCOMM and Iridium satellites. DoD and NOAA are government agencies that operate many satellites as well. During Phase 2, Emergent will seek proposal calls and Broad Agency Announcements for opportunities to integrate GEMS into Non-NASA missions. Looking outside of the space domain, GEMS could be applied to domains which use a large number of distributed systems and are highly automated, such as manufacturing. Opportunities outside of the space industry would be pursued in a Phase 3 effort.

TECHNOLOGY TAXONOMY MAPPING
Telemetry, Tracking and Control
Autonomous Control and Monitoring
Computer System Architectures
Data Acquisition and End-to-End-Management
Database Development and Interfacing
Expert Systems
Software Tools for Distributed Analysis and Simulation

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Stottler Henke Associates, Inc.
951 Mariner's Island Blvd., Suite 360
San Mateo, CA 94404-1585
(650) 981-2700

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Carolyn Maxwell
maxwell@stottlerhenke.com
951 Mariner's Island Blvd., Suite 360
San Mateo,  CA 94404-2526
(650) 931-2700