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	+ Home		Additions to the NASA Aeronautics and Space Database as of 12/21/2009 20090041614 NASA Johnson Space Center, Houston, TX, United States Operational Psychology Perspective Holland, Al; November 20, 2009; In English; Decadal Survey in Life and Physical Sciences Space, 20 Nov. 2009, Irvine, CA, United States; Original contains color illustrations Report No.(s): JSC-CN-19308; No Copyright; Avail.: CASI: A04, Hardcopy Avail Online: http://hdl.handle.net/2060/20090041614 This slide presentation reviews the history of long duration spaceflight, and the changes in the International Space Station crew and the effect that this has had on the psychology of astronaut selection and training. CASI LONG DURATION SPACE FLIGHT; SPACE PSYCHOLOGY; INTERNATIONAL SPACE STATION 20090041616 NASA Johnson Space Center, Houston, TX, United States Sizing of "Mother Ship and Catcher" Missions for LEO Small Debris and for GEO Large Object Capture Bacon, John B.; Dec. 8, 2009; In English; International Conference on Orbital Debris Removal, 8-10 Dec. 2009, Chantilly, VA, United States; Original contains color and black and white illustrations Contract(s)/Grant(s): 581570.02.02.02.07 Report No.(s): JSC-CN-19380; No Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090041616 Most LEO debris lies in a limited number of inclination "bands" associated with specific useful orbits. Objects in such narrow inclination bands have all possible Right Ascensions of Ascending Node (RAANs), creating a different orbit plane for nearly every piece of debris. However, a low-orbiting satellite will always phase in RAAN faster than debris objects in higher orbits at the same inclination, potentially solving the problem. Such a low-orbiting base can serve as a "mother ship" that can tend and then send small, disposable common individual catcher/deboost devices--one for each debris object--as the facility drifts into the same RAAN as each higher object. The dV necessary to catch highly-eccentric orbit debris in the center of the band alternatively allows the capture of less-eccentric debris in a wider inclination range around the center. It is demonstrated that most LEO hazardous debris can be removed from orbit in three years, using a single LEO launch of one mother ship--with its onboard magazine of freeflying low-tech catchers--into each of ten identified bands, with second or potentially third launches into only the three highest-inclination bands. The nearly 1000 objects near the geostationary orbit present special challenges in mass, maneuverability, and ultimate disposal options, leading to a dramatically different architecture and technology suite than the LEO solution. It is shown that the entire population of near-GEO derelict objects can be gathered and tethered together within a 3 year period for future scrap-yard operations using achievable technologies and only two earth launches. Author LOW EARTH ORBITS; SPACE DEBRIS; ORBITAL MANEUVERS; TETHERING; GEOSYNCHRONOUS ORBITS 20090041618 NASA Glenn Research Center, Cleveland, OH, United States Pre-Flight Characterization of Samples for the MISSE-7 Spacesuit Fabric Exposure Experiment Gaier, James R.; McCue, Terry R.; Clark, Gregory W.; Rogers, Kerry J.; Mengesu, Tsega; October 2009; In English; Original contains color and black and white illustrations Contract(s)/Grant(s): WBS 936374.04.08.03 Report No.(s): NASA/TM-2009-215810; E-17073; Copyright; Avail.: CASI: A05, Hardcopy Avail Online: http://hdl.handle.net/2060/20090041618 A series of six sample spacesuit pressure garment assembly (PGA) fabric samples were prepared for the Materials International Space Station Experiment 7 (MISSE-7) flight experiment to test the effects of damage by lunar dust on the susceptibility of the fabrics to radiation damage. These included pristine Apollo-era fluorinated ethylene-propylene (FEP) fabric, Apollo-era FEP fabric that had been abraded with JSC-1A lunar simulant, and a piece of Alan Bean s Apollo 12 PGA sectioned from near the left knee. Also included was a sample of pristine orthofabric, and orthofabric that had been abraded to two different levels with JSC-1A. The samples were characterized using optical microscopy, field emission scanning electron microscopy, and atomic force microscopy. Two sets of six samples were then loaded in space environment exposure hardware, one of which was stored as control samples. The other set was affixed to the MISSE-7 experiment package, and will be mounted on the International Space Station, and exposed to the wake-side low Earth orbit environment. It will be retrieved after an exposure of approximately 12 months, and returned for post flight analysis. Author LUNAR DUST; GARMENTS; SPACE SUITS; FABRICS; AEROSPACE ENVIRONMENTS; POSTFLIGHT ANALYSIS; RADIATION DAMAGE; SCANNING ELECTRON MICROSCOPY 20090041627 NASA Johnson Space Center, Houston, TX, United States Arctic and Antarctic Analogs for Planetary Surface Traverses Hoffman, Stephen J.; Cameron, A. O.; [2009]; In English; Earth and Space 2010 Conference, 14-17 Mar. 2010, Honolulu, HI, United States; Original contains color and black and white illustrations Contract(s)/Grant(s): NNC09QA39D Report No.(s): JSC-CN-19402; Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090041627 The proposed paper summarizes the workshop presentations and discusses several of the key findings or lessons including: (1) A recognition that NASA s current approach for long duration planetary surface operations has fundamental differences from any of the operational approaches described by the invited speakers. These approaches drive the crew size and skill mix to accomplish basic objectives and, in turn, drive the logistical pyramid needed to support these operations. NASA will review the operational approaches of the organizations represented to understand the differentiating factors. NASA will then decide if it should alter its current approach to surface exploration. (2) There are potential parallels between key characteristics of the systems used for exploration in these environments, such as heated volume as an analog for pressurized volume or energy usage for various activities. NASA will look at these characteristics to identify which could help with preliminary planning and gather raw data from the presenters to model these characteristics. (3) New technologies are being applied and design approaches are being tailored to take advantage of these technologies on both side. Interactions between these two communities has begun or is expanding to understand how these new technologies are being leveraged: NASA habitation designers are exchanging ideas and approaches with the Antarctic station designers; Antarctic support Author PLANETARY SURFACES; ARCTIC REGIONS; ANTARCTIC REGIONS; CREW SIZE 20090041704 NASA Johnson Space Center, Houston, TX, United States Spacecraft Internal Acoustic Environment Modeling Chu, SShao-sheng R.; Allen, Christopher S.; [2009]; In English; HRP Investigators' Workshop, 3-5 Feb. 2010, Houston, TX, United States; Original contains color illustrations Report No.(s): JSC-CN-19411; Copyright; Avail.: CASI: A01, Hardcopy Avail Online: http://hdl.handle.net/2060/20090041704 Acoustic modeling can be used to identify key noise sources, determine/analyze sub-allocated requirements, keep track of the accumulation of minor noise sources, and to predict vehicle noise levels at various stages in vehicle development, first with estimates of noise sources, later with experimental data. In FY09, the physical mockup developed in FY08, with interior geometric shape similar to Orion CM (Crew Module) IML (Interior Mode Line), was used to validate SEA (Statistical Energy Analysis) acoustic model development with realistic ventilation fan sources. The sound power levels of these sources were unknown a priori, as opposed to previous studies that RSS (Reference Sound Source) with known sound power level was used. The modeling results were evaluated based on comparisons to measurements of sound pressure levels over a wide frequency range, including the frequency range where SEA gives good results. Sound intensity measurement was performed over a rectangular-shaped grid system enclosing the ventilation fan source. Sound intensities were measured at the top, front, back, right, and left surfaces of the and system. Sound intensity at the bottom surface was not measured, but sound blocking material was placed tinder the bottom surface to reflect most of the incident sound energy back to the remaining measured surfaces. Integrating measured sound intensities over measured surfaces renders estimated sound power of the source. The reverberation time T6o of the mockup interior had been modified to match reverberation levels of ISS US Lab interior for speech frequency bands, i.e., 0.5k, 1k, 2k, 4 kHz, by attaching appropriately sized Thinsulate sound absorption material to the interior wall of the mockup. Sound absorption of Thinsulate was modeled in three methods: Sabine equation with measured mockup interior reverberation time T60, layup model based on past impedance tube testing, and layup model plus air absorption correction. The evaluation/validation was carried out by acquiring octave band microphone data simultaneously at ten fixed locations throughout the mockup. SPLs (Sound Pressure Levels) predicted by our SEA model match well with measurements for our CM mockup, with a more complicated shape. Additionally in FY09, background NC noise (Noise Criterion) simulation and MRT (Modified Rhyme Test) were developed and performed in the mockup to determine the maximum noise level in CM habitable volume for fair crew voice communications. Numerous demonstrations of simulated noise environment in the mockup and associated SIL (Speech Interference Level) via MRT were performed for various communities, including members from NASA and Orion prime-/sub-contractors. Also, a new HSIR (Human-Systems Integration Requirement) for limiting pre- and post-landing SIL was proposed. Author SPACECRAFT ENVIRONMENTS; ACOUSTICS; BACKGROUND NOISE; FREQUENCY RANGES; NOISE INTENSITY; SYSTEMS INTEGRATION; VOICE COMMUNICATION; SOUND PRESSURE; SPACECRAFT MODULES; STATISTICAL ANALYSIS Additions to the NASA Aeronautics and Space Database as of 12/22/2009 20090041726 NASA Glenn Research Center, Cleveland, OH, United States 2008 NASA Seal/Secondary Air System Workshop Steinetz, Bruce M., Editor; Hendricks, Robert C., Editor; Delgado, Irebert R., Editor; November 2009; In English; 2008 NASA Seal/Secondary Air System Workshop, 18 Nov. 2008, Cleveland, OH, United States; Original contains color illustrations Contract(s)/Grant(s): WBS 092837.04.01.04.04.03 Report No.(s): NASA/CP-2009-215677; E-17043; Copyright; Avail.: CASI: A13, Hardcopy: C01, CD-ROM Avail Online: http://hdl.handle.net/2060/20090041726 The 2008 NASA Seal/Secondary Air System Workshop covered the following topics: (i) Overview of NASA s new Orion project aimed at developing a new spacecraft that will fare astronauts to the International Space Station, the Moon, Mars, and beyond; (ii) Overview of NASA s fundamental aeronautics technology project; (iii) Overview of NASA Glenn s seal project aimed at developing advanced seals for NASA s turbomachinery, space, and reentry vehicle needs; (iv) Reviews of NASA prime contractor, vendor, and university advanced sealing concepts, test results, experimental facilities, and numerical predictions; and (v) Reviews of material development programs relevant to advanced seals development. Turbine engine studies have shown that reducing seal leakage as well as high-pressure turbine (HPT) blade tip clearances will reduce fuel burn, lower emissions, retain exhaust gas temperature margin, and increase range. Turbine seal development topics covered include a method for fast-acting HPT blade tip clearance control, noncontacting low-leakage seals, intershaft seals, and a review of engine seal performance requirements for current and future Army engine platforms. Author SEALING; AERONAUTICAL ENGINEERING; EXHAUST GASES; TURBINE ENGINES; TURBOMACHINERY; NUMERICAL ANALYSIS; GAS TEMPERATURE; HIGH PRESSURE; THERMAL BARRIERS (PLASMA CONTROL) 20090041727 NASA Glenn Research Center, Cleveland, OH, United States Overview of CEV Thermal Protection System Seal Development DeMange, Jeff; Taylor, Shawn; Dunlap, Patrick; Steinetz, Bruce; Delgado, Irebert; Finkbeiner, Josh; Mayer, John; 2008 NASA Seal/Secondary Air System Workshop; November 2009; pp. 253-26; In English; Original contains color illustrations Copyright; Avail.: CASI: A03, Hardcopy; Available from CASI on CD-ROM only as part of the entire parent document Avail Online: http://hdl.handle.net/2060/20090041727 NASA GRC supporting design, development, and implementation of numerous seal systems for the Orion CEV: a) HS-to-BS interface. b) Compression pad. HS-to-BS Interface Seal System: a) design has evolved as a result of changes with the CEV TPS. b) Seal system is currently under development/evaluation. Coupon level tests, Arc jet tests, and Validation test development. Compression Pad: a) Finalizing design options. b) Evaluating material candidates. Author DESIGN ANALYSIS; SYSTEMS ENGINEERING; THERMAL PROTECTION; SEALS (STOPPERS) 20090041728 Parker-Hannifin Corp., North Haven, CT, United States Ultra-High Temperature Metallic Seal/Energizer Development for Aero Propulsion and Gas Turbine Applications Cornett, Ken; Newman, Jesse; Datta, Amit; 2008 NASA Seal/Secondary Air System Workshop; November 2009; pp. 271-28; In English; Original contains color illustrations Copyright; Avail.: CASI: A03, Hardcopy; Available from CASI on CD-ROM only as part of the entire parent document Avail Online: http://hdl.handle.net/2060/20090041728 The industry is requiring seals to operate at higher and higher temperatures. Traditional static seal designs and materials experience stress relaxation, losing their ability to maintain contact with moving flanges. Ultra High Temperature seal development program is a multiphase program with incremental increases in seal operating temperatures. Author SEALS (STOPPERS); HIGH TEMPERATURE; OPERATING TEMPERATURE; FLANGES; AIRCRAFT ENGINES; GAS TURBINE ENGINES 20090041729 NASA, Washington, DC, United States Fundamental Aeronautics Program Misra, Ajay; 2008 NASA Seal/Secondary Air System Workshop; November 2009; pp. 25-5; In English; Original contains color illustrations Copyright; Avail.: CASI: A03, Hardcopy; Available from CASI on CD-ROM only as part of the entire parent document Avail Online: http://hdl.handle.net/2060/20090041729 The Overarching Mission of NASA's Aeronautics Research Mission Directorate (ARMD) is: To advance U.S. technological leadership in aeronautics in partnership with industry, academia, and other government agencies that conduct aeronautics-related research. ARMD supports the Agency's goal of developing a balanced overall program of science, exploration, and aeronautics, and ARMD's research plans also directly support the National Aeronautics R&D Policy and accompanying Executive Order 131419. Author AERONAUTICS; RESEARCH AND DEVELOPMENT; LEADERSHIP; RESEARCH MANAGEMENT 20090041730 Rolls-Royce Corp., Indianapolis, IN, United States Foil Face Seal Testing Munson, John; 2008 NASA Seal/Secondary Air System Workshop; November 2009; pp. 131-13; In English; Original contains color illustrations Copyright; Avail.: CASI: A02, Hardcopy; Available from CASI on CD-ROM only as part of the entire parent document Avail Online: http://hdl.handle.net/2060/20090041730 In the seal literature you can find many attempts by various researchers to adapt film riding seals to the gas turbine engine. None have been successful, potential distortion of the sealing faces is the primary reason. There is a film riding device that does accommodate distortion and is in service in aircraft applications, namely the foil bearing. More specifically a foil thrust bearing. These are not intended to be seals, and they do not accommodate large axial movement between shaft & static structure. By combining the 2 a unique type of face seal has been created. It functions like a normal face seal. The foil thrust bearing replaces the normal primary sealing surface. The compliance of the foil bearing allows the foils to track distortion of the mating seal ring. The foil seal has several perceived advantages over existing hydrodynamic designs, enumerated in the chart. Materials and design methodology needed for this application already exist. Also the load capacity requirements for the foil bearing are low since it only needs to support itself and overcome friction forces at the antirotation keys. Author FOIL BEARINGS; SEALING; SEALS (STOPPERS); THRUST BEARINGS; LOADS (FORCES); FRICTION; SHAFTS (MACHINE ELEMENTS) 20090041731 NASA Glenn Research Center, Cleveland, OH, United States Overview of NASA Glenn Seal Project Steinetz, Bruce M.; Dunlap, Patrick H., Jr.; Proctor, Margaret; Delgado, Irebert; Finkbeiner,Joshua; deGroh, Henry; Ritzert, Frank; Daniels, Christopher; DeMange, Jeff; Taylor, Shawn; Wasowski, Janice; Smith, Ian; Penney, Nicholas; Garafolo, Nicholas; 2008 NASA Seal/Secondary Air System Workshop; November 2009; pp. 57-9; In English; Original contains color and black and white illustrations Copyright; Avail.: CASI: A03, Hardcopy; Available from CASI on CD-ROM only as part of the entire parent document Avail Online: http://hdl.handle.net/2060/20090041731 NASA Glenn is currently performing seal research supporting both advanced turbine engine development and advanced space vehicle/propulsion system development. Studies have shown that decreasing parasitic leakage by applying advanced seals will increase turbine engine performance and decrease operating costs. Studies have also shown that higher temperature, long life seals are critical in meeting next generation space vehicle and propulsion system goals in the areas of performance, reusability, safety, and cost. Advanced docking system seals need to be very robust resisting space environmental effects while exhibiting very low leakage and low compression and adhesion forces. NASA Glenn is developing seal technology and providing technical consultation for the Agencys key aero- and space technology development programs. Author SEALS (STOPPERS); AEROSPACE ENGINEERING; TURBINE ENGINES; SYSTEMS ENGINEERING; SEALING; LEAKAGE; AEROSPACE ENVIRONMENTS; ENGINE DESIGN 20090041732 GE Global Research Center, Niskayuna, NY, United States An Overview of Non-Metallic Brush Seal Technology Ruggiero, Eric J.; 2008 NASA Seal/Secondary Air System Workshop; November 2009; pp. 193-20; In English; Original contains color and black and white illustrations Copyright; Avail.: CASI: A03, Hardcopy; Available from CASI on CD-ROM only as part of the entire parent document Avail Online: http://hdl.handle.net/2060/20090041732 Non-metallic brush seals are ultra-low flow sealing elements ideal for low pressure differentials (<30 psid) and low temperature (typically <300 degF) applications. The compliant bristle pack of a non-metallic brush seal is advantageous in terms of sealing capability during transients. However, if not designed properly, the bristle pack compliance can be detrimental to the performance of the seal. GE GLobal Research has investigated the stiffness and heat generation properties of non-metallic brush seals made from Kevlar and Carbon Fiber. The presentation will review the progress made on the design points of the seals, as well as highlight some current commercial applications of the technology. Author SEALING; BRUSH SEALS; ELASTIC PROPERTIES; CARBON FIBERS; HEAT GENERATION; KEVLAR (TRADEMARK) 20090041733 NASA Glenn Research Center, Cleveland, OH, United States Preliminary Test Results of a Non-Contacting Finger Seal on a Herringbone-Grooved Rotor Proctor, Margaret P.; Delgado, Irebert R.; 2008 NASA Seal/Secondary Air System Workshop; November 2009; pp. 139-15; In English; Original contains color and black and white illustrations Copyright; Avail.: CASI: A03, Hardcopy; Available from CASI on CD-ROM only as part of the entire parent document Avail Online: http://hdl.handle.net/2060/20090041733 The baseline non-contacting finger seal is a NASA patented design. The primary difference between it and Gul Aroras design patented by AlliedSignal is that there are no lift pads on the high pressure fingers. The baseline non-contacting finger seal is comprised of a back plate, aft spacer, aft (or low pressure) finger element, forward (or high pressure) finger element, forward spacer, and front plate. The components are held together with 20 flat head screws. A typical seal would have a back plate of approximately the same thickness as the front plate and would be riveted together. The thicker back plate allows use of threaded fasteners so that different finger elements can be tested without having to replace all the individual seal components. The finger elements are essentially washers made of thin sheet stock with multiple curved slots machined around the inner diameter to form the fingers. They are clocked so that the fingers of one cover the slots of the other. The aft finger element fingers have axial extensions or "lift pads" at the seal id that are concentric to the rotor. The fingers act as cantilever beams and flex in response to rotor dynamic motion and radial growth of the rotor due to centrifugal or thermal forces. Author SEALS (STOPPERS); CANTILEVER BEAMS; ROTOR DYNAMICS; ROTORS; CENTRIFUGAL FORCE; FASTENERS 20090041734 NASA Glenn Research Center, Cleveland, OH, United States NASA's Constellation Program Baumeister, Joseph; 2008 NASA Seal/Secondary Air System Workshop; November 2009; pp. 1-2; In English; Original contains color illustrations Copyright; Avail.: CASI: A03, Hardcopy; Available from CASI on CD-ROM only as part of the entire parent document Avail Online: http://hdl.handle.net/2060/20090041734 NASA has established 6 Themes for Exploration: 1) USE THE MOON: Reduce risks and cost and increase productivity of future missions by testing technologies, systems, and operations in a planetary environment other than the Earth. 2) PURSUE SCIENTIFIC: Engage in scientific investigations of the Moon (solar system processes), on the Moon (use the unique environment), and from the Moon (to study other celestial phenomena). 3) EXTEND PERMANENT HUMAN PRESENCE: Develop the capabilities and infrastructure required to expand the number of people, the duration, the self-sufficiency, and the degree of non-governmental activity. 4) EXPAND EARTH S ECONOMIC SPHERE: Create new markets based on lunar activity that will return economic, technological, and quality-of-life benefits. 5) ENHANCE GLOBAL SECURTIY: Provide a challenging, shared, and peaceful global vision that unites nations in pursuit of common objectives. 6) ENGAGE, INSPIRE: Excite the public about space, encourage students to pursue careers in high technology fields, ensure that individuals enter the workforce with the scientific and technical knowledge necessary to sustain exploration. Author CONSTELLATION PROGRAM; PLANETARY ENVIRONMENTS; SOLAR SYSTEM; MARKET RESEARCH; MOON 20090041735 NASA Glenn Research Center, Cleveland, OH, United States Synthetic and Biomass Alternate Fueling in Aviation Hendricks, Robert C.; Bushnell, Dennis M.; 2008 NASA Seal/Secondary Air System Workshop; November 2009; pp. 91-13; In English; Original contains color illustrations Copyright; Avail.: CASI: A03, Hardcopy; Available from CASI on CD-ROM only as part of the entire parent document Avail Online: http://hdl.handle.net/2060/20090041735 Must use earth's most abundant natural resources - Biomass, Solar, Arid land (43%), Seawater (97%) with nutrients (80%) plus brackish waters and nutrients resolve environmental triangle of conflicts energy-food-freshwater and ultrafine particulate hazards. Requires Paradigm Shift - Develop and Use Solar* for energy; Biomass for aviation and hybrid-electric-compressed air mobility fueling with transition to hydrogen long term. Author BIOMASS; WATER RESOURCES; EARTH RESOURCES; REFUELING; COMPRESSED AIR; HAZARDS; HYDROGEN 20090041736 Timken Co., Canton, OH, United States Low-Torque Seal Development Lattime, Scott B.; Borowski, Richard; 2008 NASA Seal/Secondary Air System Workshop; November 2009; pp. 159-19; In English; Original contains color and black and white illustrations Copyright; Avail.: CASI: A03, Hardcopy; Available from CASI on CD-ROM only as part of the entire parent document Avail Online: http://hdl.handle.net/2060/20090041736 The EcoTurn Class K production prototypes have passed all AAR qualification tests and received conditional approval. The accelerated life test on the second set of seals is in progress. Due to the performance of the first set, no problems are expected.The seal has demonstrated superior performance over the HDL seal in the test lab with virtually zero torque and excellent contamination exclusion and grease retention. Author ACCELERATED LIFE TESTS; SEALS (STOPPERS); PERFORMANCE TESTS; TORQUE; EXCLUSION 20090041737 Parker-Hannifin Corp., San Diego, CA, United States Design and Analysis of Molded Elastomer Seals Yetter, Paul; Zhang, Kai; 2008 NASA Seal/Secondary Air System Workshop; November 2009; pp. 233-25; In English; Original contains color illustrations Copyright; Avail.: CASI: A03, Hardcopy; Available from CASI on CD-ROM only as part of the entire parent document Avail Online: http://hdl.handle.net/2060/20090041737 Modeling Materials: a) Hyperelastic model used for room temperature and higher, but has limitations at predicting response at different compressive rates and at low temperatures. b) Viscoelastic model is rarely used, and needs more research and application. Test and Characterization of Materials: a) Better material characterization using biaxial tension vs simple compression testing modes is debatable. b) Testing at high and low temperature is challenging. Author LOW TEMPERATURE; HIGH TEMPERATURE; ELASTOMERS; VISCOELASTICITY; ROOM TEMPERATURE; COMPRESSIBILITY; DESIGN ANALYSIS; SEALING 20090041738 General Electric Energy, Greenville, SC, United States Update on DOE Advanced IGCC/H2 Gas Turbine Chupp, Ray; 2008 NASA Seal/Secondary Air System Workshop; November 2009; pp. 207-22; In English; Original contains color illustrations Contract(s)/Grant(s): DE-FC26-05NT42643 Copyright; Avail.: CASI: A03, Hardcopy; Available from CASI on CD-ROM only as part of the entire parent document Avail Online: http://hdl.handle.net/2060/20090041738 Cooling Flow Reduction: a) Focus on improving turbine hot gas path part cooling efficiency. b) Applicable to current metallic turbine components and synergistic with advanced materials. c) Address challenges of IGCC/hydrogen fuel environment (for example, possible cooling hole plugging). Leakage Flow Reduction: a) Focus on decreasing turbine parasitic leakages, i.e. between static-to-static, static-to-rotating turbine parts. b) Develop improved seal designs in a variety of important areas. Purge Flow Reduction: a) Focus on decreasing required flows to keep rotor disk cavities within temperature limits. b) Develop improved sealing at the cavity rims and modified flow geometries to minimize hot gas ingestion and aerodynamic impact. Author HEAT TRANSFER; TURBINES; HIGH TEMPERATURE GASES; GAS PATH ANALYSIS; CAVITY FLOW; SEALING; FLOW GEOMETRY; GAS COOLING; HYDROGEN FUELS 20090041739 NASA Glenn Research Center, Cleveland, OH, United States Overview of LIDS Docking Seals Development Dunlap, Patrick; Steinetz, Bruce; Daniels, Christopher; 2008 NASA Seal/Secondary Air System Workshop; November 2009; pp. 223-23; In English; Original contains color illustrations Copyright; Avail.: CASI: A02, Hardcopy; Available from CASI on CD-ROM only as part of the entire parent document Avail Online: http://hdl.handle.net/2060/20090041739 GRC is supporting JSC by developing LIDS main interface seals Seal development and testing is occurring at both sub-scale and full-scale levels: a) Small-scale tests performed to define seal materials and evaluate exposure to space environments. b) Medium-scale testing: 1) Permits evaluation of candidate seal designs at faster pace than for full-scale seals. 2) Leak rates and loads can be scaled up to full-scale for indication of seal performance. c) Full-scale test rigs used for seal development and flight qualification tests and to assess on-orbit anomalies if needed. GRC responsible for delivering flight hardware seals to JSC approx.2013 for integration into LIDS flight units. Author SEALS (STOPPERS); AEROSPACE ENVIRONMENTS; PERFORMANCE TESTS; LOADS (FORCES); FULL SCALE TESTS 20090041741 NASA, Washington, DC, United States NASA Tech Briefs, December 2009 December 2009; In English; Original contains color and black and white illustrations Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090041741 Topics include: A Deep Space Network Portable Radio Science Receiver; Detecting Phase Boundaries in Hard-Sphere Suspensions; Low-Complexity Lossless and Near-Lossless Data Compression Technique for Multispectral Imagery; Very-Long-Distance Remote Hearing and Vibrometry; Using GPS to Detect Imminent Tsunamis; Stream Flow Prediction by Remote Sensing and Genetic Programming; Pilotless Frame Synchronization Using LDPC Code Constraints; Radiometer on a Chip; Measuring Luminescence Lifetime With Help of a DSP; Modulation Based on Probability Density Functions; Ku Telemetry Modulator for Suborbital Vehicles; Photonic Links for High-Performance Arraying of Antennas; Reconfigurable, Bi-Directional Flexfet Level Shifter for Low-Power, Rad-Hard Integration; Hardware-Efficient Monitoring of I/O Signals; Video System for Viewing From a Remote or Windowless Cockpit; Spacesuit Data Display and Management System; IEEE 1394 Hub With Fault Containment; Compact, Miniature MMIC Receiver Modules for an MMIC Array Spectrograph; Waveguide Transition for Submillimeter-Wave MMICs; Magnetic-Field-Tunable Superconducting Rectifier; Bonded Invar Clip Removal Using Foil Heaters; Fabricating Radial Groove Gratings Using Projection Photolithography; Gratings Fabricated on Flat Surfaces and Reproduced on Non-Flat Substrates; Method for Measuring the Volume-Scattering Function of Water; Method of Heating a Foam-Based Catalyst Bed; Small Deflection Energy Analyzer for Energy and Angular Distributions; Polymeric Bladder for Storing Liquid Oxygen; Pyrotechnic Simulator/Stray-Voltage Detector; Inventions Utilizing Microfluidics and Colloidal Particles; RuO2 Thermometer for Ultra-Low Temperatures; Ultra-Compact, High-Resolution LADAR System for 3D Imaging; Dual-Channel Multi-Purpose Telescope; Objective Lens Optimized for Wavefront Delivery, Pupil Imaging, and Pupil Ghosting; CMOS Camera Array With Onboard Memory; Quickly Approximating the Distance Between Two Objects; Processing Images of Craters for Spacecraft Navigation; Adaptive Morphological Feature-Based Object Classifier for a Color Imaging System; Rover Slip Validation and Prediction Algorithm; Safety and Quality Training Simulator; Supply-Chain Optimization Template; Algorithm for Computing Particle/Surface Interactions; Cryogenic Pupil Alignment Test Architecture for Aberrated Pupil Images; and Thermal Transport Model for Heat Sink Design. Author ANGULAR DISTRIBUTION; BIT SYNCHRONIZATION; CRYOGENIC TEMPERATURE; DATA COMPRESSION; DISPLAY DEVICES; ENERGY DISTRIBUTION; INTEGRATED CIRCUITS; MICROWAVE CIRCUITS; PARTICLE INTERACTIONS; PROBABILITY DENSITY FUNCTIONS; WAVEGUIDES; VIBRATION MEASUREMENT; TELEMETRY; SUPERCONDUCTIVITY; SUBMILLIMETER WAVES 20090041742 California Inst. of Tech., Pasadena, CA, United States Low-Complexity Lossless and Near-Lossless Data Compression Technique for Multispectral Imagery Xie, Hua; Klimesh, Matthew A.; NASA Tech Briefs, December 2009; December 2009; pp. ; In English Report No.(s): NPO-46625; Copyright; Avail.: CASI: A01, Hardcopy Avail Online: http://hdl.handle.net/2060/20090041742 http://www.techbriefs.com/component/content/article/6346 This work extends the lossless data compression technique described in Fast Lossless Compression of Multispectral- Image Data, (NPO-42517) NASA Tech Briefs, Vol. 30, No. 8 (August 2006), page 26. The original technique was extended to include a near-lossless compression option, allowing substantially smaller compressed file sizes when a small amount of distortion can be tolerated. Near-lossless compression is obtained by including a quantization step prior to encoding of prediction residuals. The original technique uses lossless predictive compression and is designed for use on multispectral imagery. A lossless predictive data compression algorithm compresses a digitized signal one sample at a time as follows: First, a sample value is predicted from previously encoded samples. The difference between the actual sample value and the prediction is called the prediction residual. The prediction residual is encoded into the compressed file. The decompressor can form the same predicted sample and can decode the prediction residual from the compressed file, and so can reconstruct the original sample. A lossless predictive compression algorithm can generally be converted to a near-lossless compression algorithm by quantizing the prediction residuals prior to encoding them. In this case, since the reconstructed sample values will not be identical to the original sample values, the encoder must determine the values that will be reconstructed and use these values for predicting later sample values. The technique described here uses this method, starting with the original technique, to allow near-lossless compression. The extension to allow near-lossless compression adds the ability to achieve much more compression when small amounts of distortion are tolerable, while retaining the low complexity and good overall compression effectiveness of the original algorithm. Author DATA COMPRESSION; IMAGERY; CODERS; CODING; ALGORITHMS 20090041743 California Inst. of Tech., Pasadena, CA, United States Very-Long-Distance Remote Hearing and Vibrometry Maleki, Lute; Yu, Nan; Matsko, Andrey; Savchenkov, Anatoliy; NASA Tech Briefs, December 2009; December 2009; pp. ; In English Report No.(s): NPO-45309; Copyright; Avail.: CASI: A01, Hardcopy Avail Online: http://hdl.handle.net/2060/20090041743 http://www.techbriefs.com/component/content/article/6345 A proposed development of laser-based instrumentation systems would extend the art of laser Doppler vibrometry beyond the prior limits of laser-assisted remote hearing and industrial vibrometry for detecting defects in operating mechanisms. A system according to the proposal could covertly measure vibrations of objects at distances as large as thousands of kilometers and could process the measurement data to enable recognition of vibrations characteristic of specific objects of interest, thereby enabling recognition of the objects themselves. A typical system as envisioned would be placed in orbit around the Earth for use as a means of determining whether certain objects on or under the ground are of interest as potential military targets. Terrestrial versions of these instruments designed for airborne or land- or sea-based operation could be similarly useful for military or law-enforcement purposes. Prior laser-based remote-hearing systems are not capable of either covert operation or detecting signals beyond modest distances when operated at realistic laser power levels. The performances of prior systems for recognition of objects by remote vibrometry are limited by low signal-to-noise ratios and lack of filtering of optical signals returned from targets. The proposed development would overcome these limitations. A system as proposed would include a narrow-band laser as its target illuminator, a lock-in-detection receiver subsystem, and a laser-power-control subsystem that would utilize feedback of the intensity of background illumination of the target to adjust the laser power. The laser power would be set at a level high enough to enable the desired measurements but below the threshold of detectability by an imaginary typical modern photodetector located at the target and there exposed to the background illumination. The laser beam would be focused tightly on the distant target, such that the receiving optics would be exposed to only one speckle. The return signal would be extremely-narrow-band filtered (to sub-kilohertz bandwidth) in the optical domain by a whispering-gallery- mode filter so as to remove most of the background illumination. The filtered optical signal would be optically amplified. This combination of optical filtering and optical amplification would provide an optical signal that would be strong enough to be detectable but not so strong as to saturate the detector in the lock-in detection subsystem. Author WHISPERING GALLERY MODES; HEARING; REMOTE CONTROL; VIBRATION MEASUREMENT; OPTICAL COMMUNICATION; FEEDBACK; DATA PROCESSING; DETECTION; SIGNAL TO NOISE RATIOS 20090041744 NASA Goddard Space Flight Center, Greenbelt, MD, United States RuO2 Thermometer for Ultra-Low Temperatures Hait, Thomas; Shirron, Peter J.; DiPirro, Michael; NASA Tech Briefs, December 2009; December 2009; pp. 2; In English Report No.(s): GSC-15690-1; Copyright; Avail.: CASI: A01, Hardcopy Avail Online: http://hdl.handle.net/2060/20090041744 http://www.techbriefs.com/component/content/article/6371 A small, high-resolution, low-power thermometer has been developed for use in ultra-low temperatures that uses multiple RuO2 chip resistors. The use of commercially available thick-film RuO2 chip resistors for measuring cryogenic temperatures is well known due to their low cost, long-term stability, and large resistance change. Derived from text CRYOGENIC TEMPERATURE; THERMOMETERS; RUTHENIUM COMPOUNDS; OXYGEN COMPOUNDS; TEMPERATURE MEASUREMENT 20090041745 SiWave, Inc., Arcadia, CA, United States Ultra-Compact, High-Resolution LADAR System for 3D Imaging Xu, Jing; Gutierrez, Roman; NASA Tech Briefs, December 2009; December 2009; pp. 2; In English Report No.(s): MSC-23873-1; Copyright; Avail.: CASI: A01, Hardcopy Avail Online: http://hdl.handle.net/2060/20090041745 http://www.techbriefs.com/component/content/article/6372 An eye-safe LADAR system weighs under 500 grams and has range resolution of 1 mm at 10 m. This laser uses an adjustable, tiny microelectromechanical system (MEMS) mirror that was made in SiWave to sweep laser frequency. The size of the laser device is small (70x50x13 mm). The LADAR uses all the mature fiber-optic telecommunication technologies in the system, making this innovation an efficient performer. The tiny size and light weight makes the system useful for commercial and industrial applications including surface damage inspections, range measurements, and 3D imaging. Author IMAGING TECHNIQUES; HIGH RESOLUTION; MICROELECTROMECHANICAL SYSTEMS; LASER RANGE FINDERS 20090041746 NASA Goddard Space Flight Center, Greenbelt, MD, United States Magnetic-Field-Tunable Superconducting Rectifier Sadleir, John E.; NASA Tech Briefs, December 2009; December 2009; pp. 1; In English Report No.(s): GSC-15643-1; Copyright; Avail.: CASI: A01, Hardcopy Avail Online: http://hdl.handle.net/2060/20090041746 http://www.techbriefs.com/component/content/article/6349 Superconducting electronic components have been developed that provide current rectification that is tunable by design and with an externally applied magnetic field to the circuit component. The superconducting material used in the device is relatively free of pinning sites with its critical current determined by a geometric energy barrier to vortex entry. The ability of the vortices to move freely inside the device means this innovation does not suffer from magnetic hysteresis effects changing the state of the superconductor. The invention requires a superconductor geometry with opposite edges along the direction of current flow. In order for the critical current asymmetry effect to occur, the device must have different vortex nucleation conditions at opposite edges. Alternative embodiments producing the necessary conditions include edges being held at different temperatures, at different local magnetic fields, with different current-injection geometries, and structural differences between opposite edges causing changes in the size of the geometric energy barrier. An edge fabricated with indentations of the order of the coherence length will significantly lower the geometric energy barrier to vortex entry, meaning vortex passage across the device at lower currents causing resistive dissipation. The existing prototype is a two-terminal device consisting of a thin-film su - perconducting strip operating at a temperature below its superconducting transition temperature (Tc). Opposite ends of the strip are connected to electrical leads made of a higher Tc superconductor. The thin-film lithographic process provides an easy means to alter edge-structures, current-injection geo - metries, and magnetic-field conditions at the edges. The edge-field conditions can be altered by using local field(s) generated from dedicated higher Tc leads or even using the device s own higher Tc superconducting leads. Author MAGNETIC FIELDS; SUPERCONDUCTORS (MATERIALS); RECTIFIERS; ELECTRIC CONDUCTORS; TRANSITION TEMPERATURE; MAGNETIC EFFECTS; THIN FILMS 20090041747 ZIN Technologies, Inc., Brook Park, OH, United States Spacesuit Data Display and Management System Hall, David G.; Sells, Aaron; Shah, Hemal; NASA Tech Briefs, December 2009; December 2009; pp. 1; In English Report No.(s): LEW-18399-1; Copyright; Avail.: CASI: A01, Hardcopy Avail Online: http://hdl.handle.net/2060/20090041747 http://www.techbriefs.com/component/content/article/6356 A prototype embedded avionics system has been designed for the next generation of NASA extra-vehicular-activity (EVA) spacesuits. The system performs biomedical and other sensor monitoring, image capture, data display, and data transmission. An existing NASA Phase I and II award winning design for an embedded computing system (ZIN vMetrics - BioWATCH) has been modified. The unit has a reliable, compact form factor with flexible packaging options. These innovations are significant, because current state-of-the-art EVA spacesuits do not provide capability for data displays or embedded data acquisition and management. The Phase 1 effort achieved Technology Readiness Level 4 (high fidelity breadboard demonstration). The breadboard uses a commercial-grade field-programmable gate array (FPGA) with embedded processor core that can be upgraded to a space-rated device for future revisions. Author AVIONICS; SPACE SUITS; DISPLAY DEVICES; DATA MANAGEMENT; EXTRAVEHICULAR ACTIVITY 20090041748 Honeywell, Inc., Phoenix, AZ, United States IEEE 1394 Hub With Fault Containment Paulitsch, Michael; Hall, Brendan; Driscoll, Kevin R.; NASA Tech Briefs, December 2009; December 2009; pp. 1; In English Report No.(s): MSC-24459-1; Copyright; Avail.: CASI: A01, Hardcopy Avail Online: http://hdl.handle.net/2060/20090041748 http://www.techbriefs.com/component/content/article/6357 This innovation is designed to prevent a single end system communication node from negatively influencing the whole system s behavior so that the network system can still operate if an end node is faulty. Placing a hub (star) in the middle of the system prevents propagation of critical control information that other end systems would react to, like block reset messages. Author CONTAINMENT; INFORMATION SYSTEMS; FAULT DETECTION 20090041749 ITT Space Systems Div., United States Objective Lens Optimized for Wavefront Delivery, Pupil Imaging, and Pupil Ghosting Olzcak, Gene; NASA Tech Briefs, December 2009; December 2009; pp. 2; In English Report No.(s): GSC-15675-1; Copyright; Avail.: CASI: A01, Hardcopy Avail Online: http://hdl.handle.net/2060/20090041749 An interferometer objective lens (or diverger) may be used to transform a collimated beam into a diverging or converging beam. This innovation provides an objective lens that has diffraction-limited optical performance that is optimized at two sets of conjugates: imaging to the objective focus and imaging to the pupil. The lens thus provides for simultaneous delivery of a high-quality beam and excellent pupil resolution properties. Author IMAGING TECHNIQUES; LENSES; GHOSTS 20090041750 Opto-Knowledge Systems, Inc., United States CMOS Camera Array With Onboard Memory Gat, Nahum; NASA Tech Briefs, December 2009; December 2009; pp. 2; In English Report No.(s): GSC-14902-1; Copyright; Avail.: CASI: A01, Hardcopy Avail Online: http://hdl.handle.net/2060/20090041750 A compact CMOS (complementary metal oxide semiconductor) camera system has been developed with high resolution (1.3 Megapixels), a USB (universal serial bus) 2.0 interface, and an onboard memory. Exposure times, and other operating parameters, are sent from a control PC via the USB port. Data from the camera can be received via the USB port and the interface allows for simple control and data capture through a laptop computer. Derived from text CAMERAS; CMOS 20090041751 LinCom Corp., Houston, TX, United States Quickly Approximating the Distance Between Two Objects Hammen, David; NASA Tech Briefs, December 2009; December 2009; pp. 2; In English Report No.(s): MSC-23264-1; Copyright; Avail.: CASI: A01, Hardcopy Avail Online: http://hdl.handle.net/2060/20090041751 http://www.techbriefs.com/component/content/article/6378 A method of quickly approximating the distance between two objects (one smaller, regarded as a point; the other larger and complexly shaped) has been devised for use in computationally simulating motions of the objects for the purpose of planning the motions to prevent collisions. Derived from text SIMULATION; DISTANCE; ESTIMATING 20090041752 PhotoSense, LLC, United States Measuring Luminescence Lifetime With Help of a DSP Danielson, J. D. S.; NASA Tech Briefs, December 2009; December 2009; pp. 1; In English Report No.(s): MSC-22906-1; Copyright; Avail.: CASI: A01, Hardcopy Avail Online: http://hdl.handle.net/2060/20090041752 http://www.techbriefs.com/component/content/article/6360 An instrument for measuring the lifetime of luminescence (fluorescence or phosphorescence) includes a digital signal processor (DSP) as the primary means of control, generation of excitation signals, and analysis of response signals. The DSP hardware in the present instrument makes it possible to switch among a variety of operating modes by making changes in software only. Derived from text DIGITAL SYSTEMS; LUMINESCENCE; SIGNAL PROCESSING 20090041753 NASA Goddard Space Flight Center, Greenbelt, MD, United States Bonded Invar Clip Removal Using Foil Heaters Pontius, James T.; Tuttle, James G.; NASA Tech Briefs, December 2009; December 2009; pp. 1; In English Report No.(s): GSC-15770-1; Copyright; Avail.: CASI: A01, Hardcopy Avail Online: http://hdl.handle.net/2060/20090041753 http://www.techbriefs.com/component/content/article/6361 A new process uses local heating and temperature monitoring to soften the adhesive under Invar clips enough that they can be removed without damaging the composite underneath or other nearby bonds. Two 1x1 in. (approx.2.5x2.5 cm), 10-W/sq in. (approx.1.6-W/sq cm), 80-ohm resistive foil Kapton foil heaters, with pressure-sensitive acrylic adhesive backing, are wired in parallel to a 50-V, 1-A limited power supply. At 1 A, 40 W are applied to the heater pair. The temperature is monitored in the clip radius and inside the tube, using a dual thermocouple readout. Several layers of aluminum foil are used to speed the heat up, allowing clips to be removed in less than five minutes. The very local heating via the foil heaters allows good access for clip removal and protects all underlying and adjacent materials. Author CLIPS; HEATERS; KAPTON (TRADEMARK); ADHESIVES; METAL FOILS; NICKEL ALLOYS; ACRYLIC RESINS; IRON ALLOYS 20090041754 NASA Goddard Space Flight Center, Greenbelt, MD, United States Thermal Transport Model for Heat Sink Design Chervenak, James A.; Kelley, Richard L.; Brown, Ari D.; Smith, Stephen J.; Kilbourne, Caroline a.; NASA Tech Briefs, December 2009; December 2009; pp. 2; In English Report No.(s): GSC-15671-1; Copyright; Avail.: CASI: A01, Hardcopy Avail Online: http://hdl.handle.net/2060/20090041754 http://www.techbriefs.com/component/content/article/6380 A document discusses the development of a finite element model for describing thermal transport through microcalorimeter arrays in order to assist in heat-sinking design. A fabricated multi-absorber transition edge sensor (PoST) was designed in order to reduce device wiring density by a factor of four. The finite element model consists of breaking the microcalorimeter array into separate elements, including the transition edge sensor (TES) and the silicon substrate on which the sensor is deposited. Each element is then broken up into subelements, whose surface area subtends 10 10 microns. The heat capacity per unit temperature, thermal conductance, and thermal diffusivity of each subelement are the model inputs, as are the temperatures of each subelement. Numerical integration using the Finite in Time Centered in Space algorithm of the thermal diffusion equation is then performed in order to obtain a temporal evolution of the subelement temperature. Thermal transport across interfaces is modeled using a thermal boundary resistance obtained using the acoustic mismatch model. The document concludes with a discussion of the PoST fabrication. PoSTs are novel because they enable incident x-ray position sensitivity with good energy resolution and low wiring density. Author HEAT SINKS; THERMAL DIFFUSIVITY; FABRICATION; FINITE ELEMENT METHOD; CALORIMETERS; THERMAL RESISTANCE; THERMAL CONDUCTIVITY; NUMERICAL INTEGRATION; MATHEMATICAL MODELS 20090041755 Honeywell, Inc., Phoenix, AZ, United States Hardware-Efficient Monitoring of I/O Signals Driscoll, Kevin R.; Hall, Brendan; Paulitsch, Michael; NASA Tech Briefs, December 2009; December 2009; pp. 1; In English Report No.(s): MSC-24458-1; Copyright; Avail.: CASI: A01, Hardcopy Avail Online: http://hdl.handle.net/2060/20090041755 http://www.techbriefs.com/component/content/article/6355 In this invention, command and monitor functionality is moved between the two independent pieces of hardware, in which one had been dedicated to command and the other had been dedicated to monitor, such that some command and some monitor functionality appears in each. The only constraint is that the monitor for signal cannot be in the same hardware as the command I/O it is monitoring. The splitting of the command outputs between independent pieces of hardware may require some communication between them, i.e. an intra-switch trunk line. This innovation reduces the amount of wasted hardware and allows the two independent pieces of hardware to be designed identically in order to save development costs. Author SWITCHES; COMMUNICATION EQUIPMENT; MONITORS 20090041756 NASA Goddard Space Flight Center, Greenbelt, MD, United States Algorithm for Computing Particle/Surface Interactions Hughes, David W.; NASA Tech Briefs, December 2009; December 2009; pp. 2; In English Report No.(s): GSC-15364-1; Copyright; Avail.: CASI: A01, Hardcopy Avail Online: http://hdl.handle.net/2060/20090041756 http://www.techbriefs.com/component/content/article/6374 An algorithm has been devised for predicting the behaviors of sparsely spatially distributed particles impinging on a solid surface in a rarefied atmosphere. Under the stated conditions, prior particle-transport models in which (1) dense distributions of particles are treated as continuum fluids; or (2) sparse distributions of particles are considered to be suspended in and to diffuse through fluid streams are not valid. Author ALGORITHMS; PARTICLE INTERACTIONS; SOLID SURFACES 20090041758 California Inst. of Tech., Pasadena, CA, United States Radiometer on a Chip Chattopadhyay, Goutam; Gill, John J.; Mehdi, Imran; Lee, Choonsup; Schlecht, Erich T.; Skalare, Anders; Ward, John S.; Siegel, Peter H.; Thomas, Bertrand C.; NASA Tech Briefs, December 2009; December 2009; pp. 1; In English Report No.(s): NPO-46542; Copyright; Avail.: CASI: A01, Hardcopy Avail Online: http://hdl.handle.net/2060/20090041758 http://www.techbriefs.com/component/content/article/6359 The radiometer together to provide a robust, making vertically wafer level, customizing the lightweight assembly performing pieces in a more Derived from text RADIOMETERS; WAFERS; CHIPS (ELECTRONICS) 20090041759 California Inst. of Tech., Pasadena, CA, United States Compact, Miniature MMIC Receiver Modules for an MMIC Array Spectrograph Kangaslahti, Pekka P.; Gaier, Todd C.; Cooperrider, Joelle T.; Samoska, Lorene A.; Soria, Mary M.; ODwyer, Ian J.; Weinreb, Sander; Custodero, Brian; Owen, Heahter; Grainge, Keith; Church, Sarah; Lai, Richard; Mei, Xiaobing; NASA Tech Briefs, December 2009; December 2009; pp. 14-1; In English Report No.(s): NPO-46522; Copyright; Avail.: CASI: A01, Hardcopy Avail Online: http://hdl.handle.net/2060/20090041759 http://www.techbriefs.com/component/content/article/6348 A single-pixel prototype of a W-band detector module with a digital back-end was developed to serve as a building block for large focal-plane arrays of monolithic millimeter-wave integrated circuit (MMIC) detectors. The module uses low-noise amplifiers, diode-based mixers, and a WR10 waveguide input with a coaxial local oscillator. State-of-the-art InP HEMT (high electron mobility transistor) MMIC amplifiers at the front end provide approximately 40 dB of gain. The measured noise temperature of the module, at an ambient temperature of 300 K, was found to be as low as 450 K at 95 GHz. The modules will be used to develop multiple instruments for astrophysics radio telescopes, both on the ground and in space. The prototype is being used by Stanford University to characterize noise performance at cryogenic temperatures. The goal is to achieve a 30-50 K noise temperature around 90 GHz when cooled to a 20 K ambient temperature. Further developments include characterization of the IF in-phase (I) and quadrature (Q) signals as a function of frequency to check amplitude and phase; replacing the InP low-noise amplifiers with state-of-the-art 35-nm-gate-length NGC low-noise amplifiers; interfacing the front-end module with a digital back-end spectrometer; and developing a scheme for local oscillator and IF distribution in a future array. While this MMIC is being developed for use in radio astronomy, it has the potential for use in other industries. Applications include automotive radar (both transmitters and receivers), communication links, radar systems for collision avoidance, production monitors, ground-penetrating sensors, and wireless personal networks. Author MICROWAVE CIRCUITS; HIGH ELECTRON MOBILITY TRANSISTORS; NOISE TEMPERATURE; TRANSISTOR AMPLIFIERS; AMBIENT TEMPERATURE; RADIO TELESCOPES; LOW NOISE; COMMUNICATION NETWORKS 20090041760 California Inst. of Tech., Pasadena, CA, United States Processing Images of Craters for Spacecraft Navigation Cheng, Yang; Johnson, Andrew E.; Matthies, Larry H.; NASA Tech Briefs, December 2009; December 2009; pp. 2; In English Report No.(s): NPO-40122; Copyright; Avail.: CASI: A01, Hardcopy Avail Online: http://hdl.handle.net/2060/20090041760 A crater-detection algorithm has been conceived to enable automation of what, heretofore, have been manual processes for utilizing images of craters on a celestial body as landmarks for navigating a spacecraft flying near or landing on that body. The images are acquired by an electronic camera aboard the spacecraft, then digitized, then processed by the algorithm, which consists mainly of the following steps: 1. Edges in an image detected and placed in a database. 2. Crater rim edges are selected from the edge database. 3. Edges that belong to the same crater are grouped together. 4. An ellipse is fitted to each group of crater edges. 5. Ellipses are refined directly in the image domain to reduce errors introduced in the detection of edges and fitting of ellipses. 6. The quality of each detected crater is evaluated. It is planned to utilize this algorithm as the basis of a computer program for automated, real-time, onboard processing of crater-image data. Experimental studies have led to the conclusion that this algorithm is capable of a detection rate >93 percent, a false-alarm rate <5 percent, a geometric error <0.5 pixel, and a position error <0.3 pixel. Author CRATERS; IMAGE PROCESSING; SPACE NAVIGATION; SPACECRAFT LANDING; ONBOARD DATA PROCESSING; MANUAL CONTROL 20090041761 United Space Alliance, Houston, TX, United States Safety and Quality Training Simulator Scobby, Pete T.; NASA Tech Briefs, December 2009; December 2009; pp. 2; In English Report No.(s): MSC-23232-1; Copyright; Avail.: CASI: A01, Hardcopy Avail Online: http://hdl.handle.net/2060/20090041761 http://www.techbriefs.com/component/content/article/6375 A portable system of electromechanical and electronic hardware and documentation has been developed as an automated means of instructing technicians in matters of safety and quality. The system enables elimination of most of the administrative tasks associated with traditional training. Customized, performance-based, hands-on training with integral testing is substituted for the traditional instructional approach of passive attendance in class followed by written examination. Derived from text SAFETY; TRAINING SIMULATORS; SIMULATION 20090041762 Foster-Miller Associates, Inc., Waltham, MA, United States Polymeric Bladder for Storing Liquid Oxygen Walker, David H.; Harvey, Andrew C.; Leary, William; NASA Tech Briefs, December 2009; December 2009; pp. 2; In English Report No.(s): MSC-22943-1; Copyright; Avail.: CASI: A01, Hardcopy Avail Online: http://hdl.handle.net/2060/20090041762 http://www.techbriefs.com/component/content/article/6368 A proposed system for storing oxygen in liquid form and dispensing it in gaseous form is based on (1) initial subcooling of the liquid oxygen; (2) containing the liquid oxygen in a flexible vessel; (3) applying a gas spring to the flexible vessel to keep the oxygen compressed above the saturation pressure and, thus, in the liquid state; and (4) using heat leakage into the system for vaporizing the oxygen to be dispensed. In a typical prior system based on these principles, the flexible vessel is a metal bellows housed in a rigid tank, and the gas spring consists of pressurized helium in the tank volume surrounding the bellows. Unfortunately, the welds in the bellows corrugations are subject to fatigue, and, because bellows have large ullage, a correspondingly large fraction of the oxygen content cannot be expelled. In the proposed system, the flexible vessel would be a bladder made of a liquid- crystal polymer (LCP). (LCPs are strong and compatible with liquid oxygen.) In comparison with a metal bellows, a polymeric bladder would have less ullage and would weigh less. In experiments involving fatigue cycling at liquid-nitrogen temperatures, two LCPs were found to be suitable for this application. Author LIQUID OXYGEN; DISPENSERS; VAPORIZING; BELLOWS; LIQUID CRYSTALS; HELIUM 20090041763 NASA Goddard Space Flight Center, Greenbelt, MD, United States Dual-Channel Multi-Purpose Telescope Howard, Joseph M.; Content, David; NASA Tech Briefs, December 2009; December 2009; pp. 2; In English Report No.(s): GSC-15574-1; Copyright; Avail.: CASI: A01, Hardcopy Avail Online: http://hdl.handle.net/2060/20090041763 http://www.techbriefs.com/component/content/article/6373 A dual-channel telescope allows for a design with a good, for design starts with a Korsch telescope image internal due to the aberration balancing The the system where the narrow picked off by Derived from text CASSEGRAIN OPTICS; TELESCOPES 20090041764 California Inst. of Tech., Pasadena, CA, United States A Deep Space Network Portable Radio Science Receiver Jongeling, Andre P.; Sigman, Elliott H.; Chandra, Kumar; Trinh, Joseph T.; Navarro, Robert; Rogstad, Stephen P.; Goodhart, Charles E.; Proctor, Robert C.; Finley, Susan G.; White, Leslie A.; NASA Tech Briefs, December 2009; December 2009; pp. ; In English Report No.(s): NPO-46289; Copyright; Avail.: CASI: A01, Hardcopy Avail Online: http://hdl.handle.net/2060/20090041764 http://www.techbriefs.com/component/content/article/6341 The Radio Science Receiver (RSR) is an open-loop receiver installed in NASA s Deep Space Network (DSN), which digitally filters and records intermediate-frequency (IF) analog signals. The RSR is an important tool for the Cassini Project, which uses it to measure perturbations of the radio-frequency wave as it travels between the spacecraft and the ground stations, allowing highly detailed study of the composition of the rings, atmosphere, and surface of Saturn and its satellites. Derived from text DEEP SPACE NETWORK; INTERMEDIATE FREQUENCIES; RECEIVERS 20090041765 NASA Goddard Space Flight Center, Greenbelt, MD, United States Ku Telemetry Modulator for Suborbital Vehicles Bundick, Steven; Bishop, Jim; Newman, David; Zaki, Nazrul; NASA Tech Briefs, December 2009; December 2009; pp. 1; In English Report No.(s): GSC-15456-1; Copyright; Avail.: CASI: A01, Hardcopy Avail Online: http://hdl.handle.net/2060/20090041765 http://www.techbriefs.com/component/content/article/6358 A modulator utilizing the Ku-band instead of the usual S-band has been developed to improve transmission rates for suborbital platforms. Derived from text MODULATORS; SUPERHIGH FREQUENCIES; TELEMETRY 20090041766 NASA Glenn Research Center, Cleveland, OH, United States Modulation Based on Probability Density Functions Williams, Glenn L.; NASA Tech Briefs, December 2009; December 2009; pp. 10-1; In English Report No.(s): LEW-17650-1; Copyright; Avail.: CASI: A01, Hardcopy Avail Online: http://hdl.handle.net/2060/20090041766 http://www.techbriefs.com/component/content/article/6352 A proposed method of modulating a sinusoidal carrier signal to convey digital information involves the use of histograms representing probability density functions (PDFs) that characterize samples of the signal waveform. The method is based partly on the observation that when a waveform is sampled (whether by analog or digital means) over a time interval at least as long as one half cycle of the waveform, the samples can be sorted by frequency of occurrence, thereby constructing a histogram representing a PDF of the waveform during that time interval. Derived from text DIGITAL DATA; MODULATION; PROBABILITY DENSITY FUNCTIONS; SINE WAVES 20090041767 California Inst. of Tech., Pasadena, CA, United States Photonic Links for High-Performance Arraying of Antennas Huang, Shouhua; Tjoelker, Robert; NASA Tech Briefs, December 2009; December 2009; pp. 11-1; In English; Original contains color illustrations Report No.(s): NPO-44130; Copyright; Avail.: CASI: A01, Hardcopy Avail Online: http://hdl.handle.net/2060/20090041767 http://www.techbriefs.com/component/content/article/6353 An architecture for arraying microwave antennas in the next generation of NASA s Deep Space Network (DSN) involves the use of all photonic links between (1) the antennas in a given array and (2) a signal processing center. In this architecture, all affected parts at each antenna pedestal [except a front-end low-noise amplifier for the radio-frequency (RF) signal coming from the antenna and an optical transceiver to handle monitor and control (M/C) signals] would be passive optical parts Derived from text MICROWAVE ANTENNAS; SIGNAL PROCESSING; ANTENNA ARRAYS; PHOTONICS 20090041768 Colorado School of Mines, Golden, CO, United States Inventions Utilizing Microfluidics and Colloidal Particles Marr, David W.; Gong, Tieying; Oakey, John; Terray, Alexander V.; Wu, David T.; NASA Tech Briefs, December 2009; December 2009; pp. 20-2; In English Report No.(s): MSC-24160-1/1-1/2-1/3-1; Copyright; Avail.: CASI: A01, Hardcopy Avail Online: http://hdl.handle.net/2060/20090041768 http://www.techbriefs.com/component/content/article/6370 Several related inventions pertain to families of devices that utilize microfluidics and/or colloidal particles to obtain useful physical effects. The families of devices can be summarized as follows: (1) Microfluidic pumps and/or valves wherein colloidal-size particles driven by electrical, magnetic, or optical fields serve as the principal moving parts that propel and/or direct the affected flows. (2) Devices that are similar to the aforementioned pumps and/or valves except that they are used to manipulate light instead of fluids. The colloidal particles in these devices are substantially constrained to move in a plane and are driven to spatially order them into arrays that function, variously, as waveguides, filters, or switches for optical signals. (3) Devices wherein the ultra-laminar nature of microfluidic flows is exploited to effect separation, sorting, or filtering of colloidal particles or biological cells in suspension. (4) Devices wherein a combination of confinement and applied electrical and/or optical fields forces the colloidal particles to become arranged into three-dimensional crystal lattices. Control of the colloidal crystalline structures could be exploited to control diffraction of light. (5) Microfluidic devices, incorporating fluid waveguides, wherein switching of flows among different paths would be accompanied by switching of optical signals. Derived from text COLLOIDS; MICROFLUIDIC DEVICES; PUMPS; SWITCHES 20090041769 American Semiconductor, Inc., Boise, ID, United States Reconfigurable, Bi-Directional Flexfet Level Shifter for Low-Power, Rad-Hard Integration DeGregorio, Kelly; Wilson, Dale G.; NASA Tech Briefs, December 2009; December 2009; pp. 1; In English Report No.(s): GSC-15565-1; Copyright; Avail.: CASI: A01, Hardcopy Avail Online: http://hdl.handle.net/2060/20090041769 http://www.techbriefs.com/component/content/article/6347 Two prototype Reconfigurable, Bi-directional Flexfet Level Shifters (ReBiLS) have been developed, where one version is a stand-alone component designed to interface between external low voltage and high voltage, and the other version is an embedded integrated circuit (IC) for interface between internal low-voltage logic and external high-voltage components. Targeting stand-alone and embedded circuits separately allows optimization for these distinct applications. Both ReBiLS designs use the commercially available 180-nm Flex fet Independently Double-Gated (IDG) SOI CMOS (silicon on insulator, complementary metal oxide semiconductor) technology. Embedded ReBiLS circuits were integrated with a Reed-Solomon (RS) encoder using CMOS Ultra-Low-Power Radiation Tolerant (CULPRiT) double-gated digital logic circuits. The scope of the project includes: creation of a new high-voltage process, development of ReBiLS circuit designs, and adjustment of the designs to maximize performance through simulation, layout, and manufacture of prototypes. The primary technical objectives were to develop a high-voltage, thick oxide option for the 180-nm Flexfet process, and to develop a stand-alone ReBiLS IC with two 8-channel I/O busses, 1.8 2.5 I/O on the low-voltage pins, 5.0-V-tolerant input and 3.3-V output I/O on the high-voltage pins, and 100-MHz minimum operation with 10-pF external loads. Another objective was to develop an embedded, rad-hard ReBiLS I/O cell with 0.5-V low-voltage operation for interface with core logic, 5.0-V-tolerant input and 3.3-V output I/O pins, and 100-MHz minimum operation with 10- pF external loads. A third objective was to develop a 0.5- V Reed-Solomon Encoder with embedded ReBilS I/O: Transfer the existing CULPRiT RS encoder from a 0.35-micron bulk-CMOS process to the ASI 180-nm Flexfet, rad-hard SOI Process. 0.5-V low-voltage core logic. 5.0-V-tolerant input and 3.3-V output I/O pins. 100-MHz minimum operation with 10- pF external loads. The stand-alone ReBiLS chip will allow system designers to provide efficient bi-directional communication between components operating at different voltages. Embedding the ReBiLS cells into the proven Reed-Solomon encoder will demonstrate the ability to support new product development in a commercially viable, rad-hard, scalable 180-nm SOI CMOS process. Author INTEGRATED CIRCUITS; FIELD EFFECT TRANSISTORS; LOGIC CIRCUITS; COMMUNICATION EQUIPMENT; DIGITAL ELECTRONICS; SOI (SEMICONDUCTORS); LOW VOLTAGE; HIGH VOLTAGES; ELECTRIC POTENTIAL 20090041770 NASA Goddard Space Flight Center, Greenbelt, MD, United States Small Deflection Energy Analyzer for Energy and Angular Distributions Herrero, Federico A.; NASA Tech Briefs, December 2009; December 2009; pp. 19-2; In English Report No.(s): GSC-15610-1; Copyright; Avail.: CASI: A01, Hardcopy Avail Online: http://hdl.handle.net/2060/20090041770 http://www.techbriefs.com/component/content/article/6367 The development of the Small Deflection Energy Analyzer (SDEA) charged-particle spectrometer for energy and angle distributions responds to a longstanding need to measure the wind velocity vector in Earth s thermosphere, and to obtain the ion-drift vector in the ionosphere. The air and ions above 120 km are endowed with bulk velocities and temperatures just like air near the ground, but with separate spatial and temporal variations. It is important to understand these not only for study of the physics and chemistry of the Sun-Earth connection, but also for spacecraft orbit predictions, and communications through the ionosphere. The SDEA consists of a pair of parallel conducting plates separated by a small distance, with an entrance slit on one end, and an exit slit on the other. A voltage applied to these plates develops an electric field between the plates, and this field deflects ions passing through it. If an ion has too little energy, it will strike one of the plates. If it has too much, it will strike the back wall. An ion with the amount of energy being searched for will have its trajectory bent just enough to exit the back slit. The SDEA units are compact, rectangular, and operate with low voltages. The units can be built up into small arrays. These arrays could be used either to widen the field of view or to sharpen an existing one. This approach can also be used to obtain angular distributions in two planes simultaneously, thus cutting down the ion source power requirements in half. This geometry has enabled a new mass-spectrometer concept that can provide miniaturized mass spectrometers for use in industrial plants, air-pollution monitoring, and noxious-gas detection. Author ANGULAR DISTRIBUTION; ENERGY DISTRIBUTION; DEFLECTION; TEMPORAL DISTRIBUTION; CHARGED PARTICLES; SPECTROMETERS; WIND VELOCITY; IONOSPHERIC DRIFT; THERMOSPHERE; SPATIAL DISTRIBUTION 20090041771 ASRC Aerospace Corp., Cocoa Beach, FL, United States Pyrotechnic Simulator/Stray-Voltage Detector Greenfield, Terry; NASA Tech Briefs, December 2009; December 2009; pp. 2; In English Report No.(s): KSC-13282; Copyright; Avail.: CASI: A01, Hardcopy Avail Online: http://hdl.handle.net/2060/20090041771 http://www.techbriefs.com/component/content/article/6369 The concept for a dual test item has been developed for use in simulating live initiators/detonators during ground testing to verify the proper operation of the safing and firing circuitry for ground and flight systems ordnance as well as continuous monitoring for any stray voltages. Previous ordnance simulators have consisted of fuses, flash bulbs, inert devices with bridge wires, and actual live ordnance items mounted in test chambers. Stray voltage detectors have included devices connected to the firing circuits for continuous monitoring and a final no-voltage test just prior to ordnance connection. The purpose of this combined ordnance simulation and stray-voltage detection is to provide an improved and comprehensive method to ensure the ordnance circuitry is verified safe and operational. Author TEST CHAMBERS; DETONATORS; ORDNANCE; SIMULATORS; CIRCUITS; GROUND TESTS; WIRE BRIDGE CIRCUITS 20090041772 NASA Goddard Space Flight Center, Greenbelt, MD, United States Cryogenic Pupil Alignment Test Architecture for Aberrated Pupil Images Bos, Brent; Kubalak, David A.; Antonille, Scott; Ohl, Raymond; Hagopian, John G.; NASA Tech Briefs, December 2009; December 2009; pp. 2; In English Report No.(s): GSC-15650-1; Copyright; Avail.: CASI: A01, Hardcopy Avail Online: http://hdl.handle.net/2060/20090041772 http://www.techbriefs.com/component/content/article/6379 A document describes cryogenic test architecture for the James Webb Space Telescope (JWST) integrated science instrument module (ISIM). The ISIM element primarily consists of a mechanical metering structure, three science instruments, and a fine guidance sensor. One of the critical optomechanical alignments is the co-registration of the optical telescope element (OTE) exit pupil with the entrance pupils of the ISIM instruments. The test architecture has been developed to verify that the ISIM element will be properly aligned with the nominal OTE exit pupil when the two elements come together. The architecture measures three of the most critical pupil degrees-of-freedom during optical testing of the ISIM element. The pupil measurement scheme makes use of specularly reflective pupil alignment references located inside the JWST instruments, ground support equipment that contains a pupil imaging module, an OTE simulator, and pupil viewing channels in two of the JWST flight instruments. Pupil alignment references (PARs) are introduced into the instrument, and their reflections are checked using the instrument's mirrors. After the pupil imaging module (PIM) captures a reflected PAR image, the image will be analyzed to determine the relative alignment offset. The instrument pupil alignment preferences are specularly reflective mirrors with non-reflective fiducials, which makes the test architecture feasible. The instrument channels have fairly large fields of view, allowing PAR tip/tilt tolerances on the order of 0.5deg. Author PUPILS; JAMES WEBB SPACE TELESCOPE; DEGREES OF FREEDOM; IMAGING TECHNIQUES; GUIDANCE SENSORS; FLIGHT INSTRUMENTS 20090041773 California Inst. of Tech., Pasadena, CA, United States Using GPS to Detect Imminent Tsunamis Song, Y. Tony; NASA Tech Briefs, December 2009; December 2009; pp. 7-; In English Report No.(s): NPO-45940; Copyright; Avail.: CASI: A01, Hardcopy Avail Online: http://hdl.handle.net/2060/20090041773 http://www.techbriefs.com/component/content/article/6342 A promising method of detecting imminent tsunamis and estimating their destructive potential involves the use of Global Positioning System (GPS) data in addition to seismic data. Application of the method is expected to increase the reliability of global tsunami-warning systems, making it possible to save lives while reducing the incidence of false alarms. Tsunamis kill people every year. The 2004 Indian Ocean tsunami killed about 230,000 people. The magnitude of an earthquake is not always a reliable indication of the destructive potential of a tsunami. The 2004 Indian Ocean quake generated a huge tsunami, while the 2005 Nias (Indonesia) quake did not, even though both were initially estimated to be of the similar magnitude. Between 2005 and 2007, five false tsunami alarms were issued worldwide. Such alarms result in negative societal and economic effects. GPS stations can detect ground motions of earthquakes in real time, as frequently as every few seconds. In the present method, the epicenter of an earthquake is located by use of data from seismometers, then data from coastal GPS stations near the epicenter are used to infer sea-floor displacements that precede a tsunami. The displacement data are used in conjunction with local topographical data and an advanced theory to quantify the destructive potential of a tsunami on a new tsunami scale, based on the GPS-derived tsunami energy, much like the Richter Scale used for earthquakes. An important element of the derivation of the advanced theory was recognition that horizontal sea-floor motions contribute much more to generation of tsunamis than previously believed. The method produces a reliable estimate of the destructive potential of a tsunami within minutes typically, well before the tsunami reaches coastal areas. The viability of the method was demonstrated in computational tests in which the method yielded accurate representations of three historical tsunamis for which well-documented ground-motion measurements were available. Development of a global tsunami-warning system utilizing an expanded network of coastal GPS stations was under consideration at the time of reporting the information for this article. Author DETECTION; GLOBAL POSITIONING SYSTEM; TSUNAMI WAVES; SEISMOLOGY; EARTHQUAKES 20090041774 California Inst. of Tech., Pasadena, CA, United States Rover Slip Validation and Prediction Algorithm Yen, Jeng; NASA Tech Briefs, December 2009; December 2009; pp. 2; In English Report No.(s): NPO-45240; Copyright; Avail.: CASI: A01, Hardcopy Avail Online: http://hdl.handle.net/2060/20090041774 http://www.techbriefs.com/component/content/article/6376 A physical-based simulation has been developed for the Mars Exploration Rover (MER) mission that applies a slope-induced wheel-slippage to the rover location estimator. Using the digital elevation map from the stereo images, the computational method resolves the quasi-dynamic equations of motion that incorporate the actual wheel-terrain speed to estimate the gross velocity of the vehicle. Based on the empirical slippage measured by the Visual Odometry software of the rover, this algorithm computes two factors for the slip model by minimizing the distance of the predicted and actual vehicle location, and then uses the model to predict the next drives. This technique, which has been deployed to operate the MER rovers in the extended mission periods, can accurately predict the rover position and attitude, mitigating the risk and uncertainties in the path planning on high-slope areas. Author MARS EXPLORATION; ROVING VEHICLES; SLOPES; TRAJECTORY PLANNING; POSITION (LOCATION); EQUATIONS OF MOTION; DEPLOYMENT 20090041775 NASA Glenn Research Center, Cleveland, OH, United States Adaptive Morphological Feature-Based Object Classifier for a Color Imaging System McDowell, Mark; Gray, Elizabeth; NASA Tech Briefs, December 2009; December 2009; pp. 23-2; In English; Original contains color illustrations Report No.(s): LEW-18291-1; Copyright; Avail.: CASI: A01, Hardcopy Avail Online: http://hdl.handle.net/2060/20090041775 Utilizing a Compact Color Microscope Imaging System (CCMIS), a unique algorithm has been developed that combines human intelligence along with machine vision techniques to produce an autonomous microscope tool for biomedical, industrial, and space applications. This technique is based on an adaptive, morphological, feature-based mapping function comprising 24 mutually inclusive feature metrics that are used to determine the metrics for complex cell/objects derived from color image analysis. Some of the features include: Area (total numbers of non-background pixels inside and including the perimeter), Bounding Box (smallest rectangle that bounds and object), centerX (x-coordinate of intensity-weighted, center-of-mass of an entire object or multi-object blob), centerY (y-coordinate of intensity-weighted, center-of-mass, of an entire object or multi-object blob), Circumference (a measure of circumference that takes into account whether neighboring pixels are diagonal, which is a longer distance than horizontally or vertically joined pixels), . Elongation (measure of particle elongation given as a number between 0 and 1. If equal to 1, the particle bounding box is square. As the elongation decreases from 1, the particle becomes more elongated), . Ext_vector (extremal vector), . Major Axis (the length of a major axis of a smallest ellipse encompassing an object), . Minor Axis (the length of a minor axis of a smallest ellipse encompassing an object), . Partial (indicates if the particle extends beyond the field of view), . Perimeter Points (points that make up a particle perimeter), . Roundness [(4(pi) x area)/perimeter(squared)) the result is a measure of object roundness, or compactness, given as a value between 0 and 1. The greater the ratio, the rounder the object.], . Thin in center (determines if an object becomes thin in the center, (figure-eight-shaped), . Theta (orientation of the major axis), . Smoothness and color metrics for each component (red, green, blue) the minimum, maximum, average, and standard deviation within the particle are tracked. These metrics can be used for autonomous analysis of color images from a microscope, video camera, or digital, still image. It can also automatically identify tumor morphology of stained images and has been used to detect stained cell phenomena (see figure). Author COLOR; IMAGING TECHNIQUES; MORPHOLOGY; CLASSIFIERS; IMAGE ANALYSIS; FIELD OF VIEW 20090041776 NASA Glenn Research Center, Cleveland, OH, United States Method of Heating a Foam-Based Catalyst Bed Fortini, Arthur J.; Williams, Brian E.; McNeal, Shawn R.; NASA Tech Briefs, December 2009; December 2009; pp. 1; In English Report No.(s): LEW-18155-1; Copyright; Avail.: CASI: A01, Hardcopy Avail Online: http://hdl.handle.net/2060/20090041776 http://www.techbriefs.com/component/content/article/6366 A method of heating a foam-based catalyst bed has been developed using silicon carbide as the catalyst support due to its readily accessible, high surface area that is oxidation-resistant and is electrically conductive. The foam support may be resistively heated by passing an electric current through it. This allows the catalyst bed to be heated directly, requiring less power to reach the desired temperature more quickly. Designed for heterogeneous catalysis, the method can be used by the petrochemical, chemical processing, and power-generating industries, as well as automotive catalytic converters. Catalyst beds must be heated to a light-off temperature before they catalyze the desired reactions. This typically is done by heating the assembly that contains the catalyst bed, which results in much of the power being wasted and/or lost to the surrounding environment. The catalyst bed is heated indirectly, thus requiring excessive power. With the electrically heated catalyst bed, virtually all of the power is used to heat the support, and only a small fraction is lost to the surroundings. Although the light-off temperature of most catalysts is only a few hundred degrees Celsius, the electrically heated foam is able to achieve temperatures of 1,200 C. Lower temperatures are achievable by supplying less electrical power to the foam. Furthermore, because of the foam s open-cell structure, the catalyst can be applied either directly to the foam ligaments or in the form of a catalyst- containing washcoat. This innovation would be very useful for heterogeneous catalysis where elevated temperatures are needed to drive the reaction. Author HEATING; CATALYSTS; FOAMS; HETEROGENEITY; HIGH TEMPERATURE 20090041777 LightSmyth Technologies, Inc., Eugene, OR, United States Fabricating Radial Groove Gratings Using Projection Photolithography Iazikov, Dmitri; Mossberg, Thomas W.; NASA Tech Briefs, December 2009; December 2009; pp. 1; In English Report No.(s): GSC-15686-1; Copyright; Avail.: CASI: A01, Hardcopy Avail Online: http://hdl.handle.net/2060/20090041777 http://www.techbriefs.com/component/content/article/6364 Projection photolithography has been used as a fabrication method for radial grove gratings. Use of photolithographic method for diffraction grating fabrication represents the most significant breakthrough in grating technology in the last 60 years, since the introduction of holographic written gratings. Unlike traditional methods utilized for grating fabrication, this method has the advantage of producing complex diffractive groove contours that can be designed at pixel-by-pixel level, with pixel size currently at the level of 45 45 nm. Typical placement accuracy of the grating pixels is 10 nm over 30 nm. It is far superior to holographic, mechanically ruled or direct e-beam written gratings and results in high spatial coherence and low spectral cross-talk. Due to the smooth surface produced by reactive ion etch, such gratings have a low level of randomly scattered light. Also, due to high fidelity and good surface roughness, this method is ideally suited for fabrication of radial groove gratings. The projection mask is created using a laser writer. A single crystal silicon wafer is coated with photoresist, and then the projection mask, with its layer of photoresist, is exposed for patterning in a stepper or scanner. To develop the photoresist, the fabricator either removes the exposed areas (positive resist) of the unexposed areas (negative resist). Next, the patterned and developed photoresist silicon substrate is subjected to reactive ion etching. After this step, the substrate is cleaned. The projection mask is fabricated according to electronic design files that may be generated in GDS file format using any suitable CAD (computer-aided design) or other software program. Radial groove gratings in off-axis grazing angle of incidence mount are of special interest for x-ray spectroscopy, as they allow achieving higher spectral resolution for the same grating area and have lower alignment tolerances than traditional in-plane grating scheme. This is especially critical for NASA Constellation- X project that will utilize hundreds of gratings all of which need to be precisely aligned for x-ray observation of space. Author PHOTOLITHOGRAPHY; GROOVES; GRATINGS (SPECTRA); FABRICATION; SINGLE CRYSTALS; SPECTRAL RESOLUTION 20090041778 NASA Goddard Space Flight Center, Greenbelt, MD, United States Gratings Fabricated on Flat Surfaces and Reproduced on Non-Flat Substrates Content, David; Iazikov, Dmitri; Mossberg, Thomas W.; Greiner, Christopher M.; NASA Tech Briefs, December 2009; December 2009; pp. 17-1; In English Report No.(s): GSC-15769-1; Copyright; Avail.: CASI: A01, Hardcopy Avail Online: http://hdl.handle.net/2060/20090041778 http://www.techbriefs.com/component/content/article/6362 A method has been developed for fabricating gratings on flat substrates, and then reproducing the groove pattern on a curved (concave or convex) substrate and a corresponding grating device. First, surface relief diffraction grating grooves are formed on flat substrates. For example, they may be fabricated using photolithography and reactive ion etching, maskless lithography, holography, or mechanical ruling. Then, an imprint of the grating is made on a deformable substrate, such as plastic, polymer, or other materials using thermoforming, hot or cold embossing, or other methods. Interim stamps using electroforming, or other methods, may be produced for the imprinting process or if the same polarity of the grating image is required. The imprinted, deformable substrate is then attached to a curved, rigid substrate using epoxy or other suitable adhesives. The imprinted surface is facing away from the curved rigid substrate. As an alternative fabrication method, after grating is imprinted on the deformable substrate as described above, the grating may be coated with thin conformal conductive layer (for example, using vacuum deposition of gold). Then the membrane may be mounted over an opening in a pressured vessel in a manner of a membrane on a drum, grating side out. The pressure inside of the vessel may be changed with respect to the ambient pressure to produce concave or convex membrane surface. The shape of the opening may control the type of the surface curvature (for example, a circular opening would create spherical surface, oval opening would create toroidal surface, etc.). After that, well-known electroforming methods may be used to create a replica of the grating on the concave or convex membrane. For example, the pressure vessel assembly may be submerged into an electro-forming solution and negative electric potential applied to the metal coated membrane using an insulated wire. Positive electric potential may be then applied to a nickel or other metal plate submerged into the same solution. Metal ions would transfer from the plate through the solution into the membrane, producing high fidelity metal replica of the grating on the membrane. In one variation, an adhesive may be deposited on the deformable substrate, and then cured without touching the rigid, curved substrate. Edges of the deformable substrate may be attached to the rigid substrate to ensure uniform deformation of the deformable substrate. The assembly may be performed in vacuum, and then taken out to atmospheric pressure conditions to ensure that no air is trapped between the deformable and rigid substrates. Alternatively, a rigid surface with complementary curvature to the rigid substrate may be used to ensure uniform adhesion of the deformable substrate to the rigid substrate. Liquid may be applied to the surface of the deformable substrate to uniformly distribute pressure across its surface during the curing or hardening of the adhesive, or the film may be pressed into the surface using a deformable object or surface. After the attachment is complete, the grooves may be coated with reflective or dielectric layers to improve diffraction efficiency. Author GRATINGS (SPECTRA); FLAT SURFACES; FABRICATION; CONTROL SURFACES; PRESSURE VESSELS; PHOTOLITHOGRAPHY; METAL PLATES; ELECTROFORMING; ELECTRIC POTENTIAL 20090041779 Sequoia Scientific, Inc., United States Method for Measuring the Volume-Scattering Function of Water Agrawal, Yogesh C.; NASA Tech Briefs, December 2009; December 2009; pp. 1; In English Report No.(s): GSC-15395-1; Copyright; Avail.: CASI: A01, Hardcopy Avail Online: http://hdl.handle.net/2060/20090041779 http://www.techbriefs.com/component/content/article/6365 The volume scattering function (VSF) of seawater affects visibility, remote sensing properties, in-water light propagation, lidar performance, and the like. Currently, it s possible to measure only small forward angles of VSF, or to use cumbersome, large, and non-autonomous systems. This innovation is a method of measuring the full range of VSF using a portable instrument. A single rapid-sensing photosensor is used to scan a green laser beam, which delivers the desired measurement. By using a single sensor, inter-calibration is avoided. A compact design is achieved by using drift-free detector electronics, fiber optics, and a new type of photomultiplier. This provides a high angular resolution of 1 or better, as well as the ability to focus in on a VSF region of particular interest. Currently, the total scattering of light is measured as a difference from the other two parts of the light budget equation. This innovation will allow the direct calculation of the total scattering of light by taking an integral of the VSF over all angles. This directly provides one of the three components of the light budget equation, allowing greater versatility in its calculation. Author SCATTERING FUNCTIONS; RADIATION MEASURING INSTRUMENTS; SEA WATER; REMOTE SENSING; VISIBILITY; OPTICAL RADAR; LIGHT SCATTERING; ANGULAR RESOLUTION; FIBER OPTICS 20090041780 United Space Alliance, Houston, TX, United States Supply-Chain Optimization Template Quiett, William F.; Sealing, Scott L.; NASA Tech Briefs, December 2009; December 2009; pp. 2; In English Report No.(s): MSC-23423-1; Copyright; Avail.: CASI: A01, Hardcopy Avail Online: http://hdl.handle.net/2060/20090041780 http://www.techbriefs.com/component/content/article/6377 The Supply-Chain Optimization Template (SCOT) is an instructional guide for identifying, evaluating, and optimizing (including re-engineering) aerospace- oriented supply chains. The SCOT was derived from the Supply Chain Council s Supply-Chain Operations Reference (SCC SCOR) Model, which is more generic and more oriented toward achieving a competitive advantage in business. Derived from text COMMERCE; SUPPLYING; AEROSPACE INDUSTRY 20090041781 California Inst. of Tech., Pasadena, CA, United States Pilotless Frame Synchronization Using LDPC Code Constraints Jones, Christopher; Vissasenor, John; NASA Tech Briefs, December 2009; December 2009; pp. ; In English; Original contains color illustrations Report No.(s): NPO-45032; Copyright; Avail.: CASI: A01, Hardcopy Avail Online: http://hdl.handle.net/2060/20090041781 http://www.techbriefs.com/component/content/article/6351 A method of pilotless frame synchronization devised for low-density pilotless frame synchronization, symbols; instead, the selected The the bandwidth of the signal is associated with disadvantage processing needed for frame Derived from text BIT SYNCHRONIZATION; DATA PROCESSING; ERROR DETECTION CODES; SIGNAL TRANSMISSION 20090041782 Texas A&M Univ., United States Video System for Viewing From a Remote or Windowless Cockpit Banerjee, Amamath; NASA Tech Briefs, December 2009; December 2009; pp. 13-1; In English Report No.(s): MSC-23777-1; Copyright; Avail.: CASI: A01, Hardcopy Avail Online: http://hdl.handle.net/2060/20090041782 http://www.techbriefs.com/component/content/article/6354 A system of electronic hardware and software synthesizes, in nearly real time, an image of a portion of a scene surveyed by as many as eight video cameras aimed, in different directions, at portions of the scene. This is a prototype of systems that would enable a pilot to view the scene outside a remote or windowless cockpit. The outputs of the cameras are digitized. Direct memory addressing is used to store the data of a few captured images in sequence, and the sequence is repeated in cycles. Cylindrical warping is used in merging adjacent images at their borders to construct a mosaic image of the scene. The mosaic-image data are written to a memory block from which they can be rendered on a head-mounted display (HMD) device. A subsystem in the HMD device tracks the direction of gaze of the wearer, providing data that are used to select, for display, the portion of the mosaic image corresponding to the direction of gaze. The basic functionality of the system has been demonstrated by mounting the cameras on the roof of a van and steering the van by use of the images presented on the HMD device. Author DISPLAY DEVICES; VIEWING; COCKPITS; CAMERAS; REAL TIME OPERATION; CYLINDRICAL BODIES 20090041783 NASA Glenn Research Center, Cleveland, OH, United States Detecting Phase Boundaries in Hard-Sphere Suspensions McDowell, Mark; Rogers, Richard B.; Gray, Elizabeth; NASA Tech Briefs, December 2009; December 2009; pp. 5-; In English; Original contains color and black and white illustrations Report No.(s): LEW-18157-1; Copyright; Avail.: CASI: A01, Hardcopy Avail Online: http://hdl.handle.net/2060/20090041783 http://www.techbriefs.com/component/content/article/6340 A special image-data-processing technique has been developed for use in experiments that involve observation, via optical microscopes equipped with electronic cameras, of moving boundaries between the colloidal-solid and colloidal-liquid phases of colloidal suspensions of monodisperse hard spheres. During an experiment, it is necessary to adjust the position of a microscope to keep the phase boundary within view. A boundary typically moves at a speed of the order of microns per hour. Because an experiment can last days or even weeks, it is impractical to require human intervention to keep the phase boundary in view. The present image-data-processing technique yields results within a computation time short enough to enable generation of automated-microscope-positioning commands to track the moving phase boundary Derived from text BOUNDARIES; COLLOIDS; IMAGE PROCESSING; PHASE TRANSFORMATIONS; CRYSTALLIZATION 20090041784 Northrop Grumman Corp., United States Waveguide Transition for Submillimeter-Wave MMICs Leong, Kevin M.; Deal, William R.; Radisic, Vesna; Mei, Xiaobing; Uyeda, Jansen; Lai, Richard; Fung, King Man; Gaier, Todd C.; NASA Tech Briefs, December 2009; December 2009; pp. 1; In English Report No.(s): NPO-46237; Copyright; Avail.: CASI: A01, Hardcopy Avail Online: http://hdl.handle.net/2060/20090041784 http://www.techbriefs.com/component/content/article/6350 An integrated waveguide-to-MMIC (monolithic microwave integrated circuit) chip operating in the 300-GHz range is designed to operate well on high-permittivity semiconductor substrates typical for an MMIC amplifier, and allows a wider MMIC substrate to be used, enabling integration with larger MMICs (power amplifiers). The waveguide-to- CBCPW (conductor-backed coplanar waveguide) transition topology is based on an integrated dipole placed in the E-plane of the waveguide module. It demonstrates low loss and good impedance matching. Measurement and simulation demonstrate that the loss of the transition and waveguide loss is less than 1-dB over a 340-to-380-GHz bandwidth. A transition is inserted along the propagation direction of the waveguide. This transition uses a planar dipole aligned with the maximum E-field of the TE10 waveguide mode as an inter face between the waveguide and the MMIC. Mode conversion between the coplanar striplines (CPS) that feed the dipole and the CBCPW transmission line is accomplished using a simple air-bridge structure. The bottom side ground plane is truncated at the same reference as the top-side ground plane, leaving the end of the MMIC suspended in air. Author INTEGRATED CIRCUITS; MICROWAVE CIRCUITS; SUBMILLIMETER WAVES; TRANSMISSION LINES; WAVEGUIDES; IMPEDANCE MATCHING; SEMICONDUCTORS (MATERIALS); POWER AMPLIFIERS 20090041825 NASA Langley Research Center, Hampton, VA, United States Benefits to the Simulation Training Community of a New ANSI Standard for the Exchange of Aero Simulation Models Hildreth, Bruce L.; Jackson, E. Bruce; November 30, 2009; In English; Interservice/Industry Training, Simulation and Education Conference (I/ITSEC 2009), 30 Nov. - 3 Dec. 2009, Orlando, FL, United States; Original contains color and black and white illustrations Contract(s)/Grant(s): WBS 869021.05.07.07.21 Report No.(s): 9019-0929-0301; LF99-9097; Copyright; Avail.: CASI: A02, Hardcopy Avail Online: http://hdl.handle.net/2060/20090041825 The American Institute of Aeronautics Astronautics (AIAA) Modeling and Simulation Technical Committee is in final preparation of a new standard for the exchange of flight dynamics models. The standard will become an ANSI standard and is under consideration for submission to ISO for acceptance by the international community. some aspects that should provide benefits to the simulation training community. Use of the new standard by the training simulation community will reduce development, maintenance and technical refresh investment on each device. Furthermore, it will significantly lower the cost of performing model updates to improve fidelity or expand the envelope of the training device. Higher flight fidelity should result in better transfer of training, a direct benefit to the pilots under instruction. Costs of adopting the standard are minimal and should be paid back within the cost of the first use for that training device. standard achieves these advantages by making it easier to update the aerodynamic model. It provides a standard format for the model in a custom eXtensible Markup Language (XML) grammar, the Dynamic Aerospace Vehicle Exchange Markup Language (DAVE-ML). It employs an existing XML grammar, MathML, to describe the aerodynamic model in an input data file, eliminating the requirement for actual software compilation. The major components of the aero model become simply an input data file, and updates are simply new XML input files. It includes naming and axis system conventions to further simplify the exchange of information. Author SIMULATION; TRAINING DEVICES; FLIGHT SIMULATORS; STANDARDS; STANDARDIZATION 20090041828 NASA Langley Research Center, Hampton, VA, United States A Multidisciplinary Tool for Systems Analysis of Planetary Entry, Descent, and Landing (SAPE) Samareah, Jamshid A.; November 2009; In English; Original contains color and black and white illustrations Contract(s)/Grant(s): WBS 346620.04.07.01.01.02 Report No.(s): NASA/TM-2009-215950; L-19730; LF99-9217; No Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090041828 SAPE is a Python-based multidisciplinary analysis tool for systems analysis of planetary entry, descent, and landing (EDL) for Venus, Earth, Mars, Jupiter, Saturn, Uranus, Neptune, and Titan. The purpose of SAPE is to provide a variable-fidelity capability for conceptual and preliminary analysis within the same framework. SAPE includes the following analysis modules: geometry, trajectory, aerodynamics, aerothermal, thermal protection system, and structural sizing. SAPE uses the Python language-a platform-independent open-source software for integration and for the user interface. The development has relied heavily on the object-oriented programming capabilities that are available in Python. Modules are provided to interface with commercial and government off-the-shelf software components (e.g., thermal protection systems and finite-element analysis). SAPE runs on Microsoft Windows and Apple Mac OS X and has been partially tested on Linux. Author SYSTEMS ANALYSIS; ATMOSPHERIC ENTRY; DESCENT; LANDING; SYSTEMS INTEGRATION; LANGUAGE PROGRAMMING; MULTIDISCIPLINARY DESIGN OPTIMIZATION 20090041834 NASA Glenn Research Center, Cleveland, OH, United States Broadband Shock Noise in Internally-Mixed Dual-Stream Jets Bridges, James E.; November 2009; In English; 15th Aeroacoustics Conference (30th AIAA Aeroacoustics Conference), 11-13 May 2009, Miami, FL, United States Contract(s)/Grant(s): WBS 984754.02.07.03.17.03 Report No.(s): NASA/TM-2009-215817; AIAA-Paper-2009-3210; E-17079; No Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090041834 Broadband shock noise (BBSN) has been studied in some detail in single-flow jets and recently in dual-stream jets with separate flow exhaust systems. Shock noise is of great concern in these latter cases because of the noise created for the aircraft cabin by the underexpanded nozzle flow at cruise. Another case where shock noise is of concern is in the case of future supersonic aircraft that are expected to have bypass ratios small enough to justify internally mixed exhaust systems, and whose mission will push cycles to the point of imperfectly expanded flows. Dual-stream jets with internally mixed plume have some simplifying aspects relative to the separate flow jets, having a single shock structure given by the common nozzle pressure. This is used to separate the contribution of the turbulent shear layer to the broadband shock noise. Shock structure is held constant while the geometry and strength of the inner and merged shear layers are varying by changing splitter area ratio and core stream temperature. Flow and noise measurements are presented which document the efforts at separating the contribution of the inner shear layer to the broadband shock noise. Author AERODYNAMIC NOISE; NOZZLE FLOW; NOISE MEASUREMENT; FLOW NOISE; SHOCK WAVES; BYPASS RATIO; SHEAR LAYERS 20090041838 NASA Johnson Space Center, Houston, TX, United States Bisphosphonate as a Countermeasure to Space Flight-Induced Bone Loss Spector, Elisabeth; LeBlanc, A.; Sibonga, J.; Matsumoto, T.; Jones, J.; Smith, S. M.; Shackelford, L.; Shapiro, J.; Lang, T.; Evans, H.; Spector, E.; Nakamura, T.; Kohri, K.; Ohshima, H.; [2009]; In English; HRP Investigators' Workshop, 3-5 Feb. 2010, Houston, TX, United States Report No.(s): JSC-CN-19424; Copyright; Avail.: CASI: A01, Hardcopy Avail Online: http://hdl.handle.net/2060/20090041838 The purpose of this research is to determine whether anti-resorptive pharmaceuticals such as bisphosphonates, in conjunction with the routine in-flight exercise program, will protect ISS crewmembers from the regional decreases in bone mineral density and bone strength and the increased renal stone risk documented on previous long-duration space flights [1-3]. Losses averaged ~ 1 to 2 percent per month in such regions as the lumbar spine and hip. Although losses showed significant heterogeneity among individuals and between bones within a given subject, space flight-induced bone loss was a consistent finding. More than 90 percent of astronauts and cosmonauts on long-duration flights (average 171 days) aboard Mir and the ISS, had a minimum 5 percent loss in at least one skeletal site, 40 percent of them had a 10 percent or greater loss in at least one skeletal site, and 22 percent of the Mir cosmonauts experienced a 15 to 20 percent loss in at least one site. These losses occurred even though the crewmembers performed time-consuming in-flight exercise regimens. Moreover, a recent study of 16 ISS astronauts using quantitative computed tomography (QCT) demonstrated trabecular bone losses from the hip averaging 2.3 percent per month [4]. These losses were accompanied by significant losses in hip bone strength that may not be recovered quickly [5]. This rapid loss of bone mass results from a combination of increased and uncoupled remodeling, as demonstrated by increased resorption with little or no change in bone formation markers [6-7]. This elevated remodeling rate likely affects the cortical and trabecular architecture and may lead to irreversible changes. In addition to bone loss, the resulting hypercalciuria increases renal stone risk. Therefore, it is logical to attempt to attenuate this increased remodeling with anti-resorption drugs such as bisphosphonates. Success with alendronate was demonstrated in a bed rest study [8]. This work has been extended to space flight and two dosing regimens: 1) an oral dose of 70 mg of alendronate taken weekly during flight or 2) a single intravenous (IV) dose of 4 mg of zoledronic acid given several weeks before flight. Currently the study is focusing on the oral option because of NASA s safety concerns with the IV-administered drug. The protocol requests 10 male or female crewmembers on ISS flights of 90 days or longer. Controls are 16 previous ISS crewmembers with QCT scans of the hip performed by these same investigators. The primary outcome measure for this study is hip trabecular bone mineral density measured by QCT, but other measures of bone mass are performed including peripheral QCT (pQCT) and dual-energy x-ray absorptiometry. Serum and urinary bone markers and renal stone risk measured before, during, and after flight are included. Postflight data are currently being collected from 2 ISS crewmembers. Two additional crewmembers will return this spring after ~6-month missions. To date no untoward effects have been encountered. Author BONE DEMINERALIZATION; BONE MINERAL CONTENT; COUNTERMEASURES; INTRAVENOUS PROCEDURES; PHYSICAL EXERCISE; ASTRONAUTS; MUSCULOSKELETAL SYSTEM Additions to the NASA Aeronautics and Space Database as of 12/23/2009 20090041865 NASA Johnson Space Center, Houston, TX, United States Implementing Earned Value Management in the CxP EVA Systems Project Office Sorge, Les L.; [2009]; In English; Project Management Challenge 2010, 9-10 Feb. 2010, Galveston, TX, United States; Original contains color illustrations Contract(s)/Grant(s): 731384 Report No.(s): JSC-CN-19416; Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090041865 Earned Value Management (EVM), like project management, is as much art as it is science to develop an implementation plan for a project. This presentation will cover issues that were overcome and the implementation strategy to deploy Earned Value Management (EVM) within the Constellation Program (CxP), EVA Systems Project Office (ESPO), as well as discuss additional hurdles that currently prevent the organization from optimizing EVM. Each organization and each project within an organization needs to mold an EVM implementation plan around existing processes and tools, while at the same time revising those existing processes and tools as necessary to make them compatible with EVM. The ESPO EVM implementation covers work breakdown structure, organizational breakdown structure, control account, work/planning package development; integrated master schedule development using an integrated master plan; incorporating reporting requirements for existing funding process such as Planning, Programming, Budgeting, and Execution (PPBE) and JSC Internal Task Agreements (ITA); and interfacing with other software tools such as the Systems Applications and Products (SAP) accounting system and the CxP wInsight EVM analysis tool. However, there are always areas for improvement and EVM is no exception. As EVM continues to mature within the NASA CxP, these areas will continue to be worked to resolution to provide the Program Managers, Project Managers, and Control Account Managers the best EVM data possible to make informed decisions. Author PROJECT MANAGEMENT; BUDGETING; CONSTELLATION PROGRAM 20090041867 NASA Johnson Space Center, Houston, TX, United States Lunar Sample Compendium Meyer, C.; [2009]; In English; 41st Lunar and Planetary Science Conference, 1 Mar. 2010, Woodlands, TX, United States Report No.(s): JSC-CN-19298; No Copyright; Avail.: CASI: A01, Hardcopy Avail Online: http://hdl.handle.net/2060/20090041867 The Lunar Sample Compendium is a succinct summary of what has been learned from the study of Apollo and Luna samples of the Moon. Basic information is compiled, sample-by-sample, in the form of an advanced catalog in order to provide a basic description of each sample. Information presented is carefully attributed to the original source publication, thus the Compendium also serves as a ready access to the now vast scientific literature pertaining to lunar smples. The Lunar Sample Compendium is a work in progress (and may always be). Future plans include: adding sections on additional samples, adding new thin section photomicrographs, replacing the faded photographs with newly digitized photos from the original negatives, attempting to correct the age data using modern decay constants, adding references to each section, and adding an internal search engine. Derived from text LUNAR GEOLOGY; LUNAR ROCKS; SELENOLOGY; LUNAR COMPOSITION; LUNAR MARIA; CHARACTERIZATION; DESCRIPTIONS; DOCUMENTATION Additions to the NASA Aeronautics and Space Database as of 12/24/2009 20090042106 NASA Johnson Space Center, Houston, TX, United States Sensorimotor Adaptability Training Improves Motor and Dual-Task Performance Bloomberg, J.J.; Peters, B.T.; Mulavara, A.P.; Brady, R.; Batson, C.; Cohen, H.S.; [2009]; In English; NASA Human Research Program Investigators' Workshop, 3-5 Feb. 2010, Houston, TX, United States Contract(s)/Grant(s): NCC9-58 Report No.(s): JSC-CN-19370; Copyright; Avail.: CASI: A01, Hardcopy Avail Online: http://hdl.handle.net/2060/20090042106 The overall objective of our project is to develop a sensorimotor adaptability (SA) training program designed to facilitate recovery of functional capabilities when astronauts transition to different gravitational environments. The goal of our current study was to determine if SA training using variation in visual flow and support surface motion produces improved performance in a novel sensory environment and demonstrate the retention characteristics of SA training. Author ADAPTATION; HUMAN PERFORMANCE; ASTRONAUT TRAINING; SENSORIMOTOR PERFORMANCE 20090042311 NASA Dryden Flight Research Center, Edwards, CA, United States UAVSAR: Airborne L-band Radar for Repeat Pass Interferometry Moes, Timothy R.; December 2009; In English; Introduction to Radar Remote Sensing: Theory, Techniques, and Applications Workshop, 1 Dec. 2009, San Jose, Costa Rica; Original contains color and black and white illustrations Report No.(s): DFRC-1095; No Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090042311 The primary objectives of the UAVSAR Project were to: a) develop a miniaturized polarimetric L-band synthetic aperture radar (SAR) for use on an unmanned aerial vehicle (UAV) or piloted vehicle. b) develop the associated processing algorithms for repeat-pass differential interferometric measurements using a single antenna. c) conduct measurements of geophysical interest, particularly changes of rapidly deforming surfaces such as volcanoes or earthquakes. Two complete systems were developed. Operational Science Missions began on February 18, 2009 ... concurrent development and testing of the radar system continues. Author AIRBORNE RADAR; SYNTHETIC APERTURE RADAR; ULTRAHIGH FREQUENCIES; PILOTLESS AIRCRAFT; INTERFEROMETRY; GEOPHYSICS; POLARIMETRY; ALGORITHMS; MINIATURIZATION 20090042346 NASA Glenn Research Center, Cleveland, OH, United States Highly Efficient Design-of-Experiments Methods for Combining CFD Analysis and Experimental Data Anderson, Bernhard H.; Haller, Harold S.; January 05, 2009; In English; 47th AIAA Aerospace Sciences, 5-9 Jan. 2009, Orlando, FL, United States; Original contains color and black and white illustrations Contract(s)/Grant(s): NNL04AA11B Report No.(s): E-17138-V; Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090042346 It is the purpose of this study to examine the impact of "highly efficient" Design-of-Experiments (DOE) methods for combining sets of CFD generated analysis data with smaller sets of Experimental test data in order to accurately predict performance results where experimental test data were not obtained. The study examines the impact of micro-ramp flow control on the shock wave boundary layer (SWBL) interaction where a complete paired set of data exist from both CFD analysis and Experimental measurements By combining the complete set of CFD analysis data composed of fifteen (15) cases with a smaller subset of experimental test data containing four/five (4/5) cases, compound data sets (CFD/EXP) were generated which allows the prediction of the complete set of Experimental results No statistical difference were found to exist between the combined (CFD/EXP) generated data sets and the complete Experimental data set composed of fifteen (15) cases. The same optimal micro-ramp configuration was obtained using the (CFD/EXP) generated data as obtained with the complete set of Experimental data, and the DOE response surfaces generated by the two data sets were also not statistically different. Author COMPUTATIONAL FLUID DYNAMICS; EXPERIMENT DESIGN; SHOCK WAVES; WAVE INTERACTION 20090042356 NASA Glenn Research Center, Cleveland, OH, United States Design of Experiments for Both Experimental and Analytical Study of Exhaust Plume Effects on Sonic Boom Castner, Raymond S.; January 05, 2009; In English; 47th AIAA Aerospace Sciences Meeting Including The New Horizons Forum and Aerospace Exposition, 5-8 Jan. 2009, Orlando, Fl, United States; Original contains color and black and white illustrations Report No.(s): E-17141; No Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090042356 Computational fluid dynamics (CFD) analysis has been performed to study the plume effects on sonic boom signature for isolated nozzle configurations. The objectives of these analyses were to provide comparison to past work using modern CFD analysis tools, to investigate the differences of high aspect ratio nozzles to circular (axisymmetric) nozzles, and to report the effects of under expanded nozzle operation on boom signature. CFD analysis was used to address the plume effects on sonic boom signature from a baseline exhaust nozzle. Nearfield pressure signatures were collected for nozzle pressure ratios (NPRs) between 6 and 10. A computer code was used to extrapolate these signatures to a ground-observed sonic boom N-wave. Trends show that there is a reduction in sonic boom N-wave signature as NPR is increased from 6 to 10. As low boom designs are developed and improved, there will be a need for understanding the interaction between the aircraft boat tail shocks and the exhaust nozzle plume. These CFD analyses will provide a baseline study for future analysis efforts. For further study, a design of experiments has been conducted to develop a hybrid method where both CFD and small scale wind tunnel testing will validate the observed trends. The CFD and testing will be used to screen a number of factors which are important to low boom propulsion integration, including boat tail angle, nozzle geometry, and the effect of spacing and stagger on nozzle pairs. To design the wind tunnel experiment, CFD was instrumental in developing a model which would provide adequate space to observe the nozzle and boat tail shock structure without interference from the wind tunnel walls. Author COMPUTATIONAL FLUID DYNAMICS; EXHAUST NOZZLES; PLUMES; EXPERIMENT DESIGN; WIND TUNNEL TESTS; SONIC BOOMS; PRESSURE RATIO; HIGH ASPECT RATIO; NOZZLE GEOMETRY 20090042358 NASA Glenn Research Center, Cleveland, OH, United States A Multi-Mode Blade Damping Control using Shunted Piezoelectric Transducers with Active Feedback Structure Choi, Benjamin; Morrison, Carlos; Min, James; March 24, 2009; In English; P-SAR Conference, 24-26 Mar. 2009, Myrtle Beach, SC, United States; Original contains color illustrations Contract(s)/Grant(s): WBS 561581.02.08.03.15.03 Report No.(s): E-17142-V; No Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090042358 The Structural Dynamics and. Mechanics branch (RXS) is developing smart adaptive structures to improve fan blade damping at resonances using piezoelectric (PE) transducers. In this presentation, only one shunted PE transducer was used to demonstrate active control of multi-mode blade resonance damping on a titanium alloy (Ti-6A1-4V) flat plate model, regardless of bending, torsion, and 2-stripe modes. This work would have a significant impact on the conventional passive shunt damping world because the standard feedback control design tools can now be used to design and implement electric shunt for vibration control. In other words, the passive shunt circuit components using massive inductors and. resistors for multi-mode resonance control can be replaced with digital codes. Furthermore, this active approach with multi patches can simultaneously control several modes in the engine operating range. Dr. Benjamin Choi presented the analytical and experimental results from this work at the Propulsion-Safety and. Affordable Readiness (P-SAR) Conference in March, 2009. Author FAN BLADES; PIEZOELECTRIC TRANSDUCERS; DYNAMIC STRUCTURAL ANALYSIS; DYNAMIC RESPONSE; SMART STRUCTURES; ELECTRIC CONTROL; VIBRATION DAMPING; TITANIUM ALLOYS; FEEDBACK CONTROL 20090042363 NASA Johnson Space Center, Houston, TX, United States Lunar Human Research Requirements (LHRR) Denkins, Pamela; November 05, 2009; In English Report No.(s): HRP-47076; JSC-CN-19428; No Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090042363 Biomedical research will be conducted during transit and on the surface of the Moon to prepare for extended stays on the Moon and to prepare for the exploration of Mars. The objective of the Human Research Program (HRP) is to preserve the health and enhance performance of astronaut explorers. Specific objectives of the HRP include developing the knowledge, capabilities, and necessary countermeasures and technologies in support of human space exploration; focusing on mitigating the highest risks to crew health and performance; and defining and improving human spaceflight medical, environmental, behavioral, and human factors standards. This document contains a detailed description of the resource accommodations, interfaces, and environments to be provided by the Constellation Program (CxP) to support the HRP research in transit and on the lunar surface. Covered, specifically, are the requirements for mass and volume transport; crew availability; ground operations, baseline data collection, and payload processing; power, and data. Volumes and mass are given for transport of conditioned samples only. They do not account for the engineering solution that the Constellation Program will implement (refrigerator/freezer volume/mass). This document does not account for requirements on the Orion vehicle for transportation to and from the International Space Station (ISS). The ISS Program has supplied requirements for this mission. Derived from text AEROSPACE MEDICINE; CONSTELLATION PROGRAM; LUNAR SURFACE; MANNED SPACE FLIGHT; LUNAR ENVIRONMENT; BIOASTRONAUTICS; LUNAR LOGISTICS; MISSION PLANNING 20090042364 NASA Glenn Research Center, Cleveland, OH, United States Thermal Interface Evaluation of Heat Transfer from a Pumped Loop to Titanium-Water Thermosyphons Jaworske, Donald A.; Sanzi, James L.; Gibson, Marc A.; Sechkar, Edward A.; August 02, 2009; In English; 7th International Energy Conversion Engineering Conference, 2-5 Aug. 2009, Denver, CO, United States; Original contains color illustrations Contract(s)/Grant(s): WBS 463169.04.03.05.04 Report No.(s): E-17025-P; Copyright; Avail.: CASI: A02, Hardcopy Avail Online: http://hdl.handle.net/2060/20090042364 Titanium-water thermosyphons are being considered for use in the heat rejection system for lunar outpost fission surface power. Key to their use is heat transfer between a closed loop heat source and the heat pipe evaporators. This work describes laboratory testing of several interfaces that were evaluated for their thermal performance characteristics, in the temperature range of 350 to 400 K, utilizing a water closed loop heat source and multiple thermosyphon evaporator geometries. A gas gap calorimeter was used to measure heat flow at steady state. Thermocouples in the closed loop heat source and on the evaporator were used to measure thermal conductance. The interfaces were in two generic categories, those immersed in the water closed loop heat source and those clamped to the water closed loop heat source with differing thermal conductive agents. In general, immersed evaporators showed better overall performance than their clamped counterparts. Selected clamped evaporator geometries offered promise. Author HEAT TRANSFER; THERMOSIPHONS; TITANIUM; WATER; INTERFACES; HEAT SOURCES 20090042365 NASA Glenn Research Center, Cleveland, OH, United States Towards an "All Speed" Unstructured Upwind Scheme Loh, Ching Y.; Jorgenson, Philip C.E.; June 22, 2009; In English; 19th AIAA Computational Fluid Dynamics Conference/39th AIAA Fluid Dynamics Conference, 22-25 Jun. 2009, San Antonio, TX, United States; Original contains color and black and white illustrations Contract(s)/Grant(s): WBS 561581.02.08.03.13.04 Report No.(s): E-17158-P; Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090042365 In the authors previous studies [1], a time-accurate, upwind finite volume method (ETAU scheme) for computing compressible flows on unstructured grids was proposed. The scheme is second order accurate in space and time and yields high resolution in the presence of discontinuities. The scheme features a multidimensional limiter and multidimensional numerical dissipation. These help to stabilize the numerical process and to overcome the annoying pathological behaviors of upwind schemes. In the present paper, it will be further shown that such multidimensional treatments also lead to a nearly all-speed or Mach number insensitive upwind scheme. For flows at very high Mach number, e.g., 10, local numerical instabilities or the pathological behaviors are suppressed, while for flows at very low Mach number, e.g., 0.02, computation can be directly carried out without invoking preconditioning. For flows in different Mach number regimes, i.e., low, medium, and high Mach numbers, one only needs to adjust one or two parameters in the scheme. Several examples with low and high Mach numbers are demonstrated in this paper. Thus, the ETAU scheme is applicable to a broad spectrum of flow regimes ranging from high supersonic to low subsonic, appropriate for both CFD (computational fluid dynamics) and CAA (computational aeroacoustics). Author UPWIND SCHEMES (MATHEMATICS); MACH NUMBER; COMPUTATIONAL FLUID DYNAMICS; COMPUTATIONAL AEROACOUSTICS; UNSTRUCTURED GRIDS (MATHEMATICS); FINITE VOLUME METHOD; DISCONTINUITY 20090042369 NASA Glenn Research Center, Cleveland, OH, United States A Lunar Surface System Supportability Technology Development Roadmap Oeftering, Richard C.; Struk, Peter M.; Taleghani, Barmac K.; September 14, 2009; In English; AIAA Space 2009 Conference and Exposition, 14-17 Sep. 2009, Pasadena, CA, United States; Original contains color illustrations Contract(s)/Grant(s): WBS 431767.04.01.04 Report No.(s): E-17160-P; No Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090042369 This paper discusses the establishment of a Supportability Technology Development Roadmap as a guide for developing capabilities intended to allow NASA's Constellation program to enable a supportable, sustainable and affordable exploration of the Moon and Mars. Presented is a discussion of "supportability", in terms of space facility maintenance, repair and related logistics and a comparison of how lunar outpost supportability differs from the International Space Station. Supportability lessons learned from NASA and Department of Defense experience and their impact on a future lunar outpost is discussed. A supportability concept for future missions to the Moon and Mars that involves a transition from a highly logistics dependent to a logistically independent operation is discussed. Lunar outpost supportability capability needs are summarized and a supportability technology development strategy is established. The resulting Lunar Surface Systems Supportability Strategy defines general criteria that will be used to select technologies that will enable future flight crews to act effectively to respond to problems and exploit opportunities in a environment of extreme resource scarcity and isolation. This strategy also introduces the concept of exploiting flight hardware as a supportability resource. The technology roadmap involves development of three mutually supporting technology categories, Diagnostics Test & Verification, Maintenance & Repair, and Scavenging & Recycling. The technology roadmap establishes two distinct technology types, "Embedded" and "Process" technologies, with different implementation and thus different criteria and development approaches. The supportability technology roadmap addresses the technology readiness level, and estimated development schedule for technology groups that includes down-selection decision gates that correlate with the lunar program milestones. The resulting supportability technology roadmap is intended to develop a set of technologies with widest possible capability and utility with a minimum impact on crew time and training and remain within the time and cost constraints of the Constellation program Author LUNAR SURFACE; CONSTELLATION PROGRAM; FLIGHT CREWS; LUNAR PROGRAMS; LESSONS LEARNED; INTERNATIONAL SPACE STATION; LOGISTICS; EDUCATION 20090042372 NASA Glenn Research Center, Cleveland, OH, United States Performance of an SOI Boot-Strapped Full-Bridge MOSFET Driver, Type CHT-FBDR, under Extreme Temperatures Patterson, Richard; Hammoud, Ahmad; September 2009; In English; Original contains color and black and white illustrations Contract(s)/Grant(s): NNC06BA07BWBS 724297.40.43.03.01 Report No.(s): E-17166-Inf; Copyright; Avail.: CASI: A02, Hardcopy Avail Online: http://hdl.handle.net/2060/20090042372 Electronic systems designed for use in deep space and planetary exploration missions are expected to encounter extreme temperatures and wide thermal swings. Silicon-based devices are limited in their wide-temperature capability and usually require extra measures, such as cooling or heating mechanisms, to provide adequate ambient temperature for proper operation. Silicon-On-Insulator (SOI) technology, on the other hand, lately has been gaining wide spread use in applications where high temperatures are encountered. Due to their inherent design, SOI-based integrated circuit chips are able to operate at temperatures higher than those of the silicon devices by virtue of reducing leakage currents, eliminating parasitic junctions, and limiting internal heating. In addition, SOI devices provide faster switching, consume less power, and offer improved radiation-tolerance. Very little data, however, exist on the performance of such devices and circuits under cryogenic temperatures. In this work, the performance of an SOI bootstrapped, full-bridge driver integrated circuit was evaluated under extreme temperatures and thermal cycling. The investigations were carried out to establish a baseline on the functionality and to determine suitability of this device for use in space exploration missions under extreme temperature conditions. Author CRYOGENIC TEMPERATURE; SOI (SEMICONDUCTORS); THERMAL CYCLING TESTS; FIELD EFFECT TRANSISTORS; INTEGRATED CIRCUITS; AMBIENT TEMPERATURE 20090042373 NASA Glenn Research Center, Cleveland, OH, United States A Wide Range Temperature Sensor Using SOI Technology Patterson, Richard L.; Elbuluk, Malik E.; Hammoud, Ahmad; May 24, 2009; In English; Original contains black and white illustrations Contract(s)/Grant(s): NNC06BA07BWBS 724297.40.43.03.01 Report No.(s): E-17167-P; Copyright; Avail.: CASI: A01, Hardcopy Avail Online: http://hdl.handle.net/2060/20090042373 Silicon-on-insulator (SOI) technology is becoming widely used in integrated circuit chips for its advantages over the conventional silicon counterpart. The decrease in leakage current combined with lower power consumption allows electronics to operate in a broader temperature range. This paper describes the performance of an SOIbased temperature sensor under extreme temperatures and thermal cycling. The sensor comprised of a temperature-to-frequency relaxation oscillator circuit utilizing an SOI precision timer chip. The circuit was evaluated under extreme temperature exposure and thermal cycling between -190 C and +210 C. The results indicate that the sensor performed well over the entire test temperature range and it was able to re-start at extreme temperatures. Author SOI (SEMICONDUCTORS); TEMPERATURE SENSORS; INTEGRATED CIRCUITS; ENERGY CONSUMPTION; THERMAL CYCLING TESTS; TIMING DEVICES; TEST RANGES 20090042375 NASA Glenn Research Center, Cleveland, OH, United States Raman Channel Temperature Measurement of SiC MESFET as a Function of Ambient Temperature and DC Power Ponchak, George E.; Eldridge, Jeffrey J.; Krainsky, Isay L.; June 07, 2009; In English; 2009 International Microwable Symposium, 7-12 Jun. 2009, Boston, MA, United States; Original contains color illustrations Contract(s)/Grant(s): WBS 645846.02.07.03.11.04.02 Report No.(s): E-17168-P; No Copyright; Avail.: CASI: A01, Hardcopy Avail Online: http://hdl.handle.net/2060/20090042375 Raman spectroscopy is used to measure the junction temperature of a Cree SiC MESFET as a function of the ambient temperature and DC power. The carrier temperature, which is approximately equal to the ambient temperature, is varied from 25 C to 450 C, and the transistor is biased with VDS=10V and IDS of 50 mA and 100 mA. It is shown that the junction temperature is approximately 52 and 100 C higher than the ambient temperature for the DC power of 500 and 1000 mW, respectively. Author FIELD EFFECT TRANSISTORS; TEMPERATURE MEASUREMENT; AMBIENT TEMPERATURE; RAMAN SPECTROSCOPY 20090042380 NASA Glenn Research Center, Cleveland, OH, United States LOX Tank Helium Removal for Propellant Scavenging Chato, David J.; January 05, 2009; In English; Aerospace Sciences Meeting, 8 Jan. 2008, Orlando, FL, United States; Original contains color illustrations Contract(s)/Grant(s): WBS 182306.06.01.03.04 Report No.(s): E-17143-V; No Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090042380 System studies have shown a significant advantage to reusing the hydrogen and oxygen left in these tanks after landing on the Moon in fuel cells to generate power and water for surface systems. However in the current lander concepts, the helium used to pressurize the oxygen tank can substantially degrade fuel cell power and water output by covering the reacting surface with inert gas. This presentation documents an experimental investigation of methods to remove the helium pressurant while minimizing the amount of the oxygen lost. This investigation demonstrated that significant quantities of Helium (greater than 90% mole fraction) remain in the tank after draining. Although a single vent cycle reduced the helium quantity, large amounts of helium remained. Cyclic venting appeared to be more effective. Three vent cycles were sufficient to reduce the helium to small (less than 0.2%) quantities. Two vent cycles may be sufficient since once the tank has been brought up to pressure after the second vent cycle the helium concentration has been reduced to the less than 0.2% level. The re-pressurization process seemed to contribute to diluting helium. This is as expected since in order to raise the pressure liquid oxygen must be evaporated. Estimated liquid oxygen loss is on the order of 82 pounds (assuming the third vent cycle is not required). Author HELIUM; LIQUID OXYGEN; LIQUID ROCKET PROPELLANTS; SCAVENGING; PROPELLANT TANKS 20090042383 NASA Glenn Research Center, Cleveland, OH, United States Investigation of Unsteady Flow Behavior in Transonic Compressor Rotors with LES and PIV Measurements Hah, Chunill; Voges, Melanie; Mueller, Martin; Schiffer, Heinz-Peter; September 07, 2009; In English; 2009 ISABE Conference, 7-11 Sep. 2009, Montreal, Canada; Original contains color illustrations Contract(s)/Grant(s): WBS 984754.02.07.03.13.03 Report No.(s): ISABE-2009-02; E-17156-P; Copyright; Avail.: CASI: A02, Hardcopy Avail Online: http://hdl.handle.net/2060/20090042383 In the present study, unsteady flow behavior in a modern transonic axial compressor rotor is studied in detail with large eddy simulation (LES) and particle image velocimetry (PIV). The main purpose of the study is to advance the current understanding of the flow field near the blade tip in an axial transonic compressor rotor near the stall and peak-efficiency conditions. Flow interaction between the tip leakage vortex and the passage shock is inherently unsteady in a transonic compressor. Casing-mounted unsteady pressure transducers have been widely applied to investigate steady and unsteady flow behavior near the casing. Although many aspects of flow have been revealed, flow structures below the casing cannot be studied with casing-mounted pressure transducers. In the present study, unsteady velocity fields are measured with a PIV system and the measured unsteady flow fields are compared with LES simulations. The currently applied PIV measurements indicate that the flow near the tip region is not steady even at the design condition. This self-induced unsteadiness increases significantly as the compressor rotor operates near the stall condition. Measured data from PIV show that the tip clearance vortex oscillates substantially near stall. The calculated unsteady characteristics of the flow from LES agree well with the PIV measurements. Calculated unsteady flow fields show that the formation of the tip clearance vortex is intermittent and the concept of vortex breakdown from steady flow analysis does not seem to apply in the current flow field. Fluid with low momentum near the pressure side of the blade close to the leading edge periodically spills over into the adjacent blade passage. The present study indicates that stall inception is heavily dependent on unsteady behavior of the flow field near the leading edge of the blade tip section for the present transonic compressor rotor. Author LARGE EDDY SIMULATION; PARTICLE IMAGE VELOCIMETRY; TRANSONIC COMPRESSORS; UNSTEADY FLOW; COMPRESSOR ROTORS; ROTOR BLADES (TURBOMACHINERY) Additions to the NASA Aeronautics and Space Database as of 12/25/2009 20090042496 NASA Langley Research Center, Hampton, VA, United States Operational Improvements From Using the In-Trail Procedure in the North Atlantic Organized Track System Chartrand, Ryan C.; Bussink, Frank J.; Graff, Thomas J.; Jones, Kenneth M.; October 2009; In English; Original contains color and black and white illustrations Report No.(s): NASA/TM-2009-215939; L-19466; LF99-6894; Copyright; Avail.: CASI: A04, Hardcopy Avail Online: http://hdl.handle.net/2060/20090042496 This paper explains the computerized batch processing experiment examining the operational impacts of the introduction of Automatic Dependent Surveillance-Broadcast (ADS-B) equipment and the In-Trail Procedure (ITP) to the North Atlantic Organized Track System. This experiment was conducted using the Traffic Manager (TMX), a desktop simulation capable of simulating airspace environments and aircraft operations. ADS-B equipment can enable the use of new ground and airborne procedures, such as the ITP. ITP is among the first of these new procedures, which will make use of improved situation awareness in the local surrounding airspace of ADS-B equipped aircraft to enable more efficient oceanic flight level changes. The collected data were analyzed with respect to multiple operationally relevant parameters including fuel burn, request approval rates, and the distribution of fuel savings. This experiment showed that through the use of ADS-B or ADS-B and the ITP that operational improvements and benefits could be achieved. Author SURVEILLANCE; ENVIRONMENT SIMULATION; BROADCASTING; AIRSPACE; MIRROR FUSION 20090042511 NASA Langley Research Center, Hampton, VA, United States Exploring a Method for Improving Turbulent Separated-Flow Predictions with kappa-omega Models Rumsey, Christopher L.; December 2009; In English; Original contains color and black and white illustrations Contract(s)/Grant(s): WBS 561581.02.08.07.20.15 Report No.(s): NASA/TM-2009-215952; L-19779; LF99-9618; No Copyright; Avail.: CASI: A04, Hardcopy Avail Online: http://hdl.handle.net/2060/20090042511 A particular failing of Reynolds-averaged Navier-Stokes separated turbulent flow computations is addressed within the context of a kappa-omega two-equation turbulence model. The failing is the tendency for turbulence models to under-predict turbulent shear stress in the shear layers of some separation bubbles, yielding late boundary layer reattachment and recovery. Inspired by unpublished work of Volker, Langtry, and Menter, the author undertook an independent investigation in an attempt to improve the ability of the Menter shear stress transport (SST) model to predict flowfield characteristics in and downstream of separation bubbles. The fix is an ad hoc term that is a function of the local ratio of turbulent production to dissipation; it is used to multiply the omega-destruction term, increasing eddy viscosity in separated regions. With this fix, several flowfields are investigated. Results show that, although the "separation fix" can provide dramatic improvement in some cases, it is not consistently good for all flows. Thus, although it may prove helpful in many situations in its current form, this model may benefit from further refinements, including better sensitization to the energetics of turbulence in the separated region. Author COMPUTATIONAL FLUID DYNAMICS; EDDY VISCOSITY; TURBULENCE MODELS; SEPARATED FLOW; BOUNDARY LAYERS; FLOW DISTRIBUTION; NAVIER-STOKES EQUATION; REYNOLDS AVERAGING; SHEAR STRESS; TURBULENT FLOW 20090042518 NASA Langley Research Center, Hampton, VA, United States Metrics for the NASA Airspace Systems Program Smith, Jeremy C.; Neitzke, Kurt W.; December 2009; In English; Original contains color illustrations Contract(s)/Grant(s): WBS 411931.02.71.07.01 Report No.(s): NASA/SP-2009-6115; LF99-9261; L-19732; No Copyright; Avail.: CASI: A04, Hardcopy Avail Online: http://hdl.handle.net/2060/20090042518 This document defines an initial set of metrics for use by the NASA Airspace Systems Program (ASP). ASP consists of the NextGen-Airspace Project and the NextGen-Airportal Project. The work in each project is organized along multiple, discipline-level Research Focus Areas (RFAs). Each RFA is developing future concept elements in support of the Next Generation Air Transportation System (NextGen), as defined by the Joint Planning and Development Office (JPDO). In addition, a single, system-level RFA is responsible for integrating concept elements across RFAs in both projects and for assessing system-wide benefits. The primary purpose of this document is to define a common set of metrics for measuring National Airspace System (NAS) performance before and after the introduction of ASP-developed concepts for NextGen as the system handles increasing traffic. The metrics are directly traceable to NextGen goals and objectives as defined by the JPDO and hence will be used to measure the progress of ASP research toward reaching those goals. The scope of this document is focused on defining a common set of metrics for measuring NAS capacity, efficiency, robustness, and safety at the system-level and at the RFA-level. Use of common metrics will focus ASP research toward achieving system-level performance goals and objectives and enable the discipline-level RFAs to evaluate the impact of their concepts at the system level. Author AIRSPACE; NATIONAL AIRSPACE SYSTEM; NASA PROGRAMS; AIR TRANSPORTATION; MANAGEMENT PLANNING 20090042519 NASA Langley Research Center, Hampton, VA, United States An Amplitude-Based Estimation Method for International Space Station (ISS) Leak Detection and Localization Using Acoustic Sensor Networks Tian, Jialin; Madaras, Eric I.; November 2009; In English; Original contains color illustrations Contract(s)/Grant(s): WBS 401769.06.03.01.02.12 Report No.(s): NASA/TM-2009-215948; LF99-9595; L-19789; No Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090042519 The development of a robust and efficient leak detection and localization system within a space station environment presents a unique challenge. A plausible approach includes the implementation of an acoustic sensor network system that can successfully detect the presence of a leak and determine the location of the leak source. Traditional acoustic detection and localization schemes rely on the phase and amplitude information collected by the sensor array system. Furthermore, the acoustic source signals are assumed to be airborne and far-field. Likewise, there are similar applications in sonar. In solids, there are specialized methods for locating events that are used in geology and in acoustic emission testing that involve sensor arrays and depend on a discernable phase front to the received signal. These methods are ineffective if applied to a sensor detection system within the space station environment. In the case of acoustic signal location, there are significant baffling and structural impediments to the sound path and the source could be in the near-field of a sensor in this particular setting. Author SIGNAL DETECTORS; SOUND DETECTING AND RANGING; LEAKAGE; ACOUSTIC EMISSION; INTERNATIONAL SPACE STATION; SIGNAL TRANSMISSION; SOUND GENERATORS; SOUND WAVES 20090042520 NASA Langley Research Center, Hampton, VA, United States Very Long Single and Few-Walled Boron Nitride Nanotubes via the Pressurized Vapor/Condenser Method Smith, Michael W.; Jordan, Kevin C.; Park, Cheol; Kim, Jae-Woo; Lillehei, Peter T.; Crooks, Roy; Harrison, Joycelyn S.; November 16, 2009; In English; Original contains color and black and white illustrations Contract(s)/Grant(s): DE-AC05-06OR23177WBS 561581.02.08.07.15.02 Report No.(s): LF99-9752; LAR-17535-1; Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090042520 A new method for producing long, small diameter, single and few-walled, boron nitride nanotubes (BNNTs) in macroscopic quantities is reported. The pressurized vapor/condenser (PVC) method produces, without catalysts, highly crystalline, very long, small diameter, BNNTs. Palm-sized, cotton-like masses of BNNT raw material were grown by this technique and spun directly into centimeters-long yarn. Nanotube lengths were observed to be 100 times that of those grown by the most closely related method. Self-assembly and growth models for these long BNNTs are discussed. Author NANOTUBES; BORON NITRIDES; CRYSTALLINITY; CATALYSTS 20090042540 Advanced Cooling Technologies, Inc., Lancaster, PA, United States High Temperature Variable Conductance Heat Pipes for Radioisotope Stirling Systems Tarau, Calin; Walker, Kara L.; Anderson, William G.; February 24, 2009; In English; Original contains color and black and white illustrations Contract(s)/Grant(s): NNC07QA40P; NNC08CA17CWBS 138494.01.04.01 Report No.(s): E-17181-p; Copyright; Avail.: CASI: A02, Hardcopy Avail Online: http://hdl.handle.net/2060/20090042540 In a Stirling radioisotope system, heat must continually be removed from the GPHS modules, to maintain the GPHS modules and surrounding insulation at acceptable temperatures. Normally, the Stirling convertor provides this cooling. If the Stirling convertor stops in the current system, the insulation is designed to spoil, preventing damage to the GPHS, but also ending the mission. An alkali-metal Variable Conductance Heat Pipe (VCHP) is under development to allow multiple stops and restarts of the Stirling convertor. The status of the ongoing effort in developing this technology is presented in this paper. An earlier, preliminary design had a radiator outside the Advanced Stirling Radioisotope Generator (ASRG) casing, used NaK as the working fluid, and had the reservoir located on the cold side adapter flange. The revised design has an internal radiator inside the casing, with the reservoir embedded inside the insulation. A large set of advantages are offered by this new design. In addition to reducing the overall size and mass of the VCHP, simplicity, compactness and easiness in assembling the VCHP with the ASRG are significantly enhanced. Also, the permanently elevated temperatures of the entire VCHP allows the change of the working fluid from a binary compound (NaK) to single compound (Na). The latter, by its properties, allows higher performance and further mass reduction of the system. Preliminary design and analysis shows an acceptable peak temperature of the ASRG case of 140 C while the heat losses caused by the addition of the VCHP are 1.8 W. Author CONDUCTIVE HEAT TRANSFER; STIRLING CYCLE; HIGH TEMPERATURE; HEAT PIPES; RESERVOIRS; WORKING FLUIDS; DESIGN ANALYSIS 20090042542 National Inst. of Aerospace, Hampton, VA, United States Panel Stiffener Debonding Analysis using a Shell/3D Modeling Technique Krueger, Ronald; Ratcliffe, James G.; Minguet, Pierre J.; June 11, 2008; In English; Original contains color illustrations Contract(s)/Grant(s): WBS 698259.02.07.07.03.03 Report No.(s): LF99-7182; Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090042542 A shear loaded, stringer reinforced composite panel is analyzed to evaluate the fidelity of computational fracture mechanics analyses of complex structures. Shear loading causes the panel to buckle. The resulting out -of-plane deformations initiate skin/stringer separation at the location of an embedded defect. The panel and surrounding load fixture were modeled with shell elements. A small section of the stringer foot, web and noodle as well as the panel skin near the delamination front were modeled with a local 3D solid model. Across the width of the stringer fo to, the mixed-mode strain energy release rates were calculated using the virtual crack closure technique. A failure index was calculated by correlating the results with a mixed-mode failure criterion of the graphite/epoxy material. The objective was to study the effect of the fidelity of the local 3D finite element model on the computed mixed-mode strain energy release rates and the failure index. Author COMPOSITE STRUCTURES; DELAMINATING; FINITE ELEMENT METHOD; BUCKLING; COMPUTATIONAL MECHANICS; DEBONDING (MATERIALS); FRACTURE MECHANICS; GRAPHITE-EPOXY COMPOSITES 20090042555 Southwest Research Inst., San Antonio, TX, United States; ATK Space Systems, Inc., Beltsville, MD, United States Model for the Effect of Fiber Bridging on the Fracture Resistance of Reinforced-Carbon-Carbon Chan, Kwai S.; Lee, Yi-Der; Hudak, Stephen J., Jr.; November 2009; In English; Original contains color and black and white illustrations Contract(s)/Grant(s): NNL07AA00BWBS 869021.05.07.04.99 Report No.(s): NASA/CR-2009-215947; LF99-9886; Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090042555 A micromechanical methodology has been developed for analyzing fiber bridging and resistance-curve behavior in reinforced-carbon-carbon (RCC) panels with a three-dimensional (3D) composite architecture and a silicon carbide (SiC) surface coating. The methodology involves treating fiber bridging traction on the crack surfaces in terms of a weight function approach and a bridging law that relates the bridging stress to the crack opening displacement. A procedure has been developed to deduce material constants in the bridging law from the linear portion of the K-resistance curve. This report contains information on the application of procedures and outcomes. Author SURFACE CRACKS; CARBON; FRACTURE STRENGTH; CRACK OPENING DISPLACEMENT; THREE DIMENSIONAL COMPOSITES; SILICON CARBIDES; CRACK BRIDGING; MICROMECHANICS Additions to the NASA Aeronautics and Space Database as of 12/28/2009 20090042581 NASA Glenn Research Center, Cleveland, OH, United States Assessment of Operation of EMK21 MEMS Silicon Oscillator Over Wide Temperature Range Patterson, Richard L.; Hammoud, Ahmad; March 31, 2009; In English; Original contains color and black and white illustrations Contract(s)/Grant(s): NNC06BA07B; CASX22009DWBS 724297.40.43.03.01 Report No.(s): E-17161; Copyright; Avail.: CASI: A02, Hardcopy Avail Online: http://hdl.handle.net/2060/20090042581 Electronic control systems, data-acquisition instrumentation, and microprocessors require accurate timing signals for proper operation. Traditionally, ceramic resonators and crystal oscillators provided this clock function for the majority of these systems. Over the last few years, MEMS (Micro-Electro-Mechanical Systems) resonator-based oscillators began to surface as commercial-off-the-shelf (COTS) parts by a few companies. These quartz-free, miniature silicon devices could easily replace the traditional crystal oscillators in providing the timing/clock function for many digital and analog circuits. They are reported to provide stable output frequency, offer great tolerance to shock and vibration, and are immune to electro-static discharge [ 1-2]. In addition, they are encapsulated in compact lead-free packages and cover a wide frequency range (1 MHz to 125 MHz). The small size of the MEMS oscillators along with their thermal stability make them ideal candidates for use in space exploration missions. Limited data, however, exist on the performance and reliability of these devices under operation in applications where extreme temperatures or thermal cycling swings, which are typical of space missions, are encountered. This report presents the results of the work obtained on the evaluation of an Ecliptek Corporation MEMS silicon oscillator chip under extreme temperatures. Derived from text MICROELECTROMECHANICAL SYSTEMS; OSCILLATORS; THERMAL CYCLING TESTS; TIME SIGNALS; TIMING DEVICES; TIME MEASUREMENT 20090042583 NASA Glenn Research Center, Cleveland, OH, United States Assessment of SOI AND Gate, Type CHT-7408, for Operation in Extreme Temperature Environments Patterson, Richard; Hammoud, Ahmad; Dones, Keishla Rivera; August 2009; In English; Original contains color and black and white illustrations Contract(s)/Grant(s): NNC06BA07B; CASX22009DWBS 724297.40.43.03.01 Report No.(s): E-17162; Copyright; Avail.: CASI: A02, Hardcopy Avail Online: http://hdl.handle.net/2060/20090042583 Electronic parts based on silicon-on-insulator (SOI) technology are finding widespread applications due to their ability to operate in harsh environments and the benefits they offer as compared to their silicon counterparts. Due to their construction, they are tailored for high temperature operation and show good tolerance to radiation events. In addition, their inherent design lessens the formation of parasitic junctions, thereby reducing leakage currents, decreasing power consumption, and enhancing speed. These devices are typically rated in temperature capability from -55 C to about +225 C, and their characteristics over this temperature range are documented in data sheets. Since electronics in some of NASA space exploration missions are required to operate under extreme temperature conditions, both cold and hot, their characteristic behavior within the full temperature spectrum must be determined to establish suitability for use in space applications. The effects of extreme temperature exposure on the performance of a new commercial-off-the-shelf (COTS) SOI AND gate device were evaluated in this work. The high temperature, quad 2-inputs AND gate device, which was recently introduced by CISSOID, is fabricated using a CMOS SOI process. Some of the specifications of the CHT-7408 chip are listed in a table. By supplying a constant DC voltage to one gate input and a 10 kHz square wave into the other associated gate input, the chip was evaluated in terms of output response, output rise (t(sub r)) and fall times (tf), and propagation delays (using a 50% level between input and output during low to high (tPLH) and high to low (tPHL) transitions). The supply current of the gate circuit was also obtained. These parameters were recorded at various test temperatures between -195 C and +250 C using a Sun Systems environmental chamber programmed at a temperature rate of change of 10 C/min. In addition, the effects of thermal cycling on this chip were determined by exposing it to a total of 12 cycles between -195 C and +250 C. Following the cycling activity, measurements were performed again at the test temperatures of -195 C, +21 C, and +250 C. Derived from text SOI (SEMICONDUCTORS); TEMPERATURE EFFECTS; THERMAL CYCLING TESTS; ELECTRONIC EQUIPMENT; GATES (CIRCUITS); LOGIC CIRCUITS 20090042620 Henry Ford Hospital, Detroit, MI, United States Ultrasound in Space Medicine Dulchavsky, Scott A.; Sargsyan, A.E.; November 30, 2009; In English; 3rd WINFOCUS (World Interactive Network Focused on Critical UltraSound) Italian Congress, 28-30 Nov. 2009, Bologna, Italy; Original contains color illustrations Report No.(s): JSC-CN-19374; Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090042620 This slide presentation reviews the use of ultrasound as a diagnostic tool in microgravity environments. The goals of research in ultrasound usage in space environments are: (1) Determine accuracy of ultrasound in novel clinical conditions. (2) Determine optimal training methodologies, (3) Determine microgravity associated changes and (4) Develop intuitive ultrasound catalog to enhance autonomous medical care. Also uses of Ultrasound technology in terrestrial applications are reviewed. CASI AEROSPACE ENVIRONMENTS; AEROSPACE MEDICINE; ULTRASONICS; TELEMEDICINE 20090042621 NASA Johnson Space Center, Houston, TX, United States Life Sciences Data Archive (LSDA) in the Post-Shuttle Era Fitts, Mary A.; Johnson-Throop, Kathy; Havelka, Jacque; Thomas, Diedre; [2009]; In English; 2010 NASA Human Research Program Investigators' Workshop, 3-5 Feb. 2010, Houston, TX, United States Report No.(s): JSC-CN-19381; Copyright; Avail.: CASI: A01, Hardcopy Avail Online: http://hdl.handle.net/2060/20090042621 Now, more than ever before, NASA is realizing the value and importance of their intellectual assets. Principles of knowledge management, the systematic use and reuse of information/experience/expertise to achieve a specific goal, are being applied throughout the agency. LSDA is also applying these solutions, which rely on a combination of content and collaboration technologies, to enable research teams to create, capture, share, and harness knowledge to do the things they do well, even better. In the early days of spaceflight, space life sciences data were been collected and stored in numerous databases, formats, media-types and geographical locations. These data were largely unknown/unavailable to the research community. The Biomedical Informatics and Health Care Systems Branch of the Space Life Sciences Directorate at JSC and the Data Archive Project at ARC, with funding from the Human Research Program through the Exploration Medical Capability Element, are fulfilling these requirements through the systematic population of the Life Sciences Data Archive. This project constitutes a formal system for the acquisition, archival and distribution of data for HRP-related experiments and investigations. The general goal of the archive is to acquire, preserve, and distribute these data and be responsive to inquiries from the science communities. Author LIFE SCIENCES; HEALTH; DATA ACQUISITION; DATA BASES; SPACE FLIGHT 20090042624 NASA White Sands Test Facility, NM, United States In-Situ NDE Characterization of Kevlar and Carbon Composite Micromechanics for Improved COPV Health Monitoring Waller, Jess M.; Saulsberry, Regor L.; [2009]; In English; Original contains color and black and white illustrations Report No.(s): JSC-CN-19383; No Copyright; Avail.: CASI: A02, Hardcopy Avail Online: http://hdl.handle.net/2060/20090042624 This project is a subtask of a multi-center project to advance the state-of-the-art by developing NDE techniques that are capable of evaluating stress rupture (SR) degradation in Kevlar/epoxy (K/Ep) composite overwrapped pressure vessels (COPVs), and damage progression in carbon/epoxy (C/Ep) COPVs. In this subtask, acoustic emission (AE) data acquired during intermittent load hold tensile testing of K/Ep and C/Ep composite tow materials-of-construction used in COPV fabrication were analyzed to monitor progressive damage during the approach to tensile failure. Insight into the progressive damage of composite tow was gained by monitoring AE event rate, energy, source location, and frequency. Source location based on arrival time data was used to discern between significant AE attributable to microstructural damage and spurious AE attributable to background and grip noise. One of the significant findings was the observation of increasing violation of the Kaiser effect (Felicity ratio < 1.0) with damage accumulation. Author COMPOSITE MATERIALS; COMPOSITE WRAPPING; EPOXY MATRIX COMPOSITES; EPOXY RESINS; KEVLAR (TRADEMARK); MICROMECHANICS; NONDESTRUCTIVE TESTS 20090042634 Southwest Sciences, Inc., Santa Fe, NM United States Dense Pattern Optical Multipass Cell Silver, Joel A., Inventor; January 13, 2009; In English Contract(s)/Grant(s): NNA04CB22C; DE-FG02-03ER83779 Patent Info.: July 21, 2004US-Patent-7,477,377; US-Patent-Appl-SN-10/896,608 No Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090042634 A multiple pass optical cell and method comprising providing a pair of opposed cylindrical mirrors having curved axes with substantially equal focal lengths, positioning an entrance hole for introducing light into the cell and an exit hole for extracting light from the cell, wherein the entrance hole and exit hole are coextensive or non-coextensive, introducing light into the cell through the entrance hole, and extracting light from the cell through the exit hole. Official Gazette of the U.S. Patent and Trademark Office OPTICAL PATHS; OPTICAL MEASURING INSTRUMENTS 20090042635 NASA, Washington, DC United States Image Processing for Binarization Enhancement via Fuzzy Reasoning Dominguez, Jesus A., Inventor; February 24, 2009; In English Patent Info.: December 1, 2004US-Patent-7,496,237; US-Patent-Appl-SN-11/010,698 No Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090042635 A technique for enhancing a gray-scale image to improve conversions of the image to binary employs fuzzy reasoning. In the technique, pixels in the image are analyzed by comparing the pixel's gray scale value, which is indicative of its relative brightness, to the values of pixels immediately surrounding the selected pixel. The degree to which each pixel in the image differs in value from the values of surrounding pixels is employed as the variable in a fuzzy reasoning-based analysis that determines an appropriate amount by which the selected pixel's value should be adjusted to reduce vagueness and ambiguity in the image and improve retention of information during binarization of the enhanced gray-scale image. Official Gazette of the U.S. Patent and Trademark Office IMAGE PROCESSING; FUZZY SYSTEMS Additions to the NASA Aeronautics and Space Database as of 12/29/2009 20090042638 NASA Johnson Space Center, Houston, TX, United States How Configuration Management Helps Projects Innovate and Communicate Cioletti, Louis A.; Guidry, Carla F.; [2009]; In English; NASA Project Management Challenge, 9-10 Feb. 2010, Galveston, TX, United States; Original contains color illustrations Report No.(s): JSC-CN-19405; Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090042638 This slide presentation reviews the concept of Configuration Management (CM) and compares it to the standard view of Project management (PM). It presents two PM models: (1) Kepner-Tregoe,, and the Deming models, describes why projects fail, and presents methods of how CM helps projects innovate and communicate. CASI CONFIGURATION MANAGEMENT; PROJECT MANAGEMENT; MANAGEMENT PLANNING 20090042641 NASA Johnson Space Center, Houston, TX, United States Project Interface Requirements Process including Shuttle Lessons Learned Bauch, Garland T.; February 09, 2009; In English; Project Management Challenge 2010, 9-10 Feb. 2009, Galveston, TX, United States; Original contains color illustrations Report No.(s): JSC-CN-19425; No Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090042641 This slide presentation reviews specific "lessons learned" approaches ot ensure interface requirements lead the way in communicating project element requirements across the interfaces. Derived from text MANAGEMENT PLANNING; SYSTEMS ENGINEERING; INTERFACES 20090042647 NASA Johnson Space Center, Houston, TX, United States Lunar Analog Feasibility Study Results Cromwell, Ronita L.; Neigut, Joe; December 09, 2009; In English; Lunar Analog Review, 9 Dec. 2009, Houston, TX, United States; Original contains color illustrations Report No.(s): JSC-CN-19436; Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090042647 This slide presentation reviews a study designed to determine the feasibility of using a 9.5 deg head-up tilt bed rest model to simulate the effects of the 1/6 g load to the human body that exists on the lunar surface. The effect of different types of compression stockings, the pre-bed rest diet, and the use of a specific exercise program were reviewed for comfort, force verification and plasma volume shift CASI BED REST; LUNAR SURFACE; HEAD UP TILT; GRAVITATIONAL PHYSIOLOGY; PHYSIOLOGICAL RESPONSES; AEROSPACE MEDICINE; PHYSIOLOGICAL EFFECTS 20090042655 Northwestern Univ., Evanston, IL, United States Human Research Program Human Health Countermeasures Element Sensorimotor Risk Standing Review Panel (SRP) Final Report Peterson, Barry; November 2009; In English; Original contains black and white illustrations Report No.(s): JSC-CN-19459; Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090042655 The Sensorimotor Risk Standing Review Panel (SRP) met at the NASA Johnson Space Center on October 4-6, 2009 to discuss the areas of future research targeted by the Human Health Countermeasures (HHC) Element of the Human Research Program (HRP). Using evidence-based knowledge as a background for risks, NASA had identified gaps in knowledge to address those risks. Ongoing and proposed tasks were presented to address the gaps. The charge to the Sensorimotor Risk SRP was to review the gaps, evaluate whether the tasks addressed these gaps and to make recommendations to NASA s HRP Science Management Office regarding the SRP's review. The SRP was requested to evaluate the practicality of the proposed efforts in light of the realistic demands placed on the HRP. In short, all tasks presented in the Integrated Research Plan (IRP) should address specific risks related to the challenges faced by the astronauts as a result of prolonged exposure to microgravity. All tasks proposed to fill the gaps in knowledge should provide applied, translational data necessary to address the specific risks. Several presentations were made to the SRP during the site visit and the SRP spent sufficient time to address the panel charge, either as a group or in separate sessions. The SRP made a final debriefing to the HRP Program Scientist. Taking the evidence and the risk as givens, the SRP reached the following conclusions: 1) the panel is very supportive of and endorses the present activities of the Sensorimotor Risk; and the panel is likewise supportive of the gaps and associated tasks in the IRP; 2) overall, the tasks addressed the gaps in the IRP; 3) there were some gaps and tasks that merit further enhancement and some new gaps/tasks that the SRP recommends. Derived from text SENSORIMOTOR PERFORMANCE; PHYSIOLOGICAL TESTS; AEROSPACE MEDICINE; ASTRONAUT PERFORMANCE 20090042692 NASA Goddard Space Flight Center, Greenbelt, MD, United States On DESTINY Science Instrument Electrical and Electronics Subsystem Framework Kizhner, Semion; Benford, Dominic J.; Lauer, Tod R.; [2009]; In English; 2010 IEEE Aerospace Conference, 6-13 Mar. 2010, Big Sky, MT, United States; Original contains color illustrations Report No.(s): IEEEAC Paper 1429; Copyright; Avail.: CASI: A02, Hardcopy Avail Online: http://hdl.handle.net/2060/20090042692 Future space missions are going to require large focal planes with many sensing arrays and hundreds of millions of pixels all read out at high data rates'' . This will place unique demands on the electrical and electronics (EE) subsystem design and it will be critically important to have high technology readiness level (TRL) EE concepts ready to support such missions. One such omission is the Joint Dark Energy Mission (JDEM) charged with making precise measurements of the expansion rate of the universe to reveal vital clues about the nature of dark energy - a hypothetical form of energy that permeates all of space and tends to increase the rate of the expansion. One of three JDEM concept studies - the Dark Energy Space Telescope (DESTINY) was conducted in 2008 at the NASA's Goddard Space Flight Center (GSFC) in Greenbelt, Maryland. This paper presents the EE subsystem framework, which evolved from the DESTINY science instrument study. It describes the main challenges and implementation concepts related to the design of an EE subsystem featuring multiple focal planes populated with dozens of large arrays and millions of pixels. The focal planes are passively cooled to cryogenic temperatures (below 140 K). The sensor mosaic is controlled by a large number of Readout Integrated Circuits and Application Specific Integrated Circuits - the ROICs/ASICs in near proximity to their sensor focal planes. The ASICs, in turn, are serviced by a set of "warm" EE subsystem boxes performing Field Programmable Gate Array (FPGA) based digital signal processing (DSP) computations of complex algorithms, such as sampling-up-the-ramp algorithm (SUTR), over large volumes of fast data streams. The SUTR boxes are supported by the Instrument Control/Command and Data Handling box (ICDH Primary and Backup boxes) for lossless data compression, command and low volume telemetry handling, power conversion and for communications with the spacecraft. The paper outlines how the JDEM DESTINY concept instrument EE subsystem can be built now, a design; which is generally U.S. Government work not protected by U.S. copyright IEEEAC paper # 1429. Version 4. Updated October 19, 2009 applicable to a wide variety of missions using large focal planes with lar ge mosaics of sensors. Author PIXELS; APPLICATION SPECIFIC INTEGRATED CIRCUITS; SIGNAL PROCESSING; FIELD-PROGRAMMABLE GATE ARRAYS; DATA FLOW ANALYSIS; DATA COMPRESSION; FOCAL PLANE DEVICES 20090042714 NASA Goddard Space Flight Center, Greenbelt, MD, United States The Morphology of Passively Evolving Galaxies at Z-2 from HST/WFC3 in the Hubble Ultra Deep Field Cassata, P.; Giavalisco, M.; Guo, Yicheng; Ferguson, H.; Koekemoer, A.; Renzini, A.; Fontana, A.; Salimbeni, S.; Dickinson, M.; Casertano, S.; Conselice, C.J.; Grogin, N.; Lotz, J.M.; Papovich, C.; Lucas, R.A.; Straughn, A.; Gardner, J.P.; Moustakas, L.; November 05, 2009; In English; Original contains black and white illustrations Contract(s)/Grant(s): NAS5-26555 Copyright; Avail.: CASI: A02, Hardcopy Avail Online: http://hdl.handle.net/2060/20090042714 We discuss near-IR images of six passive galaxies (SSFR< 10(exp -2)/Gyr) at redshift 1.3 < z < 2.4 with stellar mass M approx 10(exp 11) solar mass, selected from the Great Observatories Origins Deep Survey (GOODS), obtained with WFC3/IR and the Hubble Space Telescope (HST). These WFC3 images provide the deepest and highest angular resolution view of the optical rest-frame morphology of such systems to date. We find that the light profile of these; galaxies is generally regular and well described by a Sersic model with index typical of today's spheroids. We confirm the existence of compact and massive early-type galaxies at z approx. 2: four out of six galaxies have T(sub e) approx. 1 kpc or less. The WFC3 images achieve limiting surface brightness mu approx. 26.5 mag/sq arcsec in the F160W bandpass; yet there is no evidence of a faint halo in the five compact galaxies of our sample, nor is a halo observed in their stacked image. We also find very weak "morphological k-correction" in the galaxies between the rest-frame UV (from the ACS z band), and the rest-frame optical (WFC3 H band): the visual classification, Sersic indices and physical sizes of these galaxies are independent or only mildly dependent on the wavelength, within the errors. Author COMPACT GALAXIES; STELLAR MASS; BRIGHTNESS; RED SHIFT; NEAR INFRARED RADIATION; HUBBLE SPACE TELESCOPE Additions to the NASA Aeronautics and Space Database as of 12/30/2009 20090042722 NASA Glenn Research Center, Cleveland, OH, United States Passively Shunted Piezoelectric Damping of Centrifugally-Loaded Plates Duffy, Kirsten P.; Provenza, Andrew J.; Trudell, Jeffrey J.; Min, James B.; May 04, 2009; In English; AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference, 4-7 May 2009, Palm Springs, CA, United States; Original contains color and black and white illustrations Contract(s)/Grant(s): NNC07TA60TWBS 561581.02.08.03.15.03 Report No.(s): E-17155-1; Copyright; Avail.: CASI: A02, Hardcopy Avail Online: http://hdl.handle.net/2060/20090042722 Researchers at NASA Glenn Research Center have been investigating shunted piezoelectric circuits as potential damping treatments for turbomachinery rotor blades. This effort seeks to determine the effects of centrifugal loading on passively-shunted piezoelectric - damped plates. Passive shunt circuit parameters are optimized for the plate's third bending mode. Tests are performed both non-spinning and in the Dynamic Spin Facility to verify the analysis, and to determine the effectiveness of the damping under centrifugal loading. Results show that a resistive shunt circuit will reduce resonant vibration for this configuration. However, a tuned shunt circuit will be required to achieve the desired damping level. The analysis and testing address several issues with passive shunt circuit implementation in a rotating system, including piezoelectric material integrity under centrifugal loading, shunt circuit implementation, and tip mode damping. Author BYPASSES; CENTRIFUGAL FORCE; DAMPING; PIEZOELECTRICITY; TURBOMACHINERY; CIRCUITS; SPIN TESTS 20090042723 NASA Glenn Research Center, Cleveland, OH, United States Development of Jet Noise Power Spectral Laws Using SHJAR Data Khavaran, Abbas; Bridges, James; October 2009; In English; FROM 30th AIAA Aeroacoustics Conference, 11-13 May 2009, Miami, FL, United States; Original contains color and black and white illustrations Contract(s)/Grant(s): NNC06BA07BWBS 561581.02.08.03.18.02 Report No.(s): NASA/TM-2009-215674; AIAA Paper 2009-3378; E-17036; Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090042723 High quality jet noise spectral data measured at the Aeroacoustic Propulsion Laboratory at the NASA Glenn Research Center is used to examine a number of jet noise scaling laws. Configurations considered in the present study consist of convergent and convergent-divergent axisymmetric nozzles. Following the work of Viswanathan, velocity power factors are estimated using a least squares fit on spectral power density as a function of jet temperature and observer angle. The regression parameters are scrutinized for their uncertainty within the desired confidence margins. As an immediate application of the velocity power laws, spectral density in supersonic jets are decomposed into their respective components attributed to the jet mixing noise and broadband shock associated noise. Subsequent application of the least squares method on the shock power intensity shows that the latter also scales with some power of the shock parameter. A modified shock parameter is defined in order to reduce the dependency of the regression factors on the nozzle design point within the uncertainty margins of the least squares method. Author JET AIRCRAFT NOISE; AERODYNAMIC NOISE; AEROACOUSTICS; JET MIXING FLOW; NOZZLE DESIGN; CONVERGENT NOZZLES; EMISSION SPECTRA 20090042724 NASA Johnson Space Center, Houston, TX, United States Space Shuttle Orbiter Main Engine Ignition Acoustic Pressure Loads Issue: Recent Actions to Install Wireless Instrumentation on STS-129 Wells, Nathan; Studor, George; December 10, 2009; In English; FROM 25th Propulsion Systems Hazards Joint Subcommittie Meeting, 7-11 Dec. 2009, La Jolla, CA, United States; Original contains color and black and white illustrations Contract(s)/Grant(s): WBS 869021.05.05.01.04 Report No.(s): JSC-CN-19417; No Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090042724 This slide presentation reviews the development and construction of the wireless acoustic instruments surrounding the space shuttle's main engines in preparation for STS-129. The presentation also includes information on end-of-life processing and the mounting procedure for the devices. CASI SOUND PRESSURE; IGNITION; ROCKET ENGINE NOISE; WIRELESS COMMUNICATION 20090042731 NASA Goddard Space Flight Center, Greenbelt, MD, United States Contribution of Soil Moisture Information to Streamflow Prediction in the Snowmelt Season: A Continental-Scale Analysis Reichle, Rolf; Mahanama, Sarith; Koster, Randal; Lettenmaier, Dennis; August 24, 2009; In English; 6th International Scientific Conference on the Global Energy and Water Cycle/Global Energy and Water Experiment, 24-28 Aug. 2009, Melbourne, Australia Copyright; Avail.: CASI: A01, Hardcopy Avail Online: http://hdl.handle.net/2060/20090042731 In areas dominated by winter snowcover, the prediction of streamflow during the snowmelt season may benefit from three pieces of information: (i) the accurate prediction of weather variability (precipitation, etc.) leading up to and during the snowmelt season, (ii) estimates of the amount of snow present during the winter season, and (iii) estimates of the amount of soil moisture underlying the snowpack during the winter season. The importance of accurate meteorological predictions and wintertime snow estimates is obvious. The contribution of soil moisture to streamflow prediction is more subtle yet potentially very important. If the soil is dry below the snowpack, a significant fraction of the snowmelt may be lost to streamflow and potential reservoir storage, since it may infiltrate the soil instead for later evaporation. Such evaporative losses are presumably smaller if the soil below the snowpack is wet. In this paper, we use a state-of-the-art land surface model to quantify the contribution of wintertime snow and soil moisture information -- both together and separately -- to skill in forecasting springtime streamflow. We find that soil moisture information indeed contributes significantly to streamflow prediction skill. Derived from text DRAINAGE; FORECASTING; SNOW COVER; SOIL MOISTURE; SURFACE WATER; STREAMS; WATER FLOW; SPRING (SEASON) 20090042733 NASA Glenn Research Center, Cleveland, OH, United States Probabilistic Estimation of Critical Flaw Sizes in the Primary Structure Welds of the Ares I-X Launch Vehicle Pai, Shantaram S.; Hoge, Peter A.; Patel, B. M.; Nagpal, Vinod K.; November 2009; In English; ASME Turbo Expo 2008 Conference, 9-13 Jun. 2008, Berlin, Germany; Original contains color illustrations Contract(s)/Grant(s): WBS 136905.0.10.80.20.40.01 Report No.(s): NASA/TM-2009-215583; GT2008-50626; E-16824; Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090042733 The primary structure of the Ares I-X Upper Stage Simulator (USS) launch vehicle is constructed of welded mild steel plates. There is some concern over the possibility of structural failure due to welding flaws. It was considered critical to quantify the impact of uncertainties in residual stress, material porosity, applied loads, and material and crack growth properties on the reliability of the welds during its pre-flight and flight. A criterion--an existing maximum size crack at the weld toe must be smaller than the maximum allowable flaw size--was established to estimate the reliability of the welds. A spectrum of maximum allowable flaw sizes was developed for different possible combinations of all of the above listed variables by performing probabilistic crack growth analyses using the ANSYS finite element analysis code in conjunction with the NASGRO crack growth code. Two alternative methods were used to account for residual stresses: (1) The mean residual stress was assumed to be 41 ksi and a limit was set on the net section flow stress during crack propagation. The critical flaw size was determined by parametrically increasing the initial flaw size and detecting if this limit was exceeded during four complete flight cycles, and (2) The mean residual stress was assumed to be 49.6 ksi (the parent material s yield strength) and the net section flow stress limit was ignored. The critical flaw size was determined by parametrically increasing the initial flaw size and detecting if catastrophic crack growth occurred during four complete flight cycles. Both surface-crack models and through-crack models were utilized to characterize cracks in the weld toe. Author LAUNCH VEHICLES; STRUCTURAL FAILURE; WELDED JOINTS; ARES 1 LAUNCH VEHICLE; CRACK PROPAGATION; MECHANICAL PROPERTIES; RESIDUAL STRESS; SURFACE CRACKS; YIELD STRENGTH 20090042735 California Inst. of Tech., Pasadena, CA United States Monopolar fuel cell stack coupled together without use of top or bottom cover plates or tie rods Narayanan, Sekharipuram R., Inventor; Valdez, Thomas I., Inventor; September 8, 2009; In English Patent Info.: April 9, 2003US-Patent-7,585,577; US-Patent-Appl-SN-10/410,761 No Copyright; Avail.: CASI: A02, Hardcopy Avail Online: http://hdl.handle.net/2060/20090042735 A monopolar fuel cell stack comprises a plurality of sealed unit cells coupled together. Each unit cell comprises two outer cathodes adjacent to corresponding membrane electrode assemblies and a center anode plate. An inlet and outlet manifold are coupled to the anode plate and communicate with a channel therein. Fuel flows from the inlet manifold through the channel in contact with the anode plate and flows out through the outlet manifold. The inlet and outlet manifolds are arranged to couple to the inlet and outlet manifolds respectively of an adjacent one of the plurality of unit cells to permit fuel flow in common into all of the inlet manifolds of the plurality of the unit cells when coupled together in a stack and out of all of the outlet manifolds of the plurality of unit cells when coupled together in a stack. Official Gazette of the U.S. Patent and Trademark Office CELL CATHODES; HYDROGEN OXYGEN FUEL CELLS 20090042742 NASA Goddard Space Flight Center, Greenbelt, MD, United States A GCM Study of Responses of the Atmospheric Water Cycle of West Africa and the Atlantic to Saharan Dust Radiative Forcing Lau, K. M.; Kim, K. M.; Sud, Y. C.; Walker, G. K.; August 2009; In English; Original contains black and white illustrations Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090042742 The responses of the atmospheric water cycle and climate of West Africa and the Atlantic to radiative forcing of Saharan dust are studied using the NASA finite volume general circulation model (fvGCM), coupled to a mixed layer ocean. We find evidence of an "elevated heat pump" (EHP) mechanism that underlines the responses of the atmospheric water cycle to dust forcing as follow. During the boreal summerr, as a result of large-scale atmospheric feedback triggered by absorbing dust aerosols, rainfall and cloudiness are ehanIed over the West Africa/Eastern Atlantic ITCZ, and suppressed over the West Atlantic and Caribbean region. Shortwave radiation absorption by dust warms the atmosphere and cools the surface, while longwave has the opposite response. The elevated dust layer warms the air over West Africa and the eastern Atlantic. As the warm air rises, it spawns a large-scale onshore flow carrying the moist air from the eastern Atlantic and the Gulf of Guinea. The onshore flow in turn enhances the deep convection over West Africa land, and the eastern Atlantic. The condensation heating associated with the ensuing deep convection drives and maintains an anomalous large-scale east-west overturning circulation with rising motion over West Africa/eastern Atlantic, and sinking motion over the Caribbean region. The response also includes a strengthening of the West African monsoon, manifested in a northward shift of the West Africa precipitation over land, increased low-level westerlies flow over West Africa at the southern edge of the dust layer, and a near surface westerly jet underneath the dust layer overr the Sahara. The dust radiative forcing also leads to significant changes in surface energy fluxes, resulting in cooling of the West African land and the eastern Atlantic, and warming in the West Atlantic and Caribbean. The EHP effect is most effective for moderate to highly absorbing dusts, and becomes minimized for reflecting dust with single scattering albedo at0.95 or higher. Author AEROSOLS; AFRICA; ATMOSPHERIC CIRCULATION; CLIMATE; CONVECTION; DUST; RADIATIVE FORCING; SAHARA DESERT (AFRICA); WATER; METEOROLOGY; AIR LAND INTERACTIONS; ATMOSPHERIC HEATING 20090042747 Wyle Information Services, LLC, United States Time-Series Analysis of Remotely-Sensed SeaWiFS Chlorophyll in River-Influenced Coastal Regions Acker, James G.; McMahon, Erin; Shen, Suhung; Hearty, Thomas; Casey, Nancy; EARSeL (European Association of Remote Sensing Laboratories) eProceedings; [2009]; vol. Volume 8; issue No. 2; pp. 114-13; In English; Original contains color illustrations Contract(s)/Grant(s): NNG06EG68C Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090042747 The availability of a nearly-continuous record of remotely-sensed chlorophyll a data (chl a) from the Sea-viewing Wide Field-of-view Sensor (SeaWiFS) mission, now longer than ten years, enables examination of time-series trends for multiple global locations. Innovative data analysis technology available on the World Wide Web facilitates such analyses. In coastal regions influenced by river outflows, chl a is not always indicative of actual trends in phytoplankton chlorophyll due to the interference of colored dissolved organic matter and suspended sediments; significant chl a timeseries trends for coastal regions influenced by river outflows may nonetheless be indicative of important alterations of the hydrologic and coastal environment. Chl a time-series analysis of nine marine regions influenced by river outflows demonstrates the simplicity and usefulness of this technique. The analyses indicate that coastal time-series are significantly influenced by unusual flood events. Major river systems in regions with relatively low human impact did not exhibit significant trends. Most river systems with demonstrated human impact exhibited significant negative trends, with the noteworthy exception of the Pearl River in China, which has a positive trend. Author CHLOROPHYLLS; COASTAL WATER; REMOTE SENSING; SEA-VIEWING WIDE FIELD-OF-VIEW SENSOR; TIME SERIES ANALYSIS 20090042749 NASA Glenn Research Center, Cleveland, OH, United States The Advanced Noise Control Fan Baseline Measurements McAllister, Joseph; Loew, Raymond A.; Lauer, Joel T.; Stuliff, Daniel L.; October 2009; In English; 47th Aerospace Sciences Meeting, 5-8 Jan. 2009, Orlando, FL, United States; Original contains color and black and white illustrations Contract(s)/Grant(s): WBS 561581.02.08.03.18.02 Report No.(s): NASA/TM-2009-215595; AIAA Paper 2009-0624; E-16886; Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090042749 The NASA Glenn Research Center s (NASA Glenn) Advanced Noise Control Fan (ANCF) was developed in the early 1990s to provide a convenient test bed to measure and understand fan-generated acoustics, duct propagation, and radiation to the farfield. As part of a complete upgrade, current baseline and acoustic measurements were documented. Extensive in-duct, farfield acoustic, and flow field measurements are reported. This is a follow-on paper to documenting the operating description of the ANCF. Author NOISE REDUCTION; ACOUSTIC MEASUREMENT; SOUND WAVES; FAR FIELDS 20090042751 NASA Glenn Research Center, Cleveland, OH, United States Experimental Investigation of the Application of Microramp Flow Control to an Oblique Shock Interaction Hirt, Stefanie M.; Anderson, Bernhard H.; November 2009; In English; 47th Aerospace Sciences Meeting, 5-8 Jan. 2009, Orlando, FL, United States; Original contains color and black and white illustrations Contract(s)/Grant(s): WBS 984754.02.07.03.13.02 Report No.(s): NASA/TM-2009-215630; AIAA Paper 2009-919; E-16942; No Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090042751 The effectiveness of microramp flow control devices in controlling an oblique shock interaction was tested in the 15- by 15-Centimeter Supersonic Wind Tunnel at NASA Glenn Research Center. Fifteen microramp geometries were tested varying the height, chord length, and spacing between ramps. Measurements of the boundary layer properties downstream of the shock reflection were analyzed using design of experiments methods. Results from main effects, D-optimal, full factorial, and central composite designs were compared. The designs provided consistent results for a single variable optimization. Author OBLIQUE SHOCK WAVES; BOUNDARY LAYERS; SHOCK WAVE INTERACTION; EXPERIMENT DESIGN; FACTORIAL DESIGN 20090042763 NASA Goddard Space Flight Center, Greenbelt, MD, United States The Global Space-Based Inter-Calibration System (GSICS) Goldberg, M; Ohring, G.; Butler, J.; Cao, C.; Datla, R.; Doelling, D.; Gartner, V.; Hewison, T.; Iacovazzi, B.; Kim, D.; Kurino, T.; Lafeuille, J.; Minnis, P.; Renaut, D.; Schmetz, J.; Tobin, D.; Wang, L.; Weng, F.; Wu, X.; Yu, F.; Zhang, P.; Zhu, T.; [2009]; In English; Original contains color and black and white illustrations Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090042763 The Global Space-based Inter-Calibration System (GSICS) is a new international program to assure the comparability of satellite measurements taken at different times and locations by different instruments operated by different satellite agencies. Sponsored by the World Meteorological Organization and the Coordination Group for Meteorological Satellites, GSICS will inter-calibrate the instruments of the international constellation of operational low-earth-orbiting (LEO) and geostationary (GEO) environmental satellites and tie these to common reference standards. The intercomparability of the observations will result in more accurate measurements for assimilation in numerical weather prediction models, construction of more reliable climate data records, and progress towards achieving the societal goals of the Global Earth Observation System of Systems. GSICS includes globally coordinated activities for pre-launch instrument characterization, on-board routine calibration, sensor intercomparison of near-simultaneous observations of individual scenes or overlapping time series, vicarious calibration using Earth-based or celestial references, and field campaigns. An initial strategy uses high accuracy satellite instruments, such as the NASA Moderate Resolution Imaging Spectroradiometer (MODIS) and Atmospheric Infrared Sounder (AIRS), and the European Organization for the Exploitation of Meteorological Satellites (EUMETSAT) Centre National d'Etudes Spatiales (CNES) Infrared Atmospheric Sounding Interferometer (IASI), as space-based reference standards for inter-calibrating the operational satellite sensors. Inter-calibration results obtained thus far are summarized and future plans are presented. Agencies participating in the program include Centre National d Etudes Spatiales, China Meteorological Administration, EUMETSAT, Japan Meteorological Agency, Korea Meteorological Administration, NASA, National Institute of Standards and Technology, and NOAA. Author INTERCALIBRATION; MODIS (RADIOMETRY); SATELLITE INSTRUMENTS; SYSTEMS ENGINEERING; MATHEMATICAL MODELS 20090042764 NASA Goddard Space Flight Center, Greenbelt, MD, United States Responding to Climate Change: Adelie Penguins Confront Astronomical and Ocean Boundaries Ballard, Grant; Toniolo, Viola; Ainley, David G.; Parkinson, Claire L.; Arrigo, Kevin R.; Trathan, Phil N.; [2009]; In English; Original contains black and white illustrations Contract(s)/Grant(s): NNG05GR19G; OPP 0440643 Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090042764 Long-distance migration enables many organisms to take advantage of lucrative breeding and feeding opportunities during summer at high latitudes and then to move to lower, more temperate latitudes for the remainder of the year. The latitudinal range of the Ad lie penguin spans ~ 22 deg. Penguins from northern colonies may not migrate, but due to the high latitude of Ross Island colonies, these penguins almost certainly undertake the longest migrations for the species. Previous work has suggested that Adelies require both pack ice and some ambient light at all times of year. Over a 3-yr period, which included winters of both extensive and reduced sea ice, we investigated migratory routes and characteristics and wintering locations of Adelie Penguins from two colonies of very different size on Ross Island, Ross Sea, the southernmost colonies for any penguin. We acquired data from 3-16 Geolocation Sensors affixed to penguins each year at both Cape Royds and Cape Crozier in 2003-2005. Migrations averaged 12,760 km, with the longest being 17,600 km, and were in part facilitated by pack ice movement. Trip distances varied annually, but not by colony. Penguins rarely traveled north of the main sea ice pack, and used areas with high sea-ice concentration, ranging from 75-85%, about 500 km inward from the ice edge. They also used locations where there was some twilight (2-7 hr with sun greater than 6 below horizon). We review how Adelie Penguin migration has likely changed since withdrawal of the West Antarctic Ice 35 Sheet across the Ross Sea beginning 12,000 yBP. If sea ice extent in the Ross Sea sector decreases, as predicted by climate models, we can expect change in wintering areas, the location of which ultimately may be limited more by the availability of adequate light for visual foraging than by the availability of suitable pack-ice. Author CLIMATE CHANGE; OCEANS; ANTARCTIC REGIONS; CLIMATE MODELS; PHENOLOGY; BIRDS 20090042768 NASA Glenn Research Center, Cleveland, OH, United States Axial and Centrifugal Compressor Mean Line Flow Analysis Method Veres, Joseph P.; November 2009; In English; 47th Aerospace Sciences Meeting, 5-8 Jan. 2009, Orlando, FL, United States; Original contains black and white illustrations Contract(s)/Grant(s): WBS 561581.02.08.03.21.03 Report No.(s): NASA/TM-2009-215585; AIAA Paper 2009-1641; E-16825; No Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090042768 This paper describes a method to estimate key aerodynamic parameters of single and multistage axial and centrifugal compressors. This mean-line compressor code COMDES provides the capability of sizing single and multistage compressors quickly during the conceptual design process. Based on the compressible fluid flow equations and the Euler equation, the code can estimate rotor inlet and exit blade angles when run in the design mode. The design point rotor efficiency and stator losses are inputs to the code, and are modeled at off design. When run in the off-design analysis mode, it can be used to generate performance maps based on simple models for losses due to rotor incidence and inlet guide vane reset angle. The code can provide an improved understanding of basic aerodynamic parameters such as diffusion factor, loading levels and incidence, when matching multistage compressor blade rows at design and at part-speed operation. Rotor loading levels and relative velocity ratio are correlated to the onset of compressor surge. NASA Stage 37 and the three-stage NASA 74-A axial compressors were analyzed and the results compared to test data. The code has been used to generate the performance map for the NASA 76-B three-stage axial compressor featuring variable geometry. The compressor stages were aerodynamically matched at off-design speeds by adjusting the variable inlet guide vane and variable stator geometry angles to control the rotor diffusion factor and incidence angles. Author TURBOCOMPRESSORS; FLUID FLOW; COMPUTATIONAL FLUID DYNAMICS; COMPRESSIBLE FLUIDS; DESIGN ANALYSIS; GUIDE VANES; CENTRIFUGAL COMPRESSORS Additions to the NASA Aeronautics and Space Database as of 12/31/2009 20090042796 NASA Goddard Space Flight Center, Greenbelt, MD, United States Workshop on Sustainable Infrastructure with NASA Science Mission Directorate and NASA's Office of Infrastructure Representatives Rosenzweig, Cynthia; Brown, Molly; [2009]; In English; Climate Change Impacts and Adapptation, 28-30 Jul. 2009, Cocoa Beach, FL, United States No Copyright; Avail.: CASI: A01, Hardcopy Avail Online: http://hdl.handle.net/2060/20090042796 NASA conducted a workshop in July 2009 to bring together their experts in the climate science and climate impacts domains with their institutional stewards. The workshop serves as a pilot for how a federal agency can start to: a) understand current and future climate change risks, b) develop a list of vulnerable institutional capabilities and assets, and c) develop next steps so flexible adaptation strategies can be developed and implemented. 63 attendees (26 scientists and over 30 institutional stewards) participated in the workshop, which extended across all or part of three days. Author CLIMATE CHANGE; NASA PROGRAMS; ADAPTATION; MISSION PLANNING 20090042797 NASA Goddard Space Flight Center, Greenbelt, MD, United States Evaluation of Surface and Near-Surface Melt Characteristics on the Greenland Ice Sheet using MODIS and QuikSCAT Data Hall, Dorothy K.; Nghiem, Son V.; Schaaf, Crystal B.; DiGirolamo, Nicolo E.; [2009]; In English; To be published in Journal of Geophysical Research/American Geophysical Union, FROM, FROM, FROM; Original contains color illustrations Copyright; Avail.: CASI: A04, Hardcopy Avail Online: http://hdl.handle.net/2060/20090042797 The Greenland Ice Sheet has been the focus of much attention recently because of increasing melt in response to regional climate warming. To improve our ability to measure surface melt, we use remote-sensing data products to study surface and near-surface melt characteristics of the Greenland Ice Sheet for the 2007 melt season when record melt extent and runoff occurred. Moderate Resolution Imaging Spectroradiometer (MODIS) daily land-surface temperature (LST), MODIS daily snow albedo, and a special diurnal melt product derived from QuikSCAT (QS) scatterometer data, are all effective in measuring the evolution of melt on the ice sheet. These daily products, produced from different parts of the electromagnetic spectrum, are sensitive to different geophysical features, though QS- and MODIS-derived melt generally show excellent correspondence when surface melt is present on the ice sheet. Values derived from the daily MODIS snow albedo product drop in response to melt, and change with apparent grain-size changes. For the 2007 melt season, the QS and MODIS LST products detect 862,769 square kilometers and 766,184 square kilometers of melt, respectively. The QS product detects about 11% greater melt extent than is detected by the MODIS LST product probably because QS is more sensitive to surface melt, and can detect subsurface melt. The consistency of the response of the different products demonstrates unequivocally that physically-meaningful melt/freeze boundaries can be detected. We have demonstrated that these products, used together, can improve the precision in mapping surface and near-surface melt extent on the Greenland Ice Sheet. Author GREENLAND; MODIS (RADIOMETRY); CLIMATOLOGY; GEOPHYSICS; ALBEDO; SURFACE PROPERTIES 20090042798 Maryland Univ., College Park, MD, United States A Reference Model for Software and System Inspections. White Paper He, Lulu; Shull, Forrest; [2009]; In English; Original contains color and black and white illustrations Contract(s)/Grant(s): NNX08AZ60G Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090042798 Software Quality Assurance (SQA) is an important component of the software development process. SQA processes provide assurance that the software products and processes in the project life cycle conform to their specified requirements by planning, enacting, and performing a set of activities to provide adequate confidence that quality is being built into the software. Typical techniques include: (1) Testing (2) Simulation (3) Model checking (4) Symbolic execution (5) Management reviews (6) Technical reviews (7) Inspections (8) Walk-throughs (9) Audits (10) Analysis (complexity analysis, control flow analysis, algorithmic analysis) (11) Formal method Our work over the last few years has resulted in substantial knowledge about SQA techniques, especially the areas of technical reviews and inspections. But can we apply the same QA techniques to the system development process? If yes, what kind of tailoring do we need before applying them in the system engineering context? If not, what types of QA techniques are actually used at system level? And, is there any room for improvement.) After a brief examination of the system engineering literature (especially focused on NASA and DoD guidance) we found that: (1) System and software development process interact with each other at different phases through development life cycle (2) Reviews are emphasized in both system and software development. (Figl.3). For some reviews (e.g. SRR, PDR, CDR), there are both system versions and software versions. (3) Analysis techniques are emphasized (e.g. Fault Tree Analysis, Preliminary Hazard Analysis) and some details are given about how to apply them. (4) Reviews are expected to use the outputs of the analysis techniques. In other words, these particular analyses are usually conducted in preparation for (before) reviews. The goal of our work is to explore the interaction between the Quality Assurance (QA) techniques at the system level and the software level. Derived from text COMPUTER PROGRAMMING; COMPUTER PROGRAMS; QUALITY CONTROL; SOFTWARE ENGINEERING; SOFTWARE RELIABILITY; COMPUTER SYSTEMS DESIGN; COMPUTER SYSTEMS PERFORMANCE 20090042799 NASA Goddard Space Flight Center, Greenbelt, MD, United States Discovery of a 115 Day Orbital Period in the Ultraluminous X-ray Source NGC 5408 X-1 Strohmayer, Tod E.; [2009]; In English; Original contains black and white illustrations No Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090042799 We report the detection of a 115 day periodicity in SWIFT/XRT monitoring source (ULX) NGC 5408 X-1. Our ongoing X-ray flux approximately twice weekly and has now a temporal baseline of ti 485 days. Periodogram analysis reveals a significant +/- 4 days. The modulation is detected of 3.2 x 10(exp -4) . The fractional modulation amplitude decreases 0.02 above 1 keV to 0.24 +/- 0.02 below the profile evolves as well, becoming less sharply peaked at with a periodic process, required to confirm the coherent nature of the Spectral analysis indicates that NGC 5408 X-1 can reach 0.3 - 10 We suggest that, like the 62 day period (X41.4-1-60), the periodicity detected in NGC 5408 X-1 represents containing the ULX. If this is only be a giant or supergiant star. Author LUMINOSITY; PERIODIC VARIATIONS; X RAY ASTRONOMY; BLACK HOLES (ASTRONOMY); X RAY STARS; STELLAR OSCILLATIONS; GALAXIES 20090042802 NASA Glenn Research Center, Cleveland, OH, United States Simulating Bone Loss in Microgravity Using Mathematical Formulations of Bone Remodeling Pennline, James A.; November 2009; In English; Original contains color illustrations Contract(s)/Grant(s): WBS 516724.02.02.08.01 Report No.(s): NASA/TM-2009-215824; E-17086; No Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090042802 Most mathematical models of bone remodeling are used to simulate a specific bone disease, by disrupting the steady state or balance in the normal remodeling process, and to simulate a therapeutic strategy. In this work, the ability of a mathematical model of bone remodeling to simulate bone loss as a function of time under the conditions of microgravity is investigated. The model is formed by combining a previously developed set of biochemical, cellular dynamics, and mechanical stimulus equations in the literature with two newly proposed equations; one governing the rate of change of the area of cortical bone tissue in a cross section of a cylindrical section of bone and one governing the rate of change of calcium in the bone fluid. The mechanical stimulus comes from a simple model of stress due to a compressive force on a cylindrical section of bone which can be reduced to zero to mimic the effects of skeletal unloading in microgravity. The complete set of equations formed is a system of first order ordinary differential equations. The results of selected simulations are displayed and discussed. Limitations and deficiencies of the model are also discussed as well as suggestions for further research. Author BONE DEMINERALIZATION; MATHEMATICAL MODELS; MUSCULOSKELETAL SYSTEM; BIOCHEMISTRY; MICROGRAVITY 20090042803 NASA Goddard Space Flight Center, Greenbelt, MD, United States Arc Second Alignment of International X-Ray Observatory Mirror Segments in a Fixed Structure Evans, Tyler C.; Chan, Kai-Wing; [2009]; In English; Original contains black and white illustrations Contract(s)/Grant(s): NNG07CA21C No Copyright; Avail.: CASI: A02, Hardcopy Avail Online: http://hdl.handle.net/2060/20090042803 The optics for the International X-Ray Observatory (IXO) require alignment and integration of about fourteen thousand thin mirror segments to achieve the mission goal of 3.0 square meters of effective area at 1.25 keV with an angular resolution of five arc seconds. These mirror segments are 0.4mm thick, and 200 to 400mm in size, which makes it hard not to impart distortion at the subarc second level. This paper outlines the precise alignment, verification testing, and permanent bonding techniques developed at NASA's Goddard Space Flight Center (GSFC). These techniques are used to overcome the challenge of transferring thin mirror segments from a temporary mount to a fixed structure with arc second alignment and minimal figure distortion. Recent advances in technology development in addition to the automation of several processes have produced significant results. This paper will highlight the recent advances in alignment, testing, and permanent bonding techniques as well as the results they have produced. Author ALIGNMENT; MIRRORS; X RAY ASTRONOMY; OBSERVATORIES; SEGMENTS; IMAGING TECHNIQUES 20090042804 NASA Goddard Space Flight Center, Greenbelt, MD, United States X-ray Reflected Spectra from Accretion Disk Models. I. Constant Density Atmospheres Garcia, Javier; Kallman, Timothy R.; [2009]; In English Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090042804 We present new models for illuminated accretion disks, their structure and reprocessed emission. We consider the effects of incident X-rays on the surface of an accretion disk by solving simultaneously the equations of radiative transfer, energy balance and ionization equilibrium over a large range of column densities. We assume plane-parallel geometry and azimuthal symmetry, such that each calculation corresponds to a ring at a given distance from the central object. Our models include recent and complete atomic data for K-shell of the iron and oxygen isonuclear sequences. We examine the effect on the spectrum of fluorescent Ka line emission and absorption in the emitted spectrum. We also explore the dependence of the spectrum on the strength of the incident X-rays and other input parameters, and discuss the importance of Comptonization on the emitted spectrum. Author ACCRETION DISKS; MATHEMATICAL MODELS; X RAY SPECTRA; ACTIVE GALACTIC NUCLEI; ILLUMINATING; STELLAR STRUCTURE; X RAY ASTRONOMY 20090042805 NASA Goddard Space Flight Center, Greenbelt, MD, United States Fiber Laser Development for LISA Numata, Kenji; Chen, Jeffrey R.; [2009]; In English; Original contains black and white illustrations Copyright; Avail.: CASI: A02, Hardcopy Avail Online: http://hdl.handle.net/2060/20090042805 We have developed a linearly-polarized Ytterbium-doped fiber ring laser with single longitudinal-mode output at 1064nm for LISA and other space applications. Single longitudinal-mode selection was achieved by using a fiber Bragg grating (FBG) and a fiber Fabry-Perot (FFP). The FFP also serves as a frequency-reference within our ring laser. Our laser exhibits comparable low frequency and intensity noise to Non-Planar Ring Oscillator (NPRO). By using a fiber-coupled phase modulator as a frequency actuator, the laser frequency can be electro-optically tuned at a rate of 100kHz. It appears that our fiber ring laser is promising for space applications where robustness of fiber optics is desirable. Author FIBER LASERS; FIBER OPTICS; OPTICAL FIBERS; LASER MATERIALS; BRAGG GRATINGS; RING LASERS 20090042807 NASA Goddard Space Flight Center, Greenbelt, MD, United States Discovery of Photon Index Saturation in the Black Hole Binary GRS 1915+105 Titarchuk, Lev; Seifina, Elena; [2009]; In English; Original contains black and white illustrations Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090042807 We present a study of the correlations between spectral, timing properties and mass accretion rate observed in X-rays from the Galactic Black Hole (BH) binary GRS 1915+105 during the transition between hard and soft states. We analyze all transition episodes from this source observed with Rossi X-ray Timing Explorer (RXTE), coordinated with Ryle Radio Telescope (RT) observations. We show that broad-band energy spectra of GRS 1915+105 during all these spectral states can be adequately presented by two Bulk Motion Comptonization (BMC) components: a hard component (BMC1, photon index Gamma(sub 1) = 1.7 -- 3.0) with turnover at high energies and soft thermal component (BMC2, Gamma(sub 2) = 2.7 -- 4.2) with characteristic color temperature < or = 1 keV, and the red-skewed iron line (LAOR) component. We also present observable correlations between the index and the normalization of the disk "seed" component. The use of "seed" disk normalization, which is presumably proportional to mass accretion rate in the disk, is crucial to establish the index saturation effect during the transition to the soft state. We discovered the photon index saturation of the soft and hard spectral components at values of < or approximately equal 4.2 and 3 respectively. We present a physical model which explains the index-seed photon normalization correlations. We argue that the index saturation effect of the hard component (BMC1) is due to the soft photon Comptonization in the converging inflow close to 1311 and that of soft component is due to matter accumulation in the transition layer when mass accretion rate increases. Furthermore we demonstrate a strong correlation between equivalent width of the iron line and radio flux in GRS 1915+105. In addition to our spectral model components we also find a strong feature of "blackbody-like" bump which color temperature is about 4.5 keV in eight observations of the intermediate and soft states. We discuss a possible origin of this "blackbody-like" emission. Author ACCRETION DISKS; BLACK HOLES (ASTRONOMY); ENERGY SPECTRA; PHOTONS; X RAY ASTRONOMY; BLACK BODY RADIATION 20090042810 NASA Goddard Space Flight Center, Greenbelt, MD, United States Extraterrestrial Amino Acids in the Almahata Sitta Meteorite Glavin, Daniel P.; Aubrey, Andrew D.; Callahan, Michael P.; Dworkin, Jason P.; Elsila, Jamie E.; Parker, Eric T.; Bada, Jeffrey L.; [2009]; In English; Original contains black and white illustrations Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090042810 Amino acid analysis of a meteorite fragment of asteroid 2008 TC(sub 3) called Almahata Sitta reverse-phase high-performance liquid chromatography coupled with spectrometry (HPLC-FD/ToF-MS) as part consortium. HPLC analyses of hot-water extracts from the meteorite six-carbon aliphatic amino acids and one- to three carbon parts-per-billion (ppb). The amino acids alanine, Beta-amino-n-butyric acid (Beta-ABA), 2-amino-2- 2-aminopentanoic acid (norvaline) in the meteorite were amino acids are indigenous to the meteorite and not amino acids were also identified in the background levels including alpha-aminoisobutyric acid (alpha-AIB), 4-amino-2- 4-amino-3-methylbutanoic acid, and 3-, 4-, and 5-aminopentanoic acid. and AlB in Almahata Sitta are approximately 1000 times lower than the carbonaceous meteorite Murchison. The abundances and unusual distribution of five carbon amino acids in Almahata carbonaceous meteorites and may be due to extensive alteration of amino acids on the parent asteroid by partial melting during formation or Author AMINO ACIDS; SHOCK HEATING; UREILITES; METEORITIC COMPOSITION; ISOTOPE RATIOS 20090042811 NASA Goddard Space Flight Center, Greenbelt, MD, United States Understanding the X-ray Flaring from Eta Carinae Moffat, A.F.J.; Corcoran, Michael F.; [2009]; In English; Original contains black and white illustrations Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090042811 We quantify the rapid variations in X-ray brightness ("flares") from the extremely massive colliding wind binary Eta Carinae seen during the past three orbital cycles by RXTE. The observed flares tend to be shorter in duration and more frequent as periastron is approached, although the largest ones tend to be roughly constant in strength at all phases. Plausible scenarios include (1) the largest of multi-scale stochastic wind clumps from the LBV component entering and compressing the hard X-ray emitting wind-wind collision (WWC) zone, (2) large-scale corotating interacting regions in the LBV wind sweeping across the WWC zone, or (3) instabilities intrinsic to the WWC zone. The first one appears to be most consistent with the observations, requiring homologously expanding clumps as they propagate outward in the LBV wind and a turbulence-like powerlaw distribution of clumps, decreasing in number towards larger sizes, as seen in Wolf-Rayet winds. Author ORBITAL ELEMENTS; X RAY TIMING EXPLORER; WOLF-RAYET STARS; STOCHASTIC PROCESSES; BRIGHTNESS; TURBULENCE; STELLAR ORBITS 20090042816 NASA Glenn Research Center, Cleveland, OH, United States Impact Testing on Reinforced Carbon-Carbon Flat Panels with Ice Projectiles for the Space Shuttle Return to Flight Program Melis, Matthew E.; Revilock, Duane M.; Pereira, Michael J.; Lyle, Karen H.; November 2009; In English; Original contains color illustrations Contract(s)/Grant(s): WBS 377816.06.03.02.04 Report No.(s): NASA/TM-2009-213641; E-15129; No Copyright; Avail.: CASI: A11, Hardcopy Avail Online: http://hdl.handle.net/2060/20090042816 Following the tragedy of the Orbiter Columbia (STS-107) on February 1, 2003, a major effort commenced to develop a better understanding of debris impacts and their effect on the space shuttle subsystems. An initiative to develop and validate physics-based computer models to predict damage from such impacts was a fundamental component of this effort. To develop the models it was necessary to physically characterize reinforced carbon-carbon (RCC) along with ice and foam debris materials, which could shed on ascent and impact the orbiter RCC leading edges. The validated models enabled the launch system community to use the impact analysis software LS-DYNA (Livermore Software Technology Corp.) to predict damage by potential and actual impact events on the orbiter leading edge and nose cap thermal protection systems. Validation of the material models was done through a three-level approach: Level 1--fundamental tests to obtain independent static and dynamic constitutive model properties of materials of interest, Level 2--subcomponent impact tests to provide highly controlled impact test data for the correlation and validation of the models, and Level 3--full-scale orbiter leading-edge impact tests to establish the final level of confidence for the analysis methodology. This report discusses the Level 2 test program conducted in the NASA Glenn Research Center (GRC) Ballistic Impact Laboratory with ice projectile impact tests on flat RCC panels, and presents the data observed. The Level 2 testing consisted of 54 impact tests in the NASA GRC Ballistic Impact Laboratory on 6- by 6-in. and 6- by 12-in. flat plates of RCC and evaluated three types of debris projectiles: Single-crystal, polycrystal, and "soft" ice. These impact tests helped determine the level of damage generated in the RCC flat plates by each projectile and validated the use of the ice and RCC models for use in LS-DYNA. Author CARBON-CARBON COMPOSITES; COMPOSITE STRUCTURES; DYNAMIC MODELS; FLAT PLATES; ICE; IMPACT TESTS; MATHEMATICAL MODELS 20090042817 NASA Glenn Research Center, Cleveland, OH, United States Engine Conceptual Design Studies for a Hybrid Wing Body Aircraft Tong, Michael T.; Jones, Scott M.; Haller, William J.; Handschuh, Robert F.; November 2009; In English; ASME Turbo 2009, 8-12 Jun. 2009, Orlando, FL, United States; Original contains black and white illustrations Contract(s)/Grant(s): WBS 561581.02.08.03.13.03 Report No.(s): NASA/TM-2009-215680; GT2009-59568; ARL-TR-4719; E-16910-1; No Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090042817 Worldwide concerns of air quality and climate change have made environmental protection one of the most critical issues in aviation today. NASA s current Fundamental Aeronautics Research program is directed at three generations of aircraft in the near, mid and far term, with initial operating capability around 2015, 2020, and 2030, respectively. Each generation has associated goals for fuel burn, NOx, noise, and field-length reductions relative to today s aircrafts. The research for the 2020 generation is directed at enabling a hybrid wing body (HWB) aircraft to meet NASA s aggressive technology goals. This paper presents the conceptual cycle and mechanical designs of the two engine concepts, podded and embedded systems, which were proposed for a HWB cargo freighter. They are expected to offer significant benefits in noise reductions without compromising the fuel burn. Author ENGINE DESIGN; ENVIRONMENT PROTECTION; NITROGEN OXIDES; NOISE REDUCTION; AERONAUTICAL ENGINEERING; AIR QUALITY 20090042818 NASA Glenn Research Center, Cleveland, OH, United States Advanced Noise Control Fan Aerodynamic Performance Bozak, Richard F., Jr.; November 2009; In English; Original contains color and black and white illustrations Contract(s)/Grant(s): WBS 561581.02.08.03.18.02 Report No.(s): NASA/TM-2009-215807; E-17070; No Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090042818 The Advanced Noise Control Fan at the NASA Glenn Research Center is used to experimentally analyze fan generated acoustics. In order to determine how a proposed noise reduction concept affects fan performance, flow measurements can be used to compute mass flow. Since tedious flow mapping is required to obtain an accurate mass flow, an equation was developed to correlate the mass flow to inlet lip wall static pressure measurements. Once this correlation is obtained, the mass flow for future configurations can be obtained from the nonintrusive wall static pressures. Once the mass flow is known, the thrust and fan performance can be evaluated. This correlation enables fan acoustics and performance to be obtained simultaneously without disturbing the flow. Author NOISE REDUCTION; AERODYNAMIC CHARACTERISTICS; INLET PRESSURE; STATIC PRESSURE; FLOW MEASUREMENT; FLOW DISTRIBUTION; MASS FLOW; ACOUSTICS 20090042819 NASA Glenn Research Center, Cleveland, OH, United States Windage Power Loss in Gas Foil Bearings and the Rotor-Stator Clearance of High Speed Generators Operating in High Pressure Environments Bruckner, Robert J.; November 2009; In English; ASME Turbo Expo 2009, 8-12 Jun. 2009, Orlando, FL, United States; Original contains color and black and white illustrations Contract(s)/Grant(s): WBS 877686.02.07.03.01.01.14 Report No.(s): NASA/TM-2009-215826; GT2009-60118; E-17088; No Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090042819 Closed Brayton Cycle (CBC) and Closed Supercritical Cycle (CSC) engines are prime candidates to convert heat from a reactor into electric power for robotic space exploration and habitation. These engine concepts incorporate a permanent magnet starter/generator mounted on the engine shaft along with the requisite turbomachinery. Successful completion of the long-duration missions currently anticipated for these engines will require designs that adequately address all losses within the machine. The preliminary thermal management concept for these engine types is to use the cycle working fluid to provide the required cooling. In addition to providing cooling, the working fluid will also serve as the bearing lubricant. Additional requirements, due to the unique application of these microturbines, are zero contamination of the working fluid and entirely maintenance-free operation for many years. Losses in the gas foil bearings and within the rotor-stator gap of the generator become increasingly important as both rotational speed and mean operating pressure are increased. This paper presents the results of an experimental study, which obtained direct torque measurements on gas foil bearings and generator rotor-stator gaps. Test conditions for these measurements included rotational speeds up to 42,000 revolutions per minute, pressures up to 45 atmospheres, and test gases of nitrogen, helium, and carbon dioxide. These conditions provided a maximum test Taylor number of nearly one million. The results show an exponential rise in power loss as mean operating density is increased for both the gas foil bearing and generator windage. These typical "secondary" losses can become larger than the total system output power if conventional design paradigms are followed. A nondimensional analysis is presented to extend the experimental results into the CSC range for the generator windage. Author FOIL BEARINGS; BRAYTON CYCLE; CLOSED CYCLES; TURBOMACHINERY; HIGH PRESSURE; ROTORS; SHAFTS (MACHINE ELEMENTS) 20090042820 NASA Glenn Research Center, Cleveland, OH, United States Bayes Analysis and Reliability Implications of Stress-Rupture Testing a Kevlar/Epoxy COPV Using Temperature and Pressure Acceleration Phoenix, S. Leigh; Kezirian, Michael T.; Murthy, Pappu L. N.; November 2009; In English; 50th Structures, Structural Dynamics, and Materials Conference, 4-7 May 2009, Palm Springs, CA, United States; Original contains color and black and white illustrations Contract(s)/Grant(s): WBS 869021.03.03.02.01 Report No.(s): NASA/TM-2009-215830; AIAA Paper 2009-2569; E-17091; Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090042820 Composite Overwrapped Pressure Vessels (COPVs) that have survived a long service time under pressure generally must be recertified before service is extended. Flight certification is dependent on the reliability analysis to quantify the risk of stress rupture failure in existing flight vessels. Full certification of this reliability model would require a statistically significant number of lifetime tests to be performed and is impractical given the cost and limited flight hardware for certification testing purposes. One approach to confirm the reliability model is to perform a stress rupture test on a flight COPV. Currently, testing of such a Kevlar49 (Dupont)/epoxy COPV is nearing completion. The present paper focuses on a Bayesian statistical approach to analyze the possible failure time results of this test and to assess the implications in choosing between possible model parameter values that in the past have had significant uncertainty. The key uncertain parameters in this case are the actual fiber stress ratio at operating pressure, and the Weibull shape parameter for lifetime; the former has been uncertain due to ambiguities in interpreting the original and a duplicate burst test. The latter has been uncertain due to major differences between COPVs in the database and the actual COPVs in service. Any information obtained that clarifies and eliminates uncertainty in these parameters will have a major effect on the predicted reliability of the service COPVs going forward. The key result is that the longer the vessel survives, the more likely the more optimistic stress ratio model is correct. At the time of writing, the resulting effect on predicted future reliability is dramatic, increasing it by about one "nine," that is, reducing the predicted probability of failure by an order of magnitude. However, testing one vessel does not change the uncertainty on the Weibull shape parameter for lifetime since testing several vessels would be necessary. Author PRESSURE VESSELS; COMPOSITE WRAPPING; WEIBULL DENSITY FUNCTIONS; RELIABILITY ANALYSIS; STRESS ANALYSIS; EPOXY RESINS; KEVLAR (TRADEMARK); BAYES THEOREM 20090042821 NASA Glenn Research Center, Cleveland, OH, United States The Case for Intelligent Propulsion Control for Fast Engine Response Litt, Jonathan S.; Frederick, Dean K.; Guo, Ten-Huei; November 2009; In English; Infotech@Aerospace Conference, 6-9, Seattle, WA, United States Contract(s)/Grant(s): WBS 457280.02.07.03.04.03 Report No.(s): NASA/TM-2009-215668; AIAA Paper 2009-1876; E-17010; Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090042821 Damaged aircraft have occasionally had to rely solely on thrust to maneuver as a consequence of losing hydraulic power needed to operate flight control surfaces. The lack of successful landings in these cases inspired research into more effective methods of utilizing propulsion-only control. That research demonstrated that one of the major contributors to the difficulty in landing is the slow response of the engines as compared to using traditional flight control. To address this, research is being conducted into ways of making the engine more responsive under emergency conditions. This can be achieved by relaxing controller limits, adjusting schedules, and/or redesigning the regulators to increase bandwidth. Any of these methods can enable faster response at the potential expense of engine life and increased likelihood of stall. However, an example sensitivity analysis revealed a complex interaction of the limits and the difficulty in predicting the way to achieve the fastest response. The sensitivity analysis was performed on a realistic engine model, and demonstrated that significantly faster engine response can be achieved compared to standard Bill of Material control. However, the example indicates the need for an intelligent approach to controller limit adjustment in order for the potential to be fulfilled. Author CONTROLLERS; FLIGHT CONTROL; ENGINE CONTROL; PROPULSION; REGULATORS; CONTROL SURFACES 20090042822 NASA Langley Research Center, Hampton, VA, United States Pion Total Cross Section in Nucleon - Nucleon Collisions Norbury, John W.; December 2009; In English; Original contains color illustrations Contract(s)/Grant(s): WBS 651549.02.07.01 Report No.(s): NASA/TP-2009-215953; L-19597; No Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090042822 Total cross section parameterizations for neutral and charged pion production in nucleon - nucleon collisions are compared to experimental data over the projectile momentum range from threshold to 300 GeV. Both proton - proton and proton - neutron reactions are considered. Overall excellent agreement between parameterizations and experiment is found, except for notable disagreements near threshold. In addition, the hypothesis that the neutral pion production cross section can be obtained from the average charged pion cross section is checked. The theoretical formulas presented in the paper obey this hypothesis for projectile momenta below 500 GeV. The results presented provide a test of engineering tools used to calculate the pion component of space radiation. Author PIONS; PARAMETERIZATION; PROTONS; NUCLEAR REACTIONS; EXTRATERRESTRIAL RADIATION; NEUTRONS; ATOMIC COLLISIONS 20090042823 NASA Langley Research Center, Hampton, VA, United States Experimental Behavior of Fatigued Single Stiffener PRSEUS Specimens Jegley, Dawn C.; December 2009; In English; Original contains color and black and white illustrations Contract(s)/Grant(s): WBS 699959.02.08.07.02.02 Report No.(s): NASA/TM-2009-215955; L-19782; LF99-9677; No Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090042823 NASA, the Air Force Research Laboratory and The Boeing Company have worked to develop new low-cost, light-weight composite structures for aircraft. A Pultruded Rod Stitched Efficient Unitized Structure (PRSEUS) concept has been developed which offers advantages over traditional metallic structure. In this concept a stitched carbon-epoxy material system has been developed with the potential for reducing the weight and cost of transport aircraft structure by eliminating fasteners, thereby reducing part count and labor. By adding unidirectional carbon rods to the top of stiffeners, the panel becomes more structurally efficient. This combination produces a more damage tolerant design. This document describes the results of experimentation on PRSEUS specimens loaded in unidirectional compression in fatigue and to failure. Author COMPOSITE STRUCTURES; EPOXY MATRIX COMPOSITES; DURABILITY; MILITARY TECHNOLOGY; WEIGHT REDUCTION 20090042837 NASA Glenn Research Center, Cleveland, OH, United States Concept for a Low-Cost, High-Efficiency Precipitation Radar System Based on Ferroelectric Reflectarray Antenna Romanofsky, Robert; Mueller, Carl; Chandrasekar, Chandra V.; October 2009; In English; 2009 Radar Conference, 4-8 May 2009, Pasadena, CA, United States; Original contains color illustrations Contract(s)/Grant(s): WBS 439432.04.04.01 Report No.(s): NASA/TM-2009-215663; E-17005; Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090042837 This work proposes a concept on a novel scanning phased array, based on thin film ferroelectric phase shifters, for an X-band precipitation monostatic radar. Author FERROELECTRICITY; ANTENNA ARRAYS; METEOROLOGICAL RADAR; SUPERHIGH FREQUENCIES; REFLECTOR ANTENNAS; PRECIPITATION (METEOROLOGY); LOW COST 20090042841 NASA Goddard Space Flight Center, Greenbelt, MD, United States Suzaku Observation of Strong Fluorescent Iron Line Emission from the Young Stellar Object V1647 Ori during Its New X-ray Outburst Hamaguchi, Kenji; Grosso, Nicolas; Kastner, Joel H.; Weintraub, David A.; Richmond, Michael; [2009]; In English; Original contains black and white illustrations Contract(s)/Grant(s): NNX09AC11GRTOP 344-53-51 Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090042841 The Suzaku X-ray satellite observed the young stellar object V1647 Ori on 2008 October 8 during the new mass accretion outburst reported in August 2008. During the 87 ksec observation with a net exposure of 40 ks, V1647 Ori showed a. high level of X-ray emission with a gradual decrease in flux by a factor of 5 and then displayed an abrupt flux increase by an order of magnitude. Such enhanced X-ray variability was also seen in XMM-Newton observations in 2004 and 2005 during the 2003-2005 outburst, but has rarely been observed for other young stellar objects. The spectrum clearly displays emission from Helium-like iron, which is a signature of hot plasma (kT approx.5 keV). It also shows a fluorescent iron Ka line with a remarkably large equivalent width of approx. 600 eV. Such a, large equivalent width indicates that a part of the incident X-ray emission that irradiates the circumstellar material and/or the stellar surface is hidden from our line of sight. XMM-Newton spectra during the 2003-2005 outburst did not show a strong fluorescent iron Ka line ; so that the structure of the circumstellar gas very close to the stellar core that absorbs and re-emits X-ray emission from the central object may have changed in between 2005 and 2008. This phenomenon may be related to changes in the infrared morphology of McNeil's nebula between 2004 and 2008. Author STELLAR ENVELOPES; STARS; LINE OF SIGHT; INFRARED RADIATION; FLUORESCENCE; EXPOSURE; SIGNATURES 20090042850 Houston Univ., Houston, TX United States Shape memory alloy actuated adaptive exhaust nozzle for jet engine Song, Gangbing, Inventor; Ma, Ning, Inventor; September 15, 2009; In English Patent Info.: August 29, 2005US-Patent-7,587,899; US-Patent-Appl-SN-11/214,418 No Copyright; Avail.: CASI: A02, Hardcopy Avail Online: http://hdl.handle.net/2060/20090042850 The proposed adaptive exhaust nozzle features an innovative use of the shape memory alloy (SMA) actuators for actively control of the opening area of the exhaust nozzle for jet engines. The SMA actuators remotely control the opening area of the exhaust nozzle through a set of mechanism. An important advantage of using SMA actuators is the reduction of weight of the actuator system for variable area exhaust nozzle. Another advantage is that the SMA actuator can be activated using the heat from the exhaust and eliminate the need of other energy source. A prototype has been designed and fabricated. The functionality of the proposed SMA actuated adaptive exhaust nozzle is verified in the open-loop tests. Official Gazette of the U.S. Patent and Trademark Office SHAPE MEMORY ALLOYS; EXHAUST NOZZLES; JET ENGINES; ACTUATORS 20090042852 NASA, Washington, DC United States Magnetic field response sensor for conductive media Woodard, Stanley E., Inventor; Taylor, Bryant D., Inventor; September 15, 2009; In English Patent Info.: June 2, 2006US-Patent-7,589,525; US-Patent-Appl-SN-11/421,886 No Copyright; Avail.: CASI: A02, Hardcopy Avail Online: http://hdl.handle.net/2060/20090042852 A magnetic field response sensor comprises an inductor placed at a fixed separation distance from a conductive surface to address the low RF transmissivity of conductive surfaces. The minimum distance for separation is determined by the sensor response. The inductor should be separated from the conductive surface so that the response amplitude exceeds noise level by a recommended 10 dB. An embodiment for closed cavity measurements comprises a capacitor internal to said cavity and an inductor mounted external to the cavity and at a fixed distance from the cavity's wall. An additional embodiment includes a closed cavity configuration wherein multiple sensors and corresponding antenna are positioned inside the cavity, with the antenna and inductors maintained at a fixed distance from the cavity's wall. Official Gazette of the U.S. Patent and Trademark Office RADIO FREQUENCIES; INDUCTORS; MAGNETIC FIELDS; NOISE INTENSITY; CAPACITORS 20090042854 NASA, Washington, DC United States Phased-array optical whispering gallery mode modulation and method Strekalov, Dmitry V., Inventor; September 15, 2009; In English Patent Info.: October 15, 2008US-Patent-7,590,313; US-Patent-Appl-SN-12/251,607 No Copyright; Avail.: CASI: A02, Hardcopy Avail Online: http://hdl.handle.net/2060/20090042854 A whispering gallery mode (WGM) resonator device and method capable of filtering sidebands of optical modulators are provided. The method includes providing an optical resonator adapted to support whispering gallery modes and forming a first field and a second field from a first location and a second location, respectively, at the circumference of the optical resonator and being separated by an arc angle, .alpha.. The method includes adjusting relative phase between the first field and the second field in accordance to a differential phase, .beta., and combining the first and the second fields into an output. Particular selection of the arc angle, .alpha., and the differential phase, .beta., can determine the function of the output. Official Gazette of the U.S. Patent and Trademark Office PHASED ARRAYS; OPTICAL RESONATORS; WHISPERING GALLERY MODES; RESONATORS 20090042856 NASA, Washington, DC United States Systems and methods for detecting a failure event in a field programmable gate array Ng, Tak-Kwong, Inventor; Herath, Jeffrey A., Inventor; September 15, 2009; In English Patent Info.: September 14, 2006US-Patent-7,590,904; US-Patent-Appl-SN-11/531,703 No Copyright; Avail.: CASI: A02, Hardcopy Avail Online: http://hdl.handle.net/2060/20090042856 An embodiment generally relates to a method of self-detecting an error in a field programmable gate array (FPGA). The method includes writing a signature value into a signature memory in the FPGA and determining a conclusion of a configuration refresh operation in the FPGA. The method also includes reading an outcome value from the signature memory. Official Gazette of the U.S. Patent and Trademark Office FIELD-PROGRAMMABLE GATE ARRAYS; DETECTION; ERRORS; FAILURE 20090042858 Children's Hospital of Los Angeles, Los Angeles, CA United States Non-invasive in vivo measurement of macular carotenoids Lambert, James L., Inventor; Borchert, Mark S., Inventor; September 22, 2009; In English Contract(s)/Grant(s): NAS7-1407 Patent Info.: February 5, 2004US-Patent-7,593,763; US-Patent-Appl-SN-10/773,099 No Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090042858 A non-invasive in vivo method for assessing macular carotenoids includes performing Optical Coherence Tomography (OCT) on a retina of a subject. A spatial representation of carotenoid levels in the macula based on data from the OCT of the retina can be generated. Official Gazette of the U.S. Patent and Trademark Office IN VIVO METHODS AND TESTS; CAROTENOIDS; RETINA; TOMOGRAPHY 20090042860 NASA Johnson Space Center, Houston, TX, United States Activation of Lunar Dust Via Grinding and UV Radiation Wallace, W. T.; Jeevarajan, Antony S.; Taylor, L. A.; December 08, 2009; In English; Lunar Airborne Dust Toxicity Assessment Group, 8 Dec. 2009, Houston, TX, United States; Original contains color and black and white illustrations Report No.(s): JSC-CN-19474; Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090042860 This slide presentation reviews how lunar dust is activated. The presentation includes information on soil chemistry, grinding, and UV exposure. CASI EXPOSURE; LUNAR DUST; ULTRAVIOLET RADIATION 20090042865 NASA Langley Research Center, Hampton, VA, United States A Relationship Between Constraint and the Critical Crack Tip Opening Angle Johnston, William M.; James, Mark A.; December 2009; In English; Original contains black and white illustrations Contract(s)/Grant(s): NNL07AA00B; NNL078M74TWBS 658259.02.07.07.03 Report No.(s): NASA/CR-2009-215930; LF99-9198; Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090042865 Of the various approaches used to model and predict fracture, the Crack Tip Opening Angle (CTOA) fracture criterion has been successfully used for a wide range of two-dimensional thin-sheet and thin plate applications. As thicker structure is considered, modeling the full three-dimensional fracture process will become essential. This paper investigates relationships between the local CTOA evaluated along a three-dimensional crack front and the corresponding local constraint. Previously reported tunneling crack front shapes were measured during fracture by pausing each test and fatigue cycling the specimens to mark the crack surface. Finite element analyses were run to model the tunneling shape during fracture, with the analysis loading conditions duplicating those tests. The results show an inverse relationship between the critical fracture value and constraint which is valid both before maximum load and after maximum load. Author CRACK TIPS; MATHEMATICAL MODELS; MECHANICAL PROPERTIES; CONSTRAINTS; FRACTURE MECHANICS 20090042868 NASA Marshall Space Flight Center, Huntsville, AL, United States Verification of the ASTM G-124 Purge Equation Robbins, Katherine E.; Davis, Samuel Eddie; October 07, 2009; In English; Twelfth International Symposium on Flammability and Sensitivity of Materials in Oxygen Enriched Atmospheres, 7-9 Oct. 2009, Berlin, Germany; Original contains black and white illustrations Report No.(s): M09-0198; Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090042868 ASTM G-124 seeks to evaluate combustion characteristics of metals in high-purity (greater than 99%) oxygen atmospheres. ASTM G-124 provides the following equation to determine the minimum number of purges required to reach this level of purity in a test chamber: n = -4/log10(Pa/Ph), where "n" is the total number of purge cycles required, Ph is the absolute pressure used for the purge on each cycle and Pa is the atmospheric pressure or the vent pressure. The origin of this equation is not known and has been the source of frequent questions as to its accuracy and reliability. This paper shows the derivation of the G-124 purge equation, and experimentally explores the equation to determine if it accurately predicts the number of cycles required. Author METAL COMBUSTION; PURGING; COMBUSTION CHAMBERS; OXYGEN ANALYZERS; BURNING RATE; TEST CHAMBERS 20090042870 NASA, Washington, DC United States Orbital foamed material extruder Tucker, Dennis S., Inventor; September 29, 2009; In English Patent Info.: November 19, 2007US-Patent-7,594,530; US-Patent-Appl-SN-11/942,322 No Copyright; Avail.: CASI: A02, Hardcopy Avail Online: http://hdl.handle.net/2060/20090042870 This invention is a process for producing foamed material in space comprising the steps of: rotating the material to simulate the force of gravity; heating the rotating material until it is molten; extruding the rotating, molten material; injecting gas into the extruded, rotating, molten material to produce molten foamed material; allowing the molten foamed material to cool to below melting temperature to produce the foamed material. The surface of the extruded foam may be heated to above melting temperature and allowed to cool to below melting temperature. The extruded foam may also be cut to predetermined length. The starting material may be metal or glass. Heating may be accomplished by electrical heating elements or by solar heating. Official Gazette of the U.S. Patent and Trademark Office EXTRUDING; HEATING; FOAMING; FOAMS; MELTING 20090042871 NASA, Washington, DC United States Resin infusion of layered metal/composite hybrid and resulting metal/composite hybrid laminate Cano, Roberto J., Inventor; Grimsley, Brian W., Inventor; Weiser, Erik S., Inventor; Jensen, Brian J., Inventor; September 29, 2009; In English Patent Info.: July 31, 2006US-Patent-7,595,112; US-Patent-Appl-SN-11/461,150 No Copyright; Avail.: CASI: A02, Hardcopy Avail Online: http://hdl.handle.net/2060/20090042871 A method of fabricating a metal/composite hybrid laminate is provided. One or more layered arrangements are stacked on a solid base to form a layered structure. Each layered arrangement is defined by a fibrous material and a perforated metal sheet. A resin in its liquid state is introduced along a portion of the layered structure while a differential pressure is applied across the laminate structure until the resin permeates the fibrous material of each layered arrangement and fills perforations in each perforated metal sheet. The resin is cured thereby yielding a metal/composite hybrid laminate. Official Gazette of the U.S. Patent and Trademark Office LAMINATES; FABRICATION; METAL SHEETS; RESINS 20090042872 California Inst. of Tech., Pasadena, CA United States Anti- reflective device having an anti-reflection surface formed of silicon spikes with nano-tips Bae, Youngsman, Inventor; Mooasser, Sohrab, Inventor; Manohara, Harish, Inventor; Lee, Choonsup, Inventor; Bae, Kungsam, Inventor; September 29, 2009; In English Patent Info.: September 7, 2006US-Patent-7,595,477; US-Patent-Appl-SN-11/518,537 No Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090042872 Described is a device having an anti-reflection surface. The device comprises a silicon substrate with a plurality of silicon spikes formed on the substrate. A first metallic layer is formed on the silicon spikes to form the anti-reflection surface. The device further includes an aperture that extends through the substrate. A second metallic layer is formed on the substrate. The second metallic layer includes a hole that is aligned with the aperture. A spacer is attached with the silicon substrate to provide a gap between an attached sensor apparatus. Therefore, operating as a Micro-sun sensor, light entering the hole passes through the aperture to be sensed by the sensor apparatus. Additionally, light reflected by the sensor apparatus toward the first side of the silicon substrate is absorbed by the first metallic layer and silicon spikes and is thereby prevented from being reflected back toward the sensor apparatus. Official Gazette of the U.S. Patent and Trademark Office SILICON; SUBSTRATES; METAL SURFACES 20090042873 NASA, Washington, DC United States Video image stabilization and registration--plus Hathaway, David H., Inventor; September 29, 2009; In English Patent Info.: July 1, 2005US-Patent-7,595,841; US-Patent-Appl-SN-11/174,210 No Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090042873 A method of stabilizing a video image displayed in multiple video fields of a video sequence includes the steps of: subdividing a selected area of a first video field into nested pixel blocks; determining horizontal and vertical translation of each of the pixel blocks in each of the pixel block subdivision levels from the first video field to a second video field; and determining translation of the image from the first video field to the second video field by determining a change in magnification of the image from the first video field to the second video field in each of horizontal and vertical directions, and determining shear of the image from the first video field to the second video field in each of the horizontal and vertical directions. Official Gazette of the U.S. Patent and Trademark Office IMAGE PROCESSING; STABILIZATION; PIXELS; IMAGING TECHNIQUES 20090042874 NASA, Washington, DC United States Project management tool Maluf, David A., Inventor; Gawdiak, Yuri O., Inventor; Bell, David G., Inventor; Gurram, Mohana M., Inventor; September 29, 2009; In English Patent Info.: August 25, 2004US-Patent-7,596,416; US-Patent-Appl-SN-10/928,874 No Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090042874 A system for managing a project that includes multiple tasks and a plurality of workers. Input information includes characterizations based upon a human model, a team model and a product model. Periodic reports, such as a monthly report, a task plan report, a budget report and a risk management report, are generated and made available for display or further analysis. An extensible database allows searching for information based upon context and upon content. Official Gazette of the U.S. Patent and Trademark Office MANAGEMENT SYSTEMS; PROJECT MANAGEMENT; REPORTS 20090042875 Illinois Univ., Urbana, IL United States Self-healing elastomer system Keller, Michael W., Inventor; Sottos, Nancy R., Inventor; White, Scott R., Inventor; August 4, 2009; In English Patent Info.: June 2, 2006US-Patent-7,569,625; US-Patent-Appl-SN-11/421,993 No Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090042875 A composite material includes an elastomer matrix, a set of first capsules containing a polymerizer, and a set of second capsules containing a corresponding activator for the polymerizer. The polymerizer may be a polymerizer for an elastomer. The composite material may be prepared by combining a first set of capsules containing a polymerizer, a second set of capsules containing a corresponding activator for the polymerizer, and a matrix precursor, and then solidifying the matrix precursor to form an elastomeric matrix. Official Gazette of the U.S. Patent and Trademark Office COMPOSITE MATERIALS; ELASTOMERS; POLYMER CHEMISTRY; CRACK CLOSURE; MATRIX MATERIALS Additions to the NASA Aeronautics and Space Database as of 01/01/2010 20090042879 Virginia Tech Intellectual Properties, Inc., Blacksburg, VA United States Plasma torch for ignition, flameholding and enhancement of combustion in high speed flows O'Brien, Walter F., Inventor; Billingsley, Matthew C., Inventor; Sanders, Darius D., Inventor; Schetz, Joseph A., Inventor; August 11, 2009; In English Contract(s)/Grant(s): NAG1-02108 Patent Info.: May 18, 2006US-Patent-7,571,598; US-Patent-Appl-SN-11/419,168 No Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090042879 Preheating of fuel and injection into a plasma torch plume fro adjacent the plasma torch plume provides for only ignition with reduced delay but improved fuel-air mixing and fuel atomization as well as combustion reaction enhancement. Heat exchange also reduced erosion of the anode of the plasma torch. Fuel mixing atomization, fuel mixture distribution enhancement and combustion reaction enhancement are improved by unsteady plasma torch energization, integral formation of the heat exchanger, fuel injection nozzle and plasma torch anode in a more compact, low-profile arrangement which is not intrusive on a highspeed air flow with which the invention is particularly effective and further enhanced by use of nitrogen as a feedstock material and inclusion of high pressure gases in the fuel to cause effervescence during injection. Official Gazette of the U.S. Patent and Trademark Office COMBUSTION; FLAME HOLDERS; HIGH SPEED; IGNITION; PLASMA TORCHES 20090042880 Vermont Univ., Burlington, VT United States Self-healing cable for extreme environments Huston, Dryver R., Inventor; Tolmie, Bernard R., Inventor; August 4, 2009; In English Contract(s)/Grant(s): NCC5-581 Patent Info.: May 15, 2007US-Patent-7,569,774; US-Patent-Appl-SN-11/803,430 No Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090042880 Self-healing cable apparatus and methods disclosed. The self-healing cable has a central core surrounded by an adaptive cover that can extend over the entire length of the self-healing cable or just one or more portions of the self-healing cable. The adaptive cover includes an axially and/or radially compressible-expandable (C/E) foam layer that maintains its properties over a wide range of environmental conditions. A tape layer surrounds the C/E layer and is applied so that it surrounds and axially and/or radially compresses the C/E layer. When the self-healing cable is subjected to a damaging force that causes a breach in the outer jacket and the tape layer, the corresponding localized axially and/or radially compressed portion of the C/E foam layer expands into the breach to form a corresponding localized self-healed region. The self-healing cable is manufacturable with present-day commercial self-healing cable manufacturing tools. Official Gazette of the U.S. Patent and Trademark Office COAXIAL CABLES; SELF REPAIRING DEVICES; SELF SEALING; COMPRESSIBILITY; FOAMS 20090042881 Honeywell International, Inc., Morristown, NJ United States Antenna reconfiguration verification and validation Becker, Robert C., Inventor; Meyers, David W., Inventor; Muldoon, Kelly P., Inventor; Carlson, Douglas R., Inventor; Drexler, Jerome P., Inventor; August 11, 2009; In English Contract(s)/Grant(s): NNC04AA44A Patent Info.: January 30, 2006US-Patent-7,573,272; US-Patent-Appl-SN-11/343,006 No Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090042881 A method of testing the electrical functionality of an optically controlled switch in a reconfigurable antenna is provided. The method includes configuring one or more conductive paths between one or more feed points and one or more test point with switches in the reconfigurable antenna. Applying one or more test signals to the one or more feed points. Monitoring the one or more test points in response to the one or more test signals and determining the functionality of the switch based upon the monitoring of the one or more test points. Official Gazette of the U.S. Patent and Trademark Office ANTENNA DESIGN; FEED SYSTEMS 20090042882 SRI International Corp., Menlo Park, CA United States Formal methods for modeling and analysis of hybrid systems Tiwari, Ashish, Inventor; Lincoln, Patrick D., Inventor; August 11, 2009; In English Contract(s)/Grant(s): NAS1-00108 Patent Info.: February 10, 2004US-Patent-7,574,334; US-Patent-Appl-SN-10/775,419 No Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090042882 A technique based on the use of a quantifier elimination decision procedure for real closed fields and simple theorem proving to construct a series of successively finer qualitative abstractions of hybrid automata is taught. The resulting abstractions are always discrete transition systems which can then be used by any traditional analysis tool. The constructed abstractions are conservative and can be used to establish safety properties of the original system. The technique works on linear and non-linear polynomial hybrid systems: the guards on discrete transitions and the continuous flows in all modes can be specified using arbitrary polynomial expressions over the continuous variables. An exemplar tool in the SAL environment built over the theorem prover PVS is detailed. The technique scales well to large and complex hybrid systems. Official Gazette of the U.S. Patent and Trademark Office MATHEMATICAL MODELS; FORMALISM; COMPLEX SYSTEMS; AUTOMATA THEORY 20090042883 NASA, Washington, DC United States Finite-difference simulation and visualization of elastodynamics in time-evolving generalized curvilinear coordinates Kaul, Upender K., Inventor; August 11, 2009; In English Patent Info.: January 19, 2006US-Patent-7,574,338; US-Patent-Appl-SN-11/340,002 No Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090042883 Modeling and simulation of free and forced structural vibrations is essential to an overall structural health monitoring capability. In the various embodiments, a first principles finite-difference approach is adopted in modeling a structural subsystem such as a mechanical gear by solving elastodynamic equations in generalized curvilinear coordinates. Such a capability to generate a dynamic structural response is widely applicable in a variety of structural health monitoring systems. This capability (1) will lead to an understanding of the dynamic behavior of a structural system and hence its improved design, (2) will generate a sufficiently large space of normal and damage solutions that can be used by machine learning algorithms to detect anomalous system behavior and achieve a system design optimization and (3) will lead to an optimal sensor placement strategy, based on the identification of local stress maxima all over the domain. Official Gazette of the U.S. Patent and Trademark Office ELASTODYNAMICS; SIMULATION; SYSTEMS ENGINEERING; STRUCTURAL HEALTH MONITORING; SPHERICAL COORDINATES 20090042884 Rice Univ., Houston, TX United States Selective functionalization of carbon nanotubes Strano, Michael S., Inventor; Usrey, Monica, Inventor; Barone, Paul, Inventor; Dyke, Christopher A., Inventor; Tour, James M., Inventor; Kittrell, W. Carter, Inventor; Hauge, Robert H., Inventor; Smalley, Richard E., Inventor; August 11, 2009; In English Contract(s)/Grant(s): NCC9-77; NCC1-10203 Patent Info.: July 29, 2004US-Patent-7,572,426; US-Patent-Appl-SN-10/566,073 No Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090042884 The present invention is directed toward methods of selectively functionalizing carbon nanotubes of a specific type or range of types, based on their electronic properties, using diazonium chemistry. The present invention is also directed toward methods of separating carbon nanotubes into populations of specific types or range(s) of types via selective functionalization and electrophoresis, and also to the novel compositions generated by such separations. Official Gazette of the U.S. Patent and Trademark Office CARBON NANOTUBES; AZO COMPOUNDS; ELECTROPHORESIS 20090042885 Cell separation using electric fields Mangano, Joseph, Inventor; Eppich, Henry, Inventor; August 11, 2009; In English Contract(s)/Grant(s): NCCW-0065 Patent Info.: April 23, 2003US-Patent-7,572,623; US-Patent-Appl-SN-10/422,310 No Copyright; Avail.: CASI: A04, Hardcopy Avail Online: http://hdl.handle.net/2060/20090042885 The present invention involves methods and devices which enable discrete objects having a conducting inner core, surrounded by a dielectric membrane to be selectively inactivated by electric fields via irreversible breakdown of their dielectric membrane. One important application of the invention is in the selection, purification, and/or purging of desired or undesired biological cells from cell suspensions. According to the invention, electric fields can be utilized to selectively inactivate and render non-viable particular subpopulations of cells in a suspension, while not adversely affecting other desired subpopulations. According to the inventive methods, the cells can be selected on the basis of intrinsic or induced differences in a characteristic electroporation threshold, which can depend, for example, on a difference in cell size and/or critical dielectric membrane breakdown voltage. The invention enables effective cell separation without the need to employ undesirable exogenous agents, such as toxins or antibodies. The inventive method also enables relatively rapid cell separation involving a relatively low degree of trauma or modification to the selected, desired cells. The inventive method has a variety of potential applications in clinical medicine, research, etc., with two of the more important foreseeable applications being stem cell enrichment/isolation, and cancer cell purging. Official Gazette of the U.S. Patent and Trademark Office CLINICAL MEDICINE; CELLS (BIOLOGY); ELECTRIC FIELDS; DIELECTRICS; BIOTECHNOLOGY 20090042886 Tufts Univ., Medford, MA United States Templated native silk smectic gels Jin, Hyoung-Joon, Inventor; Park, Jae-Hyung, Inventor; Valluzzi, Regina, Inventor; August 11, 2009; In English Contract(s)/Grant(s): NAG8-1699 Patent Info.: October 31, 2003US-Patent-7,572,894; US-Patent-Appl-SN-10/533,611 No Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090042886 One aspect of the present invention relates to a method of preparing a fibrous protein smectic hydrogel by way of a solvent templating process, comprising the steps of pouring an aqueous fibrous protein solution into a container comprising a solvent that is not miscible with water; sealing the container and allowing it to age at about room temperature; and collecting the resulting fibrous protein smectic hydrogel and allowing it to dry. Another aspect of the present invention relates to a method of obtaining predominantly one enantiomer from a racemic mixture, comprising the steps of pouring an aqueous fibrous protein solution into a container comprising a solvent that is not miscible with water; sealing the container and allowing it to age at about room temperature; allowing the enantiomers of racemic mixture to diffuse selectively into the smectic hydrogel in solution; removing the smectic hydrogel from the solution; rinsing predominantly one enantiomer from the surface of the smectic hydrogel; and extracting predominantly one enantiomer from the interior of the smectic hydrogel. The present invention also relates to a smectic hydrogel prepared according to an aforementioned method. Official Gazette of the U.S. Patent and Trademark Office GELS; LIQUID CRYSTALS; SILK 20090042887 NASA, Washington, DC United States Ultrasonic stir welding process and apparatus Ding, R. Jeffrey, Inventor; August 4, 2009; In English Patent Info.: January 29, 2007US-Patent-7,568,608; US-Patent-Appl-SN-11/700,972 No Copyright; Avail.: CASI: A02, Hardcopy Avail Online: http://hdl.handle.net/2060/20090042887 An ultrasonic stir welding device provides a method and apparatus for elevating the temperature of a work piece utilizing at least one ultrasonic heater. Instead of relying on a rotating shoulder to provide heat to a workpiece an ultrasonic heater is utilized to provide ultrasonic energy to the workpiece. A rotating pin driven by a motor assembly performs the weld on the workpiece. A handheld version can be constructed as well as a fixedly mounted embodiment. Official Gazette of the U.S. Patent and Trademark Office ULTRASONIC WELDING; FRICTION STIR WELDING; HEATERS 20090042888 NASA, Washington, DC United States WGM resonators for studying orbital angular momentum of a photon, and methods Matsko, Andrey B., Inventor; Savchenkov, Anatoliy A., Inventor; Maleki, Lute, Inventor; Strekalov, Dmitry V., Inventor; August 4, 2009; In English Patent Info.: June 19, 2006US-Patent-7,570,850; US-Patent-Appl-SN-11/424,916 No Copyright; Avail.: CASI: A02, Hardcopy Avail Online: http://hdl.handle.net/2060/20090042888 An optical system, device, and method that are capable of generating high-order Bessel beams and determining the orbital angular momentum of at least one of the photons of a Bessel beam are provided. The optical system and device include a tapered waveguide having an outer surface defined by a diameter that varies along a longitudinal axis of the waveguide from a first end to an opposing second end. The optical system and device include a resonator that is arranged in optical communication with the first end of the tapered waveguide such that an evanescent field emitted from (i) the waveguide can be coupled with the resonator, or (ii) the resonator can be coupled with the waveguide. Official Gazette of the U.S. Patent and Trademark Office ANGULAR MOMENTUM; OPTICAL COMMUNICATION; PHOTONS; RESONATORS; WAVEGUIDES 20090042904 NASA, Washington, DC United States Multi-wavelength time-coincident optical communications system and methods thereof Lekki, John, Inventor; Nguyen, Quang-Viet, Inventor; August 11, 2009; In English Patent Info.: May 5, 2006US-Patent-7,574,137; US-Patent-Appl-SN-11/418,304 No Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090042904 An optical communications transmitter includes a oscillator source, producing a clock signal, a data source, producing a data signal, a modulating circuit for modulating the clock signal using the data signal to produce modulating signals, optical drivers, receiving the modulating signals and producing optical driving signals based on the modulating signals and optical emitters, producing small numbers of photons based on the optical driving signals. The small numbers of photons are time-correlated between at least two separate optical transmission wavelengths and quantum states and the small number of photons can be detected by a receiver to reform the data signal. Official Gazette of the U.S. Patent and Trademark Office OPTICAL COMMUNICATION; OSCILLATORS; LIGHT TRANSMISSION; TRANSMITTERS; MODULATION; CLOCKS 20090042907 NASA, Washington, DC United States Applications of sub-audible speech recognition based upon electromyographic signals Jorgensen, C. Charles, Inventor; Betts, Bradley J., Inventor; August 11, 2009; In English Patent Info.: June 24, 2005US-Patent-7,574,357; US-Patent-Appl-SN-11/169,265 No Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090042907 Method and system for generating electromyographic or sub-audible signals (''SAWPs'') and for transmitting and recognizing the SAWPs that represent the original words and/or phrases. The SAWPs may be generated in an environment that interferes excessively with normal speech or that requires stealth communications, and may be transmitted using encoded, enciphered or otherwise transformed signals that are less subject to signal distortion or degradation in the ambient environment. Official Gazette of the U.S. Patent and Trademark Office SPEECH RECOGNITION; SIGNAL DISTORTION; DEGRADATION 20090042909 Carnegie Institution of Washington, Washington, DC United States Mixture including hydrogen and hydrocarbon having pressure-temperature stability Mao, Wendy L., Inventor; Mao, Ho-Kwang, Inventor; August 18, 2009; In English Contract(s)/Grant(s): NAG5-11613 Patent Info.: January 19, 2006US-Patent-7,574,868; US-Patent-Appl-SN-11/334,348 No Copyright; Avail.: CASI: A02, Hardcopy Avail Online: http://hdl.handle.net/2060/20090042909 The invention relates to a method of storing hydrogen that employs a mixture of hydrogen and a hydrocarbon that can both be used as fuel. In one embodiment, the method involves maintaining a mixture including hydrogen and a hydrocarbon in the solid state at ambient pressure and a temperature in excess of about 10 K. Official Gazette of the U.S. Patent and Trademark Office HYDROCARBONS; HYDROGEN; PRESSURE; TEMPERATURE; STABILITY 20090042911 NASA, Washington, DC United States Diagnosable structured logic array Whitaker, Sterling, Inventor; Miles, Lowell, Inventor; Gambles, Jody, Inventor; Maki, Gary K., Inventor; August 18, 2009; In English Contract(s)/Grant(s): NNG06GB45G Patent Info.: June 15, 2007US-Patent-7,576,562; US-Patent-Appl-SN-11/818,845 No Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090042911 A diagnosable structured logic array and associated process is provided. A base cell structure is provided comprising a logic unit comprising a plurality of input nodes, a plurality of selection nodes, and an output node, a plurality of switches coupled to the selection nodes, where the switches comprises a plurality of input lines, a selection line and an output line, a memory cell coupled to the output node, and a test address bus and a program control bus coupled to the plurality of input lines and the selection line of the plurality of switches. A state on each of the plurality of input nodes is verifiably loaded and read from the memory cell. A trusted memory block is provided. The associated process is provided for testing and verifying a plurality of truth table inputs of the logic unit. Official Gazette of the U.S. Patent and Trademark Office COMPUTER STORAGE DEVICES; MEMORY (COMPUTERS); SWITCHES 20090042916 NASA, Washington, DC United States Removal of PCB and other halogenated organic contaminants found in ex situ structures Quinn, Jacqueline W., Inventor; Clausen, Christian A., Inventor; Geiger, Cherie L., Inventor; Coon, Christina, Inventor; Filipek, Laura B., Inventor; Berger, Cristina M., Inventor; Milum, Kristen M., Inventor; September 1, 2009; In English Patent Info.: August 15, 2007US-Patent-7,582,682; US-Patent-Appl-SN-11/838,916 No Copyright; Avail.: CASI: A02, Hardcopy Avail Online: http://hdl.handle.net/2060/20090042916 Emulsified systems of a surfactant-stabilized, biodegradable water-in-solvent emulsion with bimetallic particles contained with the emulsion droplets are useful at removing PCBs from ex situ structures. The hydrophobic emulsion system draws PCBs through the solvent/surfactant membrane. Once inside the membrane, the PCBs diffuse into the bimetallic particles and undergo degradation. The PCBs continue to enter, diffuse, degrade, and biphenyl will exit the particle maintaining a concentration gradient across the membrane and maintaining a driving force of the reaction. Official Gazette of the U.S. Patent and Trademark Office SURFACTANTS; EMULSIONS; DROPS (LIQUIDS); HYDROPHOBICITY; POLYCHLORINATED BIPHENYLS; SOLVENTS; POLYPHENYLS 20090042918 Mobitrum Corp., Silver Spring, MD United States Method and system for mesh network embedded devices Wang, Ray, Inventor; September 8, 2009; In English Contract(s)/Grant(s): NNS05AA34C Patent Info.: February 17, 2006US-Patent-7,586,888; US-Patent-Appl-SN-11/356,900 No Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090042918 A method and system for managing mesh network devices. A mesh network device with integrated features creates an N-way mesh network with a full mesh network topology or a partial mesh network topology. Official Gazette of the U.S. Patent and Trademark Office COMPUTATIONAL GRIDS; EMBEDDING 20090042920 NASA, Washington, DC United States Electrically conductive, optically transparent polymer/carbon nanotube composites and process for preparation thereof Park, Cheol, Inventor; Watson, Kent A., Inventor; Ounaies, Zoubeida, Inventor; Connell, John W., Inventor; Smith, Joseph G., Inventor; Harrison, Joycelyn S., Inventor; September 15, 2009; In English Patent Info.: November 1, 2002US-Patent-7,588,699; US-Patent-Appl-SN-10/288,797 No Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090042920 The present invention is directed to the effective dispersion of carbon nanotubes (CNTs) into polymer matrices. The nanocomposites are prepared using polymer matrices and exhibit a unique combination of properties, most notably, high retention of optical transparency in the visible range (i.e., 400 800 nm), electrical conductivity, and high thermal stability. By appropriate selection of the matrix resin, additional properties such as vacuum ultraviolet radiation resistance, atomic oxygen resistance, high glass transition (T.sub.g) temperatures, and excellent toughness can be attained. The resulting nanocomposites can be used to fabricate or formulate a variety of articles such as coatings on a variety of substrates, films, foams, fibers, threads, adhesives and fiber coated prepreg. The properties of the nanocomposites can be adjusted by selection of the polymer matrix and CNT to fabricate articles that possess high optical transparency and antistatic behavior. Official Gazette of the U.S. Patent and Trademark Office ELECTRICAL RESISTIVITY; POLYMER MATRIX COMPOSITES; NANOCOMPOSITES; CARBON NANOTUBES; FAR ULTRAVIOLET RADIATION 20090042921 NASA, Washington, DC United States Microencapsulation system and method Morrison, Dennis R., Inventor; September 15, 2009; In English Patent Info.: July 3, 2006US-Patent-7,588,703; US-Patent-Appl-SN-11/428,465 No Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090042921 A microencapsulation apparatus is provided which is configured to form co-axial multi-lamellar microcapsules from materials discharged from first and second microsphere dispensers of the apparatus. A method of fabricating and processing microcapsules is also provided which includes forming distinct droplets comprising one or more materials and introducing the droplets directly into a solution bath to form a membrane around the droplets such that a plurality of microcapsules are formed. A microencapsulation system is provided which includes a microcapsule production unit, a fluidized passage for washing and harvesting microcapsules dispensed from the microcapsule production unit and a flow sensor for sizing and counting the microcapsules. In some embodiments, the microencapsulation system may further include a controller configured to simultaneously operate the microcapsule production unit, fluidized passage and flow sensor to process the microcapsules in a continuous manner. Official Gazette of the U.S. Patent and Trademark Office MICROPARTICLES; ENCAPSULATING; FABRICATION; DISPENSERS; CONTROLLERS; MEMBRANES 20090042923 NASA, Washington, DC United States Tunable optical assembly with vibration dampening Allison, Sidney G., Inventor; Shams, Qamar A., Inventor; Fox, Robert L., Inventor; Fox, legal representative, Christopher L., Inventor; Fox Chattin, legal representative, Melanie L., Inventor; August 25, 2009; In English Patent Info.: May 23, 2006US-Patent-7,580,323; US-Patent-Appl-SN-11/419,818 No Copyright; Avail.: CASI: A02, Hardcopy Avail Online: http://hdl.handle.net/2060/20090042923 An optical assembly is formed by one or more piezoelectric fiber composite actuators having one or more optical fibers coupled thereto. The optical fiber(s) experiences strain when actuation voltage is applied to the actuator(s). Light passing through the optical fiber(s) is wavelength tuned by adjusting the actuation voltage. Official Gazette of the U.S. Patent and Trademark Office PIEZOELECTRIC ACTUATORS; FIBER COMPOSITES; ELECTRIC POTENTIAL; OPTICAL FIBERS 20090042924 QorTek, Inc., Williamsport, PA United States Thin nearly wireless adaptive optical device Knowles, Gareth J., Inventor; Hughes, Eli, Inventor; July 7, 2009; In English Contract(s)/Grant(s): NAS5-03014 Patent Info.: August 19, 2008US-Patent-7,556,388; US-Patent-Appl-SN-12/193,951 No Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090042924 A thin nearly wireless adaptive optical device capable of dynamically modulating the shape of a mirror in real time to compensate for atmospheric distortions and/or variations along an optical material is provided. The device includes an optical layer, a substrate, at least one electronic circuit layer with nearly wireless architecture, an array of actuators, power electronic switches, a reactive force element, and a digital controller. Actuators are aligned so that each axis of expansion and contraction intersects both substrate and reactive force element. Electronics layer with nearly wireless architecture, power electronic switches, and digital controller are provided within a thin-film substrate. The size and weight of the adaptive optical device is solely dominated by the size of the actuator elements rather than by the power distribution system. Official Gazette of the U.S. Patent and Trademark Office OPTICAL EQUIPMENT; WIRELESS COMMUNICATION; ACTUATORS; DIGITAL SYSTEMS; SWITCHING CIRCUITS 20090042925 Puerto Rico Univ., San Juan, Puerto Rico Branched nanostructures and method of synthesizing the same Fonseca, Luis F., Inventor; Resto, Oscar, Inventor; Sola, Francisco, Inventor; May 5, 2009; In English Contract(s)/Grant(s): NCC3-1034 Patent Info.: October 27, 2005US-Patent-7,528,060; US-Patent-Appl-SN-11/260,710 No Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090042925 A branched nanostructure is synthesized. A porous material, with pores having a diameter of approximately 1 .mu.m or less, is placed in a vacuum. It is irradiated with an electron beam. This causes a trunk to grow from the porous material and further causes branches to grow from the trunk. Official Gazette of the U.S. Patent and Trademark Office NANOSTRUCTURES (DEVICES); IRRADIATION 20090042926 Northwestern Univ., Evanston, IL United States Carbonyl-functionalized thiophene compounds and related device structures Marks, Tobin J., Inventor; Facchetti, Antonio, Inventor; May 5, 2009; In English Contract(s)/Grant(s): NCC2-3163 Patent Info.: September 14, 2005US-Patent-7,528,176; US-Patent-Appl-SN-11/227,559 No Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090042926 Carbonyl-functionalized oligo/polythiophene compounds, and related semiconductor components and related device structures. Official Gazette of the U.S. Patent and Trademark Office CARBONYL COMPOUNDS; THIOPHENES; POLYMERS 20090042927 Illinois Univ., Urbana, IL United States Distinguishing non-resonant four-wave-mixing noise in coherent stokes and anti-stokes Raman scattering Marks, Daniel L., Inventor; Boppart, Stephen A., Inventor; September 8, 2009; In English Contract(s)/Grant(s): NAS2-02057 Patent Info.: February 28, 2005US-Patent-7,586,618; US-Patent-Appl-SN-11/068,739 No Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090042927 A method of examining a sample comprises exposing the sample to a pump pulse of electromagnetic radiation for a first period of time, exposing the sample to a stimulant pulse of electromagnetic radiation for a second period of time which overlaps in time with at least a portion of the first exposing, to produce a signal pulse of electromagnetic radiation for a third period of time, and interfering the signal pulse with a reference pulse of electromagnetic radiation, to determine which portions of the signal pulse were produced during the exposing of the sample to the stimulant pulse. The first and third periods of time are each greater than the second period of time. Official Gazette of the U.S. Patent and Trademark Office COHERENT SCATTERING; FOUR-WAVE MIXING; RAMAN SPECTRA; TIME SIGNALS; ELECTROMAGNETIC RADIATION 20090042928 Photon Systems, Covina, CA United States Electron beam pumped semiconductor laser Hug, William F., Inventor; Reid, Ray D., Inventor; September 15, 2009; In English Contract(s)/Grant(s): NAS2-02086 Patent Info.: October 5, 2005US-Patent-7,590,161; US-Patent-Appl-SN-11/245,418 No Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090042928 Electron-beam-pumped semiconductor ultra-violet optical sources (ESUVOSs) are disclosed that use ballistic electron pumped wide bandgap semiconductor materials. The sources may produce incoherent radiation and take the form of electron-beam-pumped light emitting triodes (ELETs). The sources may produce coherent radiation and take the form of electron-beam-pumped laser triodes (ELTs). The ELTs may take the form of electron-beam-pumped vertical cavity surface emitting lasers (EVCSEL) or edge emitting electron-beam-pumped lasers (EEELs). The semiconductor medium may take the form of an aluminum gallium nitride alloy that has a mole fraction of aluminum selected to give a desired emission wavelength, diamond, or diamond-like carbon (DLC). The sources may be produced from discrete components that are assembled after their individual formation or they may be produced using batch MEMS-type or semiconductor-type processing techniques to build them up in a whole or partial monolithic manner, or combination thereof. Official Gazette of the U.S. Patent and Trademark Office SEMICONDUCTOR LASERS; ELECTRON BEAMS; SURFACE EMITTING LASERS; MICROELECTROMECHANICAL SYSTEMS; COHERENT RADIATION; LASER CAVITIES; FREE ELECTRON LASERS 20090042929 Massachusetts Univ., Boston, MA United States Measuring tissue oxygenation Soyemi, Olusola O., Inventor; Soller, Babs R., Inventor; Yang, Ye, Inventor; May 12, 2009; In English Contract(s)/Grant(s): NCC9-58 Patent Info.: May 30, 2007US-Patent-7,532,919; US-Patent-Appl-SN-11/755,643 No Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090042929 Methods and systems for calculating tissue oxygenation, e.g., oxygen saturation, in a target tissue are disclosed. In some embodiments, the methods include: (a) directing incident radiation to a target tissue and determining reflectance spectra of the target tissue by measuring intensities of reflected radiation from the target tissue at a plurality of radiation wavelengths; (b) correcting the measured intensities of the reflectance spectra to reduce contributions thereto from skin and fat layers through which the incident radiation propagates; (c) determining oxygen saturation in the target tissue based on the corrected reflectance spectra; and (d) outputting the determined value of oxygen saturation. Official Gazette of the U.S. Patent and Trademark Office OXYGENATION; SATURATION 20090042930 NASA, Washington, DC United States Multi-user investigation organizer Keller, Richard M., Inventor; Panontin, Tina L., Inventor; Carvalho, Robert E., Inventor; Sturken, Ian, Inventor; Williams, James F., Inventor; Wolfe, Shawn R., Inventor; Gawdiak, Yuri O., Inventor; September 15, 2009; In English Patent Info.: November 5, 2003US-Patent-7,590,606; US-Patent-Appl-SN-10/703,039 No Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090042930 A system that allows a team of geographically dispersed users to collaboratively analyze a mishap event. The system includes a reconfigurable ontology, including instances that are related to and characterize the mishap, a semantic network that receives, indexes and stores, for retrieval, viewing and editing, the instances and links between the instances, a network browser interface for retrieving and viewing screens that present the instances and links to other instances and that allow editing thereof, and a rule-based inference engine, including a collection of rules associated with establishment of links between the instances. A possible conclusion arising from analysis of the mishap event may be characterized as one or more of: not a credible conclusion; an unlikely conclusion; a credible conclusion; conclusion needs analysis; conclusion needs supporting data; conclusion proposed to be closed; and an un-reviewed conclusion. Official Gazette of the U.S. Patent and Trademark Office EDITING; VIEWING; INFERENCE 20090042931 NASA, Washington, DC United States MEMS switches having non-metallic crossbeams Scardelletti, Maximillian C, Inventor; September 1, 2009; In English Patent Info.: March 22, 2007US-Patent-7,583,169; US-Patent-Appl-SN-11/689,770 No Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090042931 A RF MEMS switch comprising a crossbeam of SiC, supported by at least one leg above a substrate and above a plurality of transmission lines forming a CPW. Bias is provided by at least one layer of metal disposed on a top surface of the SiC crossbeam, such as a layer of chromium followed by a layer of gold, and extending beyond the switch to a biasing pad on the substrate. The switch utilizes stress and conductivity-controlled non-metallic thin cantilevers or bridges, thereby improving the RF characteristics and operational reliability of the switch. The switch can be fabricated with conventional silicon integrated circuit (IC) processing techniques. The design of the switch is very versatile and can be implemented in many transmission line mediums. Official Gazette of the U.S. Patent and Trademark Office FABRICATION; MICROELECTROMECHANICAL SYSTEMS; SWITCHES; RADIO FREQUENCIES 20090042932 California Inst. of Tech., Pasadena, CA United States Non-unitary probabilistic quantum computing circuit and method Williams, Colin P., Inventor; Gingrich, Robert M., Inventor; September 15, 2009; In English Patent Info.: December 7, 2004US-Patent-7,590,607; US-Patent-Appl-SN-11/007,792 No Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090042932 A quantum circuit performing quantum computation in a quantum computer. A chosen transformation of an initial n-qubit state is probabilistically obtained. The circuit comprises a unitary quantum operator obtained from a non-unitary quantum operator, operating on an n-qubit state and an ancilla state. When operation on the ancilla state provides a success condition, computation is stopped. When operation on the ancilla state provides a failure condition, computation is performed again on the ancilla state and the n-qubit state obtained in the previous computation, until a success condition is obtained. Official Gazette of the U.S. Patent and Trademark Office QUANTUM COMPUTATION; CIRCUITS; FAILURE 20090042933 Massachusetts Inst. of Tech., Cambridge, MA United States Metal-doped semiconductor nanoparticles and methods of synthesis thereof Ren, Zhifeng, Inventor; Chen, Gang, Inventor; Poudel, Bed, Inventor; Kumar, Shankar, Inventor; Wang, Wenzhong, Inventor; Dresselhaus, Mildred, Inventor; September 8, 2009; In English Contract(s)/Grant(s): NAS3-03108 Patent Info.: May 3, 2005US-Patent-7,586,033; US-Patent-Appl-SN-11/120,729 No Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090042933 The present invention generally relates to binary or higher order semiconductor nanoparticles doped with a metallic element, and thermoelectric compositions incorporating such nanoparticles. In one aspect, the present invention provides a thermoelectric composition comprising a plurality of nanoparticles each of which includes an alloy matrix formed of a Group IV element and Group VI element and a metallic dopant distributed within the matrix. Official Gazette of the U.S. Patent and Trademark Office THERMOELECTRICITY; NANOPARTICLES; SEMICONDUCTORS (MATERIALS); DOPED CRYSTALS 20090042934 NASA, Washington, DC United States Piezoelectrically enhanced photocathode Beach, Robert A., Inventor; Nikzad, Shouleh, Inventor; Strittmatter, Robert P., Inventor; Bell, Lloyd Douglas, Inventor; September 22, 2009; In English Patent Info.: February 9, 2005US-Patent-7,592,747; US-Patent-Appl-SN-11/056,633 No Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090042934 A photocathode, for generating electrons in response to incident photons in a photodetector, includes a base layer having a first lattice structure and an active layer having a second lattice structure and epitaxially formed on the base layer, the first and second lattice structures being sufficiently different to create a strain in the active layer with a corresponding piezoelectrically induced polarization field in the active layer, the active layer having a band gap energy corresponding to a desired photon energy. Official Gazette of the U.S. Patent and Trademark Office ELECTRONS; ENERGY GAPS (SOLID STATE); PHOTOCATHODES; PHOTOMETERS 20090042935 Massachusetts Inst. of Tech., Cambridge, MA United States Thermoelectric properties by high temperature annealing Ren, Zhifeng, Inventor; Chen, Gang, Inventor; Kumar, Shankar, Inventor; Lee, Hohyun, Inventor; September 22, 2009; In English Contract(s)/Grant(s): NAS3-03108 Patent Info.: April 6, 2005US-Patent-7,591,913; US-Patent-Appl-SN-11/100,950 No Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090042935 The present invention generally provides methods of improving thermoelectric properties of alloys by subjecting them to one or more high temperature annealing steps, performed at temperatures at which the alloys exhibit a mixed solid/liquid phase, followed by cooling steps. For example, in one aspect, such a method of the invention can include subjecting an alloy sample to a temperature that is sufficiently elevated to cause partial melting of at least some of the grains. The sample can then be cooled so as to solidify the melted grain portions such that each solidified grain portion exhibits an average chemical composition, characterized by a relative concentration of elements forming the alloy, that is different than that of the remainder of the grain. Official Gazette of the U.S. Patent and Trademark Office THERMOELECTRICITY; CHEMICAL COMPOSITION; ANNEALING; HIGH TEMPERATURE 20090042936 NASA, Washington, DC United States Composite powder particles Parker, Donald S., Inventor; MacDowell, Louis G., Inventor; September 1, 2009; In English Patent Info.: August 18, 2005US-Patent-7,582,147; US-Patent-Appl-SN-11/208,122 No Copyright; Avail.: CASI: A02, Hardcopy Avail Online: http://hdl.handle.net/2060/20090042936 A liquid coating composition including a coating vehicle and composite powder particles disposed within the coating vehicle. Each composite powder particle may include a magnesium component, a zinc component, and an indium component. Official Gazette of the U.S. Patent and Trademark Office MAGNESIUM; COATING; ZINC; POWDER (PARTICLES); INDIUM 20090042937 NASA, Washington, DC United States Emission control system Parrish, Clyde F., Inventor; Chung, J. Landy, Inventor; September 1, 2009; In English Patent Info.: January 14, 2005US-Patent-7,582,271; US-Patent-Appl-SN-11/040,294 No Copyright; Avail.: CASI: A02, Hardcopy Avail Online: http://hdl.handle.net/2060/20090042937 Methods and apparatus utilizing hydrogen peroxide are useful to reduce SOx and mercury (or other heavy metal) emissions from combustion flue gas streams. The methods and apparatus may further be modified to reduce NOx emissions. Continuous concentration of hydrogen peroxide to levels approaching or exceeding propellant-grade hydrogen peroxide facilitates increased system efficiency. In this manner, combustion flue gas streams can be treated for the removal of SOx and heavy metals, while isolating useful by-products streams of sulfuric acid as well as solids for the recovery of the heavy metals. Where removal of NOx emissions is included, nitric acid may also be isolated for use in fertilizer or other industrial applications. Official Gazette of the U.S. Patent and Trademark Office NITROGEN OXIDES; SULFURIC ACID; COMBUSTION; BY-PRODUCTS; HYDROGEN PEROXIDE; MATERIALS RECOVERY; METAL COMBUSTION; NITRIC ACID Additions to the NASA Aeronautics and Space Database as of 01/04/2010 20090042939 United Technologies Corp., East Hartford, CT United States Application of a mixed metal oxide catalyst to a metallic substrate Sevener, Kathleen M., Inventor; Lohner, Kevin A., Inventor; Mays, Jeffrey A., Inventor; Wisner, Daniel L., Inventor; March 31, 2009; In English Contract(s)/Grant(s): NCC8-193 Patent Info.: April 1, 2003US-Patent-7,510,995; US-Patent-Appl-SN-10/404,935 No Copyright; Avail.: CASI: A02, Hardcopy Avail Online: http://hdl.handle.net/2060/20090042939 A method for applying a mixed metal oxide catalyst to a metallic substrate for the creation of a robust, high temperature catalyst system for use in decomposing propellants, particularly hydrogen peroxide propellants, for use in propulsion systems. The method begins by forming a prepared substrate material consisting of a metallic inner substrate and a bound layer of a noble metal intermediate. Alternatively, a bound ceramic coating, or frit, may be introduced between the metallic inner substrate and noble metal intermediate when the metallic substrate is oxidation resistant. A high-activity catalyst slurry is applied to the surface of the prepared substrate and dried to remove the organic solvent. The catalyst layer is then heat treated to bind the catalyst layer to the surface. The bound catalyst layer is then activated using an activation treatment and calcinations to form the high-activity catalyst system. Official Gazette of the U.S. Patent and Trademark Office CATALYSTS; HIGH TEMPERATURE; METAL OXIDES; SUBSTRATES; METALS; PROPULSION SYSTEM CONFIGURATIONS 20090042940 California Inst. of Tech., Pasadena, CA United States Phase measurement device using inphase and quadrature components for phase estimation Halverson, Peter G., Inventor; Ware, Brent, Inventor; Shaddock, Daniel A., Inventor; Spero, Robert E., Inventor; March 31, 2009; In English Patent Info.: July 24, 2007US-Patent-7,511,469; US-Patent-Appl-SN-11/880,889 No Copyright; Avail.: CASI: A02, Hardcopy Avail Online: http://hdl.handle.net/2060/20090042940 A phasemeter for estimating the phase of a signal. For multi-tone signals, multiple phase estimates may be provided. An embodiment includes components operating in the digital domain, where a sampled input signal is multiplied by cosine and sine terms to provide estimates of the inphase and quadrature components. The quadrature component provides an error signal that is provided to a feedback loop, the feedback loop providing a model phase that tends to track the phase of a tone in the input signal. The cosine and sine terms are generated from the model phase. The inphase and quadrature components are used to form a residual phase, which is added to the model phase to provide an estimate of the phase of the input signal. Other embodiments are described and claimed. Official Gazette of the U.S. Patent and Trademark Office PHASE DETECTORS; QUADRATURES; SIGNAL DETECTION; SIGNAL PROCESSING 20090042941 ITT Mfg. Enterprises, Inc., Wilmington, DE United States Crossed beam roof target for motion tracking Olczak, Eugene, Inventor; March 31, 2009; In English Contract(s)/Grant(s): NAS5-02200 Patent Info.: April 10, 2007US-Patent-7,511,804; US-Patent-Appl-SN-11/786,262 No Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090042941 A system for detecting motion between a first body and a second body includes first and second detector-emitter pairs, disposed on the first body, and configured to transmit and receive first and second optical beams, respectively. At least a first optical rotator is disposed on the second body and configured to receive and reflect at least one of the first and second optical beams. First and second detectors of the detector-emitter pairs are configured to detect the first and second optical beams, respectively. Each of the first and second detectors is configured to detect motion between the first and second bodies in multiple degrees of freedom (DOFs). The first optical rotator includes a V-notch oriented to form an apex of an isosceles triangle with respect to a base of the isosceles triangle formed by the first and second detector-emitter pairs. The V-notch is configured to receive the first optical beam and reflect the first optical beam to both the first and second detectors. The V-notch is also configured to receive the second optical beam and reflect the second optical beam to both the first and second detectors. Official Gazette of the U.S. Patent and Trademark Office DETECTION; EMITTERS; LIGHT BEAMS; OPTICAL MEASURING INSTRUMENTS; TRACKING (POSITION) 20090042942 NASA Goddard Space Flight Center, Greenbelt, MD, United States Neutron Imaging Camera deNolfo, Georgia A.; October 25, 2009; In English; IEEE Nuclear Science Symposium and Medical Imaging Conference, 25-29 Oct. 2009, Orlando, FL, United States; Original contains color illustrations Contract(s)/Grant(s): NNG06EO90A No Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090042942 This slide presentation reviews the Neutron Imaging Camera. The presentation also includes information about neutron imaging, neutron interactions, and camera field testing. CASI CAMERAS; NEUTRONS; RESEARCH AND DEVELOPMENT 20090042944 NASA Marshall Space Flight Center, Huntsville, AL, United States NASA Space Safety Standards and Procedures for Human Rating Requirements Shivers, C. Herbert; [2009]; In English; Original contains color and black and white illustrations Report No.(s): M09-0702; No Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090042944 The National Aeronautics and Space Administration of the United States of America (NASA) has arguably led this planet in space exploration and certainly has been one of two major leaders in those endeavors. NASA governance is institutionalized and managed in a series documents arranged in a hierarchy and flowing down to the work levels. A document tree of NASA s documentation in its totality would likely overwhelm and not be very informative. Taken in segments related to the various business topics and focusing in those segments, however, provides a logical and understandable relationship and flow of requirements and processes. That is the nature of this chapter, a selection of NASA documentation pertaining to space exploration and a description of how those documents together form the plan by which NASA business for space exploration is conducted. Information presented herein is taken from NASA publications and is available publicly and no information herein is protected by copyright or security regulations. While NASA documents are the source of information presented herein, any and all views expressed herein and any misrepresentations of NASA data that may occur herein are those of the author and should not be considered NASA official positions or statements, nor should NASA endorsement of anything presented in this work be assumed. Author NASA PROGRAMS; SPACE EXPLORATION; SAFETY; SECURITY; REGULATIONS; RATINGS 20090042946 NASA, Washington, DC United States Evolvable synthetic neural system Curtis, Steven A., Inventor; March 31, 2009; In English Patent Info.: April 8, 2005US-Patent-7,512,568; US-Patent-Appl-SN-11/109,400 No Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090042946 An evolvable synthetic neural system includes an evolvable neural interface operably coupled to at least one neural basis function. Each neural basis function includes an evolvable neural interface operably coupled to a heuristic neural system to perform high-level functions and an autonomic neural system to perform low-level functions. In some embodiments, the evolvable synthetic neural system is operably coupled to one or more evolvable synthetic neural systems in a hierarchy. Official Gazette of the U.S. Patent and Trademark Office ARTIFICIAL INTELLIGENCE; NEURAL NETS; EXPERT SYSTEMS 20090042947 NASA Marshall Space Flight Center, Huntsville, AL, United States Ares V Overview and Status Creech, Steve; Sumrall, Phil; Cockrell, Charles E., Jr.; Burris, Mike; October 12, 2009; In English; 60th International Astronautical Congress, 12-16 Oct. 2009, Daejeon, Korea, Republic of; Original contains color illustrations Report No.(s): IAC-09-D2.8.1; M09-0765; Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090042947 As part of NASA s Constellation Program to resume exploration beyond low Earth orbit (LEO), the Ares V heavy-lift cargo launch vehicle as currently conceived will be able to send more crew and cargo to more places on the Moon than the Apollo Program Saturn V. (Figure 1) It also has unprecedented cargo mass and volume capabilities that will be a national asset for science, commerce, and national defense applications. Compared to current systems, it will offer approximately five times the mass and volume to most orbits and locations. The Columbia space shuttle accident, the resulting investigation, the Vision for Space Exploration, and the Exploration Systems Architecture Study (ESAS) broadly shaped the Constellation architecture. Out of those events and initiatives emerged an architecture intended to replace the space shuttle, complete the International Space Station (ISS), resume a much more ambitious plan to explore the moon as a stepping stone to other destinations in the solar system. The Ares I was NASA s main priority because of the goal to retire the Shuttle. Ares V remains in a concept development phase, evolving through hundreds of configurations. The current reference design was approved during the Lunar Capabilities Concept Review/Ares V Mission Concept Review (LCCR/MCR) in June 2008. This reference concept serves as a starting point for a renewed set of design trades and detailed analysis into its interaction with the other components of the Constellation architecture and existing launch infrastructure. In 2009, the Ares V team was heavily involved in supporting the Review of U.S. Human Space Flight Plans Committee. Several alternative designs for Ares V have been supplied to the committee. This paper will discuss the origins of the Ares V design, the evolution to the current reference configuration, and the options provided to the review committee. Author ARES 5 CARGO LAUNCH VEHICLE; CONSTELLATION PROGRAM; HEAVY LIFT LAUNCH VEHICLES; LOW EARTH ORBITS; MISSION PLANNING; SPACE EXPLORATION; SPACECRAFT DESIGN 20090042948 University of South Florida, Tampa, FL United States High-frequency feed structure antenna apparatus and method of use Sarehraz, Mohammad, Inventor; Buckle, Kenneth A., Inventor; Stefanakos, Elias, Inventor; Weller, Thomas, Inventor; Goswami, D. Yogi, Inventor; February 3, 2009; In English Patent Info.: September 25, 2006US-Patent-7,486,236; US-Patent-Appl-SN-11/534,800 No Copyright; Avail.: CASI: A02, Hardcopy Avail Online: http://hdl.handle.net/2060/20090042948 An antenna apparatus for the reception of, and or transmission of, electromagnetic energy, the apparatus including a non-radiating dielectric waveguide aperture coupled to at least one dielectric rod antenna, which is electromagnetically coupled to a transmission line element. Official Gazette of the U.S. Patent and Trademark Office SOLAR ENERGY CONVERSION; SOLAR COLLECTORS; RECTENNAS; SOLAR RADIATION; ELECTROMAGNETISM 20090042957 NASA Glenn Research Center, Cleveland, OH, United States Polyimide Composites Based on Asymmetric Dianhydrides (a-ODPA vs a-BPDA) Chuang, Kathy C.; Criss, Jim M., Jr.; Mintz, Eric A.; May 18, 2009; In English; 54th International SAMPE Symposium, 18-21 May 2009, Baltimore, MD, United States; Original contains black and white illustrations Contract(s)/Grant(s): FA9550-06-0090WBS 984754.02.07.03.16.05 Report No.(s): E-17144-P; Copyright; Avail.: CASI: A02, Hardcopy Avail Online: http://hdl.handle.net/2060/20090042957 Two series of low-melt viscosity imide resins (2-15 poise at 260-280 C) were formulated from either asymmetric oxydiphthalic anhydride (a-ODPA) or asymmetric biphenyl dianhydride (a- BPDA) with 4-phenylethynyl endcap (PEPA), along with 3,4'-oxydianiline, 3,4 - methylenedianiline, 3,3 -methylenedianiline or 3,3 -diaminobenzophenone, using a solvent-free melt process. These low-melt viscosity imide resins were fabricated into polyimide/T650-35 carbon fabric composites by resin transfer molding (RTM). Composites from a-ODPA based resins display better open-hole compression strength and short beam shear strength from room temperature to 288 C than that of the corresponding a-BPDA based resins. However, due to the lower Tg s of a-ODPA based resins (265-330 C), their corresponding composites do not possess 315 C use capability while the a-BPDA based composites do. In essence, RTM 370 (T g = 370 C), derived from a-BPDA and 3,4 -ODA and PEPA, exhibits the best overall property performance at 315 C (600 F). Author ANHYDRIDES; ASYMMETRY; POLYIMIDES; COMPOSITE MATERIALS; FABRICATION; OLIGOMERS 20090042962 NASA Goddard Space Flight Center, Greenbelt, MD, United States Can Earth's Plants Keep Up with Us?...Satellite View of Globabl Demand on Products of Photosynthesis Imhoff, Marc Lee; October 17, 2008; In English; ASTC 2008 Annual Conference. IGLO Pre-Conference Session, 17 Oct. 2008, Philadelphia, PA, United States; Original contains color and black and white illustrations No Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090042962 This slide presentation reviews the changing global ecosystem in comparison to the growing human population. The presentation includes information on urbanization and productivity. CASI ECOSYSTEMS; PHOTOSYNTHESIS; POPULATIONS; PLANTS (BOTANY) 20090042967 NASA Glenn Research Center, Cleveland, OH, United States Operation of SOI P-Channel Field Effect Transistors, CHT-PMOS30, under Extreme Temperatures Patterson, Richard; Hammoud, Ahmad; June 2009; In English; Original contains black and white illustrations Contract(s)/Grant(s): NNC06BA07BWBS 724297.40.43.03.01 Report No.(s): E-17165-INF; No Copyright; Avail.: CASI: A02, Hardcopy Avail Online: http://hdl.handle.net/2060/20090042967 Electronic systems are required to operate under extreme temperatures in NASA planetary exploration and deep space missions. Electronics on-board spacecraft must also tolerate thermal cycling between extreme temperatures. Thermal management means are usually included in today s spacecraft systems to provide adequate temperature for proper operation of the electronics. These measures, which may include heating elements, heat pipes, radiators, etc., however add to the complexity in the design of the system, increases its cost and weight, and affects its performance and reliability. Electronic parts and circuits capable of withstanding and operating under extreme temperatures would reflect in improvement in system s efficiency, reducing cost, and improving overall reliability. Semiconductor chips based on silicon-on-insulator (SOI) technology are designed mainly for high temperature applications and find extensive use in terrestrial well-logging fields. Their inherent design offers advantages over silicon devices in terms of reduced leakage currents, less power consumption, faster switching speeds, and good radiation tolerance. Little is known, however, about their performance at cryogenic temperatures and under wide thermal swings. Experimental investigation on the operation of SOI, N-channel field effect transistors under wide temperature range was reported earlier [1]. This work examines the performance of P-channel devices of these SOI transistors. The electronic part investigated in this work comprised of a Cissoid s CHT-PMOS30, high temperature P-channel MOSFET (metal-oxide semiconductor field-effect transistor) device [2]. This high voltage, medium-power transistor is designed for geothermal well logging applications, aerospace and avionics, and automotive industry, and is specified for operation in the temperature range of -55 C to +225 C. Table I shows some specifications of this transistor [2]. The CHT-PMOS30 device was characterized at various temperatures over the range of -190 C to +225 C in terms of its voltage/current characteristic curves. The test temperatures included +22, -50, -100, -150, -175, -190, +50, +100, +150, +175, +200, and +225 C. Limited thermal cycling testing was also performed on the device. These tests consisted of subjecting the transistor to a total of twelve thermal cycles between -190 C and +225 C. A temperature rate of change of 10 C/min and a soak time at the test temperature of 10 minutes were used throughout this work. Post-cycling measurements were also performed at selected temperatures. In addition, re-start capability at extreme temperatures, i.e. power switched on while the device was soaking for a period of 20 minutes at the test temperatures of -190 C and +225 C, was investigated. Author SEMICONDUCTORS (MATERIALS); CHIPS (ELECTRONICS); CRYOGENIC TEMPERATURE; ELECTRIC POTENTIAL; FIELD EFFECT TRANSISTORS; HIGH TEMPERATURE; METAL OXIDE SEMICONDUCTORS; THERMAL CYCLING TESTS; SOI (SEMICONDUCTORS) 20090042970 NASA Marshall Space Flight Center, Huntsville, AL, United States Lunar Missions and Datasets Cohen, Barbara A.; October 20, 2009; In English; Lunar Site Planning and Construction Workshop, 20-21 Oct. 2009, Huntsville, AL, United States; Original contains color illustrations Report No.(s): M09-0822; No Copyright; Avail.: CASI: A01, Hardcopy Avail Online: http://hdl.handle.net/2060/20090042970 There are two slide presentations contained in this document. The first reviews the lunar missions from Surveyor, Galileo, Clementine, the Lunar Prospector, to upcoming lunar missions, Lunar Reconnaissance Orbiter (LRO), Lunar Crater Observation & Sensing Satellite (LCROSS), Acceleration, Reconnection, Turbulence and Electrodynamics of Moon's Interaction with the Sun (ARTEMIS), Gravity Recovery and Interior Laboratory (GRAIL), Lunar Atmosphere, Dust and Environment Explorer (LADEE), ILN and a possible Robotic sample return mission. The information that the missions about the moon is reviewed. The second set of slides reviews the lunar meteorites, and the importance of lunar meteorites to adding to our understanding of the moon. CASI MOON; SELENOLOGY; LUNAR PROBES; LUNAR EXPLORATION; LUNAR SURFACE 20090042972 NASA Langley Research Center, Hampton, VA, United States Comparison of Transport Codes, HZETRN, HETC and FLUKA, Using 1977 GCR Solar Minimum Spectra Heinbockel, John H.; Slaba, Tony C.; Tripathi, Ram K.; Blattnig, Steve R.; Norbury, John W.; Badavi, Francis F.; Townsend, Lawrence W.; Handler, Thomas; Gabriel, Tony A.; Pinsky, Lawrence S.; Reddell, Brandon; Aumann, Aric R.; December 2009; In English; Original contains color illustrations Contract(s)/Grant(s): NNL07AA36C; NNL07AA18CNNL06AA14A651549.02.07.01 Report No.(s): NASA/TP-2009-215956; L-19753; LF99-9385; Copyright; Avail.: CASI: A05, Hardcopy Avail Online: http://hdl.handle.net/2060/20090042972 The HZETRN deterministic radiation transport code is one of several tools developed to analyze the effects of harmful galactic cosmic rays (GCR) and solar particle events (SPE) on mission planning, astronaut shielding and instrumentation. This paper is a comparison study involving the two Monte Carlo transport codes, HETC-HEDS and FLUKA, and the deterministic transport code, HZETRN. Each code is used to transport ions from the 1977 solar minimum GCR spectrum impinging upon a 20 g/cm2 Aluminum slab followed by a 30 g/cm2 water slab. This research is part of a systematic effort of verification and validation to quantify the accuracy of HZETRN and determine areas where it can be improved. Comparisons of dose and dose equivalent values at various depths in the water slab are presented in this report. This is followed by a comparison of the proton fluxes, and the forward, backward and total neutron fluxes at various depths in the water slab. Comparisons of the secondary light ion 2H, 3H, 3He and 4He fluxes are also examined. Author GALACTIC COSMIC RAYS; SOLAR ACTIVITY EFFECTS; SOLAR STORMS; RADIATION TRANSPORT; MONTE CARLO METHOD; MISSION PLANNING; SOLAR CORPUSCULAR RADIATION 20090042975 NASA Langley Research Center, Hampton, VA, United States Development of Quiet Honeycomb Panels Palumbo, Daniel L.; Klos, Jacob; December 2009; In English; Original contains color and black and white illustrations Contract(s)/Grant(s): WBS 561581.02.08.07.18.02 Report No.(s): NASA/TM-2009-215954; L-19785; LF99-9714; No Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090042975 Sandwich honeycomb composite panels are lightweight and strong, and, therefore, provide a reasonable alternative to the aluminum ring framelstringer architecture currently used for most aircraft airframes. The drawback to honeycomb panels is that they radiate noise into the aircraft cabin very efficiently provoking the need for additional sound treatment which adds weight and reduces the material's cost advantage. A series of honeycomb panels were made which incorporated different design strategies aimed at reducing the honeycomb panels' radiation efficiency while at the same time maintaining its strength. The majority of the desi gns were centered around the concept of creatin g areas of reduced stiffness in the panel by adding voids and recesses to the core. The effort culminated with a reinforced./recessed panel which had 6 dB higher transmission loss than the baseline solid core panel while maintaining comparable strength. Author HONEYCOMB STRUCTURES; SANDWICH STRUCTURES; PANELS; AIRFRAMES; COMPOSITE STRUCTURES 20090042976 NASA Langley Research Center, Hampton, VA, United States Version 2 of the Protuberance Correlations for the Shuttle-Orbiter Boundary Layer Transition Tool King, Rudolph A.; Kegerise, Michael A.; Berry, Scott A.; December 2009; In English; Original contains color illustrations Contract(s)/Grant(s): WBS 599489.02.07.07.04.11.01 Report No.(s): NASA/TP-2009-215951; LF99-9855; L-19791; No Copyright; Avail.: CASI: A04, Hardcopy Avail Online: http://hdl.handle.net/2060/20090042976 Orbiter-specific transition data, acquired in four ground-based facilities (LaRC 20-Inch Mach 6 Air Tunnel, LaRC 31-Inch Mach 10 Air Tunnel, LaRC 20-Inch Mach 6 CF4 Tunnel, and CUBRC LENS-I Shock Tunnel) with three wind tunnel model scales (0.75, 0.90, and 1.8%) and from Orbiter historical flight data, have been analyzed to improve a pre-existing engineering tool for reentry transition prediction on the windward side of the Orbiter. Boundary layer transition (BLT) engineering correlations for transition induced by isolated protuberances are presented using a laminar Navier-Stokes (N-S) database to provide the relevant boundary-layer properties. It is demonstrated that the earlier version of the BLT correlation that had been developed using parameters derived from an engineering boundary-layer code has improved data collapse when developed with the N-S database. Of the new correlations examined, the proposed correlation 5, based on boundary-layer edge and wall properties, was found to provide the best overall correlation metrics when the entire database is employed. The second independent correlation (proposed correlation 7) selected is based on properties within the boundary layer at the protuberance height. The Aeroheating Panel selected a process to derive the recommended coefficients for Version 2 of the BLT Tool. The assumptions and limitations of the recommended protuberance BLT Tool V.2 are presented. Author BOUNDARY LAYER TRANSITION; SPACE SHUTTLE ORBITERS; CORRELATION; AERODYNAMIC HEATING; HYPERSONIC SPEED; PROTUBERANCES 20090042980 NASA Marshall Space Flight Center, Huntsville, AL, United States A Micro Fluorescent Activated Cell Sorter for Astrobiology Applications Platt, Donald W.; Hoover, Richard B.; August 02, 2009; In English; SPIE Optics and Photonics 2009, 2-6 Aug. 2009, San Diego, CA, United States; Original contains color and black and white illustrations Report No.(s): M10-0042; Copyright; Avail.: CASI: A02, Hardcopy Avail Online: http://hdl.handle.net/2060/20090042980 A micro-scale Fluorescent Activated Cell Sorter (microFACS) for astrobiology applications is under development. This device is designed to have a footprint of 7 cm x 7 cm x 4 cm and allow live-dead counts and sorting of cells that have fluorescent characteristics from staining. The FACS system takes advantage of microfluidics to create a cell sorter that can fit in the palm of the hand. A micron-scale channel allows cells to pass by a blue diode which causes emission of marker-expressed cells which are detected by a filtered photodetector. A small microcontroller then counts cells and operates high speed valves to select which chamber the cell is collected in (a collection chamber or a waste chamber). Cells with the expressed characteristic will be collected in the collection chamber. This system has been built and is currently being tested. We are also designing a system with integrated MEMS-based pumps and valves for a small and compact unit to fly on small satellite-based biology experiments. Author FLUORESCENCE; EXOBIOLOGY; MICROELECTROMECHANICAL SYSTEMS; PHOTOMETERS; DIODES; COUNTING 20090042984 NASA Langley Research Center, Hampton, VA, United States Turbulent Wing-Leading-Edge Correlation Assessment for the Shuttle Orbiter King, Rudolph A.; Vaughan, Matthew P.; December 2009; In English; Original contains color and black and white illustrations Contract(s)/Grant(s): WBS 599489.02.07.07.04.11.01 Report No.(s): NASA/TM-2009-215949; L-19784; LF99-9713; No Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090042984 This study was conducted in support of the Orbiter damage assessment activity that takes place for each Shuttle mission since STS-107 (STS - Space Transportation System). As part of the damage assessment activity, the state of boundary layer (laminar or turbulent) during reentry needs to be estimated in order to define the aerothermal environment on the Orbiter. Premature turbulence on the wing leading edge (WLE) is possible if a surface irregularity promotes early transition and the resulting turbulent wedge flow contaminates the WLE flow. The objective of this analysis is to develop a criterion to determine if and when the flow along the WLE experiences turbulent heating given an incoming turbulent boundary layer that contaminates the attachment line. The data to be analyzed were all obtained as part of the MH-13 Space Shuttle Orbiter Aerothermodynamic Test conducted on a 1.8%-scale Orbiter model at Calspan/University of Buffalo Research Center in the Large Energy National Shock Tunnels facility. A rational framework was used to develop a means to assess the state of the WLE flow on the Orbiter during reentry given a contaminated attachment-line flow. Evidence of turbulent flow on the WLE has been recently documented for a few STS missions during the Orbiter s flight history, albeit late in the reentry trajectory. The criterion developed herein will be compared to these flight results. Author SPACE SHUTTLE ORBITERS; BOUNDARY LAYERS; TURBULENT BOUNDARY LAYER; SPACE TRANSPORTATION SYSTEM; DAMAGE ASSESSMENT; LEADING EDGES; REENTRY TRAJECTORIES; CONTAMINANTS 20090042985 NASA Marshall Space Flight Center, Huntsville, AL, United States Satellite Test of Radiation Impact on Ramtron 512K FRAM MacLeod, Todd C.; Sayyah, Rana; Sims, W. Herb; Varnavas, Kosta A.; Ho, Fat D.; October 25, 2009; In English; 10th Annual Non-Volatile Memory Technology Symposium (NVMTS), 25-28 Oct. 2009, Portland, OR, United States; Original contains color illustrations Report No.(s): M09-0794; Copyright; Avail.: CASI: A01, Hardcopy Avail Online: http://hdl.handle.net/2060/20090042985 The Memory Test Experiment is a space test of a ferroelectric memory device on a low Earth orbit satellite. The test consists of writing and reading data with a ferroelectric based memory device. Any errors are detected and are stored on board the satellite. The data is send to the ground through telemetry once a day. Analysis of the data can determine the kind of error that was found and will lead to a better understanding of the effects of space radiation on memory systems. The test will be one of the first flight demonstrations of ferroelectric memory in a near polar orbit which allows testing in a varied radiation environment. The memory devices being tested is a Ramtron Inc. 512K memory device. This paper details the goals and purpose of this experiment as well as the development process. The process for analyzing the data to gain the maximum understanding of the performance of the ferroelectric memory device is detailed. Author FERROELECTRICITY; LOW EARTH ORBITS; COMPUTER STORAGE DEVICES; EXTRATERRESTRIAL RADIATION; ERRORS 20090042988 Idaho Univ., Moscow, ID United States Radiation tolerant combinational logic cell Maki, Gary R., Inventor; Gambles, Jody W., Inventor; Whitaker, Sterling, Inventor; February 10, 2009; In English Contract(s)/Grant(s): NNG04GE96G Patent Info.: September 25, 2006US-Patent-7,489,538; US-Patent-Appl-SN-11/527,375 No Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090042988 A system has a reduced sensitivity to Single Event Upset and/or Single Event Transient(s) compared to traditional logic devices. In a particular embodiment, the system includes an input, a logic block, a bias stage, a state machine, and an output. The logic block is coupled to the input. The logic block is for implementing a logic function, receiving a data set via the input, and generating a result f by applying the data set to the logic function. The bias stage is coupled to the logic block. The bias stage is for receiving the result from the logic block and presenting it to the state machine. The state machine is coupled to the bias stage. The state machine is for receiving, via the bias stage, the result generated by the logic block. The state machine is configured to retain a state value for the system. The state value is typically based on the result generated by the logic block. The output is coupled to the state machine. The output is for providing the value stored by the state machine. Some embodiments of the invention produce dual rail outputs Q and Q'. The logic block typically contains combinational logic and is similar, in size and transistor configuration, to a conventional CMOS combinational logic design. However, only a very small portion of the circuits of these embodiments, is sensitive to Single Event Upset and/or Single Event Transients. Official Gazette of the U.S. Patent and Trademark Office SINGLE EVENT UPSETS; LOGIC DESIGN; LOGIC CIRCUITS 20090042995 California Inst. of Tech., Pasadena, CA United States Three-dimensional hologram display system Mintz, Frederick, Inventor; Chao, Tien-Hsin, Inventor; Bryant, Nevin, Inventor; Tsou, Peter, Inventor; February 17, 2009; In English Patent Info.: August 30, 2005US-Patent-7,490,941; US-Patent-Appl-SN-11/216,803 No Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090042995 The present invention relates to a three-dimensional (3D) hologram display system. The 3D hologram display system includes a projector device for projecting an image upon a display medium to form a 3D hologram. The 3D hologram is formed such that a viewer can view the holographic image from multiple angles up to 360 degrees. Multiple display media are described, namely a spinning diffusive screen, a circular diffuser screen, and an aerogel. The spinning diffusive screen utilizes spatial light modulators to control the image such that the 3D image is displayed on the rotating screen in a time-multiplexing manner. The circular diffuser screen includes multiple, simultaneously-operated projectors to project the image onto the circular diffuser screen from a plurality of locations, thereby forming the 3D image. The aerogel can use the projection device described as applicable to either the spinning diffusive screen or the circular diffuser screen. Official Gazette of the U.S. Patent and Trademark Office DISPLAY DEVICES; HOLOGRAPHY; IMAGE RECONSTRUCTION; ROTATION; IMAGING TECHNIQUES; IMAGE PROCESSING 20090043004 Rochester Univ., NY United States Liquid crystal devices especially for use in liquid crystal point diffraction interferometer systems Marshall, Kenneth L., Inventor; February 17, 2009; In English Contract(s)/Grant(s): NAG3-2348 Patent Info.: September 21, 2004US-Patent-7,492,439; US-Patent-Appl-SN-10/945,753 No Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090043004 Liquid crystal point diffraction interferometer (LCPDI) systems that can provide real-time, phase-shifting interferograms that are useful in the characterization of static optical properties (wavefront aberrations, lensing, or wedge) in optical elements or dynamic, time-resolved events (temperature fluctuations and gradients, motion) in physical systems use improved LCPDI cells that employ a "structured" substrate or substrates in which the structural features are produced by thin film deposition or photo resist processing to provide a diffractive element that is an integral part of the cell substrate(s). The LC material used in the device may be doped with a "contrast-compensated" mixture of positive and negative dichroic dyes. Official Gazette of the U.S. Patent and Trademark Office INTERFEROMETERS; LIQUID CRYSTALS; SUBSTRATES; PHASE SHIFT; DIFFRACTION 20090043008 Florida Univ., Gainesville, FL United States Nanoscale content-addressable memory Davis, Bryan, Inventor; Principe, Jose C., Inventor; Fortes, Jose, Inventor; February 24, 2009; In English Contract(s)/Grant(s): NCC2-1363 Patent Info.: August 15, 2005US-Patent-7,495,942; US-Patent-Appl-SN-11/573,630 No Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090043008 A combined content addressable memory device and memory interface is provided. The combined device and interface includes one or more one molecular wire crossbar memories having spaced-apart key nanowires, spaced-apart value nanowires adjacent to the key nanowires, and configurable switches between the key nanowires and the value nanowires. The combination further includes a key microwire-nanowire grid (key MNG) electrically connected to the spaced-apart key nanowires, and a value microwire-nanowire grid (value MNG) electrically connected to the spaced-apart value nanowires. A key or value MNGs selects multiple nanowires for a given key or value. Official Gazette of the U.S. Patent and Trademark Office ASSOCIATIVE MEMORY; NANOWIRES; NANOTECHNOLOGY; NANOSTRUCTURES (DEVICES) 20090043010 NASA, Washington, DC United States System comprising interchangeable electronic controllers and corresponding methods Steele, Glen F., Inventor; Salazar, George A., Inventor; August 18, 2009; In English Patent Info.: March 8, 2007US-Patent-7,577,482; US-Patent-Appl-SN-11/683,770 No Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090043010 A system comprising an interchangeable electronic controller is provided with programming that allows the controller to adapt a behavior that is dependent upon the particular type of function performed by a system or subsystem component. The system reconfigures the controller when the controller is moved from one group of subsystem components to another. A plurality of application programs are provided by a server from which the application program for a particular electronic controller is selected. The selection is based on criteria such as a subsystem component group identifier that identifies the particular type of function associated with the system or subsystem group of components. Official Gazette of the U.S. Patent and Trademark Office CONTROLLERS; ELECTRICAL ENGINEERING; ELECTRONIC CONTROL Additions to the NASA Aeronautics and Space Database as of 01/05/2010 20090043011 NASA Goddard Space Flight Center, Greenbelt, MD, United States Fundamental Limits on the Imaging and Polarisation Properties of Far-Infrared Detectors Thomas, Christopher N.; Withington, Stafford; Chuss, David T.; Wollack, Edward J.; Moseley, S. Harvey; [2009]; In English; Original contains black and white illustrations Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090043011 Far-infrared bolometric detectors are used extensively in ground-based and space-borne astronomy, and thus it is important to understand their optical behaviour precisely. We have studied the intensity and polarisation response of free-space bolometers, and shown that when the size of the absorber is reduced below a wavelength, the response changes from being that of a classical optical detector to that of a few-mode antenna. We have calculated the modal content of the reception patterns, and found that for any volumetric detector having a side length of less than a wavelength, three magnetic and three electric dipoles characterize the behaviour. The size of the absorber merely determines the relative strengths of the contributions. The same formalism can be applied to thin-film absorbers, where the induced current is forced to flow in a plane. In this case, one magnetic and two electric dipoles characterize the behaviour. The ability to model easily the intensity, polarisation, and straylight characteristics of electrically-small detectors will be of great value when designing high-performance polarimetric imaging arrays. Author BOLOMETERS; IMAGING TECHNIQUES; OPTICAL EQUIPMENT 20090043012 NASA Glenn Research Center, Cleveland, OH, United States Evaluation of Advanced COTS Passive Devices for Extreme Temperature Operation Patterson, Richard; Hammoud, Ahmad; Dones, Keishla R.; June 2009; In English; Original contains color illustrations Contract(s)/Grant(s): NNC06BA07BWBS 724297.40.43.03.01 Report No.(s): E-17163; Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090043012 Electronic sensors and circuits are often exposed to extreme temperatures in many of NASA deep space and planetary surface exploration missions. Electronics capable of operation in harsh environments would be beneficial as they simplify overall system design, relax thermal management constraints, and meet operational requirements. For example, cryogenic operation of electronic parts will improve reliability, increase energy density, and extend the operational lifetimes of space-based electronic systems. Similarly, electronic parts that are able to withstand and operate efficiently in high temperature environments will negate the need for thermal control elements and their associated structures, thereby reducing system size and weight, enhancing its reliability, improving its efficiency, and reducing cost. Passive devices play a critical role in the design of almost all electronic circuitry. To address the needs of systems for extreme temperature operation, some of the advanced and most recently introduced commercial-off-the-shelf (COTS) passive devices, which included resistors and capacitors, were examined for operation under a wide temperature regime. The types of resistors investigated included high temperature precision film, general purpose metal oxide, and wirewound. Author TEMPERATURE SENSORS; CIRCUITS; HIGH TEMPERATURE ENVIRONMENTS; TEMPERATURE CONTROL; CAPACITORS; RESISTORS 20090043015 NASA Goddard Space Flight Center, Greenbelt, MD, United States Packaging Concerns/Techniques for Large Devices Sampson, Michael J.; August 31, 2009; In English; Presentation on Military and Aerospace Programmable Logic Devices (MAPLD), 31 Aug. 2009, Greenbelt, MD, United States; Original contains color and black and white illustrations No Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090043015 This slide presentation reviews packaging challenges and options for electronic parts. The presentation includes information about non-hermetic packages, space challenges for packaging and complex package variations. CASI HERMETIC SEALS; ELECTRONIC PACKAGING; EQUIPMENT SPECIFICATIONS 20090043017 NASA Marshall Space Flight Center, Huntsville, AL, United States Adaptive Control of Small Outboard-Powered Boats for Survey Applications VanZwieten, T.S.; VanZwieten, J.H.; Fisher, A.D.; October 26, 2009; In English; MTS\IEEE Oceans '09, 26-29 Oct. 2009, Biloxi, MS, United States; Original contains color and black and white illustrations Report No.(s): M09-0726; Copyright; Avail.: CASI: A02, Hardcopy Avail Online: http://hdl.handle.net/2060/20090043017 Four autopilot controllers have been developed in this work that can both hold a desired heading and follow a straight line. These PID, adaptive PID, neuro-adaptive, and adaptive augmenting control algorithms have all been implemented into a numerical simulation of a 33-foot center console vessel with wind, waves, and current disturbances acting in the perpendicular (across-track) direction of the boat s desired trajectory. Each controller is tested for its ability to follow a desired heading in the presence of these disturbances and then to follow a straight line at two different throttle settings for the same disturbances. These controllers were tuned for an input thrust of 2000 N and all four controllers showed good performance with none of the controllers significantly outperforming the others when holding a constant heading and following a straight line at this engine thrust. Each controller was then tested for a reduced engine thrust of 1200 N per engine where each of the three adaptive controllers reduced heading error and across-track error by approximately 50% after a 300 second tuning period when compared to the fixed gain PID, showing that significant robustness to changes in throttle setting was gained by using an adaptive algorithm. Author ADAPTIVE CONTROL; AUTOMATIC PILOTS; BOATS; CONTROLLERS; AIR WATER INTERACTIONS 20090043018 NASA Marshall Space Flight Center, Huntsville, AL, United States Ares V: Shifting the Payload Design Paradigm Sumrall, Phil; Creech, Steve; Cockrell, Charles E.; October 12, 2009; In English; International Astronautical Congress 2009, 12-16 Oct. 2009, Daejeon, Korea, Democratic People's Republic of; Original contains color illustrations Report No.(s): IAC-09-D2.8.2; M09-0766; M09-0796; No Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090043018 NASA is designing the Ares V heavy-lift cargo launch vehicle to send more crew and cargo to more places on the lunar surface than the 1960s-era Saturn V and to provide ongoing support for a permanent lunar outpost. This uncrewed cargo vehicle is designed to operate together with the Ares I crew vehicle (Figure 1). In addition to this role, however, its unmatched mass and volume capability represent a national asset for exploration, science, and commerce. The Ares V also enables or significantly enhances a large class of space missions not thought possible by scientists and engineers since the Saturn V program ended over 30 years ago. Compared to current systems, it will offer approximately five times the mass and volume to most orbits and locations. This should allow prospective mission planners to build robust payloads with margins that are three to five times the industry norm. The space inside the planned payload shroud has enough usable volume to launch the volumetric equivalent of approximately 10 Apollo Lunar Modules or approximately five equivalent Hubble Space Telescopes. This mass and volume capability to low-Earth orbit (LEO) enables a host of new scientific and observation platforms, such as telescopes, satellites, planetary and solar missions, as well as being able to provide the lift for future large in-space infrastructure missions, such as space based solar power and mining, Earth asteroid defense, propellant depots, etc. In addition, payload designers may also have the option of simplifying their designs or employing Ares V s payload as dumb mass to reduce technical and operational risk. The Ares V team is engaging the potential payload community now, two to three years before System Requirements Review (SRR), in order to better understand the additional requirements from the payload community that could be accommodated in the Ares V design in its conceptual phase. This paper will discuss the Ares V reference mission and capability, as well as its potential to perform other missions in the future. Author ARES 5 CARGO LAUNCH VEHICLE; PAYLOADS; LOW EARTH ORBITS; LAUNCHING; SPACECRAFT DESIGN; HEAVY LIFT LAUNCH VEHICLES 20090043023 NASA Marshall Space Flight Center, Huntsville, AL, United States; NASA Langley Research Center, Hampton, VA, United States Ares V: Overview and Status Creech, Steve; Sumrall, Phil; Cockrell, Charles E.; Burris, Mike; October 12, 2009; In English; Original contains color illustrations Report No.(s): M09-0797; No Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090043023 NASA has begun preliminary concept work on the vehicle. Over 1,700 alternatives have been investigated since ESAS. Focused on design of EDS, payload shroud, core stage, and RS-68 core stage engines. Recent point of departure update was made following the Lunar Capability Concept Review. Adds additional performance margin using an additional RS-68. Adds half segment on the first stage boosters . Shroud size is dictated by eventual size of Altair lunar lander. Also investigating alternate uses for Ares V not related to human space exploration . Astronomy applications (e.g., large aperture telescopes), . Deep space missions, DoD applications, Other applications. Author ARES 5 CARGO LAUNCH VEHICLE; SPACE EXPLORATION; DEEP SPACE; ALTAIR LUNAR LANDER; SPACE MISSIONS; PAYLOADS 20090043024 NASA Marshall Space Flight Center, Huntsville, AL, United States The Transition of High-Resolution NASA MODIS Sea Surface Temperatures into the WRF Environmental Modeling System Case, Jonathan L.; Jedlove, Gary J.; Santos, Pablo; Medlin, Jeffrey M.; Rozumalski, Robert A.; October 17, 2009; In English; FROM 2009 National Weather Association Meeting, 17-22 Oct. 2009, Norfolk, VA, United States Report No.(s): M09-0809; M10-0029; Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090043024 The NASA Short-term Prediction Research and Transition (SPoRT) Center has developed a Moderate Resolution Imaging Spectroradiometer (MODIS) sea surface temperature (SST) composite at 2-km resolution that has been implemented in version 3 of the National Weather Service (NWS) Weather Research and Forecasting (WRF) Environmental Modeling System (EMS). The WRF EMS is a complete, full physics numerical weather prediction package that incorporates dynamical cores from both the Advanced Research WRF (ARW) and the Non-hydrostatic Mesoscale Model (NMM). The installation, configuration, and execution of either the ARW or NMM models is greatly simplified by the WRF EMS to encourage its use by NWS Weather Forecast Offices (WFOs) and the university community. The WRF EMS is easy to run on most Linux workstations and clusters without the need for compilers. Version 3 of the WRF EMS contains the most recent public release of the WRF-NMM and ARW modeling system (version 3 of the ARW is described in Skamarock et al. 2008), the WRF Pre-processing System (WPS) utilities, and the WRF Post-Processing program. The system is developed and maintained by the NWS National Science Operations Officer Science and Training Resource Coordinator. To initialize the WRF EMS with high-resolution MODIS SSTs, SPoRT developed the composite product consisting of MODIS SSTs over oceans and large lakes with the NCEP Real-Time Global (RTG) filling data over land points. Filling the land points is required due to minor inconsistencies between the WRF land-sea mask and that used to generate the MODIS SST composites. This methodology ensures a continuous field that adequately initializes all appropriate arrays in WRF. MODIS composites covering the Gulf of Mexico, western Atlantic Ocean and the Caribbean are generated daily at 0400, 0700, 1600, and 1900 UTC corresponding to overpass times of the NASA Aqua and Terra polar orbiting satellites. The MODIS SST product is output in gridded binary-1 (GRIB-1) data format for a seamless incorporation into WRF via the WPS utilities. The full-resolution, 1-km MODIS product is sub-sampled to 2-km grid spacing due to limitations in handling very large dimensions in the GRIB-1 data format. The GRIB-1 files are posted online at ftp://ftp.nsstc.org/sstcomp/WRF/, which is directly accessed by the WRF EMS scripts. The MODIS SST composites are also downloaded to the EMS data server, which is accessible by the WRF EMS users and NWS WFOs. The SPoRT MODIS SST composite provides the model with superior detail of the ocean gradients around Florida and surrounding waters, whereas the operational RTG SST typically depicts a relatively smooth field and is not able to capture sharp horizontal gradients in SST. Differences of 2-3 C are common over small horizontal distances, leading to enhanced SST gradients on either side of the Gulf Stream and along the edges of the cooler shelf waters. These sharper gradients can in turn produce atmospheric responses in simulated temperature and wind fields as depicted in LaCasse et al. Differences in atmospheric verification statistics over a several month study were generally small in the vicinity of south Florida; however, the validation of SSTs at specific buoy locations revealed important improvements in the biases and RMS errors, especially in the vicinity of the cooler shelf waters off the east-central Florida coast. A current weakness in the MODIS SST product is the occurrence of occasional discontinuities caused by high latency in SST coverage due to persistent cloud cover. An enhanced method developed by Jedlovec et al. (2009, GHRSST User Symposium) reduces the occurrence of these problems by adding Advanced Microwave Scanning Radiometer -- EOS (AMSR-E) SST data to the compositing process. Enhanced SST composites are produced over the ocean regions surrounding the Continental U.S. at four times each day corresponding to Terra and Aqua equator crossing times. For a given day and overpass time, both MODInd AMSR-E data from the previous seven days form a collection used in the compositing. At each MODIS pixel, cloud-free SST values from the collection are used to form a weighted average based on their latency (number of days from the current day). In this way, recent SST data are given more weight than older data. One of the primary issues involved in incorporating the AMSR-E microwave data in the composites is the tradeoff between the decreased spatial resolution of the AMSR-E data (25 km) and the increased coverage due to its near all-weather capability. Currently, the AMSR-E is given a weight of 20% compared to MODIS data, thereby preserving the spatial structure observed in the MODIS data. Day-time (night-time) AMSR-E SST data from Aqua are used with both Terra and Aqua MODIS day-time (night-time) SST data sets. Author ATMOSPHERIC TEMPERATURE; ENVIRONMENT MODELS; NUMERICAL WEATHER FORECASTING; SEA SURFACE TEMPERATURE; ATMOSPHERIC MODELS; CLIMATE MODELS; AIR WATER INTERACTIONS 20090043025 NASA Marshall Space Flight Center, Huntsville, AL, United States Damage Tolerance of Composite Laminates from an Empirical Perspective Nettles, Alan T.; October 20, 2009; In English; Original contains color and black and white illustrations Report No.(s): M09-0811; No Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090043025 Damage tolerance consists of analysis and experimentation working together. Impact damage is usually of most concern for laminated composites. Once impacted, the residual compression strength is usually of most interest. Other properties may be of more interest than compression (application dependent). A damage tolerance program is application specific (not everyone is building aircraft). The "Building Block Approach" is suggested for damage tolerance. Advantage can be taken of the excellent fatigue resistance of damaged laminates to save time and costs. Author IMPACT DAMAGE; COMPRESSIVE STRENGTH; RESIDUAL STRENGTH; FATIGUE (MATERIALS); FRACTURE STRENGTH; LAMINATES 20090043026 NASA Marshall Space Flight Center, Huntsville, AL, United States Production of Solar Cells in Space from Non-Specific Ores by Utilization of Electronically Enhanced Sputtering Curreri, Peter A.; October 25, 2009; In English; First International Symposium on Nanotechnology, Energy, and Space, 25-28 Oct. 2009, Houston, TX, United States Report No.(s): M10-0005; No Copyright; Avail.: CASI: A01, Hardcopy Avail Online: http://hdl.handle.net/2060/20090043026 An ideal method of construction in space would utilize some form of the Universal Differentiator and Universal Constructor as described by Von Neumann (1). The Universal Differentiator is an idealized non ore specific extractive device which is capable of breaking any ore into its constituent elements, and the Universal Constructor can utilize these elements to build any device with controllability to the nanometer scale. During the Human Exploration Initiative program in the early 1990s a conceptual study was done (2) to understand whether such devices were feasible with near term technology for the utilization of space resources and energy. A candidate system was proposed which would utilize electronically enhanced sputtering as the differentiator. Highly ionized ions would be accelerated to a kinetic energy at which the interaction between them and the lattice elections in the ore would be at a maximum. Experiments have shown that the maximum disintegration of raw material occurs at an ion kinetic energy of about 5 MeV, regardless of the composition and structure of the raw material. Devices that could produce charged ion beams in this energy range in space were being tested in the early 1990s. At this energy, for example an ion in a beam of fluorine ions yields about 8 uranium ions from uranium fluoride, 1,400 hydrogen and oxygen atoms from ice, or 7,000 atoms from sulfur dioxide ice. The ions from the disintegrated ore would then be driven by an electrical field into a discriminator in the form of a mass spectrometer, where the magnetic field would divert the ions into collectors for future use or used directly in molecular beam construction techniques. The process would require 10-7 Torr vacuum which would be available in space or on the moon. If the process were used to make thin film silicon solar cells (ignoring any energy inefficiency for beam production), then energy break even for solar cells in space would occur after 14 days. Author SOLAR CELLS; CONSTRUCTION; EXTRATERRESTRIAL RESOURCES; DIFFERENTIATORS; DISCRIMINATORS; SPUTTERING 20090043027 NASA Marshall Space Flight Center, Huntsville, AL, United States The Moon is a Planet Too: Lunar Science and Robotic Exploration Cohen, Barbara A.; September 15, 2009; In English; Herzberg Institute of Astrophysics, 15 Sep. 2009, Victoria, BC, Canada; Original contains color illustrations Report No.(s): M09-0820; M09-0821; No Copyright; Avail.: CASI: A02, Hardcopy Avail Online: http://hdl.handle.net/2060/20090043027 This slide presentation reviews some of what is known about the moon, and draws parallels between the moon and any other terrestrial planet. The Moon is a cornerstone for all rocky planets The Moon is a terrestrial body, formed and evolved similarly to Earth, Mars, Mercury, Venus, and large asteroids The Moon is a differentiated body, with a layered internal structure (crust, mantle, and core) The Moon is a cratered body, preserving a record of bombardment history in the inner solar system The Moon is an active body, experiencing moonquakes, releasing primordial heat, conducting electricity, sustaining bombardment, and trapping volatile molecules Lunar robotic missions provide early science return to obtain important science and engineering objectives, rebuild a lunar science community, and keep our eyes on the Moon. These lunar missions, both past and future are reviewed. Author LUNAR EXPLORATION; SELENOLOGY; LUNAR GEOLOGY; MOON; LUNAR EVOLUTION; LUNAR PROBES 20090043028 NASA Marshall Space Flight Center, Huntsville, AL, United States Model Validation of an RSRM Transporter Through Full-scale Operational and Modal Testing Brillhart, Ralph; Davis, Joshua; Allred, Bradley; October 13, 2009; In English; Aerospace Testing Seminar, 13-15 Oct. 2009, Manhattan Beach, CA, United States; Original contains color illustrations Contract(s)/Grant(s): NAS8-97238 Report No.(s): M09-0799; Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090043028 The Reusable Solid Rocket Motor (RSRM) segments, which are part of the current Space Shuttle system and will provide the first stage of the Ares launch vehicle, must be transported from their manufacturing facility in Promontory, Utah, to a railhead in Corinne, Utah. This approximately 25-mile trip on secondary paved roads is accomplished using a special transporter system which lifts and conveys each individual segment. ATK Launch Systems (ATK) has recently obtained a new set of these transporters from Scheuerle, a company in Germany. The transporter is a 96-wheel, dual tractor vehicle that supports the payload via a hydraulic suspension. Since this system is a different design than was previously used, computer modeling with validation via test is required to ensure that the environment to which the segment is exposed is not too severe for this space-critical hardware. Accurate prediction of the loads imparted to the rocket motor is essential in order to prevent damage to the segment. To develop and validate a finite element model capable of such accurate predictions, ATA Engineering, Inc., teamed with ATK to perform a modal survey of the transport system, including a forward RSRM segment. A set of electrodynamic shakers was placed around the transporter at locations capable of exciting the transporter vehicle dynamics. Forces from the shakers with varying phase combinations were applied using sinusoidal sweep excitation. The relative phase of the shaker forcing functions was adjusted to match the shape characteristics of each of several target modes, thereby customizing each sweep run for exciting a particular mode. The resulting frequency response functions (FRF) from this series of sine sweeps allowed identification of all target modes and other higher-order modes, allowing good comparison to the finite element model. Furthermore, the survey-derived modal frequencies were correlated with peak frequencies observed during road-going operating tests. This correlation enabled verification of the most significant modes contributing to real-world loading of the motor segment under transport. After traditional model updating, dynamic simulation of the transportation environment was compared to the measured operating data to provided further validation of the analysis model. KEYWORDS Validation, correlation, modal test, rocket motor, transporter Author SOLID PROPELLANT ROCKET ENGINES; LAUNCH VEHICLES; POSITION (LOCATION); TRANSPORTER; FREQUENCY RESPONSE; COMPUTERIZED SIMULATION; ENVIRONMENT MODELS; FUNCTIONAL DESIGN SPECIFICATIONS 20090043033 NASA Marshall Space Flight Center, Huntsville, AL, United States Watershed and Hydrodynamic Modeling for Evaluating the Impact of Land Use Change on Submerged Aquatic Vegetation and Seagrasses in Mobile Bay Estes, Maurice G.; Al-Hamdan, Mohammed; Thom, Ron; Quattrochi, Dale; Woodruff, Dana; Judd, Chaeli; Ellism Jean; Watson, Brian; Rodriguez, Hugo; Johnson, Hoyt; October 26, 2009; In English; Oceans 2009, 26-30 Oct. 2009, Biloxi, MS, United States; Original contains color and black and white illustrations Report No.(s): M10-0044; Copyright; Avail.: CASI: A02, Hardcopy Avail Online: http://hdl.handle.net/2060/20090043033 There is a continued need to understand how human activities along the northern Gulf of Mexico coast are impacting the natural ecosystems. The gulf coast is experiencing rapid population growth and associated land cover/land use change. Mobile Bay, AL is a designated pilot region of the Gulf of Mexico Alliance (GOMA) and is the focus area of many current NASA and NOAA studies, for example. This is a critical region, both ecologically and economically to the entire United States because it has the fourth largest freshwater inflow in the continental USA, is a vital nursery habitat for commercially and recreational important fisheries, and houses a working waterfront and port that is expanding. Watershed and hydrodynamic modeling has been performed for Mobile Bay to evaluate the impact of land use change in Mobile and Baldwin counties on the aquatic ecosystem. Watershed modeling using the Loading Simulation Package in C++ (LSPC) was performed for all watersheds contiguous to Mobile Bay for land use Scenarios in 1948, 1992, 2001, and 2030. The Prescott Spatial Growth Model was used to project the 2030 land use scenario based on observed trends. All land use scenarios were developed to a common land classification system developed by merging the 1992 and 2001 National Land Cover Data (NLCD). The LSPC model output provides changes in flow, temperature, sediments and general water quality for 22 discharge points into the Bay. These results were inputted in the Environmental Fluid Dynamics Computer Code (EFDC) hydrodynamic model to generate data on changes in temperature, salinity, and sediment concentrations on a grid with four vertical profiles throughout the Bay s aquatic ecosystems. The models were calibrated using in-situ data collected at sampling stations in and around Mobile bay. This phase of the project has focused on sediment modeling because of its significant influence on light attenuation which is a critical factor in the health of submerged aquatic vegetation. The impact of land use change on sediment concentrations was evaluated by analyzing the LSPC and EFDC sediment simulations for the four land use scenarios. Such analysis was also performed for storm and non-storm periods. In- situ data of total suspended sediments (TSS) and light attenuation were used to develop a regression model to estimate light attenuation from TSS. This regression model was used to derive marine light attenuation estimates throughout Mobile bay using the EFDC TSS outputs. The changes in sediment concentrations and associated impact on light attenuation in the aquatic ecosystem were used to perform an ecological analysis to evaluate the impact on seagreasses and Submerged Aquatic Vegetation (SAV) habitat. This is the key product benefiting the Mobile Bay coastal environmental managers that integrates the influences of sediments due to land use driven flow changes with the restoration potential of SAVs. Author LAND USE; WATERSHEDS; SEA GRASSES; SEDIMENTS; VEGETATION; WATER QUALITY; HYDROLOGY MODELS; ECOSYSTEMS 20090043037 NASA Johnson Space Center, Houston, TX, United States Chlorine Abundances in Martian Meteorites Bogard, D.D.; Garrison, D.H.; Park, J.; [2009]; In English; Lunar and Planetary Science Conference 2010, 1-5 Mar. 2010, The Woodlands, TX, United States Report No.(s): JSC-CN-19397; Copyright; Avail.: CASI: A01, Hardcopy Avail Online: http://hdl.handle.net/2060/20090043037 Chlorine measurements made in martian surface rocks by robotic spacecraft typically give Chlorine (Cl) abundances of approximately 0.1-0.8%. In contrast, Cl abundances in martian meteorites appear lower, although data is limited, and martian nakhlites were also subjected to Cl contamination by Mars surface brines. Chlorine abundances reported by one lab for whole rock (WR) samples of Shergotty, ALH77005, and EET79001 range 108-14 ppm, whereas Cl in nakhlites range 73-1900 ppm. Measurements of Cl in various martian weathering phases of nakhlites varied 0.04-4.7% and reveal significant concentration of Cl by martian brines Martian meteorites contain much lower Chlorine than those measured in martian surface rocks and give further confirmation that Cl in these surface rocks was introduced by brines and weathering. It has been argued that Cl is twice as effective as water in lowering the melting point and promoting melting at shallower martian depths, and that significant Cl in the shergottite source region would negate any need for significant water. However, this conclusion was based on experiments that utilized Cl concentrations more analogous to martian surface rocks than to shergottite meteorites, and may not be applicable to shergottites. Derived from text CHLORINE; METEORITIC COMPOSITION; ABUNDANCE; NAKHLITES; SHERGOTTITES 20090043050 NASA Marshall Space Flight Center, Huntsville, AL, United States Oxygen Compatibility of Brass-Filled PTFE Compared to Commonly Used Fluorinated Polymers for Oxygen Systems Herald, Stephen D.; Frisby, Paul M.; Davis, Samuel Eddie; October 07, 2009; In English; 12th International Symposium on Flammability and Sensitivity on Materital in Oxygen Enriched Atmospheres, 7-9 Oct. 2009, Berlin, Germany; Original contains color and black and white illustrations Report No.(s): M09-0199; Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090043050 Safe and reliable seal materials for high-pressure oxygen systems sometimes appear to be extinct species when sought out by oxygen systems designers. Materials that seal well are easy to find, but these materials are typically incompatible with oxygen, especially in cryogenic liquid form. This incompatibility can result in seals that leak, or much worse, seals that easily ignite and burn during use. Materials that are compatible with oxygen are easy to find, such as the long list of compatible metals, but these metallic materials are limiting as seal materials. A material that seals well and is oxygen compatible has been the big game in the designer's safari. Scientists at the Materials Combustion Research Facility (MCRF), part of NASA/Marshall Space Flight Center (MSFC), are constantly searching for better materials and processes to improve the safety of oxygen systems. One focus of this effort is improving the characteristics of polymers used in the presence of an oxygen enriched environment. Very few systems can be built which contain no polymeric materials; therefore, materials which have good impact resistance, low heat of combustion, high auto-ignition temperature and that maintain good mechanical properties are essential. The scientists and engineers at the Materials Combustion Research Facility, in cooperation with seal suppliers, are currently testing a new formulation of polytetrafluoroethylene (PTFE) with Brass filler. This Brass-filled PTFE is showing great promise as a seal and seat material for high pressure oxygen systems. Early research has demonstrated very encouraging results, which could rank this material as one of the best fluorinated polymers ever tested. This paper will compare the data obtained for Brass-filled PTFE with other fluorinated polymers, such as TFE-Teflon (PTFE) , Kel-F 81, Viton A, Viton A-500, Fluorel , and Algoflon . A similar metal filled fluorinated polymer, Salox-M , was tested in comparison to Brass-filled PTFE to demonstrate the importance of the metal chosen and relative percentage of filler. General conclusions on the oxygen compatibility of this formulation are drawn, with an emphasis on comparing and contrasting the materials performance to the performance of the current state-of-the-art oxygen compatible polymers. Author HIGH PRESSURE OXYGEN; SEALS (STOPPERS); ENVIRONMENTS; POLYTETRAFLUOROETHYLENE 20090043052 Lockheed Martin Corp., Bethesda, MD United States Lightweight electrical connector split backshell Goldman, Elliot, Inventor; April 7, 2009; In English Patent Info.: May 15, 2007US-Patent-7,513,799; US-Patent-Appl-SN-11/798,525 No Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090043052 An electrical connector split backshell is provided, comprising two substantially identical backshell halves. Each half includes a first side and a cam projecting therefrom along an axis perpendicular thereto, the cam having an alignment tooth with a constant radius and an engagement section with a radius that increases with angular distance from the alignment tooth. Each half further includes a second side parallel to the first side and a circular sector opening disposed in the second side, the circular sector opening including an inner surface configured as a ramp with a constant radius, the ramp being configured to engage with an engagement section of a cam of the other half, the circular sector opening further including a relieved pocket configured to receive an alignment tooth of the cam of the other half. Each half further includes a back side perpendicular to the first and second sides and a wire bundle notch disposed in the back side, the wire bundle notch configured to align with a wire bundle notch of the other half to form a wire bundle opening. The two substantially identical halves are rotatably coupled by engaging the engagement section of each half to the ramp of the other half. Official Gazette of the U.S. Patent and Trademark Office ELECTRIC CONNECTORS; ELECTRIC WIRE; BUNDLES 20090043053 California Inst. of Tech., Pasadena, CA United States Universal programmable logic gate and routing method Fijany, Amir, Inventor; Vatan, Farrokh, Inventor; Akarvardar, Kerem, Inventor; Blalock, Benjamin, Inventor; Chen, Suheng, Inventor; Cristoloveanu, Sorin, Inventor; Kolawa, Elzbieta, Inventor; Mojarradi, Mohammad M., Inventor; Toomarian, Nikzad, Inventor; April 7, 2009; In English Patent Info.: March 15, 2006US-Patent-7,514,964; US-Patent-Appl-SN-11/377,935 No Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090043053 An universal and programmable logic gate based on G.sup.4-FET technology is disclosed, leading to the design of more efficient logic circuits. A new full adder design based on the G.sup.4-FET is also presented. The G.sup.4-FET can also function as a unique router device offering coplanar crossing of signal paths that are isolated and perpendicular to one another. This has the potential of overcoming major limitations in VLSI design where complex interconnection schemes have become increasingly problematic. Official Gazette of the U.S. Patent and Trademark Office LOGIC CIRCUITS; LOGIC PROGRAMMING; FIELD EFFECT TRANSISTORS 20090043054 California Inst. of Tech., Pasadena, CA United States Wide-temperature integrated operational amplifier Mojarradi, Mohammad, Inventor; Levanas, Greg, Inventor; Chen, Yuan, Inventor; Cozy, Raymond S., Inventor; Greenwell, Robert, Inventor; Terry, Stephen, Inventor; Blalock, Benjamin J., Inventor; April 7, 2009; In English Patent Info.: December 7, 2006US-Patent-7,514,998; US-Patent-Appl-SN-11/636,365 No Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090043054 The present invention relates to a reference current circuit. The reference circuit comprises a low-level current bias circuit, a voltage proportional-to-absolute temperature generator for creating a proportional-to-absolute temperature voltage (VPTAT), and a MOSFET-based constant-IC regulator circuit. The MOSFET-based constant-IC regulator circuit includes a constant-IC input and constant-IC output. The constant-IC input is electrically connected with the VPTAT generator such that the voltage proportional-to-absolute temperature is the input into the constant-IC regulator circuit. Thus the constant-IC output maintains the constant-IC ratio across any temperature range. Official Gazette of the U.S. Patent and Trademark Office AMPLIFIERS; INTEGRATED CIRCUITS; REGULATORS; ELECTRIC CURRENT 20090043055 Illinois Univ., Urbana, IL United States Sensor chip and apparatus for tactile and/or flow sensing Liu, Chang, Inventor; Chen, Jack, Inventor; Engel, Jonathan, Inventor; April 14, 2009; In English Contract(s)/Grant(s): NAG5-8781 Patent Info.: February 22, 2007US-Patent-7,516,671; US-Patent-Appl-SN-11/709,466 No Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090043055 A sensor chip, comprising a flexible, polymer-based substrate, and at least one microfabricated sensor disposed on the substrate and including a conductive element. The at least one sensor comprises at least one of a tactile sensor and a flow sensor. Other embodiments of the present invention include sensors and/or multi-modal sensor nodes. Official Gazette of the U.S. Patent and Trademark Office CHIPS (ELECTRONICS); FABRICATION; DETECTION 20090043056 Photon Systems, Covina, CA United States Spectroscopic chemical analysis methods and apparatus Hug, William F., Inventor; Reid, Ray D., Inventor; April 28, 2009; In English Contract(s)/Grant(s): NAS2-02086 Patent Info.: October 5, 2005US-Patent-7,525,653; US-Patent-Appl-SN-11/245,486 No Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090043056 Spectroscopic chemical analysis methods and apparatus are disclosed which employ deep ultraviolet (e.g. in the 200 nm to 300 nm spectral range) electron beam pumped wide bandgap semiconductor lasers, incoherent wide bandgap semiconductor light emitting devices, and hollow cathode metal ion lasers to perform non-contact, non-invasive detection of unknown chemical analytes. These deep ultraviolet sources enable dramatic size, weight and power consumption reductions of chemical analysis instruments. Chemical analysis instruments employed in some embodiments include capillary and gel plane electrophoresis, capillary electrochromatography, high performance liquid chromatography, flow cytometry, flow cells for liquids and aerosols, and surface detection instruments. In some embodiments, Raman spectroscopic detection methods and apparatus use ultra-narrow-band angle tuning filters, acousto-optic tuning filters, and temperature tuned filters to enable ultra-miniature analyzers for chemical identification. In some embodiments Raman analysis is conducted simultaneously with native fluorescence spectroscopy to provide high levels of sensitivity and specificity in the same instrument. Official Gazette of the U.S. Patent and Trademark Office CHEMICAL ANALYSIS; CYTOMETRY; SPECTROSCOPY; ACOUSTO-OPTICS 20090043057 NASA, Washington, DC United States Conformal gripping device Vranish, John M., Inventor; April 7, 2009; In English Patent Info.: March 21, 2007US-Patent-7,513,546; US-Patent-Appl-SN-11/689,161 No Copyright; Avail.: CASI: A02, Hardcopy Avail Online: http://hdl.handle.net/2060/20090043057 The present invention relates to a conformal gripping device. In an embodiment of the present invention a conformal gripper device may be disclosed comprising a frame that includes an array of movable pins. The device may also include a roller locking and unlocking system within the frame. The system may comprise a pair of locking rollers for each row of gripper pins to facilitate locking and unlocking the array of gripper pins on a column-by-column basis. The system may also include a striker element that may force the locking rollers to roll along an angled roll surface to facilitate unlocking of the array of pins on a column-by-column basis. The system may further include an electromagnetic actuator or solenoid and permanent magnets to facilitate movement of the striker element and the locking rollers. Official Gazette of the U.S. Patent and Trademark Office END EFFECTORS; PINS; LOCKS (FASTENERS) 20090043059 California Inst. of Tech., Pasadena, CA United States Selective functionalization of carbon nanotube tips allowing fabrication of new classes of nanoscale sensing and manipulation tools Wade, Lawrence A., Inventor; Shapiro, Ian R., Inventor; Collier, Charles Patrick, Inventor; Esplandiu, Maria J., Inventor; Bittner, Jr., Vern Garrett, Inventor; Giapis, Konstantinos P., Inventor; April 7, 2009; In English Contract(s)/Grant(s): NAS7-1407 Patent Info.: February 20, 2004US-Patent-7,514,214; US-Patent-Appl-SN-10/783,713 No Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090043059 Embodiments in accordance with the present invention relate to techniques for the growth and attachment of single wall carbon nanotubes (SWNT), facilitating their use as robust and well-characterized tools for AFM imaging and other applications. In accordance with one embodiment, SWNTs attached to an AFM tip can function as a structural scaffold for nanoscale device fabrication on a scanning probe. Such a probe can trigger, with nanometer precision, specific biochemical reactions or conformational changes in biological systems. The consequences of such triggering can be observed in real time by single-molecule fluorescence, electrical, and/or AFM sensing. Specific embodiments in accordance with the present invention utilize sensing and manipulation of individual molecules with carbon nanotubes, coupled with single-molecule fluorescence imaging, to allow observation of spectroscopic signals in response to mechanically induced molecular changes. Biological macromolecules such as proteins or DNA can be attached to nanotubes to create highly specific single-molecule probes for investigations of intermolecular dynamics, for assembling hybrid biological and nanoscale materials, or for developing molecular electronics. In one example, electrical wiring of single redox enzymes to carbon nanotube scanning probes allows observation and electrochemical control over single enzymatic reactions by monitoring fluorescence from a redox-active cofactor or the formation of fluorescent products. Enzymes ''nanowired'' to the tips of carbon nanotubes in accordance with embodiments of the present invention, may enable extremely sensitive probing of biological stimulus-response with high spatial resolution, including product-induced signal transduction. Official Gazette of the U.S. Patent and Trademark Office CARBON NANOTUBES; DETECTION; FABRICATION; MACROMOLECULES; MOLECULAR ELECTRONICS; NANOSTRUCTURE GROWTH 20090043062 NASA, Washington, DC United States Interactive inventory monitoring Spremo, Stevan M., Inventor; Udoh, Usen E., Inventor; April 14, 2009; In English Patent Info.: May 25, 2006US-Patent-7,516,890; US-Patent-Appl-SN-11/444,807 No Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090043062 Method and system for monitoring present location and/or present status of a target inventory item, where the inventory items are located on one or more inventory shelves or other inventory receptacles that communicate with an inventory base station through use of responders such as RFIDs. A user operates a hand held interrogation and display (IAD) module that communicates with, or is part of, the base station, to provide an initial inquiry. Information on location(s) of the target inventory item is also indicated visibly and/or audibly on the receptacle(s) for the user. Status information includes an assessment of operation readiness and a time, if known, that the specified inventory item or class was last removed or examined or modified. Presentation of a user access level may be required for access to the target inventory item. Another embodiment provides inventory information for a stack as a sight-impaired or hearing-impaired person passes adjacent to that stack. Official Gazette of the U.S. Patent and Trademark Office INVENTORIES; VISUAL PERCEPTION; INTERROGATION 20090043063 Alameda Applied Science Corp., San Leandro, CA United States Vacuum arc plasma thrusters with inductive energy storage driver Krishnan, Mahadevan, Inventor; April 14, 2009; In English Contract(s)/Grant(s): NAS3-02047 Patent Info.: January 31, 2006US-Patent-7,518,085; US-Patent-Appl-SN-11/384,617 No Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090043063 A plasma thruster with a cylindrical inner and cylindrical outer electrode generates plasma particles from the application of energy stored in an inductor to a surface suitable for the formation of a plasma and expansion of plasma particles. The plasma production results in the generation of charged particles suitable for generating a reaction force, and the charged particles are guided by a magnetic field produced by the same inductor used to store the energy used to form the plasma. Official Gazette of the U.S. Patent and Trademark Office ENERGY STORAGE; GAS EXPANSION; INDUCTORS; PLASMA DYNAMICS; PLASMA ENGINES 20090043065 United Space Alliance, Houston, TX United States Image and information management system Robertson, Tina L., Inventor; Raney, Michael C., Inventor; Dougherty, Dennis M., Inventor; Kent, Peter C., Inventor; Brucker, Russell X., Inventor; Lampert, Daryl A., Inventor; April 14, 2009; In English Contract(s)/Grant(s): NAS9-20000 Patent Info.: September 28, 2007US-Patent-7,519,238; US-Patent-Appl-SN-11/863,765 No Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090043065 A system and methods through which pictorial views of an object's configuration, arranged in a hierarchical fashion, are navigated by a person to establish a visual context within the configuration. The visual context is automatically translated by the system into a set of search parameters driving retrieval of structured data and content (images, documents, multimedia, etc.) associated with the specific context. The system places ''hot spots'', or actionable regions, on various portions of the pictorials representing the object. When a user interacts with an actionable region, a more detailed pictorial from the hierarchy is presented representing that portion of the object, along with real-time feedback in the form of a popup pane containing information about that region, and counts-by-type reflecting the number of items that are available within the system associated with the specific context and search filters established at that point in time. Official Gazette of the U.S. Patent and Trademark Office INFORMATION MANAGEMENT; SYSTEMS ENGINEERING; GRAPHIC ARTS 20090043068 NASA, Washington, DC United States Processing circuitry for single channel radiation detector Holland, Samuel D., Inventor; Delaune, Paul B., Inventor; Turner, Kathryn M., Inventor; April 21, 2009; In English Patent Info.: May 31, 2006US-Patent-7,521,682; US-Patent-Appl-SN-11/421,196 No Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090043068 Processing circuitry is provided for a high voltage operated radiation detector. An event detector utilizes a comparator configured to produce an event signal based on a leading edge threshold value. A preferred event detector does not produce another event signal until a trailing edge threshold value is satisfied. The event signal can be utilized for counting the number of particle hits and also for controlling data collection operation for a peak detect circuit and timer. The leading edge threshold value is programmable such that it can be reprogrammed by a remote computer. A digital high voltage control is preferably operable to monitor and adjust high voltage for the detector. Official Gazette of the U.S. Patent and Trademark Office CIRCUITS; DIGITAL SYSTEMS; HIGH VOLTAGES; RADIATION DETECTORS 20090043072 Honeywell International, Inc., Morristown, NJ United States Adaptable DC offset correction Golusky, John M., Inventor; Muldoon, Kelly P., Inventor; April 21, 2009; In English Patent Info.: October 7, 2005US-Patent-7,522,897; US-Patent-Appl-SN-11/246,044 No Copyright; Avail.: CASI: A02, Hardcopy Avail Online: http://hdl.handle.net/2060/20090043072 Methods and systems for adaptable DC offset correction are provided. An exemplary adaptable DC offset correction system evaluates an incoming baseband signal to determine an appropriate DC offset removal scheme; removes a DC offset from the incoming baseband signal based on the appropriate DC offset scheme in response to the evaluated incoming baseband signal; and outputs a reduced DC baseband signal in response to the DC offset removed from the incoming baseband signal. Official Gazette of the U.S. Patent and Trademark Office ADAPTATION; DIRECT CURRENT 20090043074 California Inst. of Tech., Pasadena, CA United States Direct methanol feed fuel cell and system Surampudi, Subbarao, Inventor; Frank, Harvey A., Inventor; Narayanan, Sekharipuram R., Inventor; Chun, William, Inventor; Jeffries-Nakamura, Barbara, Inventor; Kindler, Andrew, Inventor; Halpert, Gerald, Inventor; February 10, 2009; In English Contract(s)/Grant(s): NAS7-1407 Patent Info.: August 30, 2004US-Patent-7,488,548; US-Patent-Appl-SN-10/930,505 No Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090043074 Improvements to non acid methanol fuel cells include new formulations for materials. The platinum and ruthenium are more exactly mixed together. Different materials are substituted for these materials. The backing material for the fuel cell electrode is specially treated to improve its characteristics. A special sputtered electrode is formed which is extremely porous. The fuel cell system also comprises a fuel supplying part including a meter which meters an amount of fuel which is used by the fuel cell, and controls the supply of fuel based on said metering. Official Gazette of the U.S. Patent and Trademark Office FEED SYSTEMS; FUEL CELLS; METHYL ALCOHOL; SPUTTERING 20090043077 Columbia Univ., New York, NY United States Microfabricated rankine cycle steam turbine for power generation and methods of making the same Frechette, Luc, Inventor; Muller, Norbert, Inventor; Lee, Changgu, Inventor; February 10, 2009; In English Contract(s)/Grant(s): NAS3-02118; NAS3-03105 Patent Info.: November 15, 2004US-Patent-7,487,641; US-Patent-Appl-SN-10/988,974 No Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090043077 In accordance with the present invention, an integrated micro steam turbine power plant on-a-chip has been provided. The integrated micro steam turbine power plant on-a-chip of the present invention comprises a miniature electric power generation system fabricated using silicon microfabrication technology and lithographic patterning. The present invention converts heat to electricity by implementing a thermodynamic power cycle on a chip. The steam turbine power plant on-a-chip generally comprises a turbine, a pump, an electric generator, an evaporator, and a condenser. The turbine is formed by a rotatable, disk-shaped rotor having a plurality of rotor blades disposed thereon and a plurality of stator blades. The plurality of stator blades are interdigitated with the plurality of rotor blades to form the turbine. The generator is driven by the turbine and converts mechanical energy into electrical energy. Official Gazette of the U.S. Patent and Trademark Office FABRICATION; MINIATURIZATION; RANKINE CYCLE; TURBINE PUMPS 20090043078 Inframat Corp., Farmington, CT United States Thick film magnetic nanoparticulate composites and method of manufacture thereof Ma, Xinqing, Inventor; Zhang, Yide, Inventor; Ge, Shihui, Inventor; Zhang, Zongtao, Inventor; Yan, Dajing, Inventor; Xiao, Danny T., Inventor; February 3, 2009; In English Contract(s)/Grant(s): NAS3-00073 Patent Info.: May 14, 2004US-Patent-7,485,366; US-Patent-Appl-SN-10/846,440 No Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090043078 Thick film magnetic/insulating nanocomposite materials, with significantly reduced core loss, and their manufacture are described. The insulator coated magnetic nanocomposite comprises one or more magnetic components, and an insulating component. The magnetic component comprises nanometer scale particles (about 1 to about 100 nanometers) coated by a thin-layered insulating phase. While the intergrain interaction between the immediate neighboring magnetic nanoparticles separated by the insulating phase provides the desired soft magnetic properties, the insulating material provides high resistivity, which reduces eddy current loss. Official Gazette of the U.S. Patent and Trademark Office INSULATORS; NANOCOMPOSITES; NANOPARTICLES; THICK FILMS; MANUFACTURING 20090043081 NASA, Washington, DC United States Stepping flexures Vranish, John M., Inventor; March 17, 2009; In English Patent Info.: September 29, 2006US-Patent-7,504,921; US-Patent-Appl-SN-11/543,278 No Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090043081 An actuator for moving a load has a frame forming a race between two surfaces thereof, at least two elements joined together by at least one flexible member, the elements and the at least one flexible member being disposed between the two surfaces of the frame that forms a race, one of the elements further joined to the load by a portion of the at least one flexible member, wherein when an element comes into contact with a surface of the frame it will stick thereto absent a repelling force, and moving means disposed to selectively attract or repel a corresponding element towards or away from one or the other of the two surfaces of the frame that forms the race. The actuator effects movement of the load in a direction towards or away from the elements, by changing a position of at least one of the elements on a surface of the frame that forms the race. Official Gazette of the U.S. Patent and Trademark Office ACTUATORS; FLEXING; LOADS (FORCES); SURFACE GEOMETRY Additions to the NASA Aeronautics and Space Database as of 01/06/2010 20090043092 NASA Marshall Space Flight Center, Huntsville, AL, United States Lunar Crater Observation and Sensing Satellite (LCROSS) Cohen, Barbara A.; October 05, 2009; In English; AAS Division for Planetary Science, 5-9 Oct. 2009, Fajardo, Puerto Rico; Original contains color illustrations Report No.(s): M09-0818; No Copyright; Avail.: CASI: A02, Hardcopy Avail Online: http://hdl.handle.net/2060/20090043092 This slide presentation reviews the Lunar Crater Observation and Sensing Satellite (LCROSS). The presentation includes information about the launch vehicle, launch site, and mission overview. CASI LUNAR CRATERS; LCROSS (SATELLITE); EXTRATERRESTRIAL WATER; LUNAR EXPLORATION 20090043093 Washington Univ., Seattle, WA United States Microwell arrays with nanoholes Folch, Albert, Inventor; Kosar, Turgut Fettah, Inventor; March 10, 2009; In English Contract(s)/Grant(s): NAG9-1343 Patent Info.: April 5, 2004US-Patent-7,501,279; US-Patent-Appl-SN-10/818,743 No Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090043093 A device for conducting parallel analysis or manipulation of multiple cells or biomolecules is disclosed. In one embodiment, the device comprises a silicon chip with a microwell, and at least one membrane suspended at the bottom opening of the microwell. The suspended portion of the membrane defines a nanohole that provides access to the material on the other side of the membrane. Official Gazette of the U.S. Patent and Trademark Office BIOCHEMISTRY; NANOTECHNOLOGY; ARRAYS; CHIPS (ELECTRONICS) 20090043094 California Inst. of Tech., Pasadena, CA United States Encoders for block-circulant LDPC codes Divsalar, Dariush, Inventor; Abbasfar, Aliazam, Inventor; Jones, Christopher R., Inventor; Dolinar, Samuel J., Inventor; Thorpe, Jeremy C., Inventor; Andrews, Kenneth S., Inventor; Yao, Kung, Inventor; March 3, 2009; In English Patent Info.: June 24, 2005US-Patent-7,499,490; US-Patent-Appl-SN-11/166,041 No Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090043094 Methods and apparatus to encode message input symbols in accordance with an accumulate-repeat-accumulate code with repetition three or four are disclosed. Block circulant matrices are used. A first method and apparatus make use of the block-circulant structure of the parity check matrix. A second method and apparatus use block-circulant generator matrices. Official Gazette of the U.S. Patent and Trademark Office CODERS; MESSAGES; PARITY; MATRICES (MATHEMATICS) 20090043095 Wisconsin Alumni Research Foundation, Madison, WI United States Non-ambipolar radio-frequency plasma electron source and systems and methods for generating electron beams Hershkowitz, Noah, Inventor; Longmier, Benjamin, Inventor; Baalrud, Scott, Inventor; March 3, 2009; In English Contract(s)/Grant(s): NNC04GA82G Patent Info.: June 28, 2006US-Patent-7,498,592; US-Patent-Appl-SN-11/427,273 No Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090043095 An electron generating device extracts electrons, through an electron sheath, from plasma produced using RF fields. The electron sheath is located near a grounded ring at one end of a negatively biased conducting surface, which is normally a cylinder. Extracted electrons pass through the grounded ring in the presence of a steady state axial magnetic field. Sufficiently large magnetic fields and/or RF power into the plasma allow for helicon plasma generation. The ion loss area is sufficiently large compared to the electron loss area to allow for total non-ambipolar extraction of all electrons leaving the plasma. Voids in the negatively-biased conducting surface allow the time-varying magnetic fields provided by the antenna to inductively couple to the plasma within the conducting surface. The conducting surface acts as a Faraday shield, which reduces any time-varying electric fields from entering the conductive surface, i.e. blocks capacitive coupling between the antenna and the plasma. Official Gazette of the U.S. Patent and Trademark Office ELECTRON BEAMS; ELECTRON SOURCES; PLASMA GENERATORS; RADIO FREQUENCIES 20090043096 Stanford Univ., Palo Alto, CA United States Statistical inference of static analysis rules Engler, Dawson Richards, Inventor; March 17, 2009; In English Contract(s)/Grant(s): NAS1-98139 Patent Info.: October 20, 2003US-Patent-7,505,952; US-Patent-Appl-SN-10/689,556 No Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090043096 Various apparatus and methods are disclosed for identifying errors in program code. Respective numbers of observances of at least one correctness rule by different code instances that relate to the at least one correctness rule are counted in the program code. Each code instance has an associated counted number of observances of the correctness rule by the code instance. Also counted are respective numbers of violations of the correctness rule by different code instances that relate to the correctness rule. Each code instance has an associated counted number of violations of the correctness rule by the code instance. A respective likelihood of the validity is determined for each code instance as a function of the counted number of observances and counted number of violations. The likelihood of validity indicates a relative likelihood that a related code instance is required to observe the correctness rule. The violations may be output in order of the likelihood of validity of a violated correctness rule. Official Gazette of the U.S. Patent and Trademark Office INFERENCE; STATISTICAL ANALYSIS; CODING 20090043097 Florida Univ., Gainesville, FL United States Electric propulsion device for high power applications Roy, Subrata, Inventor; March 24, 2009; In English Contract(s)/Grant(s): NAG3-2520; NAG3-2638 Patent Info.: March 31, 2005US-Patent-7,506,497; US-Patent-Appl-SN-11/096,069 No Copyright; Avail.: CASI: A02, Hardcopy Avail Online: http://hdl.handle.net/2060/20090043097 An electric propulsion device is disclosed having an anode and a cathode. The propulsion device includes a discharge annulus having the anode adjacent an end region thereof. At least one inlet aperture is adjacent the anode, the aperture(s) having propellant gas flow therethrough into the discharge annulus. The propellant gas has an ionization potential. Opposed, dielectric walls define the annulus, with at least one of the opposed dielectric walls having pores therein, the pores having cooling gas flow therethrough into the discharge annulus and substantially adjacent the opposed dielectric wall(s). The cooling gas has an ionization potential higher than the ionization energy of the propellant gas. The cooling gas is adapted to substantially prevent at least one of secondary electron emission and sputtering of the dielectric walls. Official Gazette of the U.S. Patent and Trademark Office ELECTRIC PROPULSION; DIELECTRICS; ELECTRON EMISSION; IONIZATION POTENTIALS 20090043098 Rice Univ., Houston, TX United States Vibration damping and heat transfer using material phase changes Kloucek, Petr, Inventor; Reynolds, Daniel R., Inventor; March 24, 2009; In English Contract(s)/Grant(s): NAG5-8136 Patent Info.: June 14, 2004US-Patent-7,506,735; US-Patent-Appl-SN-10/866,973 No Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090043098 A method and apparatus wherein phase changes in a material can dampen vibrational energy, dampen noise and facilitate heat transfer. One embodiment includes a method for damping vibrational energy in a body. The method comprises attaching a material to the body, wherein the material comprises a substrate, a shape memory alloy layer, and a plurality of temperature change elements. The method further comprises sensing vibrations in the body. In addition, the method comprises indicating to at least a portion of the temperature change elements to provide a temperature change in the shape memory alloy layer, wherein the temperature change is sufficient to provide a phase change in at least a portion of the shape memory alloy layer, and further wherein the phase change consumes a sufficient amount of kinetic energy to dampen at least a portion of the vibrational energy in the body. In other embodiments, the shape memory alloy layer is a thin film. Additional embodiments include a sensor connected to the material. Official Gazette of the U.S. Patent and Trademark Office HEAT TRANSFER; VIBRATION DAMPING; PHASE CHANGE MATERIALS; SHAPE MEMORY ALLOYS 20090043100 California Inst. of Tech., Pasadena, CA United States Sub-millimeter wave frequency heterodyne detector system Siegel, Peter H., Inventor; Dengler, Robert, Inventor; Mueller, Eric R., Inventor; March 24, 2009; In English Patent Info.: October 1, 2004US-Patent-7,507,963; US-Patent-Appl-SN-10/956,734 No Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090043100 The present invention relates to sub-millimeter wave frequency heterodyne imaging systems. More specifically, the present invention relates to a sub-millimeter wave frequency heterodyne detector system for imaging the magnitude and phase of transmitted power through or reflected power off of mechanically scanned samples at sub-millimeter wave frequencies. Official Gazette of the U.S. Patent and Trademark Office FREQUENCIES; HETERODYNING; IMAGING TECHNIQUES; DETECTORS 20090043103 NASA, Washington, DC United States Apparatus for integrating a rigid structure into a flexible wall of an inflatable structure Johnson, Christopher J., Inventor; Patterson, Ross M., Inventor; Spexarth, Gary R., Inventor; March 31, 2009; In English Patent Info.: December 13, 2006US-Patent-7,509,774; US-Patent-Appl-SN-11/610,295 No Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090043103 For an inflatable structure having a flexible outer shell or wall structure having a flexible restraint layer comprising interwoven, load-bearing straps, apparatus for integrating one or more substantially rigid members into the flexible shell. For each rigid member, a corresponding opening is formed through the flexible shell for receiving the rigid member. A plurality of connection devices are mounted on the rigid member for receiving respective ones of the load-bearing straps. In one embodiment, the connection devices comprise inner connecting mechanisms and outer connecting mechanisms, the inner and outer connecting mechanisms being mounted on the substantially rigid structure and spaced along a peripheral edge portion of the structure in an interleafed array in which respective outer connecting mechanisms are interposed between adjacent pairs of inner connecting mechanisms, the outer connecting mechanisms projecting outwardly from the peripheral edge portion of the substantially rigid structure beyond the adjacent inner connecting mechanisms to form a staggered array of connecting mechanisms extending along the panel structure edge portion. In one embodiment, the inner and outer connecting mechanisms form part of an integrated, structure rotatably mounted on the rigid member peripheral edge portion. Official Gazette of the U.S. Patent and Trademark Office INFLATABLE STRUCTURES; RIGID STRUCTURES; FLEXIBILITY; WALLS 20090043104 Illinois Univ., Urbana, IL United States Microfabricated pressure and shear stress sensors Liu, Chang, Inventor; Chen, Jack, Inventor; Engel, Jonathan, Inventor; March 31, 2009; In English Contract(s)/Grant(s): NAG5-8781 Patent Info.: July 20, 2007US-Patent-7,509,869; US-Patent-Appl-SN-11/880,134 No Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090043104 A microfabricated pressure sensor. The pressure sensor comprises a raised diaphragm disposed on a substrate. The diaphragm is configured to bend in response to an applied pressure difference. A strain gauge of a conductive material is coupled to a surface of the raised diaphragm and to at least one of the substrate and a piece rigidly connected to the substrate. Official Gazette of the U.S. Patent and Trademark Office PRESSURE SENSORS; SHEAR STRESS; FABRICATION 20090043105 NASA, Washington, DC United States Method and associated apparatus for capturing, servicing, and de-orbiting earth satellites using robotics Cepollina, Frank J., Inventor; Burns, Richard D., Inventor; Holz, Jill M., Inventor; Corbo, James E., Inventor; Jedhrich, Nicholas M., Inventor; April 7, 2009; In English Patent Info.: February 2, 2007US-Patent-7,513,459; US-Patent-Appl-SN-11/670,653 No Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090043105 This invention is a method and supporting apparatus for autonomously capturing, servicing and de-orbiting a free-flying spacecraft, such as a satellite, using robotics. The capture of the spacecraft includes the steps of optically seeking and ranging the satellite using LIDAR, and matching tumble rates, rendezvousing and berthing with the satellite. Servicing of the spacecraft may be done using supervised autonomy, which is allowing a robot to execute a sequence of instructions without intervention from a remote human-occupied location. These instructions may be packaged at the remote station in a script and uplinked to the robot for execution upon remote command giving authority to proceed. Alternately, the instructions may be generated by Artificial Intelligence (AI) logic onboard the robot. In either case, the remote operator maintains the ability to abort an instruction or script at any time as well as the ability to intervene using manual override to teleoperate the robot. Official Gazette of the U.S. Patent and Trademark Office AUTONOMY; ROBOTICS; ARTIFICIAL INTELLIGENCE; EARTH ORBITS 20090043106 Boeing Co., Chicago, IL United States Risk assessment of metal vapor arcing Hill, Monika C., Inventor; Leidecker, Henning W., Inventor; August 18, 2009; In English Contract(s)/Grant(s): NAS9-20000 Patent Info.: May 21, 2007US-Patent-7,577,534; US-Patent-Appl-SN-11/751,195 No Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090043106 A method for assessing metal vapor arcing risk for a component is provided. The method comprises acquiring a current variable value associated with an operation of the component; comparing the current variable value with a threshold value for the variable; evaluating compared variable data to determine the metal vapor arcing risk in the component; and generating a risk assessment status for the component. Official Gazette of the U.S. Patent and Trademark Office METAL VAPORS; RISK ASSESSMENT 20090043107 California Inst. of Tech., Pasadena, CA United States Electro-active sensor, method for constructing the same; apparatus and circuitry for detection of electro-active species Buehler, Martin, Inventor; August 25, 2009; In English Contract(s)/Grant(s): NAS7-1407 Patent Info.: December 30, 2003US-Patent-7,578,912; US-Patent-Appl-SN-10/750,162 No Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090043107 An electro-active sensor includes a nonconductive platform with a first electrode set attached with a first side of a nonconductive platform. The first electrode set serves as an electrochemical cell that may be utilized to detect electro-active species in solution. A plurality of electrode sets and a variety of additional electrochemical cells and sensors may be attached with the nonconductive platform. The present invention also includes a method for constructing the aforementioned electro-active sensor. Additionally, an apparatus for detection and observation is disclosed, where the apparatus includes a sealable chamber for insertion of a portion of an electro-active sensor. The apparatus allows for monitoring and detection activities. Allowing for control of attached cells and sensors, a dual-mode circuitry is also disclosed. The dual-mode circuitry includes a switch, allowing the circuitry to be switched from a potentiostat to a galvanostat mode. Official Gazette of the U.S. Patent and Trademark Office DETECTION; ELECTROCHEMICAL CELLS; CIRCUITS; ELECTRODES 20090043108 University of Central Florida, Orlando, FL United States Catalytic dehydrogenation of amine borane complexes Mohajeri, Nahid, Inventor; Tabatabaie-Raissi, Ali, Inventor; Bokerman, Gary, Inventor; August 25, 2009; In English Contract(s)/Grant(s): NAG3-2751 Patent Info.: September 28, 2007US-Patent-7,578,992; US-Patent-Appl-SN-11/864,371 No Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090043108 A method of generating hydrogen includes the steps of providing an amine borane (AB) complex, at least one hydrogen generation catalyst, and a solvent, and mixing these components Hydrogen is generated. The hydrogen produced is high purity hydrogen suitable for PEM fuel cells. A hydrolytic in-situ hydrogen generator includes a first compartment that contains an amine borane (AB) complex, a second container including at least one hydrogen generation catalyst, wherein the first or second compartment includes water or other hydroxyl group containing solvent. A connecting network permits mixing contents in the first compartment with contents in the second compartment, wherein high purity hydrogen is generated upon mixing. At least one flow controller is provided for controlling a flow rate of the catalyst or AB complex. Official Gazette of the U.S. Patent and Trademark Office AMINES; BORANES; CATALYSTS; DEHYDROGENATION; CONTROLLERS 20090043111 General Electric Co., Schenectady, NY United States Coated silicon comprising material for protection against environmental corrosion Hazel, Brian Thomas, Inventor; August 25, 2009; In English Contract(s)/Grant(s): NAS3-01135 Patent Info.: August 19, 2005US-Patent-7,579,085; US-Patent-Appl-SN-11/208,245 No Copyright; Avail.: CASI: A02, Hardcopy Avail Online: http://hdl.handle.net/2060/20090043111 In accordance with an embodiment of the invention, an article is disclosed. The article comprises a gas turbine engine component substrate comprising a silicon material; and an environmental barrier coating overlying the substrate, wherein the environmental barrier coating comprises cerium oxide, and the cerium oxide reduces formation of silicate glass on the substrate upon exposure to corrodant sulfates. Official Gazette of the U.S. Patent and Trademark Office COATINGS; CORROSION PREVENTION; GAS TURBINE ENGINES; SILICON; PROTECTIVE COATINGS 20090043115 Case Western Reserve Univ., Cleveland, OH United States Wireless sensor platform for harsh environments Garverick, Steven L., Inventor; Yu, Xinyu, Inventor; Toygur, Lemi, Inventor; He, Yunli, Inventor; July 21, 2009; In English Contract(s)/Grant(s): NCA3-201; NCC3-1086 Patent Info.: September 29, 2006US-Patent-7,562,581; US-Patent-Appl-SN-11/537,488 No Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090043115 Reliable and efficient sensing becomes increasingly difficult in harsher environments. A sensing module for high-temperature conditions utilizes a digital, rather than analog, implementation on a wireless platform to achieve good quality data transmission. The module comprises a sensor, integrated circuit, and antenna. The integrated circuit includes an amplifier, A/D converter, decimation filter, and digital transmitter. To operate, an analog signal is received by the sensor, amplified by the amplifier, converted into a digital signal by the A/D converter, filtered by the decimation filter to address the quantization error, and output in digital format by the digital transmitter and antenna. Official Gazette of the U.S. Patent and Trademark Office WIRELESS COMMUNICATION; DETECTION; INTEGRATED CIRCUITS; TRANSMITTERS; DIGITAL SYSTEMS 20090043117 California Inst. of Tech., Pasadena, CA United States Apparatus and method for automated monitoring of airborne bacterial spores Ponce, Adrian, Inventor; July 21, 2009; In English Contract(s)/Grant(s): NAS7-1407 Patent Info.: April 14, 2006US-Patent-7,563,615; US-Patent-Appl-SN-11/404,382 No Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090043117 An apparatus and method for automated monitoring of airborne bacterial spores. The apparatus is provided with an air sampler, a surface for capturing airborne spores, a thermal lysis unit to release DPA from bacterial spores, a source of lanthanide ions, and a spectrometer for excitation and detection of the characteristic fluorescence of the aromatic molecules in bacterial spores complexed with lanthanide ions. In accordance with the method: computer-programmed steps allow for automation of the apparatus for the monitoring of airborne bacterial spores. Official Gazette of the U.S. Patent and Trademark Office BACTERIA; SPORES; AUTOMATIC CONTROL; AIR SAMPLING 20090043119 Ophir Corp., Littleton, CO United States Optical air data systems and methods Caldwell, Loren M., Inventor; Tang, Shoou-Yu, Inventor; O'Brien, Martin J., Inventor; July 21, 2009; In English Contract(s)/Grant(s): NAS4-02043 Patent Info.: July 17, 2006US-Patent-7,564,539; US-Patent-Appl-SN-11/488,259 No Copyright; Avail.: CASI: A03, Hardcopy Avail Online: http://hdl.handle.net/2060/20090043119 A method for remotely sensing air outside a moving aircraft includes generating laser radiation within a swept frequency range. A portion of the laser radiation is projected from the aircraft into the air to induce scattered laser radiation. Filtered scattered laser radiation, filtered laser radiation, and unfiltered laser radiation are detected. At least one actual ratio is determined from data corresponding to the filtered scattered laser radiation and the unfiltered laser radiation. One or more air parameters are d