SCAN_13-01

13-01 CELESTIAL MECHANICS AND ORBITAL CALCULATIONS
Feb 8, 2009 -- Additions to the NASA scientific and technical information knowledge base

No records are available for this topic on this date.

14-01 SPACECRAFT GROUND SUPPORT
Feb 8, 2009 -- Additions to the NASA scientific and technical information knowledge base

No records are available for this topic on this date.

14-02 TEST FACILITIES
Feb 8, 2009 -- Additions to the NASA scientific and technical information knowledge base

No records are available for this topic on this date.

14-03 SIMULATORS AND SIMULATION
Feb 8, 2009 -- Additions to the NASA scientific and technical information knowledge base

Title:
Evaluation of Recent Upgrades to the NESS (Nuclear Engine System Simulation) Code
Document ID:
20090004441
Report #:
E-16836
Sales Agency:
CASI Hardcopy A03 Copyright
Author(s):
Fittje, James E. (Analex Corp.) Schnitzler, Bruce G. (NASA Glenn Research Center)
Published:
20080721
Source:
NASA Glenn Research Center (Cleveland, OH, United States)
Pages:
18
Contract #:
NNC06BA07B
Abstract:
The Nuclear Thermal Rocket (NTR) concept is being evaluated as a potential propulsion technology for exploratory expeditions to the moon, Mars, and beyond. The need for exceptional propulsion system performance in these missions has been documented in numerous studies, and was the primary focus of a considerable effort undertaken during the Rover/NERVA program from 1955 to 1973. The NASA Glenn Research Center is leveraging this past NTR investment in their vehicle concepts and mission analysis studies with the aid of the Nuclear Engine System Simulation (NESS) code. This paper presents the additional capabilities and upgrades made to this code in order to perform higher fidelity NTR propulsion system analysis and design, and a comparison of its results to the Small Nuclear Rocket Engine (SNRE) design.
Language:
English
Notes:
44th AIAA Joint Propulsion Conference Hartford, CT 21-23 Jul. 2008

Title:
A Hybrid Communications Network Simulation-Independent Toolkit
Document ID:
20090004481
Report #:
AD-A486794, AFIT/GCS/ENG/08-08
Sales Agency:
Defense Technical Information Center (DTIC) No Copyright
Author(s):
Dines, David M
Published:
20080301
Source:
Air Force Inst. of Tech. (Wright-Patterson AFB, OH United States)
Pages:
66
Contract #:
None
Abstract:
Net-centric warfare requires information superiority to enable decision superiority, culminating in insurmountable combat power against our enemies on the battlefield. Information superiority must be attained and retained for success in today's joint/coalition battlespace. To accomplish this goal, our combat networks must reliably, expediently and completely deliver over a wide range of mobile and fixed assets. Furthermore, each asset must be given special consideration for the sensitivity, priority and volume of information required by the mission. Evolving a grand design of the enabling network will require a flexible evaluation platform to try and select the right combination of network strategies and protocols in the realms of topology control and routing. This research will result in a toolkit for ns2 that will enable rapid interfacing and evaluation of new networking algorithms and/or protocols. The toolkit will be the springboard for development of an optimal, multi-dimensional and flexible network for linking combat entities in the battlespace
Language:
English

Title:
Hydrodynamic Ram Simulator
Document ID:
20090004656
Report #:
AD-A490882, JASPO-V-07-06-001, AAC-TR-08-17
Sales Agency:
Defense Technical Information Center (DTIC) No Copyright
Author(s):
Hinrichsen, Ronald Stratton, Stephen Moussa, Albert Zhang, Gangming
Published:
20080930
Source:
Test Squadron (0780th) (Wright-Patterson AFB, OH United States)
Pages:
58
Contract #:
None
Abstract:
The objective of this work was to develop a low-cost method of evaluating hydrodynamic ram and blast effects on aircraft materials that is effective for both joint and flat plate testing and able to assess failure properties of both types of structures. The approach was to revise the design of the RamGun test device to avoid previously discovered shortfalls. This was to be done as follows: 1.)Larger test section to avoid boundary effects,2.) Elimination of internal reflections that confound data, 3.)Tuned pressure pulses that map to specific threats, 4.)Design supported by LSDYNA, 5.)Dem-val tests to verify final design. The effort was piggy-backed onto a Phase II SBIR. The focus of this report is the design support being performed by LSDYNA simulations in support of the SBIR tasks.
Language:
English

Title:
RAPID: Rapid Prototyping in Distributed Mission Operations (DMO) Environments
Document ID:
20090004659
Report #:
AD-A490913
Sales Agency:
Defense Technical Information Center (DTIC) No Copyright
Author(s):
McVearry, Ken Birman, Ken Freedman, Dan van Renesse, Robert Weatherspoon, Hakim
Published:
20081101
Source:
Odyssey Research Associates, Inc. (Ithaca, NY United States)
Pages:
41
Contract #:
FA8750-08-D-0065-0003
Abstract:
The goals of the RAPID study are to explore the limitations of current Distributed Mission Operations (DMO) systems, explore the emerging opportunities associated with Service Oriented Architecture (SOA), Global Information Grid (GIG) and Net-Centric Enterprise Services (NCES) technology trends, and to propose technical solutions and the trade-offs between them.
Language:
English

15-01 LAUNCH VEHICLES
Feb 8, 2009 -- Additions to the NASA scientific and technical information knowledge base

Title:
Overview of NASA's Integrated Design and Engineering Analysis (IDEA)Environment
Document ID:
20090004448
Report #:
None
Available Online:
http://hdl.handle.net/2060/20090004448
Sales Agency:
CASI Hardcopy A03 No Copyright
Author(s):
Robinson, Jeffrey S. (NASA Langley Research Center) Martin John G. (NASA Langley Research Center)
Published:
20081208
Source:
NASA Langley Research Center (Hampton, VA, United States)
Pages:
12
Contract #:
None
Abstract:
Historically, the design of subsonic and supersonic aircraft has been divided into separate technical disciplines (such as propulsion, aerodynamics and structures) each of which performs their design and analysis in relative isolation from others. This is possible in most cases either because the amount of interdisciplinary coupling is minimal or because the interactions can be treated as linear. The design of hypersonic airbreathing vehicles, like NASA s X-43, is quite the opposite. Such systems are dominated by strong non-linear interactions between disciplines. The design of these systems demands that a multi-disciplinary approach be taken. Furthermore, increased analytical fidelity at the conceptual design phase is highly desirable as many of the non-linearities are not captured by lower fidelity tools. Only when these systems are designed from a true multi-disciplinary perspective can the real performance benefits be achieved and complete vehicle systems be fielded. Toward this end, the Vehicle Analysis Branch at NASA Langley Research Center has been developing the Integrated Design & Engineering Analysis (IDEA) Environment. IDEA is a collaborative environment for parametrically modeling conceptual and preliminary launch vehicle configurations using the Adaptive Modeling Language (AML) as the underlying framework. The environment integrates geometry, configuration, propulsion, aerodynamics, aerothermodynamics, trajectory, closure and structural analysis into a generative, parametric, unified computational model where data is shared seamlessly between the different disciplines. Plans are also in place to incorporate life cycle analysis tools into the environment which will estimate vehicle operability, reliability and cost. IDEA is currently being funded by NASA s Hypersonics Project, a part of the Fundamental Aeronautics Program within the Aeronautics Research Mission Directorate. The environment is currently focused around a two-stage-to-orbit configuration with a turbine based combined cycle (TBCC) first stage and reusable rocket second stage. This paper provides an overview of the development of the IDEA environment, a description of the current status and detail of future plans.
Language:
English
Notes:
JANNAF 6th Modeling and Simulation Subcommittee Meeting Orlando, FL 8-12 Dec. 2008

Title:
Prerequisites for Space Drive Science
Document ID:
20090004689
Report #:
E-16869-1
Sales Agency:
Other Sources No Copyright
Author(s):
Millis, Marc G. (NASA Glenn Research Center)
Published:
20080101
Source:
NASA Glenn Research Center (Cleveland, OH, United States)
Pages:
48
Contract #:
None
Abstract:
TO CIRCUMVENT the propellant limits of rockets and the maneuvering limits of solar sails, a means to propel spacecraft using only the interactions between the spacecraft and its surrounding space is sought. A general term for such a device is space drive, which is adopted for convenience from science fiction. (This term first appeared in John Campbell's 1932, The Electronic Siege [1].) At present, the scientific foundations from which to engineer a space drive have not been discovered. In fact, the issues, unknowns, and opportunities to seek these discoveries have only recently begun to be articulated [2,3]. To set the stage for further progress, this chapter examines this topic at the level of the first step of the scientific method, specifically defining the problem. While this chapter focuses on clarifying the problem to guide future research, subsequent chapters deal separately with specific ongoing investigations. These include manipulating gravity, electromagnetic gravitational couplings, photon momentum in media, inertial modifications, quantum vacuum interactions, and others. It is important to stress that space drives might be physically impossible, and conversely, that the prerequisite discoveries have just not yet been made. To begin the discussion, the key physics issues, basic energy estimates, hypothetical propulsion concepts, and relevant topics in science are examined. In several instances, provocative conjectures are introduced to demonstrate how space drive goals are distinct from the more general scientific inquiries. The intent is to provide starting points that future researchers can use to specifically address the physics of space drives. Eventually, future research will determine if, and how, space drives are physically possible.
Language:
English
Notes:
Chapter 3 of the Book, "Frontiers in Propulsion Science" to be published as part of the AIAA "Progress in Astronautics and Aeronautics" series

15-02 SOUNDING ROCKETS
Feb 8, 2009 -- Additions to the NASA scientific and technical information knowledge base

No records are available for this topic on this date.

15-03 SPACE PROBES
Feb 8, 2009 -- Additions to the NASA scientific and technical information knowledge base

Title:
Solar Power System Design for the Solar Probe+ Mission
Document ID:
20090004577
Report #:
AIAA Paper-2008-5712, E-16841
Sales Agency:
CASI Hardcopy A02 Copyright
Author(s):
Landis, Geoffrey A. (NASA Glenn Research Center) Schmitz, Paul C. (NASA Glenn Research Center) Kinnison, James (Johns Hopkins Univ.) Fraeman, Martin (Johns Hopkins Univ.) Roufberg, Lew (Johns Hopkins Univ.) Vernon, Steve (Johns Hopkins Univ.) Wirzburger, Melissa (Johns Hopkins Univ.)
Published:
20080728
Source:
NASA Glenn Research Center (Cleveland, OH, United States)
Pages:
10
Contract #:
None
Abstract:
Solar Probe+ is an ambitious mission proposed to the solar corona, designed to make a perihelion approach of 9 solar radii from the surface of the sun. The high temperature, high solar flux environment makes this mission a significant challenge for power system design. This paper summarizes the power system conceptual design for the solar probe mission. Power supplies considered included nuclear, solar thermoelectric generation, solar dynamic generation using Stirling engines, and solar photovoltaic generation. The solar probe mission ranges from a starting distance from the sun of 1 AU, to a minimum distance of about 9.5 solar radii, or 0.044 AU, from the center of the sun. During the mission, the solar intensity ranges from one to about 510 times AM0. This requires power systems that can operate over nearly three orders of magnitude of incident intensity.
Language:
English
Notes:
6th International Energy Conversion Engineering Conference (IECEC) Cleveland, OH 28-30 Jul. 2008

15-04 SCIENTIFIC SATELLITES
Feb 8, 2009 -- Additions to the NASA scientific and technical information knowledge base

Title:
Land-use and Land-cover Change from 1974 to 2008 around Mobile Bay
Document ID:
20090004416
Report #:
SSTI-2220-0173
Sales Agency:
CASI Hardcopy A01 Copyright
Author(s):
Ellis, Jean (NASA Stennis Space Center) Spruce, Joseph (Science Systems and Applications, Inc.) Smoot, James (Science Systems and Applications, Inc.) Hilbert, Kent Swann, Roberta
Published:
20081028
Source:
NASA Stennis Space Center (Stennis Space Center, MS, United States)
Pages:
1
Contract #:
None
Abstract:
This project is a Gulf of Mexico Application Pilot in which NASA Stennis Space Center (SSC) is working within a regional collaboration network of the Gulf of Mexico Alliance. NASA researchers, with support from the NASA SSC Applied Science Program Steering Committee, employed multi-temporal Landsat data to assess land-use and land-cover (LULC) changes in the coastal counties of Mobile and Baldwin, AL, between 1974 and 2008. A multi-decadal time-series, coastal LULC product unique to NASA SSC was produced. The geographic extent and nature of change was quantified for the open water, barren, upland herbaceous, non-woody wetland, upland forest, woody wetland, and urban landscapes. The National Oceanic and Atmospheric Administration (NOAA) National Coastal Development Data Center (NCDDC) will assist with the transition of the final product to the operational end user, which primarily is the Mobile Bay National Estuary Program (MBNEP). We found substantial LULC change over the 34-year study period, much more than is evident when the change occurring in the last years. Between 1974 and 2008, the upland forest landscape lost almost 6% of the total acreage, while urban land cover increased by slightly more than 3%. With exception to open water, upland forest is the dominant landscape, accounting for about 25-30% of the total area.
Language:
English
Notes:
Mississippi-Alabama Bays and Bayous Symposium 2008 Biloxi, MS 28-29 Oct. 2008

Title:
High-velocity Interstellar Bullets in IRAS 05506+2414: A Very Young Protostar
Document ID:
20090004435
Report #:
None
Available Online:
http://hdl.handle.net/2014/41023
http://dx.doi.org/10.1086/587638
Sales Agency:
Other Sources Copyright
Author(s):
Sahai, Raghvendra (Jet Propulsion Lab., California Inst. of Tech.) Claussen, Mark (National Radio Astronomy Observatory) Sanchez Contreras, Carmen (Consejo Superior de Investigaciones Cientificas) Morris, Mark (California Univ.) Sarkar, Geetanjali (Indian Inst. of Tech.)
Journal:
The Astrophysical Journal, Volume: Volume 680 , Page: 484-494
Published:
20080610 Publisher: American Astronomical Society
Source:
Jet Propulsion Lab., California Inst. of Tech. (Pasadena, CA, United States)
Pages:
12
Contract #:
None
Abstract:
We have made a serendipitous discovery of an enigmatic outflow source, IRAS 05506+2414 (hereafter IRAS 05506), as part of a multiwavelength survey of pre-planetary nebulae (PPNs). The HST optical and near-infrared images show a bright compact central source with a jet-like extension, and a fan-like spray of high-velocity (with radial velocities up to 350 km/s) elongated knots which appear to emanate from it. These structures are possibly analogous to the near-IR bullets'' seen in the Orion Nebula. Interferometric observations at 2.6 mm show the presence of a continuum source and a high-velocity CO outflow, which is aligned with the optical jet structure. IRAS 05506 is most likely not a PPN. We find extended NH3 (1,1) emission toward IRAS 05506; these data, together with the combined presence of far-IR emission, H2O and OH masers, and CO and CS J=2-1 emission, strongly argue for a dense, dusty star-forming core associated with IRAS 05506. IRAS 05506 is probably an intermediate-mass or massive protostar, and the very short timescale (200 yr) of its outflows indicates that it is very young. If IRAS 05506 is a massive star, then the lack of radio continuum and the late G to early K spectral type we find from our optical spectra imply that in this object we are witnessing the earliest stages of its life, while its temperature is still too low to provide sufficient UV flux for ionization.
Language:
English

15-05 REENTRY VEHICLES
Feb 8, 2009 -- Additions to the NASA scientific and technical information knowledge base

Title:
Apollo Lesson Sampler: Apollo 13 Lessons Learned
Document ID:
20090004795
Report #:
None
Sales Agency:
CASI DVD C01 No Copyright
Author(s):
Interbartolo, Michael A. (NASA Johnson Space Center)
Published:
20080501
Source:
NASA Johnson Space Center (Houston, TX, United States)
Pages:
--
Contract #:
None
Abstract:
This CD-ROM contains a two-part case study of the Apollo 13 accident. The first lesson contains an overview of the electrical system hardware on the Apollo spacecraft, providing a context for the details of the oxygen tank explosion, and the failure chain reconstruction that led to the conditions present at the time of the accident. Given this background, the lesson then covers the tank explosion and immediate damage to the spacecraft, and the immediate response of Mission Control to what they saw. Part 2 of the lesson picks up shortly after the explosion of the oxygen tank on Apollo 13, and discusses how Mission Control gained insight to and understanding of the damage in the aftermath. Impacts to various spacecraft systems are presented, along with Mission Control's reactions and plans for in-flight recovery leading to a successful entry. Finally, post-flight vehicle changes are presented along with the lessons learned.
Language:
English
Notes:
Apollo 13 Blu Ray DVD and BD Live Server, December 2008

15-06 U.S.S.R. SPACECRAFT
Feb 8, 2009 -- Additions to the NASA scientific and technical information knowledge base

No records are available for this topic on this date.

16-01 SPACE TRANSPORTATION AND MANNED SPACECRAFT
Feb 8, 2009 -- Additions to the NASA scientific and technical information knowledge base

Title:
Hazard Detection Methods for Lunar Landing
Document ID:
20090004462
Report #:
None
Sales Agency:
Other Sources Copyright
Author(s):
Brady, Tye (Draper (Charles Stark) Lab., Inc.) Zimpfer, Doug (Draper (Charles Stark) Lab., Inc.) Robertson, Edward (NASA Johnson Space Center) Epp, Chirold (NASA Johnson Space Center) Paschall, Stephen (Draper (Charles Stark) Lab., Inc.)
Published:
20090101
Source:
NASA Johnson Space Center (Houston, TX, United States)
Pages:
7
Contract #:
None
Abstract:
The methods and experiences from the Apollo Program are fundamental building blocks for the development of lunar landing strategies for the Constellation Program. Each of the six lunar landing Apollo missions landed under near ideal lighting conditions. The astronauts visually performed terrain relative navigation while looking out of windows, and were greatly aided by external communication and well lit scenes. As the LM approached the landing site, the astronauts performed visual hazard detection and avoidance, also under near-ideal lighting conditions. The astronauts were looking out of the windows trying to the best of their ability to avoid rocks, slopes, and craters and find a safe landing location. NASA has expressed a desire for global lunar access for both crewed and robotic sortie lunar exploration missions (Cook, 2007) (Dale, 2006). Early NASA architecture studies have identified the lunar poles as desirable locations for early lunar missions. These polar missions have less than ideal lighting conditions and will significantly affect the way a crewed vehicle plans to land at such locales. Consequently, a variety of hazard identification methods should be considered for use by the crew to ensure a high degree of safety. This paper discusses such identification methods applicable to the poorly lit polar lunar environment, better ensuring global access for the soon to be designed Lunar Lander Vehicle (LLV).
Language:
English
Notes:
2009 IEEE Aerospace Conference Montana 7 - 14 Mar. 2009

Title:
Forecasting Proximal Femur and Wrist Fracture Caused by a Fall to the Side during Space Exploration Missions to the Moon and Mars
Document ID:
20090004579
Report #:
Paper ID 1494, E_16843
Sales Agency:
CASI Hardcopy A03 Copyright
Author(s):
Lewandowski, Beth E. (NASA Glenn Research Center) Myers, Jerry G. (NASA Glenn Research Center) Sulkowski, C. (Akron Univ.) Ruehl, K. (Rose-Hulman Inst. of Tech.) Licata, A. (Licata (A.))
Published:
20080929
Source:
NASA Glenn Research Center (Cleveland, OH, United States)
Pages:
13
Contract #:
None
Abstract:
The possibility of bone fracture in space is a concern due to the negative impact it could have on a mission. The Bone Fracture Risk Module (BFxRM) developed at the NASA Glenn Research Center is a statistical simulation that quantifies the probability of bone fracture at specific skeletal locations for particular activities or events during space exploration missions. This paper reports fracture probability predictions for the proximal femur and wrist resulting from a fall to the side during an extravehicular activity (EVA) on specific days of lunar and Martian exploration missions. The risk of fracture at the proximal femur on any given day of the mission is small and fairly constant, although it is slightly greater towards the end of the mission, due to a reduction in proximal femur bone mineral density (BMD). The risk of wrist fracture is greater than the risk of hip fracture and there is an increased risk on Mars since it has a higher gravitational environment than the moon. The BFxRM can be used to help manage the risk of bone fracture in space as an engineering tool that is used during mission operation and resource planning.
Language:
English
Notes:
59th International Astronautical Congress 2008 Glasgow, Scotland 29 Sep. - 3 Oct. 2008

Title:
Nutritional Biochemistry of Space Flight
Document ID:
20090004584
Report #:
None
Sales Agency:
Other Sources No Copyright
Author(s):
Smith, Scott M. (NASA Johnson Space Center) Zwart, Sara R. (NASA Johnson Space Center) Kloeris, Vickie L. (NASA Johnson Space Center) Heer, Martina A. (NASA Johnson Space Center)
Published:
20090101
Source:
NASA Johnson Space Center (Houston, TX, United States)
Pages:
208
Contract #:
None
Abstract:
The importance of nutrition in exploration has been documented repeatedly throughout history. For example, during the roughly 400 years between Columbus voyage and the invention of the steam engine, scurvy (vitamin C deficiency) resulted in the deaths of more sailors (> 2 million) than all other causes of death combined [1]. Since nutrients are required for the structure and function of every cell and every body system, defining the nutrient requirements for space flight and ensuring provision and intake of those nutrients are primary issues for crew health and mission success. Unique aspects of nutrition during space travel include its role in and how it is affected by physiological adaptation to weightlessness and psychological adaptation to extreme and remote environments, and the ability of nutrition and nutrients to serve as countermeasures to ameliorate the negative effects of space flight on the human body. Key areas of clinical concern for long-duration space flight include loss of body mass (and associated inadequate food intake), bone and muscle loss, increased radiation exposure, nutrient supply during extravehicular activity, and general depletion of body nutrient stores because of inadequate food supply, inadequate food intake, increased metabolism, and/or irreversible loss of nutrients. Other body systems (such as the cardiovascular and neurovestibular systems) are also affected by space flight and may affect nutrition of space travelers, or may be a target in developing nutritional means to mitigate the effects of space flight on those systems. This book is aimed at reviewing the existing knowledge of human nutrition for space flight, and pointing out gaps in this knowledge that need to be filled before we can have confidence that the risk of an inadequate food system or inadequate nutrition to support humans on expeditions to the Moon and Mars is as low as possible. Much of the existing knowledge is extrapolated from results of studies (known as ground-based analog studies) conducted in laboratories on Earth by exposing human subjects to one or more environmental conditions similar to those produced by space flight. As long ago as the 1940s [2], bed rest has frequently been used as a ground-based analog [3], albeit with a different goal than the health and safety of space travelers. The other main source of knowledge is available data from short-duration Space Shuttle flights, and longer Mir and International Space Station (ISS) flights. Historical data from the Apollo missions of 5 to almost 13 days and the Skylab 28-, 59-, and 84-day flights are also reviewed.
Language:
English
Notes:
To be published in Nutritional Biochemistry of Space Flight, Nova, Oct. 2009

Title:
Nanocomposites in Aerospace Applications
Document ID:
20090004681
Report #:
E-16855
Sales Agency:
Other Sources No Copyright
Author(s):
Meador, Michael A. (NASA Glenn Research Center)
Published:
20080101
Source:
NASA Glenn Research Center (Cleveland, OH, United States)
Pages:
68
Contract #:
None
Abstract:
Weight, durability, and functionality are critical concerns for any aerospace system. Reductions in aircraft weight can enable increased payload capacity, improved maneuverability and decreased fuel consumption and emissions. Decreases in spacecraft weight lead to reduced launch costs and enable increased payload capacity. At the present time, it costs between $10,000 and $20,000 per pound to launch an item on the Space Shuttle. Durability is an important criterion not only because it affects vehicle safety, but also because it can impact maintenance costs and schedule. Unexpected delays in the launch of the Space Shuttle can costs millions of dollars in operations costs. For long duration space missions, failure in a critical component can jeopardize the success of the mission. Performance and functionality are also key drivers for aerospace systems. Vehicle performance impacts fuel consumption and emissions as well as survivability for military aircraft. The use of multifunctional materials and components, that combine the ability to bear a mechanical load with other functions, such as lightning strike protection or damage sensing, is becoming increasingly desirable because it can lead to enhanced performance and also enable weight reductions. Adaptive materials (shape memory alloys and polymers, piezoelectric materials) are also receiving considerable attention because they can enable radical new designs for aircraft and spacecraft that incorporate morphing structures, such as aircraft wings that can bend or change their shape and aerodynamics thereby eliminating the need for ailerons. Use of adaptive structures can enable enhanced vehicle performance and fuel efficiency, and lead to reduced maintenance and improved durability. These materials could find use in advanced aircraft designs, such as the Silent Aircraft concept being developed by a team from Cambridge University and MIT.
Language:
English

17-01 SPACE COMMUNICATIONS
Feb 8, 2009 -- Additions to the NASA scientific and technical information knowledge base

Title:
Thin Film Ferroelectric Microwave Devices and their Potential for Space Applications
Document ID:
20090004545
Report #:
E-16487
Sales Agency:
Other Sources Copyright
Author(s):
Miranda, Felix A. (NASA Glenn Research Center) Romanofsky, Robert R. (NASA Glenn Research Center) Mueller, Carl H. (Qinetiq North America)
Published:
20090101
Source:
NASA Glenn Research Center (Cleveland, OH, United States)
Pages:
24
Contract #:
None
Abstract:
In this chapter we have presented a brief summary of some applications of ferroelectric thin films for practical microwave devices and their potential suitability for space applications. While the proofs-of-concept discussed above exhibited very good working properties, further optimizations are still necessary to effectively insert this technology into practice in devices such as the ferroelectric reflectarray antenna (FRA). Because of their excellent insulating properties, radiation inertness and low power consumption, thin-film ferroelectric technology will find many applications in space communication systems.
Language:
English
Notes:
Book entitled, "Ferroelectric Thin Films at Microwave Frequencies", published by Research Signpost

17-02 NAVIGATION SYSTEMS
Feb 8, 2009 -- Additions to the NASA scientific and technical information knowledge base

No records are available for this topic on this date.

17-03 GUIDANCE SYSTEMS
Feb 8, 2009 -- Additions to the NASA scientific and technical information knowledge base

No records are available for this topic on this date.

17-04 TRACKING
Feb 8, 2009 -- Additions to the NASA scientific and technical information knowledge base

Title:
Kinetic Temperature and Carbon Dioxide from Broadband Infrared Limb Emission Measurements Taken from the TIMED/SABER Instrument
Document ID:
20090004446
Report #:
None
Sales Agency:
CASI Hardcopy A03 Copyright
Author(s):
Mertens, Christopher J. (NASA Langley Research Center) Russell III, James M. (Hampton Univ.) Mlynczak, Martin G. (NASA Langley Research Center) She, Chiao-Yao (Colorado State Univ.) Schmidlin, Francis J. (NASA Wallops Flight Facility) Goldberg, Richard A. (NASA Goddard Space Flight Center) Lopez-Puertas, Manuel (Instituto de Astrofisica de Andalucia) Wintersteiner, Peter P. (Arcon Corp.) Picard, Richard H. (Air Force Research Lab.) Winick, Jeremy R. (Air Force Research Lab.) Xu, Xiaojing (Science Systems and Applications, Inc.)
Published:
20080101
Source:
NASA Langley Research Center (Hampton, VA, United States)
Pages:
35
Contract #:
None
Abstract:
The Sounding of the Atmosphere using Broadband Emission Radiometry (SABER) experiment is one of four instruments on NASA's Thermosphere-Ionosphere-Energetics and Dynamics (TIMED) satellite. SABER measures broadband infrared limb emission and derives vertical profiles of kinetic temperature (Tk) from the lower stratosphere to approximately 120 km, and vertical profiles of carbon dioxide (CO2) volume mixing ratio (vmr) from approximately 70 km to 120 km. In this paper we report on SABER Tk/CO2 data in the mesosphere and lower thermosphere (MLT) region from the version 1.06 dataset. The continuous SABER measurements provide an excellent dataset to understand the evolution and mechanisms responsible for the global two-level structure of the mesopause altitude. SABER MLT Tk comparisons with ground-based sodium lidar and rocket falling sphere Tk measurements are generally in good agreement. However, SABER CO2 data differs significantly from TIME-GCM model simulations. Indirect CO2 validation through SABER-lidar MLT Tk comparisons and SABER-radiation transfer comparisons of nighttime 4.3 micron limb emission suggest the SABER-derived CO2 data is a better representation of the true atmospheric MLT CO2 abundance compared to model simulations of CO2 vmr.
Language:
English
Notes:
Submitted to Advances in Space Research, to be published in volume 43, no. 1, pp. 15-27, January 2009.

Title:
Multi-Purpose Acoustic Target Tracking For Additive Situational Awareness
Document ID:
20090004559
Report #:
AD-A490767, ARL-TR-4654
Sales Agency:
Defense Technical Information Center (DTIC) No Copyright
Author(s):
Solomon, Latasha
Published:
20081101
Source:
Army Research Lab. (Adelphi, MD United States)
Pages:
20
Contract #:
None
Abstract:
The U.S. Army Research Laboratory (ARL) has successfully used acoustics to detect, localize, and track potential threats. This information has provided a wealth of information to the individual Soldier by supplying actionable situational awareness. Two particular scenarios where these algorithms would provide useful intelligence relate to collision avoidance and monitoring drug trafficking. This research analyzes the acoustic signals of several aerial platforms in an attempt to track each target of interest. Results of different signal-processing techniques conventional beamformer via minimum variance distortionless response (MVDR) and a Least-Squares (L-S) Estimator using time difference of arrivals (TDOA) are compared and contrasted. Application of a Kalman filter to the direction of arrival (DOA) estimates is explored. The results found that although neither algorithm performed flawlessly, the TDOA L-S method required less computation time and the MVDR algorithm produced more accurate tracking. The Kalman filter also improved results when used with both techniques.
Language:
English

Title:
CALIPSO Lidar Observations of the Optical Properties of Saharan Dust: A Case Study of Long Range Transport
Document ID:
20090004700
Report #:
LF99-5154
Sales Agency:
Other Sources Copyright
Author(s):
Liu, Zhaoyan (National Inst. of Aerospace) Omar, Ali (NASA Langley Research Center) Vaughan, Mark (Science Systems and Applications, Inc.) Hair, Jonathan (NASA Langley Research Center) Kittaka, Chieko (Science Systems and Applications, Inc.) Hu, Yongxiang (NASA Langley Research Center) Powell, Kathleen (Science Systems and Applications, Inc.) Trepte, Charles (NASA Langley Research Center) Winker, David (NASA Langley Research Center) Hostetler, Chris (NASA Langley Research Center) Ferrrare, Richard (NASA Langley Research Center) Pierce, Robert (NASA Langley Research Center)
Published:
20080101
Source:
NASA Langley Research Center (Hampton, VA, United States)
Pages:
43
Contract #:
None
Abstract:
An extensive dust storm originating on August 17, 2006 in the Sahara was observed and tracked by the CALIPSO lidar. Over the next several days, the dust layer was transported across the Atlantic Ocean and into the Gulf of Mexico. The initial stages of the event were examined using a sequence of CALIPSO measurements acquired on August 18, 19 and 20 near the source and ~1300 km and ~2400 km away over the Atlantic Ocean, respectively. The later stages of the event were assessed using the NASA HSRL measurement acquired over the Gulf of Mexico on August 28. Within the free troposphere, the intrinsic optical properties of the dust remain relatively unchanged for the first three days of transport over the Atlantic Ocean, though the optical depth decreases gradually. After the 10 day journey to the Gulf of Mexico, some changes are seen in the lidar ratios, the backscatter color ratio, and the optical depth ratio, indicating a possible shift in the particle size distribution. The dust depolarization ratio remains essentially constant (approx.0.32) at all four locations, demonstrating a notable consistency in the dust particle nonsphericity. The measured 532 nm lidar ratios are 41.3+/-3, 41.1+/-4, 41.4+/-6 and 45.6+/-0.5 sr, respectively, at locations near the source, over the Atlantic Ocean, and in the Gulf of Mexico. The corresponding 1064 nm lidar ratios are 51.8+/-5, 55.2+/-5, 53.7+/-13 and 44.0+/-8.3 sr. The backscatter color ratios are 0.74+/-0.07, 0.75+/-0.08, 0.72+/-0.04 and 0.62+/-0.01 and the optical depth ratios are 0.97+/-0.02, 1.01+/-0.05, 0.93 0.17 and 0.62+/-0.13, respectively.
Language:
English
Notes:
To be published in Journal of Geophysical Research, volume 113, Apr. 2008

18-01 SPACECRAFT ATTITUDE CONTROL AND STABILIZATION
Feb 8, 2009 -- Additions to the NASA scientific and technical information knowledge base

No records are available for this topic on this date.

18-02 RENDEZVOUS AND DOCKING
Feb 8, 2009 -- Additions to the NASA scientific and technical information knowledge base

No records are available for this topic on this date.

18-03 SPACE STATIONS
Feb 8, 2009 -- Additions to the NASA scientific and technical information knowledge base

No records are available for this topic on this date.

19-01 SPACECRAFT INSTRUMENTATION
Feb 8, 2009 -- Additions to the NASA scientific and technical information knowledge base

Title:
Validation of Aura Microwave Limb Sounder HCl Measurements
Document ID:
20090004434
Report #:
None
Available Online:
http://hdl.handle.net/2014/41019
http://dx.doi.org/10.1029/2007JD009025
Sales Agency:
Other Sources Copyright
Author(s):
Froidevaux, L. (Jet Propulsion Lab., California Inst. of Tech.) Jiang, Y. B. (Jet Propulsion Lab., California Inst. of Tech.) Lambert, A. (Jet Propulsion Lab., California Inst. of Tech.) Livesey, N. J. (Jet Propulsion Lab., California Inst. of Tech.) Read, W. G. (Jet Propulsion Lab., California Inst. of Tech.) Waters, J. W. (Jet Propulsion Lab., California Inst. of Tech.) Fuller, R. A. (Jet Propulsion Lab., California Inst. of Tech.) Marcy, T. P. (National Oceanic and Atmospheric Administration) Popp, P. J. (National Oceanic and Atmospheric Administration) Gao, R. S. (National Oceanic and Atmospheric Administration) Fahey, D. W. (National Oceanic and Atmospheric Administration) Jucks, K. W. (Harvard-Smithsonian Center for Astrophysics) Stachnik, R. A. (Jet Propulsion Lab., California Inst. of Tech.) Toon, G. C. (Jet Propulsion Lab., California Inst. of Tech.) Christensen, L. E. (Jet Propulsion Lab., California Inst. of Tech.) Webster, C. R. (Jet Propulsion Lab., California Inst. of Tech.) Bernath, P. F. (York Univ.) Boone, C. D. (Waterloo Univ.) Walker, K. A. (Toronto Univ.) Pumphrey, H. C. (Edinburgh Univ.) Harwood, R. S. (Edinburgh Univ.) Manney, G. L. (Jet Propulsion Lab., California Inst. of Tech.) Schwartz, M. J. (Jet Propulsion Lab., California Inst. of Tech.) Daffer, W. H. (Jet Propulsion Lab., California Inst. of Tech.) Drouin, B. J. (Jet Propulsion Lab., California Inst. of Tech.)
Journal:
Journal of Geophysical Research - Atmospheres, Volume: Volume 113
Published:
20080516 Publisher: American Geophysical Union
Source:
Jet Propulsion Lab., California Inst. of Tech. (Pasadena, CA, United States)
Pages:
23
Contract #:
None
Abstract:
The Earth Observing System (EOS) Microwave Limb Sounder (MLS) aboard the Aura satellite has provided daily global HCl profiles since August 2004. We provide a characterization of the resolution, random and systematic uncertainties, and known issues for the version 2.2 MLS HCl data. The MLS sampling allows for comparisons with many (~1500 to more than 3000) closely matched profiles from the Halogen Occultation Experiment (HALOE) and Atmospheric Chemistry Experiment Fourier Transform Spectrometer (ACE-FTS). These data sets provide HCl latitudinal distributions that are, overall, very similar to those from (coincident) MLS profiles, although there are some discrepancies in the upper stratosphere between the MLS and HALOE gradients. As found in previous work, MLS and ACE HCl profiles agree very well (within approximately 5%, on average), but the MLS HCl abundances are generally larger (by 10-20%) than HALOE HCl. The bias versus HALOE is unlikely to arise mostly from MLS, as a similar systematic bias (of order 15%) is not observed between average MLS and balloon-borne measurements of HCl, obtained over Fort Sumner, New Mexico, in 2004 and 2005. At the largest pressure (147 hPa) for MLS HCl, a high bias (approximately 0.2 ppbv) is apparent in analyses of low to midlatitude data versus in situ aircraft chemical ionization mass spectrometry (CIMS) HCl measurements from the Aura Validation Experiment (AVE) campaigns in 2004, 2005, and 2006; this bias is also observed in comparisons of MLS and aircraftHCl/O3 correlations. Good agreement between MLS and CIMS HCl is obtained at 100 to 68 hPa. The recommended pressure range for MLS HCl is from 100 to 0.15 hPa.
Language:
English

Title:
SDR/STRS Flight Experiment and the Role of SDR-Based Communication and Navigation Systems
Document ID:
20090004687
Report #:
E-16867
Available Online:
http://hdl.handle.net/2060/20090004687
Sales Agency:
CASI Hardcopy A03 No Copyright
Author(s):
Reinhart, Richard C. (NASA Glenn Research Center)
Published:
20080225
Source:
NASA Glenn Research Center (Cleveland, OH, United States)
Pages:
25
Contract #:
None
Abstract:
This presentation describes an open architecture SDR (software defined radio) infrastructure, suitable for space-based radios and operations, entitled Space Telecommunications Radio System (STRS). SDR technologies will endow space and planetary exploration systems with dramatically increased capability, reduced power consumption, and less mass than conventional systems, at costs reduced by vigorous competition, hardware commonality, dense integration, minimizing the impact of parts obsolescence, improved interoperability, and software re-use. To advance the SDR architecture technology and demonstrate its applicability in space, NASA is developing a space experiment of multiple SDRs each with various waveforms to communicate with NASA s TDRSS satellite and ground networks, and the GPS constellation. An experiments program will investigate S-band and Ka-band communications, navigation, and networking technologies and operations.
Language:
English
Notes:
IDGA 6th Annual Software Radio Summit Vienna, VA 25-28 Feb. 2008

19-02 SENSORS AND TRANSDUCERS
Feb 8, 2009 -- Additions to the NASA scientific and technical information knowledge base

Title:
Behavior-Based Power Management in Autonomous Mobile Robots
Document ID:
20090004473
Report #:
AD-A487084, AFIT/GCE/ENG/08-05
Sales Agency:
Defense Technical Information Center (DTIC) No Copyright
Author(s):
Fetzek, Charles A
Published:
20080327
Source:
Air Force Inst. of Tech. (Wright-Patterson AFB, OH United States)
Pages:
99
Contract #:
None
Abstract:
Current attempts to prolong a robot's battery life focus on outdated techniques that have high overhead and are not built in to the underlying robotic architecture. In this thesis, battery life is extended through development of a behavior-based power management system, including a Markov decision process (MDP) power planner. This system examines sensors needed by the currently active behavior set and powers down those not required. Predictive power planning models the domain as an MDP problem in the Deliberator. The planner creates a power policy that accounts for current and future power requirements in stochastic domains. This provides a power plan that uses lower-power consuming devices at the start of a goal sequence in order to save power for the areas where higher-power consuming sensors are needed. Power savings are observed in two case studies: Low and high sensor intensity environments. Testing reveals that in a real life scenario involving multiple goals and multiple sensors, the robot's battery charge can be extended up to 96% longer when using this system over robots that rely on traditional power management.
Language:
English

Title:
High Temperature Materials for Thin-Film Thermocouples on Silicon Wagers
Document ID:
20090004533
Report #:
PB2008-105962
Sales Agency:
CASI Hardcopy A03 No Copyright
Author(s):
Kreider, K. G. Gillen, G.
Published:
20080101
Source:
National Inst. of Standards and Technology (Gaithersburg, MD, United States)
Pages:
14
Contract #:
None
Abstract:
We are developing an instrumented calibration wafer for radiometric temperature measurements in rapid thermal processing (RTP) tools for semiconductor processing. The instrumented wafers has sputter deposited thin-film thermocouples to minimize the thermal disturbance of the wafer by the sensors. The NIST calibration wafer also employs platinum-palladium wire thermocouples to achieve a combined standard uncertainty of 0.4 deg C in temperature measurement of the thin-film thermocouple junction at 900 deg C. The high temperatures of the wafer has required the development of new thin-film material systems. We report the results of our testing and characterization of sputtered platinum, palladium, rhodium, and iridium thin films using titanium bond coats on thermally oxidized silicon wafers. Depth profiling with secondary ion mass spectrometry was used to determine the diffusion profiles from the metal film to the silicon after heat treatments as high as 1000 degrees C. Electron microscopy and optical microscopy were used to follow reactions and the deterioration of the thermoelectric films. In addition, performance tests up to 1000 degrees C in the NIST RTP test bed were used to determine the stability of the material systems.
Language:
English

Title:
Efefcts of Extraneous Radiation on the Peerformance of Lightpipe Radiation Thermometers
Document ID:
20090004535
Report #:
PB2008-105960
Sales Agency:
CASI Hardcopy A02 No Copyright
Author(s):
Meyer, C. W.
Published:
20080101
Source:
National Inst. of Standards and Technology (Gaithersburg, MD United States)
Pages:
6
Contract #:
None
Abstract:
Experiments were performed to study the influence of irradiation and heating of lightpipe radiation thermometers (LPRTs). LPRTs are currently the sensor of choice for temperature measurement in rapid thermal processing. Eight sheathed sapphire lightpipes from two separate manufacturers were used. The experiments demonstrated that the temperature of a lightpipe and the radiation surroundings can significantly affect the temperature displayed by an LPRT. The influence on the display temperature is much higher when the environment of the lightpipe is at a higher temperature than that of the surface being observed. Measurement uncertainty due to environmental influence can be minimized by calibrating the LPRT in an environment similar to that in which it will be used. The experiments showed that some lightpipes are less affected by their environment than others, suggesting that careful selection of lightpipes can also minimize the measurement uncertainty.
Language:
English

Title:
Initial Steps Toward Next-Generation, Waveform-Based, Three-Dimensional Models and Metrics to Improve Nuclear Explosion Monitoring in the Middle East
Document ID:
20090004663
Report #:
AD-A487588
Available Online:
http://hdl.handle.net/100.2/ADA487588
Sales Agency:
Defense Technical Information Center (DTIC) No Copyright
Author(s):
Savage, Brian Rodgers, Arthur J Tromp, Jeroen Covellone, Brian
Published:
20080930
Source:
Rhode Island Univ. (Kingston, RI United States) Lawrence Livermore National Lab. (Livermore, CA, United States) Princeton Univ. (NJ, United States)
Pages:
8
Contract #:
FA8718-08-C-0009
Abstract:
In an effort toward improving current seismic-velocity models for the Middle East, the initial Step of building a high-quality database of recordings from well characterized sources is essential. This high-quality database of recordings, or broadband waveforms, encompassing the region from the Mediterranean to the eastern edge of Tibet, will be the primary measure for evaluation and improvement in the iterative, waveform-based, adjoint-inversion process. Adjoint inversions, as with any waveform-based method, require precise estimates of the location, especially depth, and the faulting parameters or moment-tensor elements of the seismic sources. Imprecise locations and/or source terms will result in real changes in the amplitude and the phase of the incoming wave train; when close to a nodal plane, these changes can occur very rapidly with incoming azimuth. These errors will directly map into the resulting velocity model as uncertainty or biased values. The initial database included about 250 well recorded, regional events in the Middle East from 1990 to 2007 with magnitudes Mw> 5.5. To reduce errors in the source-depth and faulting parameters, the events were evaluated using two complementary sets of data, a regional data set contained within the Middle East and a global teleseismic data set. Regional data were first utilized at long period, omega > 20s, using the waveform-based methods of Pasyanos et al. (1996) to determine the moment tensor elements. Then shorter periods, omega > 5 s, were added, following Zhao and Helmberger (1994), to further assess errors in source depth and propagation effects by splitting apart the longer period surface waves from the shorter period, depth-sensitive Pnl waves. Problematic, or high-error, stations and paths were higher analyzed to identify systematic errors with unknown sensor responses and complex wave propagation regions.
Language:
English
Notes:
Presented at the Conference on Ground-Based Nuclear Explosion Monitoring Technologies (30th), held in Portsmouth, VA, on 23-25 Sep 2008. Published in the proceedings of the conference in Monitoring Research Review, v1 p261-267, 2008. The original document contains color images. All DTIC reproductions will be in black and white

Title:
Novel Anthracene Diimide Fluorescent Sensor
Document ID:
20090004680
Report #:
E-16854
Available Online:
http://dx.doi.org/10.1021/cm8024704
Sales Agency:
Other Sources Copyright
Author(s):
Tyson, Daniel S. (Ohio Aerospace Inst.) Carbaugh, Ashley D. (NASA Glenn Research Center) Ilhan, Faysal (Ohio Aerospace Inst.) Santos-Perez, Javier (Ohio Aerospace Inst.) Meador, Michael A. (NASA Glenn Research Center)
Journal:
Chemistry of Materials, Volume: Volume 29 , Page: 6595-6596
Published:
20080101
Source:
NASA Glenn Research Center (Cleveland, OH, United States)
Pages:
3
Contract #:
None
Abstract:
Aromatic imides and diimides have attracted considerable attention in molecular electronics, as fluorescent probes in biological systems, and as sensors for the detection of chemical species. With a few exceptions, these reports have been confined to perylene and naphthalene imides and diimides, in part because of the ready availability of the corresponding anhydride and dianhydride starting materials. We have reported the synthesis of an aniline capped anthryl diimide, 1a and its ability to function as an "on-off" sensor for pH, acid halides, and chemical surrogates for Sarin. In the "off state", fluorescence from 1a is completely quenched by intramolecular excited state charge transfer (CT) from the terminal amines. Reaction of these groups inhibits CT quenching and activates the fluorescence. This approach to chemical species detection is highly sensitive, because it is easy to recognize the "on" and "off" states of the dye. Synthesis of 1a involves the generation of o-xylylenols by photolysis of 2,5-dibenzoyl-p-xylene, 2, and their trapping in situ with 4-nitrophenylmaleimide. Although this approach is fairly straightforward, it is limited in scope because only maleimides, which are photochemically stable, can be used. To address this, we have recently prepared the corresponding anthracene dianhydride, 4, and used it to synthesize triaryl amine-terminated diimide 1b. Herein, we present the synthesis and photophysics of 1 and its potential use as a fluorescent sensor for pH and nitroaromatics and as an indicator in thermochromic materials.
Language:
English

Title:
Precipitation Model Validation in 3rd Generation Aeroturbine Disc Alloys
Document ID:
20090004682
Report #:
E-16858
Sales Agency:
CASI Hardcopy A02 Copyright
Author(s):
Olson, G. B. (QuesTek Innovations, LLC) Jou, H.-J. (QuesTek Innovations, LLC) Jung, J. (QuesTek Innovations, LLC) Sebastian, J. T. (QuesTek Innovations, LLC) Misra, A. (QuesTek Innovations, LLC) Locci, I. (NASA Glenn Research Center) Hull, D. (NASA Glenn Research Center)
Published:
20080914
Source:
NASA Glenn Research Center (Cleveland, OH, United States)
Pages:
10
Contract #:
NNC07CB01C
Abstract:
In support of application of the DARPA-AIM methodology to the accelerated hybrid thermal process optimization of 3rd generation aeroturbine disc alloys with quantified uncertainty, equilibrium and diffusion couple experiments have identified available fundamental thermodynamic and mobility databases of sufficient accuracy. Using coherent interfacial energies quantified by Single-Sensor DTA nucleation undercooling measurements, PrecipiCalc(TM) simulations of nonisothermal precipitation in both supersolvus and subsolvus treated samples show good agreement with measured gamma particle sizes and compositions. Observed longterm isothermal coarsening behavior defines requirements for further refinement of elastic misfit energy and treatment of the parallel evolution of incoherent precipitation at grain boundaries.
Language:
English
Notes:
11th International Superalloys 2008 Champion, PAu1 14-18 Sep. 2008

Title:
Model Attitude and Deformation Measurements at the NASA Glenn Research Center
Document ID:
20090004893
Report #:
E-16877
Available Online:
http://hdl.handle.net/2060/20090004893
Sales Agency:
CASI Hardcopy A03 No Copyright
Author(s):
Woike, Mark R. (NASA Glenn Research Center)
Published:
20080107
Source:
NASA Glenn Research Center (Cleveland, OH, United States)
Pages:
24
Contract #:
None
Abstract:
The NASA Glenn Research Center is currently participating in an American Institute of Aeronautics and Astronautics (AIAA) sponsored Model Attitude and Deformation Working Group. This working group is chartered to develop a best practices document dealing with the measurement of two primary areas of wind tunnel measurements, 1) model attitude including alpha, beta and roll angle, and 2) model deformation. Model attitude is a principle variable in making aerodynamic and force measurements in a wind tunnel. Model deformation affects measured forces, moments and other measured aerodynamic parameters. The working group comprises of membership from industry, academia, and the Department of Defense (DoD). Each member of the working group gave a presentation on the methods and techniques that they are using to make model attitude and deformation measurements. This presentation covers the NASA Glenn Research Center s approach in making model attitude and deformation measurements.
Language:
English
Notes:
46th AIAA Model Attitude and Deformation Working Group Meeting Reno, NV 7-10 Jan. 2008

Title:
Commercial Sensor Survey Fiscal Year 2008 Compendium Radiation Test Report
Document ID:
20090004895
Report #:
JPL Publication 08-26
Available Online:
http://dx.doi.org/2014/41025
Sales Agency:
CASI Hardcopy A03 Copyright
Author(s):
Becker, Heidi N. (Jet Propulsion Lab., California Inst. of Tech.) Dolphin, Michael D. (Jet Propulsion Lab., California Inst. of Tech.) Thorbourn, Dennis O. (Jet Propulsion Lab., California Inst. of Tech.) Alexander, James W. (Jet Propulsion Lab., California Inst. of Tech.) Salomon, Phil M. (Jet Propulsion Lab., California Inst. of Tech.)
Published:
20081001
Source:
Jet Propulsion Lab., California Inst. of Tech. (Pasadena, CA, United States)
Pages:
43
Contract #:
NAS7-03001
Abstract:
The NASA Electronic Parts and Packaging (NEPP) Program Sensor Technology Commercial Sensor Survey task is geared toward benefiting future NASA space missions with low-cost, short-duty-cycle, visible-wavelength imaging needs. Such applications could include imaging for educational outreach purposes or short surveys of spacecraft, planetary, or lunar surfaces. Under the task, inexpensive commercial grade CMOS sensors were surveyed in fiscal year 2007 (FY07) and three sensors were selected for total ionizing dose (TID) and displacement damage dose (DDD) tolerance testing. The selected sensors had to meet selection criteria chosen to support small, low-mass cameras that produce good resolution color images. These criteria were discussed in detail in [1], and are provided again in Appendix 1 of this document. This compendium provides results for all radiation testing performed in FY08 on the Micron and OmniVision sensors that were selected in FY07 for radiation tolerance testing
Language:
English

Title:
Cross reactive arrays of three-way junction sensors for steroid determination
Document ID:
20090004984
Report #:
None
Available Online:
http://hdl.handle.net/2060/20090004984
Sales Agency:
CASI Hardcopy A08 No Copyright
Author(s):
Stojanovic, Milan N. Landry, Donald Nikic, Dragan B.
Published:
20081230
Source:
Columbia Univ. (New York, NY United States)
Pages:
166
Contract #:
NAS2-02039
Abstract:
This invention provides analyte sensitive oligonucleotide compositions for detecting and analyzing analytes in solution, including complex solutions using cross reactive arrays of analyte sensitive oligonucleotide compositions.
Language:
English
Notes:
This application is a continuation-in-part of U.S. Ser. No. 10/824,158, filed Apr. 14, 2004 now abandoned, which claims the benefit of U.S. Provisional Application No. 60/462,206, filed Apr. 14, 2003; and a continuation of PCT International Application No. PCT/US2004/011696, filed Apr. 15, 2004, the contents of all of which are hereby incorporated by reference

20-01 ROCKET ENGINES, NOZZLES AND THRUST CHAMBERS
Feb 8, 2009 -- Additions to the NASA scientific and technical information knowledge base

Title:
NASA Ares I Crew Launch Vehicle Upper Stage Overview
Document ID:
20090004512
Report #:
MSFC-1038
Available Online:
http://hdl.handle.net/2060/20090004512
Sales Agency:
CASI Hardcopy A02 No Copyright
Author(s):
Davusm Daniel J. (NASA Marshall Space Flight Center) McArthur, J. Craig (NASA Marshall Space Flight Center)
Published:
20080720
Source:
NASA Marshall Space Flight Center (Huntsville, AL, United States)
Pages:
9
Contract #:
None
Abstract:
By incorporating rigorous engineering practices, innovative manufacturing processes and test techniques, a unique multi-center government/contractor partnership, and a clean-sheet design developed around the primary requirements for the International Space Station (ISS) and Lunar missions, the Upper Stage Element of NASA's Crew Launch Vehicle (CLV), the "Ares I," is a vital part of the Constellation Program's transportation system.
Language:
English
Notes:
44th AIAA/ASME/SAE/ASEE Joint Propulsion Conference Hartford,CT 20-23 Jul. 2008

Title:
Flow Control Opportunities for Propulsion Systems
Document ID:
20090004546
Report #:
E-16831
Available Online:
http://hdl.handle.net/2060/20090004546
Sales Agency:
CASI Hardcopy A01 No Copyright
Author(s):
Cutley, Dennis E. (NASA Glenn Research Center)
Published:
20080623
Source:
NASA Glenn Research Center (Cleveland, OH, United States)
Pages:
1
Contract #:
None
Abstract:
The advancement of technology in gas turbine engines used for aerospace propulsion has been focused on achieving significant performance improvements. At the system level, these improvements are expressed in metrics such as engine thrust-to-weight ratio and system and component efficiencies. The overall goals are directed at reducing engine weight, fuel burn, emissions, and noise. At a component level, these goals translate into aggressive designs of each engine component well beyond the state of the art.
Language:
English

Title:
Lessons in Systems Engineering: The SSME Weight Growth History
Document ID:
20090004620
Report #:
None
Available Online:
http://hdl.handle.net/2060/20090004620
Sales Agency:
CASI Hardcopy A03 No Copyright
Author(s):
Ryan, Richard (NASA Marshall Space Flight Center)
Published:
20080821
Source:
NASA Marshall Space Flight Center (Huntsville, AL, United States)
Pages:
11
Contract #:
None
Abstract:
This viewgraph presentation describes the Space Shuttle Main Engine (SSME) weight growth history and lessons learned from SSME weight imbalances.
Language:
English
Notes:
NASA APPL JSC Center forum on Systems Engineering Houston, TX 21 Aug. 2008

Title:
NASA's Evolutionary Xenon Thruster: The NEXT Ion Propulsion System for Solar System Exploration
Document ID:
20090004684
Report #:
E-16860
Available Online:
http://hdl.handle.net/2060/20090004684
Sales Agency:
CASI Hardcopy A03 No Copyright
Author(s):
Pencil, Eric J. (NASA Glenn Research Center) Benson, Scott W. (NASA Glenn Research Center)
Published:
20080601
Source:
NASA Glenn Research Center (Cleveland, OH, United States)
Pages:
42
Contract #:
None
Abstract:
This viewgraph presentation reviews NASA s Evolutionary Xenon Thruster (NEXT) Ion Propulsion system. The NEXT project is developing a solar electric ion propulsion system. The NEXT project is advancing the capability of ion propulsion to meet NASA robotic science mission needs. The NEXT system is planned to significantly improve performance over the state of the art electric propulsion systems, such as NASA Solar Electric Propulsion Technology Application Readiness (NSTAR). The status of NEXT development is reviewed, including information on the NEXT Thruster, the power processing unit, the propellant management system (PMS), the digital control interface unit, and the gimbal. Block diagrams NEXT system are presented. Also a review of the lessons learned from the Dawn and NSTAR systems is provided. In summary the NEXT project activities through 2007 have brought next-generation ion propulsion technology to a sufficient maturity level.
Language:
English
Notes:
Briefing prepared for New Frontiers AO

Title:
Liquid Methane/Liquid Oxygen Propellant Conditioning Feed System (PCFS) Test Rigs
Document ID:
20090004695
Report #:
E-16872
Sales Agency:
CASI Hardcopy A03 Copyright
Author(s):
Skaff, A. (Sierra Lobo, Inc.) Grasl, S. (Sierra Lobo, Inc.) Nguyen, C. (Sierra Lobo, Inc.) Hockenberry S. (Sierra Lobo, Inc.) Schubert, J. (NASA Glenn Research Center) Arrington, L. (NASA Glenn Research Center) Vasek, T. (NASA Glenn Research Center)
Published:
20081208
Source:
NASA Glenn Research Center (Cleveland, OH, United States)
Pages:
17
Contract #:
NNCO5CA95C
Abstract:
As part of their Propulsion and Cryogenic Advanced Development (PCAD) program, NASA has embarked upon an effort to develop chemical rocket engines which utilize non-toxic, cryogenic propellants such as liquid oxygen (LO2) and liquid methane (LCH4). This effort includes the development and testing of a 100 lbf Reaction Control Engine (RCE) that will be used to evaluate the performance of a LO2/LCH4 rocket engine over a broad range of propellant temperatures and pressures. This testing will take place at NASA-Glenn Research Center's (GRC) Research Combustion Laboratory (RCL) test facility in Cleveland, OH, and is currently scheduled to begin in late 2008. While the initial tests will be performed at sea level, follow-on testing will be performed at NASA-GRC's Altitude Combustion Stand (ACS) for altitude testing. In support of these tests, Sierra Lobo, Inc. (SLI) has designed, developed, and fabricated two separate portable propellant feed systems under the Propellant Conditioning and Feed System (PCFS) task: one system for LCH4, and one for LO2. These systems will be capable of supplying propellants over a large range of conditions from highly densified to several hundred pounds per square inch (psi) saturated. This paper presents the details of the PCFS design and explores the full capability of these propellant feed systems.
Language:
English
Notes:
Chemical Propulsion Information Agency - JANNAF 6th Modeling and Simulation JANNAF 4th Liquid Propulsion JANNAF 3rd Spacecraft Propulsion Joint Subcommittee Meeting Orland, FL Orland, FL Orland, FL 8-12 Dec. 2008 8-12 Dec. 2008 8-12 Dec. 2008

Title:
Magnetostrictive valve assembly
Document ID:
20090004982
Report #:
None
Available Online:
http://hdl.handle.net/2060/20090004982
Sales Agency:
CASI Hardcopy A01 No Copyright
Author(s):
Richard, James A.
Published:
20081230
Source:
NASA (Washington, DC United States)
Pages:
5
Contract #:
None
Abstract:
A magnetostrictive valve assembly includes a housing that defines a passage with a seat being formed therein. A magnetically-biased and axially-compressed magnetostrictive assembly slidingly fitted in the passage is configured as a hollow and open-ended conduit adapted to support a flow of a fluid therethrough. Current-carrying coil(s) disposed about the passage in the region of the magnetostrictive assembly generate a magnetic field in the passage when current flows through the coil(s). A hollow valve body with side ports is coupled on one end thereof to an axial end of the magnetostrictive assembly. The other end of the valve body is designed to seal with the seat formed in the housing's passage when brought into contact therewith.
Language:
English

20-02 AUXILIARY PROPULSION
Feb 8, 2009 -- Additions to the NASA scientific and technical information knowledge base

No records are available for this topic on this date.

20-03 ELECTRIC PROPULSION
Feb 8, 2009 -- Additions to the NASA scientific and technical information knowledge base

Title:
Progress in NASA Rotorcraft Propulsion
Document ID:
20090004439
Report #:
E-16832
Available Online:
http://hdl.handle.net/2060/20090004439
Sales Agency:
CASI Hardcopy A03 No Copyright
Author(s):
DellaCorte, Christopher (NASA Glenn Research Center) Johnson, Susan M. (NASA Glenn Research Center)
Published:
20081010
Source:
NASA Glenn Research Center (Cleveland, OH, United States)
Pages:
20
Contract #:
None
Abstract:
This presentation reviews recent progress made under NASA s Subsonic Rotary Wing (SRW) propulsion research activities. Advances in engines, drive systems and optimized propulsion systems are discussed. Progress in wide operability compressors, modeling of variable geometry turbine performance, foil gas bearings and multi-speed transmissions are presented.
Language:
English
Notes:
Fundamental Aeronautics Meeting 2008 Atlanta, GA 7-9 Oct. 2008

Title:
NASA's Evolutionary Xenon Thruster (NEXT) Ion Propulsion System Information Summary
Document ID:
20090004685
Report #:
E-16861
Available Online:
http://hdl.handle.net/2060/20090004685
Sales Agency:
CASI Hardcopy A03 No Copyright
Author(s):
Pencil, Eirc S. (NASA Glenn Research Center) Benson, Scott W. (NASA Glenn Research Center)
Published:
20080801
Source:
NASA Glenn Research Center (Cleveland, OH, United States)
Pages:
23
Contract #:
None
Abstract:
This document is a guide to New Frontiers mission proposal teams. The document describes the development and status of the NASA's Evolutionary Xenon Thruster (NEXT) ion propulsion system (IPS) technology, its application to planetary missions, and the process anticipated to transition NEXT to the first flight mission.
Language:
English