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Additions to the NASA Aeronautics and Space Database as of 01/30/2009
20090004148 NASA Goddard Space Flight Center, Greenbelt, MD, United States
Annular and Total Solar Eclipses of 2010
Espenak, Fred; Anderson, J.; November 2008; In English; Original contains color and black and white illustrations
Report No.(s): NASA/TP-2008-214171; No Copyright; Avail.: CASI: A05, Hardcopy
Avail Online: http://hdl.handle.net/2060/20090004148
While most NASA eclipse bulletins cover a single eclipse, this publication presents predictions for two solar eclipses during 2010. This has required a different organization of the material into the following Eclipse Predictions: The section consists of a general discussion about the eclipse path maps, Besselian elements, shadow contacts, eclipse path tables, local circumstances tables, and the lunar limb profile. Solar Eclipse of 2010 Jan 15: The section covers predictions and weather prospects for the annular eclipse. Total Solar Eclipse of 2010 Jul 11: The section covers predictions and weather prospects for the total eclipse. provides information on eye safety, solar filters, eclipse photography, and making contact timings from the path limits. contains a number of resources including information on the IAU Working Group on Eclipses, the Solar Eclipse Mailing List, the NASA eclipse bulletins on the Internet, Web sites for the two 2010 eclipses, and a summary identifying the algorithms, ephemerides, predictions.
Derived from text
IDENTIFYING; SOLAR ECLIPSES; PREDICTIONS
20090004155 NASA Johnson Space Center, Houston, TX, United States
Air Quality Monitoring: Risk-Based Choices
James, John T.; Jan. 15, 2009; In English; NASA Human Health and Performance Technology, 15 Jan. 2009, Houston, TX, United States; Original contains color and black and white illustrations
No Copyright; Avail.: CASI: A03, Hardcopy
Avail Online: http://hdl.handle.net/2060/20090004155
Air monitoring is secondary to rigid control of risks to air quality. Air quality monitoring requires us to target the credible residual risks. Constraints on monitoring devices are severe. Must transition from archival to real-time, on-board monitoring. Must provide data to crew in a way that they can interpret findings. Dust management and monitoring may be a major concern for exploration class missions.
Author
AIR QUALITY; TARGETS; RISK; REAL TIME OPERATION
20090004160 NASA Johnson Space Center, Houston, TX, United States
Human Performance in Extreme Environments
Williams, Sunita; Fiedler, Edna R.; Harrison, Albert A.; [2008]; In English
Copyright; Avail.: CASI: A03, Hardcopy
Even on a bad day, looking down from orbit is a powerful and enjoyable experience, enhanced by the knowledge that time in orbit represents only a tiny fraction of one's life. You look down at Earth and you feel a sense of peace and solidarity. You look at the stars, and because they are not obscured by atmosphere, they are far more abundant than you realized, and they shine very bright. Later on you will reflect on this as one of life's greatest moments. Today astronauts and a few wealthy space tourists have been able to experience staying on the International Space Station. As representatives of humankind in space, astronauts have to get out there and tell people what it's like, and to encourage successive generations of children to consider careers in space. Perhaps the more people who can experience this view, the nicer we will all be to one another. Astronauts must speak authoritatively, without arrogance or a lack of humility. Each astronaut is an emissary who can share his or her experiences and educate people who will not have the opportunity to fly in space. This chapter is a part of that communication process.
Author
ASTRONAUTS; SPACE EXPLORATION; VISUAL OBSERVATION; COMMUNICATION
20090004167 NASA Johnson Space Center, Houston, TX, United States
Spaceflight Toxicology
Meyers, Valerie; December 12, 2008; In English; Original contains color illustrations
Copyright; Avail.: CASI: A02, Hardcopy
This viewgraph presentation provides a review of NASA Johnson Space Center's Toxicology program. The mission of this program is to protect crews from toxic exposures during spaceflight. The presentation reviews some of the health hazards. A toxicological hazard level chart is presented that reviews the rating of hazard level, irritancy, systemic effects and containability. The program also participates in the Lunar Airborne Dust Toxicity Advisory Group.
CASI
NASA SPACE PROGRAMS; SPACE FLIGHT; TOXICITY; TOXICOLOGY; TOXIC HAZARDS; HAZARDS
20090004168 NASA Goddard Space Flight Center, Greenbelt, MD, United States
In-Flight Anomalies and Radiation Performance of NASA Missions - Selected Lessons Learned
LaBel, Kenneth A.; November 30, 2008; In English; 4th International School in the Effects of Radiation on Embedded Systems for Space applicatoins (SERESSA), 30 Nov. - 5 Dec. 2008, West Palm Beach, FL, United States; Original contains color illustrations
No Copyright; Avail.: CASI: A03, Hardcopy
Avail Online: http://hdl.handle.net/2060/20090004168
This presentation addresses in-flight electronic disturbances and radiation, specifically anomaly resolution. The process for anomaly review takes into account the environment, selected parts and design, existing and/or new radiation test data, risk probability and actions to be taken. Noise spikes and the meaning of upset in a fiber optic link are also discussed.
Derived from text
NASA SPACE PROGRAMS; SPACECRAFT ELECTRONIC EQUIPMENT; EXTRATERRESTRIAL RADIATION; RADIATION TOLERANCE; LESSONS LEARNED; ASTRIONICS; FAILURE ANALYSIS
20090004193 NASA, Washington, DC, United States
Exploring the Unknown; Selected Documents in the History of the U.S. Civil Space Program Volume 7 Human Spaceflight: Projects Mercury, Gemini, and Apollo
Logsdon, John M., Editor; Launius, Roger D., Editor; 2008; In English; Original contains black and white illustrations
Report No.(s): NASA-SP-2008-4407; No Copyright; Avail.: CASI: A99, Hardcopy
Avail Online: http://hdl.handle.net/2060/20090004193
The extension of human activity into outer space has been accompanied by a high degree of self-awareness of its historical significance. Few large-scale activities have been as extensively chronicled so closely to the time they actually occurred. Many of those who were directly involved were quite conscious that they were making history, and they kept full records of their activities. Because most of the activity in outer space was carried out under government sponsorship, it was accompanied by the documentary record required of public institutions, and there has been a spate of official and privately written histories of most major aspects of space achievement to date. When top leaders considered what course of action to pursue in space, their deliberations and decisions often were carefully put on the record. There is, accordingly, no lack of material for those who aspire to understand the origins and evolution of U.S. space policies and programs.The documents selected for inclusion in this volume are presented in two chapters: one covering the Mercury and Gemini projects and another chapter covering Project Apollo. Each section in the present volume is introduced by an overview essay. In the main, these essays are intended to introduce and complement the documents in the section and to place them in a chronological and substantive context. Each essay contains references to the documents in the section it introduces, and also contains references to documents in other volumes in this series.
Derived from text
HISTORIES; MERCURY PROJECT; GEMINI PROJECT; DOCUMENTS; NASA SPACE PROGRAMS
20090004198 NASA Johnson Space Center, Houston, TX, United States
Spacecraft Water Monitoring: Adapting to an Era of Emerging Scientific Challenges
McCoy, J. Torin; [2009]; In English; NASA Human Health and Performances Technology Workshop, 15 Jan. 2009, Houston, TX, United States; Original contains color illustrations
No Copyright; Avail.: CASI: A03, Hardcopy
Avail Online: http://hdl.handle.net/2060/20090004198
This viewgraph presentation reviews spacecraft water monitoring, and the scientific challenges associated with spacecraft water quality. The contents include: 1) Spacecraft Water 101; 2) Paradigm Shift; and 3) Technology Needs.
CASI
WATER QUALITY; ENVIRONMENTAL TESTS; INTERNATIONAL SPACE STATION; SPACECRAFT ENVIRONMENTS
20090004212 Rice Univ., Houston, TX United States
Functionalized carbon nanotube-polymer composites and interactions with radiation
Barrera, Enrique V., Inventor; Wilkins, Richard, Inventor; Shofner, Meisha, Inventor; Pulikkathara, Merlyn X., Inventor; Vaidyanathan, Ranjii, Inventor; August 5, 2008; In English
Contract(s)/Grant(s): NAS2-02102NCC1-02038
Patent Info.: November 25, 2003US-Patent-7,407,640; US-Patent-Appl-SN-10/536,688
No Copyright; Avail.: CASI: A03, Hardcopy
Avail Online: http://hdl.handle.net/2060/20090004212
The present invention involves the interaction of radiation with functionalized carbon nanotubes that have been incorporated into various host materials, particularly polymeric ones. The present invention is directed to chemistries, methods, and apparatuses which exploit this type of radiation interaction, and to the materials which result from such interactions. The present invention is also directed toward the time dependent behavior of functionalized carbon nanotubes in such composite systems.
Official Gazette of the U.S. Patent and Trademark Office
CARBON NANOTUBES; TIME DEPENDENCE
20090004213
Dynamic refractometer
Curley, Michael J., Inventor; Sarkisov, Sergey S., Inventor; November 25, 2008; In English
Contract(s)/Grant(s): NAG8-1880
Patent Info.: October 17, 2006US-Patent-7,456,942; US-Patent-Appl-SN-11/582,625
No Copyright; Avail.: CASI: A03, Hardcopy
Avail Online: http://hdl.handle.net/2060/20090004213
A refractometer computer controls the rotation of a rotary plate upon which are mounted a prism optically coupled via an optical window to a spectroscopic cell holding a resin exhibiting a dynamic refractive index during photocuring. The computer system positions the prism and spectroscopic cell relative to a visible light laser which illuminates the prism-resin interface at selected incidence angles. A photodetector mounted on the plate generates a signal to the computer proportional to intensity of an internally reflected light beam. A curing light is selectively transmitted through the prism and into the photocurable resin. The refractometer determines the intensity of the internally reflected beam a selected incidence angles and determines the effective refractive index curve of the resin at an uncured state and, optionally, at a completely cured state. Next, an amount of uncured resin and selected optical components to be joined by the resin is placed in the spectroscopic cell and irradiated with the UV light. The refractometer is fixed at a selected incidence angle and measures the intensity of an internally reflected light beam of light throughout the cure cycle. The refractometer determines the resin's refractive index of the polymeric mixture by means of extrapolation of a horizontal shift in the effective refractive index curve of the resin from an uncured state to a selected point in the cure cycle.
Official Gazette of the U.S. Patent and Trademark Office
REFRACTOMETERS; ROTATION; OPTICAL EQUIPMENT; PRISMS; REFRACTIVITY
20090004214 NASA, Washington, DC United States
Variable area nozzle including a plurality of convexly vanes with a crowned contour, in a vane to vane sealing arrangement and with nonuniform lengths
Arnold, Steven M., Inventor; Penney, Nicholas, Inventor; December 2, 2008; In English
Patent Info.: October 23, 2003US-Patent-7,458,221; US-Patent-Appl-SN-10/693,850
No Copyright; Avail.: CASI: A03, Hardcopy
Avail Online: http://hdl.handle.net/2060/20090004214
A variable area nozzle comprising a concentric support and a plurality of convexly contoured self sealing vanes is disclosed and claimed. The vanes are circumferentially and rotatably mounted to the concentric support forming a nozzle infinitely positionable between a first position corresponding to a minimum area nozzle and a second position corresponding to a maximum area nozzle. A closer, which is preferably a shape memory alloy (SMA), urges the nozzle toward the first position corresponding to a minimum area nozzle. Periodically spaced openers act between adjacent vanes to urge the nozzle to a second position corresponding to a maximum area nozzle.
Official Gazette of the U.S. Patent and Trademark Office
VANES; CONTOURS; SELF SEALING; SHAPE MEMORY ALLOYS; NOZZLES
20090004215 Drexel Univ., Philadelphia, PA United States
Piezoelectric cantilever sensors
Shih, Wan Y., Inventor; Shih, Wei-Heng, Inventor; Shen, Zuyan, Inventor; December 2, 2008; In English
Contract(s)/Grant(s): NAG2-1475
Patent Info.: October 27, 2004US-Patent-7,458,265; US-Patent-Appl-SN-10/595,570
No Copyright; Avail.: CASI: A03, Hardcopy
Avail Online: http://hdl.handle.net/2060/20090004215
A piezoelectric cantilever with a non-piezoelectric, or piezoelectric tip useful as mass and viscosity sensors. The change in the cantilever mass can be accurately quantified by monitoring a resonance frequency shift of the cantilever. For bio-detection, antibodies or other specific receptors of target antigens may be immobilized on the cantilever surface, preferably on the non-piezoelectric tip. For chemical detection, high surface-area selective absorbent materials are coated on the cantilever tip. Binding of the target antigens or analytes to the cantilever surface increases the cantilever mass. Detection of target antigens or analytes is achieved by monitoring the cantilever's resonance frequency and determining the resonance frequency shift that is due to the mass of the adsorbed target antigens on the cantilever surface. The use of a piezoelectric unimorph cantilever allows both electrical actuation and electrical sensing. Incorporating a non-piezoelectric tip (14) enhances the sensitivity of the sensor. In addition, the piezoelectric cantilever can withstand damping in highly viscous liquids and can be used as a viscosity sensor in wide viscosity range.
Official Gazette of the U.S. Patent and Trademark Office
PIEZOELECTRICITY; LEVERS; RESONANT FREQUENCIES; DETECTION; LIQUIDS
20090004216 City Univ. of New York, NY United States
Cr.sup.3+-doped laser materials and lasers and methods of making and using
Alfano, Robert R., Inventor; Bykov, Alexey, Inventor; Petricevic, Vladimir, Inventor; Sharonov, Mikhail, Inventor; December 2, 2008; In English
Contract(s)/Grant(s): NCC1-03009
Patent Info.: January 24, 2006US-Patent-7,460,574; US-Patent-Appl-SN-11/338,341
No Copyright; Avail.: CASI: A03, Hardcopy
Avail Online: http://hdl.handle.net/2060/20090004216
A laser medium includes a single crystal of chromium-doped LiSc.sub.l-xIn.sub.xGe.sub.1-ySi.sub.yO.sub.4, where 0.ltoreq.x.ltoreq.1 and 0.ltoreq.y.ltoreq.1. Preferably, x and y are not both 0. A laser, such as a tunable near infrared laser, can contain the laser medium.
Official Gazette of the U.S. Patent and Trademark Office
TUNABLE LASERS; DOPED CRYSTALS; CHROMIUM; LASER MATERIALS; NEAR INFRARED RADIATION
20090004218 California Inst. of Tech., Pasadena, CA United States
System and method for suppressing sublimation using opacified aerogel
Sakamoto, Jeff S., Inventor; Snyder, G. Jeffrey, Inventor; Calliat, Thierry, Inventor; Fleurial, Jean-Pierre, Inventor; Jones, Steven M., Inventor; Palk, Jong-Ah, Inventor; December 9, 2008; In English
Patent Info.: October 29, 2004US-Patent-7,461,512; US-Patent-Appl-SN-10/977,276
No Copyright; Avail.: CASI: A03, Hardcopy
Avail Online: http://hdl.handle.net/2060/20090004218
The present invention relates to a castable, aerogel-based, ultra-low thermal conductivity opacified insulation to suppress sublimation. More specifically, the present invention relates to an aerogel opacified with various opacifying or reflecting constituents to suppress sublimation and provide thermal insulation in thermoelectric modules. The opacifying constituent can be graded within the aerogel for increased sublimation suppression, and the density of the aerogel can similarly be graded to achieve optimal thermal insulation and sublimation suppression.
Official Gazette of the U.S. Patent and Trademark Office
THERMAL INSULATION; OPACITY; SUBLIMATION; THERMAL CONDUCTIVITY; AEROGELS; MODULES
20090004219 NASA, Washington, DC United States
Advanced resistive exercise device
Raboin, Jasen L., Inventor; Niebuhr, Jason, Inventor; Cruz, Santana F., Inventor; Lamoreaux, Christopher D., Inventor; December 9, 2008; In English
Patent Info.: January 6, 2005US-Patent-7,462,141; US-Patent-Appl-SN-11/031,942
No Copyright; Avail.: CASI: A03, Hardcopy
Avail Online: http://hdl.handle.net/2060/20090004219
The present invention relates to an exercise device, which includes a vacuum cylinder and a flywheel. The flywheel provides an inertial component to the load, which is particularly well suited for use in space as it simulates exercising under normal gravity conditions. Also, the present invention relates to an exercise device, which has a vacuum cylinder and a load adjusting armbase assembly.
Official Gazette of the U.S. Patent and Trademark Office
PHYSICAL EXERCISE; LOADS (FORCES); FLYWHEELS; GRAVITATION
20090004220 NASA, Washington, DC United States
Analyzing nonstationary financial time series via hilbert-huang transform (HHT)
Huang, Norden E., Inventor; December 9, 2008; In English
Patent Info.: October 7, 2004US-Patent-7,464,006; US-Patent-Appl-SN-10/963,470
No Copyright; Avail.: CASI: A04, Hardcopy
Avail Online: http://hdl.handle.net/2060/20090004220
An apparatus, computer program product and method of analyzing non-stationary time varying phenomena. A representation of a non-stationary time varying phenomenon is recursively sifted using Empirical Mode Decomposition (EMD) to extract intrinsic mode functions (IMFs). The representation is filtered to extract intrinsic trends by combining a number of IMFs. The intrinsic trend is inherent in the data and identifies an IMF indicating the variability of the phenomena. The trend also may be used to detrend the data.
Official Gazette of the U.S. Patent and Trademark Office
HILBERT TRANSFORMATION; TIME SERIES ANALYSIS; COMPUTER PROGRAMS; EXTRACTION
20090004221 Boeing Co., Chicago, IL United States
Folding retractable protective dome for space vehicle equipment
Clark, Paul R., Inventor; Messinger, Ross H., Inventor; December 16, 2008; In English
Contract(s)/Grant(s): NAS8-01099
Patent Info.: October 20, 2004US-Patent-7,464,900; US-Patent-Appl-SN-10/970,472
No Copyright; Avail.: CASI: A03, Hardcopy
Avail Online: http://hdl.handle.net/2060/20090004221
A folding, retractable dome for protecting a feature, such as a docking mechanism, a hatch or other equipment at an exterior surface of a space vehicle, includes a plurality of arcuate ribs, each having opposite ends respectively pinioned at opposite sides of the feature at the surface of the vehicle for rotational movement about an axis of rotation extending through the opposite ends and through an arcuate path of revolution extending over the feature, and a flexible cover attached to each of the ribs such that, in a deployed configuration of the dome, in which adjacent ribs are rotated apart from each other at a maximum relative angle therebetween, the cover is stretched generally tangentially between the adjacent ribs to form a generally arcuate shield over the feature, and in a retracted position of the dome, in which adjacent ribs are rotated together at a minimum relative angle therebetween, the cover is collapsed to define folded pleats between the adjacent ribs.
Official Gazette of the U.S. Patent and Trademark Office
RETRACTABLE EQUIPMENT; SURFACE VEHICLES; HATCHES; DOCKING; FOLDING
20090004222 Massachusetts Inst. of Tech., Cambridge, MA United States
Nanocomposites with high thermoelectric figures of merit
Chen, Gang, Inventor; Ren, Zhifeng, Inventor; Dresselhaus, Mildred, Inventor; December 16, 2008; In English
Contract(s)/Grant(s): NAS3-03108
Patent Info.: October 29, 2004US-Patent-7,465,871; US-Patent-Appl-SN-10/977,363
No Copyright; Avail.: CASI: A03, Hardcopy
Avail Online: http://hdl.handle.net/2060/20090004222
The present invention is generally directed to nanocomposite thermoelectric materials that exhibit enhanced thermoelectric properties. The nanocomposite materials include two or more components, with at least one of the components forming nano-sized structures within the composite material. The components are chosen such that thermal conductivity of the composite is decreased without substantially diminishing the composite's electrical conductivity. Suitable component materials exhibit similar electronic band structures. For example, a band-edge gap between at least one of a conduction band or a valence band of one component material and a corresponding band of the other component material at interfaces between the components can be less than about 5k.sub.BT, wherein k.sub.B is the Boltzman constant and T is an average temperature of said nanocomposite composition.
Official Gazette of the U.S. Patent and Trademark Office
THERMOELECTRICITY; THERMOELECTRIC MATERIALS; COMPOSITE MATERIALS; ENERGY GAPS (SOLID STATE); NANOCOMPOSITES
20090004223 NASA, Washington, DC United States
Device system and method for miniaturized radiation spectrometer
Stassinopoulos, Epaminondas G., Inventor; December 16, 2008; In English
Patent Info.: September 29, 2006US-Patent-7,465,926; US-Patent-Appl-SN-11/537,280
No Copyright; Avail.: CASI: A02, Hardcopy
Avail Online: http://hdl.handle.net/2060/20090004223
A device/system for radiation sensing is configured to detect high and low LET radiation. The radiation sensing system may include a high LET detector and a low LET detector coupled to the high LET detector by a CPU, wherein the high LET detector and the low LET detector are assembled within a single unit. The device/system may also include a high LET and low LET detector that may be coupled together without an internal CPU. Overall, the device/system may be a stand-alone system and/or coupled to an external processing device. The device/system may also be approximately 6.times.6.times.2 cm.sup.3 in size, making it hand portable and may weigh less or equal to approximately ninety (90) grams, and operate on less than or approximately 0.25 watts of power.
Official Gazette of the U.S. Patent and Trademark Office
RADIATION DETECTORS; MINIATURIZATION; SPECTROMETERS; DETECTION
20090004224 Nebraska Univ., Omaha, NE United States
Digital X-ray camera for quality evaluation three-dimensional topographic reconstruction of single crystals of biological macromolecules
Borgstahl, Gloria, Inventor; Lovelace, Jeff, Inventor; Snell, Edward Holmes, Inventor; Bellamy, Henry, Inventor; December 16, 2008; In English
Contract(s)/Grant(s): NAG8-1825
Patent Info.: April 5, 2006US-Patent-7,466,798; US-Patent-Appl-SN-11/278,738
No Copyright; Avail.: CASI: A02, Hardcopy
Avail Online: http://hdl.handle.net/2060/20090004224
The present invention provides a digital topography imaging system for determining the crystalline structure of a biological macromolecule, wherein the system employs a charge coupled device (CCD) camera with antiblooming circuitry to directly convert x-ray signals to electrical signals without the use of phosphor and measures reflection profiles from the x-ray emitting source after x-rays are passed through a sample. Methods for using said system are also provided.
Official Gazette of the U.S. Patent and Trademark Office
DIGITAL CAMERAS; SINGLE CRYSTALS; CHARGE COUPLED DEVICES; CCD CAMERAS; IMAGING TECHNIQUES; TOPOGRAPHY
20090004225 NASA, Washington, DC United States
Positioning system for single or multi-axis sensitive instrument calibration and calibration system for use therewith
Finley, Tom D., Inventor; Parker, Peter A., Inventor; December 23, 2008; In English
Patent Info.: June 30, 2006US-Patent-7,467,536; US-Patent-Appl-SN-11/428,017
No Copyright; Avail.: CASI: A03, Hardcopy
Avail Online: http://hdl.handle.net/2060/20090004225
A positioning and calibration system are provided for use in calibrating a single or multi axis sensitive instrument, such as an inclinometer. The positioning system includes a positioner that defines six planes of tangential contact. A mounting region within the six planes is adapted to have an inclinometer coupled thereto. The positioning system also includes means for defining first and second flat surfaces that are approximately perpendicular to one another with the first surface adapted to be oriented relative to a local or induced reference field of interest to the instrument being calibrated, such as a gravitational vector. The positioner is positioned such that one of its six planes tangentially rests on the first flat surface and another of its six planes tangentially contacts the second flat surface. A calibration system is formed when the positioning system is used with a data collector and processor.
Official Gazette of the U.S. Patent and Trademark Office
POSITIONING; CALIBRATING; FLAT SURFACES; ACCUMULATORS; DATA PROCESSING EQUIPMENT
Additions to the NASA Aeronautics and Space Database as of 02/02/2009
20090004415 Maryland Univ., College Park, MD, United States
Interim Report on Heuristics about Inspection Parameters: Updates to Heuristics Resulting from Refinement on Projects
Shull, Forrest; Seaman, Carolyn; Feldman, Raimund; Haingaertner, Ralf; Regardie, Myrna; September 30, 2008; In English; Original contains color and black and white illustrations
Contract(s)/Grant(s): NNG05GE77G
Copyright; Avail.: CASI: A04, Hardcopy
In 2008, we have continued analyzing the inspection data in an effort to better understand the applicability and effect of the inspection heuristics on inspection outcomes. Our research goals during this period are: 1. Investigate the effect of anomalies in the dataset (e.g. the very large meeting length values for some inspections) on our results 2. Investigate the effect of the heuristics on other inspection outcome variables (e.g. effort) 3. Investigate whether the recommended ranges can be modified to give inspection planners more flexibility without sacrificing effectiveness 4. Investigate possible refinements or modifications to the heuristics for specific subdomains (partitioned, e.g., by size, domain, or Center) This memo reports our results to date towards addressing these goals. In the next section, the first goal is addressed by describing the types of anomalies we have found in our dataset, how we have addressed them, and the effect of these changes on our previously reported results. In the following section, on "methodology", we describe the analyses we have conducted to address the other three goals and the results of these analyses are described in the "results" section. Finally, we conclude with future plans for continuing our investigation.
Author
HEURISTIC METHODS; INSPECTION; DEFECTS
20090004416 NASA Stennis Space Center, Stennis Space Center, MS, United States
Land-use and Land-cover Change from 1974 to 2008 around Mobile Bay
Ellis, Jean; Spruce, Joseph; Smoot, James; Hilbert, Kent; Swann, Roberta; October 28, 2008; In English; Mississippi-Alabama Bays and Bayous Symposium 2008, 28-29 Oct. 2008, Biloxi, MS, United States; Original contains color illustrations
Report No.(s): SSTI-2220-0173; Copyright; Avail.: CASI: A01, Hardcopy
This project is a Gulf of Mexico Application Pilot in which NASA Stennis Space Center (SSC) is working within a regional collaboration network of the Gulf of Mexico Alliance. NASA researchers, with support from the NASA SSC Applied Science Program Steering Committee, employed multi-temporal Landsat data to assess land-use and land-cover (LULC) changes in the coastal counties of Mobile and Baldwin, AL, between 1974 and 2008. A multi-decadal time-series, coastal LULC product unique to NASA SSC was produced. The geographic extent and nature of change was quantified for the open water, barren, upland herbaceous, non-woody wetland, upland forest, woody wetland, and urban landscapes. The National Oceanic and Atmospheric Administration (NOAA) National Coastal Development Data Center (NCDDC) will assist with the transition of the final product to the operational end user, which primarily is the Mobile Bay National Estuary Program (MBNEP). We found substantial LULC change over the 34-year study period, much more than is evident when the change occurring in the last years. Between 1974 and 2008, the upland forest landscape lost almost 6% of the total acreage, while urban land cover increased by slightly more than 3%. With exception to open water, upland forest is the dominant landscape, accounting for about 25-30% of the total area.
Author
LAND USE; TOPOGRAPHY; TERRAIN; PERIODIC VARIATIONS; GULF OF MEXICO; SATELLITE IMAGERY; LANDSAT SATELLITES
20090004419 NASA Glenn Research Center, Cleveland, OH, United States
Spray Chemical Vapor Deposition of Single-Source Precursors for Chalcopyrite I-III-VI2 Thin-Film Materials
Hepp, Aloysius F.; Banger, Kulbinder K.; Jin, Michael H.-C.; Harris, Jerry D.; McNatt, Jeremiah S.; Dickman, John E.; November 2008; In English; Original contains black and white illustrations
Contract(s)/Grant(s): NNC04AA71A; NCC3-947WBS 953033.01.03.23
Report No.(s): NASA/TP-2008-214937; E-16162-1; Copyright; Avail.: CASI: A03, Hardcopy
Thin-film solar cells on flexible, lightweight, space-qualified substrates provide an attractive approach to fabricating solar arrays with high mass-specific power. A polycrystalline chalcopyrite absorber layer is among the new generation of photovoltaic device technologies for thin film solar cells. At NASA Glenn Research Center we have focused on the development of new single-source precursors (SSPs) for deposition of semiconducting chalcopyrite materials onto lightweight, flexible substrates. We describe the syntheses and thermal modulation of SSPs via molecular engineering. Copper indium disulfide and related thin-film materials were deposited via aerosol-assisted chemical vapor deposition using SSPs. Processing and post-processing parameters were varied in order to modify morphology, stoichiometry, crystallography, electrical properties, and optical properties to optimize device quality. Growth at atmospheric pressure in a horizontal hotwall reactor at 395 C yielded the best device films. Placing the susceptor closer to the evaporation zone and flowing a more precursor-rich carrier gas through the reactor yielded shinier-, smoother-, and denser-looking films. Growth of (112)-oriented films yielded more Cu-rich films with fewer secondary phases than growth of (204)/(220)-oriented films. Post-deposition sulfur-vapor annealing enhanced stoichiometry and crystallinity of the films. Photoluminescence studies revealed four major emission bands and a broad band associated with deep defects. The highest device efficiency for an aerosol-assisted chemical vapor deposited cell was one percent.
Author
VAPOR DEPOSITION; THIN FILMS; SOLAR CELLS; SULFUR; DISULFIDES; PHOTOLUMINESCENCE
20090004420 NASA Glenn Research Center, Cleveland, OH, United States
Structural Benchmark Creep Testing for the Advanced Stirling Convertor Heater Head
Krause, David L.; Kalluri, Sreeramesh; Bowman, Randy R.; Shah, Ashwin R.; November 2008; In English; Sixth International Energy Conversion Engineering Conference (IECEC), 28-30 Jul. 2008, Cleveland, OH, United States; Original contains color and black and white illustrations
Contract(s)/Grant(s): WBS 138494.04.01.01
Report No.(s): NASA/TM-2008-215435; AIAA-2008-5774; Copyright; Avail.: CASI: A03, Hardcopy
The National Aeronautics and Space Administration (NASA) has identified the high efficiency Advanced Stirling Radioisotope Generator (ASRG) as a candidate power source for use on long duration Science missions such as lunar applications, Mars rovers, and deep space missions. For the inherent long life times required, a structurally significant design limit for the heater head component of the ASRG Advanced Stirling Convertor (ASC) is creep deformation induced at low stress levels and high temperatures. Demonstrating proof of adequate margins on creep deformation and rupture for the operating conditions and the MarM-247 material of construction is a challenge that the NASA Glenn Research Center is addressing. The combined analytical and experimental program ensures integrity and high reliability of the heater head for its 17-year design life. The life assessment approach starts with an extensive series of uniaxial creep tests on thin MarM-247 specimens that comprise the same chemistry, microstructure, and heat treatment processing as the heater head itself. This effort addresses a scarcity of openly available creep properties for the material as well as for the virtual absence of understanding of the effect on creep properties due to very thin walls, fine grains, low stress levels, and high-temperature fabrication steps. The approach continues with a considerable analytical effort, both deterministically to evaluate the median creep life using nonlinear finite element analysis, and probabilistically to calculate the heater head s reliability to a higher degree. Finally, the approach includes a substantial structural benchmark creep testing activity to calibrate and validate the analytical work. This last element provides high fidelity testing of prototypical heater head test articles; the testing includes the relevant material issues and the essential multiaxial stress state, and applies prototypical and accelerated temperature profiles for timely results in a highly controlled laboratory environment. This paper focuses on the last element and presents a preliminary methodology for creep rate prediction, the experimental methods, test challenges, and results from benchmark testing of a trial MarM-247 heater head test article. The results compare favorably with the analytical strain predictions. A description of other test findings is provided, and recommendations for future test procedures are suggested. The manuscript concludes with describing the potential impact of the heater head creep life assessment and benchmark testing effort on the ASC program.
Author
STIRLING CYCLE; CREEP PROPERTIES; DEFORMATION; CREEP RUPTURE STRENGTH; STEADY STATE CREEP; STRAIN RATE; LIFE (DURABILITY); HEAT TREATMENT; HEAT RESISTANT ALLOYS
20090004421 NASA Glenn Research Center, Cleveland, OH, United States
Assuring Life in Composite Systems
Chamis, Christos c.; November 2008; In English; Original contains black and white illustrations
Contract(s)/Grant(s): WBS 561581.02.10.03.23
Report No.(s): NASA/TM-2008-215452; E-16526-1; No Copyright; Avail.: CASI: A03, Hardcopy
Avail Online: http://hdl.handle.net/2060/20090004421
A computational simulation method is presented to assure life in composite systems by using dynamic buckling of smart composite shells as an example. The combined use of composite mechanics, finite element computer codes, and probabilistic analysis enable the effective assessment of the dynamic buckling load of smart composite shells. A universal plot is generated to estimate the dynamic buckling load of composite shells at various load rates and probabilities. The shell structure is also evaluated with smart fibers embedded in the plies right below the outer plies. The results show that, on the average, the use of smart fibers improved the shell buckling resistance by about 9% at different probabilities and delayed the buckling occurrence time. The probabilistic sensitivities results indicate that uncertainties in the fiber volume ratio and ply thickness have major effects on the buckling load. The uncertainties in the electric field strength and smart material volume fraction have moderate effects and thereby in the assured life of the shell.
Author
COMPOSITE MATERIALS; BUCKLING; PROBABILITY THEORY; SHELLS (STRUCTURAL FORMS); DYNAMIC LOADS; COMPOSITE STRUCTURES; LOADS (FORCES)
20090004422 Cleveland State Univ., Cleveland, OH, United States
Effect of Adding a Regenerator to Kornhauser's MIT "Two-Space" (Gas-Spring+Heat Exchanger) Test Rig
Ebiana, Asuquo B.; Gidugu, Praveen; November 2008; In English; Sixth International Energy Conversion Engineering Conference (IECEC), 28-30 Jul. 2008, Cleveland, OH, United States; Original contains color and black and white illustrations
Contract(s)/Grant(s): NNC05AA24AWBS 138494.04.01.01
Report No.(s): NASA/CR-2008-215480; AIAA-2008-5718; E-16657; Copyright; Avail.: CASI: A04, Hardcopy
This study employed entropy-based second law post-processing analysis to characterize the various thermodynamic losses inside a 3-space solution domain (gas spring+heat exchanger+regenerator) operating under conditions of oscillating pressure and oscillating flow. The 3- space solution domain is adapted from the 2-space solution domain (gas spring+heat exchanger) in Kornhauser's MIT test rig by modifying the heat exchanger space to include a porous regenerator system. A thermal nonequilibrium model which assumes that the regenerator porous matrix and gas average temperatures can differ by several degrees at a given axial location and time during the cycle is employed. An important and primary objective of this study is the development and application of a thermodynamic loss post-processor to characterize the major thermodynamic losses inside the 3-space model. It is anticipated that the experience gained from thermodynamic loss analysis of the simple 3-space model can be extrapolated to more complex systems like the Stirling engine. It is hoped that successful development of loss post-processors will facilitate the improvement of the optimization capability of Stirling engine analysis codes through better understanding of the heat transfer and power losses. It is also anticipated that the incorporation of a successful thermal nonequilibrium model of the regenerator in Stirling engine CFD analysis codes, will improve our ability to accurately model Stirling regenerators relative to current multidimensional thermal-equilibrium porous media models.
Author
COMPUTATIONAL FLUID DYNAMICS; GAS EXCHANGE; HEAT EXCHANGERS; STIRLING ENGINES; THERMODYNAMIC EQUILIBRIUM; POSITION (LOCATION); OSCILLATING FLOW; HEAT TRANSFER; REGENERATORS
20090004439 NASA Glenn Research Center, Cleveland, OH, United States
Progress in NASA Rotorcraft Propulsion
DellaCorte, Christopher; Johnson, Susan M.; October 10, 2008; In English; Fundamental Aeronautics Meeting 2008, 7-9 Oct. 2008, Atlanta, GA, United States; Original contains color and black and white illustrations
Contract(s)/Grant(s): WBS 877868.02.07.03.01.01
Report No.(s): E-16832; No Copyright; Avail.: CASI: A03, Hardcopy
Avail Online: http://hdl.handle.net/2060/20090004439
This presentation reviews recent progress made under NASA s Subsonic Rotary Wing (SRW) propulsion research activities. Advances in engines, drive systems and optimized propulsion systems are discussed. Progress in wide operability compressors, modeling of variable geometry turbine performance, foil gas bearings and multi-speed transmissions are presented.
Author
ROTARY WING AIRCRAFT; PROPULSION SYSTEM PERFORMANCE; PROPULSION SYSTEM CONFIGURATIONS; GAS BEARINGS; PERFORMANCE PREDICTION
20090004441 NASA Glenn Research Center, Cleveland, OH, United States
Evaluation of Recent Upgrades to the NESS (Nuclear Engine System Simulation) Code
Fittje, James E.; Schnitzler, Bruce G.; July 21, 2008; In English; 44th AIAA Joint Propulsion Conference, 21-23 Jul. 2008, Hartford, CT, United States; Original contains color and black and white illustrations
Contract(s)/Grant(s): NNC06BA07B
Report No.(s): E-16836; Copyright; Avail.: CASI: A03, Hardcopy
The Nuclear Thermal Rocket (NTR) concept is being evaluated as a potential propulsion technology for exploratory expeditions to the moon, Mars, and beyond. The need for exceptional propulsion system performance in these missions has been documented in numerous studies, and was the primary focus of a considerable effort undertaken during the Rover/NERVA program from 1955 to 1973. The NASA Glenn Research Center is leveraging this past NTR investment in their vehicle concepts and mission analysis studies with the aid of the Nuclear Engine System Simulation (NESS) code. This paper presents the additional capabilities and upgrades made to this code in order to perform higher fidelity NTR propulsion system analysis and design, and a comparison of its results to the Small Nuclear Rocket Engine (SNRE) design.
Author
PROPULSION SYSTEM PERFORMANCE; NUCLEAR ENGINE FOR ROCKET VEHICLES; COMPUTERIZED SIMULATION; SYSTEMS ANALYSIS; ROCKET ENGINE DESIGN; NUCLEAR ROCKET ENGINES
20090004444 NASA Langley Research Center, Hampton, VA, United States
Towards Verification of Unstructured-Grid Solvers
Thomas, James L.; Diskin, Boris; Rumsey, Christopher L.; December 2008; In English; Original contains color and black and white illustrations
Contract(s)/Grant(s): WBS 599489
Copyright; Avail.: CASI: A03, Hardcopy
New methodology for verification of finite-volume computational methods using unstructured grids is presented. The discretization order properties are studied in computational windows, easily constructed within a collection of grids or a single grid. Tests are performed within each window and address a combination of problem-, solution-, and discretization/grid-related features affecting discretization error convergence. The windows can be adjusted to isolate particular elements of the computational scheme, such as the interior discretization, the boundary discretization, or singularities. Studies can use traditional grid-refinement computations within a fixed window or downscaling, a recently-introduced technique in which computations are made within windows contracting toward a focal point of interest. Grids within the windows are constrained to be consistently refined, allowing a meaningful assessment of asymptotic error convergence on unstructured grids. Demonstrations of the method are shown, including a comparative accuracy assessment of commonly-used schemes on general mixed grids and the identification of local accuracy deterioration at boundary intersections. Recommendations to enable attainment of design-order discretization errors for large-scale computational simulations are given.
Author
UNSTRUCTURED GRIDS (MATHEMATICS); FINITE VOLUME METHOD; CONVERGENCE; DETERIORATION
20090004445 NASA Langley Research Center, Hampton, VA, United States
Entry, Descent, and Landing Operations Analysis for the Stardust Entry Capsule
Desai, Prasun N.; Lyons, Dan T.; Tooley, Jeff; Kangas, Julie; [2008]; In English; Original contains color and black and white illustrations
No Copyright; Avail.: CASI: A03, Hardcopy
Avail Online: http://hdl.handle.net/2060/20090004445
On the morning of January 15, 2006, the Stardust capsule successfully landed at the Utah Test and Training range in northwest Utah returning cometary samples from the comet Wild-2. An overview of the entry, descent, and landing (EDL) trajectory analysis that was performed for targeting during the mission operations phase upon final approach to Earth is described. The final orbit determination solution produced an inertial entry flight-path angle of -8.21 deg (the desired nominal value) with a 3-sigma uncertainty of +/-0.0017 deg (2% of the requirement). The navigation and EDL operations effort accurately delivered the entry capsule to the desired landing site. The final landing location was 8.1 km from the target, which was well within the allowable landing area. Overall, the Earth approach operation procedures worked well and there were no issues (logistically or performance based) that arose. As a result, the process of targeting a capsule from an interplanetary trajectory and accurately landing it on Earth was successfully demonstrated.
Author
STARDUST MISSION; DESCENT TRAJECTORIES; FLIGHT PATHS; LANDING SITES; TRAJECTORY ANALYSIS; INTERPLANETARY TRAJECTORIES; ORBIT DETERMINATION
20090004446 NASA Langley Research Center, Hampton, VA, United States
Kinetic Temperature and Carbon Dioxide from Broadband Infrared Limb Emission Measurements Taken from the TIMED/SABER Instrument
Mertens, Christopher J.; Russell III, James M.; Mlynczak, Martin G.; She, Chiao-Yao; Schmidlin, Francis J.; Goldberg, Richard A.; Lopez-Puertas, Manuel; Wintersteiner, Peter P.; Picard, Richard H.; Winick, Jeremy R.; Xu, Xiaojing; [2008]; In English; Original contains color illustrations
Copyright; Avail.: CASI: A03, Hardcopy
The Sounding of the Atmosphere using Broadband Emission Radiometry (SABER) experiment is one of four instruments on NASA's Thermosphere-Ionosphere-Energetics and Dynamics (TIMED) satellite. SABER measures broadband infrared limb emission and derives vertical profiles of kinetic temperature (Tk) from the lower stratosphere to approximately 120 km, and vertical profiles of carbon dioxide (CO2) volume mixing ratio (vmr) from approximately 70 km to 120 km. In this paper we report on SABER Tk/CO2 data in the mesosphere and lower thermosphere (MLT) region from the version 1.06 dataset. The continuous SABER measurements provide an excellent dataset to understand the evolution and mechanisms responsible for the global two-level structure of the mesopause altitude. SABER MLT Tk comparisons with ground-based sodium lidar and rocket falling sphere Tk measurements are generally in good agreement. However, SABER CO2 data differs significantly from TIME-GCM model simulations. Indirect CO2 validation through SABER-lidar MLT Tk comparisons and SABER-radiation transfer comparisons of nighttime 4.3 micron limb emission suggest the SABER-derived CO2 data is a better representation of the true atmospheric MLT CO2 abundance compared to model simulations of CO2 vmr.
Author
CARBON DIOXIDE CONCENTRATION; BROADBAND; INFRARED RADIATION; ATMOSPHERIC COMPOSITION; OPTICAL RADAR; RADIATIVE TRANSFER; MIXING RATIOS
20090004448 NASA Langley Research Center, Hampton, VA, United States
Overview of NASA's Integrated Design and Engineering Analysis (IDEA)Environment
Robinson, Jeffrey S.; Martin John G.; December 08, 2008; In English; JANNAF 6th Modeling and Simulation Subcommittee Meeting, 8-12 Dec. 2008, Orlando, FL, United States; Original contains color illustrations
Contract(s)/Grant(s): WBS 599489.02.07.07.09
No Copyright; Avail.: CASI: A03, Hardcopy
Avail Online: http://hdl.handle.net/2060/20090004448
Historically, the design of subsonic and supersonic aircraft has been divided into separate technical disciplines (such as propulsion, aerodynamics and structures) each of which performs their design and analysis in relative isolation from others. This is possible in most cases either because the amount of interdisciplinary coupling is minimal or because the interactions can be treated as linear. The design of hypersonic airbreathing vehicles, like NASA s X-43, is quite the opposite. Such systems are dominated by strong non-linear interactions between disciplines. The design of these systems demands that a multi-disciplinary approach be taken. Furthermore, increased analytical fidelity at the conceptual design phase is highly desirable as many of the non-linearities are not captured by lower fidelity tools. Only when these systems are designed from a true multi-disciplinary perspective can the real performance benefits be achieved and complete vehicle systems be fielded. Toward this end, the Vehicle Analysis Branch at NASA Langley Research Center has been developing the Integrated Design & Engineering Analysis (IDEA) Environment. IDEA is a collaborative environment for parametrically modeling conceptual and preliminary launch vehicle configurations using the Adaptive Modeling Language (AML) as the underlying framework. The environment integrates geometry, configuration, propulsion, aerodynamics, aerothermodynamics, trajectory, closure and structural analysis into a generative, parametric, unified computational model where data is shared seamlessly between the different disciplines. Plans are also in place to incorporate life cycle analysis tools into the environment which will estimate vehicle operability, reliability and cost. IDEA is currently being funded by NASA s Hypersonics Project, a part of the Fundamental Aeronautics Program within the Aeronautics Research Mission Directorate. The environment is currently focused around a two-stage-to-orbit configuration with a turbine based combined cycle (TBCC) first stage and reusable rocket second stage. This paper provides an overview of the development of the IDEA environment, a description of the current status and detail of future plans.
Author
AERODYNAMIC CONFIGURATIONS; LAUNCH VEHICLE CONFIGURATIONS; DESIGN ANALYSIS; STRUCTURAL ANALYSIS; TRAJECTORY ANALYSIS; HYPERSONIC VEHICLES; AEROTHERMODYNAMICS
20090004463 NASA Marshall Space Flight Center, Huntsville, AL, United States
The NASA MSFC Earth Global Reference Atmospheric Model-2007 Version
Leslie, F.W.; Justus, C.G.; November 2008; In English; Original contains color and black and white illustrations
Contract(s)/Grant(s): NNM04AA02C
Report No.(s): NASA/TM--2008-215581; M-1246; Copyright; Avail.: CASI: A06, Hardcopy
Reference or standard atmospheric models have long been used for design and mission planning of various aerospace systems. The NASA/Marshall Space Flight Center (MSFC) Global Reference Atmospheric Model (GRAM) was developed in response to the need for a design reference atmosphere that provides complete global geographical variability, and complete altitude coverage (surface to orbital altitudes) as well as complete seasonal and monthly variability of the thermodynamic variables and wind components. A unique feature of GRAM is that, addition to providing the geographical, height, and monthly variation of the mean atmospheric state, it includes the ability to simulate spatial and temporal perturbations in these atmospheric parameters (e.g. fluctuations due to turbulence and other atmospheric perturbation phenomena). A summary comparing GRAM features to characteristics and features of other reference or standard atmospheric models, can be found Guide to Reference and Standard Atmosphere Models. The original GRAM has undergone a series of improvements over the years with recent additions and changes. The software program is called Earth-GRAM2007 to distinguish it from similar programs for other bodies (e.g. Mars, Venus, Neptune, and Titan). However, in order to make this Technical Memorandum (TM) more readable, the software will be referred to simply as GRAM07 or GRAM unless additional clarity is needed. Section 1 provides an overview of the basic features of GRAM07 including the newly added features. Section 2 provides a more detailed description of GRAM07 and how the model output generated. Section 3 presents sample results. Appendices A and B describe the Global Upper Air Climatic Atlas (GUACA) data and the Global Gridded Air Statistics (GGUAS) database. Appendix C provides instructions for compiling and running GRAM07. Appendix D gives a description of the required NAMELIST format input. Appendix E gives sample output. Appendix F provides a list of available parameters to enable the user to generate special output. Appendix G gives an example and guidance on incorporating GRAM07 as a subroutine in other programs such as trajectory codes or orbital propagation routines.
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ATMOSPHERIC MODELS; MISSION PLANNING; NASA SPACE PROGRAMS; EARTH SCIENCES; AEROSPACE SYSTEMS; GEOPHYSICS; CLIMATOLOGY
Additions to the NASA Aeronautics and Space Database as of 02/03/2009
20090004512 NASA Marshall Space Flight Center, Huntsville, AL, United States
NASA Ares I Crew Launch Vehicle Upper Stage Overview
Davusm Daniel J.; McArthur, J. Craig; July 20, 2008; In English; 44th AIAA/ASME/SAE/ASEE Joint Propulsion Conference, 20-23 Jul. 2008, Hartford,CT, United States; Original contains color illustrations
Report No.(s): MSFC-1038; No Copyright; Avail.: CASI: A02, Hardcopy
Avail Online: http://hdl.handle.net/2060/20090004512
By incorporating rigorous engineering practices, innovative manufacturing processes and test techniques, a unique multi-center government/contractor partnership, and a clean-sheet design developed around the primary requirements for the International Space Station (ISS) and Lunar missions, the Upper Stage Element of NASA's Crew Launch Vehicle (CLV), the "Ares I," is a vital part of the Constellation Program's transportation system.
Author
CONSTELLATION PROGRAM; UPPER STAGE ROCKET ENGINES; SPACECRAFT CONFIGURATIONS; ARES 1 UPPER STAGE
20090004513 NASA Goddard Space Flight Center, Greenbelt, MD, United States
Optical Images of an Exosolar Planet 25 Light Years from Earth
Kalas, Paul; Graham, James R.; Chiang, Eugene; Fitzgerald, Michael P.; Clampin, Mark; Kite, Edwin S.; Stapelfeldt, Karl; Marois, Christian; Krist, John; November 19, 2008; In English; Original contains color and black and white illustrations
Copyright; Avail.: CASI: A03, Hardcopy
Fomalhaut is a bright star 7.7 parsecs (25 light years) from Earth that harbors a belt of cold dust with a structure consistent with gravitational sculpting by an orbiting planet. Here, we present optical observations of an exoplanet candidate, Fomalhaut b. In the plane of the belt, Fomalhaut b lies approximately 119 astronomical units (AU) from the star and 18 AU from the dust belt, matching predictions. We detect counterclockwise orbital motion using Hubble Space Telescope observations separated by 1.73 years. Dynamical models of the interaction between the planet and the belt indicate that the planet's mass is at most three times that of Jupiter for the belt to avoid gravitational disruption. The flux detected at 0.8 m is also consistent with that of a planet with mass no greater than a few times that of Jupiter. The brightness at 0.6 micron and the lack of detection at longer wavelengths suggest that the detected flux may include starlight reflected off a circumplanetary disk, with dimension comparable to the orbits of the Galilean satellites. We also observed variability of unknown origin at 0.6 micron.
Author
EXTRASOLAR PLANETS; VISUAL OBSERVATION; GAS GIANT PLANETS; PLANET DETECTION
20090004546 NASA Glenn Research Center, Cleveland, OH, United States
Flow Control Opportunities for Propulsion Systems
Cutley, Dennis E.; June 23, 2008; In English; Original contains color illustrations
Contract(s)/Grant(s): WBS 561581.02.08.03.21.03
Report No.(s): E-16831; No Copyright; Avail.: CASI: A01, Hardcopy
Avail Online: http://hdl.handle.net/2060/20090004546
The advancement of technology in gas turbine engines used for aerospace propulsion has been focused on achieving significant performance improvements. At the system level, these improvements are expressed in metrics such as engine thrust-to-weight ratio and system and component efficiencies. The overall goals are directed at reducing engine weight, fuel burn, emissions, and noise. At a component level, these goals translate into aggressive designs of each engine component well beyond the state of the art.
Author
THRUST-WEIGHT RATIO; PROPULSION SYSTEM PERFORMANCE; EXHAUST EMISSION; WEIGHT REDUCTION; GAS TURBINE ENGINES; COMBUSTION PRODUCTS
20090004550 NASA Glenn Research Center, Cleveland, OH, United States
Lunar Dust 101
Gaier, James R.; November 18, 2008; In English; Lunar Dust Filtration and Separations Workshop, 18-20 Nov. 2008, Cleveland, OH, United States; Original contains color illustrations
Contract(s)/Grant(s): WBS WBS 936374.03.03.03
Report No.(s): E-16837; No Copyright; Avail.: CASI: A03, Hardcopy
Avail Online: http://hdl.handle.net/2060/20090004550
Largely due to rock and soil samples returned during the Apollo program, much has been learned about the composition and properties of lunar regolith. Although, for the most part, the mineral composition resembles terrestrial minerals, the characteristics of the lunar environment have led to very different weathering processes. These result in substantial differences in the particle shapes, particle size distributions, and surface chemistry. These differences lead to non-intuitive adhesion, abrasion, and possible health properties that will pose challenges to future lunar missions. An overview of lunar dust composition and properties will be given with a particular emphasis on possible health effects.
Author
LUNAR DUST; SOIL SAMPLING; LUNAR ROCKS; SIZE DISTRIBUTION; SURFACE REACTIONS; WEATHERING; HEALTH
20090004551 NASA Glenn Research Center, Cleveland, OH, United States
Adsorption of Water on JSC-1A Lunar Simulant Samples
Goering, John; Sah, Shweta; Burghaus, Uwe; Street, Kenneth W.; October 09, 2008; In English; Geological Society of America Meeting, 9 Oct. 2008, Houston, TX, United States; Original contains color and black and white illustrations
Contract(s)/Grant(s): WBS 936374.03.03.03
Report No.(s): E-16838; Copyright; Avail.: CASI: A03, Hardcopy
Remote sensing probes sent to the moon in the 1990s indicated that water may exist in areas such as the bottoms of deep, permanently shadowed craters at the lunar poles, buried under regolith. Water is of paramount importance for any lunar exploration and colonization project which would require self-sustainable systems. Therefore, investigating the interaction of water with lunar regolith is pertinent to future exploration. The lunar environment can be approximated in ultra-high vacuum systems such as those used in thermal desorption spectroscopy (TDS). Questions about water dissociation, surface wetting, degree of crystallization, details of water-ice transitions, and cluster formation kinetics can be addressed by TDS. Lunar regolith specimens collected during the Apollo missions are still available though precious, so testing with simulant is required before applying to use lunar regolith samples. Hence, we used for these studies JSC-1a, mostly an aluminosilicate glass and basaltic material containing substantial amounts of plagioclase, some olivine and traces of other minerals. Objectives of this project include: 1) Manufacturing samples using as little raw material as possible, allowing the use of surface chemistry and kinetics tools to determine the feasibility of parallel studies on regolith, and 2) Characterizing the adsorption kinetics of water on the regolith simulant. This has implications for the probability of finding water on the moon and, if present, for recovery techniques. For condensed water films, complex TDS data were obtained containing multiple features, which are related to subtle rearrangements of the water adlayer. Results from JSC-1a TDS studies indicate: 1) Water dissociation on JSC-1a at low exposures, with features detected at temperatures as high as 450 K and 2) The formation of 3D water clusters and a rather porous condensed water film. It appears plausible that the sub- m sized particles act as nucleation centers.
Author
ADSORPTION; REMOTE SENSING; LUNAR ENVIRONMENT; LUNAR SOIL; SURFACE WATER; LUNAR ROCKS; OLIVINE; SURFACE REACTIONS; REGOLITH
20090004555 NASA Glenn Research Center, Cleveland, OH, United States
Gear Windage Modeling Progress - Experimental Validation Status
Kunz, Rob; Handschuh, Robert F.; October 07, 2008; In English; Original contains color and black and white illustrations
Contract(s)/Grant(s): WBS 877868.02.07.03.01.01
Report No.(s): E-16839; Copyright; Avail.: CASI: A03, Hardcopy
In the Subsonics Rotary Wing (SRW) Project being funded for propulsion work at NASA Glenn Research Center, performance of the propulsion system is of high importance. In current rotorcraft drive systems many gearing components operate at high rotational speed (pitch line velocity > 24000 ft/ min). In our testing of high speed helical gear trains at NASA Glenn we have found that the work done on the air - oil mist within the gearbox can become a significant part of the power loss of the system. This loss mechanism is referred to as windage. The effort described in this presentation is to try to understand the variables that affect windage, develop a good experimental data base to validate, the analytical project being conducted at Penn State University by Dr. Rob Kunz under a NASA SRW NRA. The presentation provides an update to the status of these efforts.
Author
MECHANICAL DRIVES; TRANSMISSIONS (MACHINE ELEMENTS); ROTARY WING AIRCRAFT; HIGH SPEED
20090004557 NASA Langley Research Center, Hampton, VA, United States
Aerothermodynamic Testing and Boundary Layer Trip Sizing of the HIFiRE Flight 1 Vehicle
Berger, Karen T.; Greene, Frank A.; Kimmel, Roger; Alba, Christopher; Johnson, Heath; [2008]; In English; Original contains color and black and white illustrations
Contract(s)/Grant(s): WBS 526282.01.07.04.05
Copyright; Avail.: CASI: A03, Hardcopy
An experimental wind tunnel test was conducted in the NASA Langley Research Center s 20-Inch Mach 6 Air Tunnel in support of the Hypersonic International Flight Research Experimentation Program. The information in this article is focused on the Flight 1 configuration, the first in a series of flight experiments. The article documents experimental measurements made over a Reynolds numbers range of 2.1x10(exp 6)/ft to 5.6x10(exp 6)/ft and angles of attack of -5 to +5 deg on several scaled ceramic heat transfer models of the Flight 1 configuration. Global heat transfer was measured using phosphor thermography and the resulting images and heat transfer distributions were used to infer the state of the boundary layer on the vehicle windside and leeside surfaces. Boundary layer trips were used to force the boundary layer turbulent and the experimental data highlighted in this article were used to size and place the boundary layer trip for the flight vehicle. The required height of the flight boundary layer trip was determined to be 0.079 in and the trip was moved from the design location of 7.87 in to 20.47 in to ensure that augmented heating would not impact the laminar side of the vehicle. Allowable roughness was selected to be 3.2x10(exp -3) in.
Author
WIND TUNNEL TESTS; AEROTHERMODYNAMICS; BOUNDARY LAYER CONTROL; REYNOLDS NUMBER; SURFACE ROUGHNESS; TURBULENCE; ANGLE OF ATTACK; BOUNDARY LAYERS
20090004558 NASA Langley Research Center, Hampton, VA, United States
Evaluation of Acoustic Emission NDE of Kevlar Composite Over Wrapped Pressure Vessels
Horne, Michael R.; Madaras, Eric I.; December 2008; In English; Original contains color and black and white illustrations
Contract(s)/Grant(s): WBS 939904.05.07
Report No.(s): NASA/TM-2008-215558; L-19534; Copyright; Avail.: CASI: A03, Hardcopy
Pressurization and failure tests of small Kevlar/epoxy COPV bottles were conducted during 2006 and 2007 by Texas Research Institute Austin, Inc., at TRI facilities. This is a report of the analysis of the Acoustic Emission (AE) data collected during those tests. Results of some of the tests indicate a possibility that AE can be used to track the stress-rupture degradation of COPV vessels.
Author
PRESSURE VESSELS; KEVLAR (TRADEMARK); EPOXY RESINS; ACOUSTIC EMISSION; DEGRADATION
Additions to the NASA Aeronautics and Space Database as of 02/04/2009
20090004576 NASA Glenn Research Center, Cleveland, OH, United States
Oxidation of Carbon/Carbon through Coating Cracks
Jacobson, N. S.; Roth, d. J.; Rauser, R. W.; Cawley, J. D.; Curry, D. M.; October 12, 2008; In English; 214th Meeting of the Electrochemical Society, 12-17 Oct. 2008, Honolulu, HI, United States; Original contains color and black and white illustrations
Contract(s)/Grant(s): WBS 377816.06.03.02.08
Report No.(s): E-16840; Copyright; Avail.: CASI: A03, Hardcopy
Reinforced carbon/carbon (RCC) is used to protect the wing leading edge and nose cap of the Space Shuttle Orbiter on re-entry. It is composed of a lay-up of carbon/carbon fabric protected by a SiC conversion coating. Due to the thermal expansion mismatch of the carbon/carbon and the SiC, the SiC cracks on cool-down from the processing temperature. The cracks act as pathways for oxidation of the carbon/carbon. A model for the diffusion controlled oxidation of carbon/carbon through machined slots and cracks is developed and compared to laboratory experiments. A symmetric cylindrical oxidation cavity develops under the slots, confirming diffusion control. Comparison of cross sectional dimensions as a function of oxidation time shows good agreement with the model. A second set of oxidation experiments was done with samples with only the natural craze cracks, using weight loss as an index of oxidation. The agreement of these rates with the model is quite reasonab
Author
CARBON-CARBON COMPOSITES; OXIDATION; SURFACE CRACKS; COATING; THERMAL EXPANSION; SILICON CARBIDES
20090004577 NASA Glenn Research Center, Cleveland, OH, United States
Solar Power System Design for the Solar Probe+ Mission
Landis, Geoffrey A.; Schmitz, Paul C.; Kinnison, James; Fraeman, Martin; Roufberg, Lew; Vernon, Steve; Wirzburger, Melissa; July 28, 2008; In English; 6th International Energy Conversion Engineering Conference (IECEC), 28-30 Jul. 2008, Cleveland, OH, United States; Original contains color and black and white illustrations
Contract(s)/Grant(s): WBS 937818.01.01.10
Report No.(s): AIAA Paper-2008-5712; E-16841; Copyright; Avail.: CASI: A02, Hardcopy
Solar Probe+ is an ambitious mission proposed to the solar corona, designed to make a perihelion approach of 9 solar radii from the surface of the sun. The high temperature, high solar flux environment makes this mission a significant challenge for power system design. This paper summarizes the power system conceptual design for the solar probe mission. Power supplies considered included nuclear, solar thermoelectric generation, solar dynamic generation using Stirling engines, and solar photovoltaic generation. The solar probe mission ranges from a starting distance from the sun of 1 AU, to a minimum distance of about 9.5 solar radii, or 0.044 AU, from the center of the sun. During the mission, the solar intensity ranges from one to about 510 times AM0. This requires power systems that can operate over nearly three orders of magnitude of incident intensity.
Author
SOLAR PROBES; SOLAR CORONA; SYSTEMS ENGINEERING; HIGH TEMPERATURE; SOLAR FLUX
20090004578 NASA Glenn Research Center, Cleveland, OH, United States
Solar Power for Near Sun, High-Temperature Missions
Landis, Geoffrey A.; May 11, 2008; In English; 33rd IEEE Photovoltaics Specialists Conference, 11-16 May 2008, San Diego, CA, United States; Original contains color illustrations
Contract(s)/Grant(s): WBS 937818.01.01.10
Report No.(s): E-16842; No Copyright; Avail.: CASI: A01, Hardcopy
Avail Online: http://hdl.handle.net/2060/20090004578
Existing solar cells lose performance at the high temperatures encountered in Mercury orbit and inward toward the sun. For future missions designed to probe environments close to the sun, it is desirable to develop array technologies for high temperature and high light intensity. Approaches to solar array design for near-sun missions include modifying the terms governing temperature of the cell and the efficiency at elevated temperature, or use of techniques to reduce the incident solar energy to limit operating temperature. An additional problem is found in missions that involve a range of intensities, such as the Solar Probe + mission, which ranges from a starting distance of 1 AU from the sun to a minimum distance of 9.5 solar radii, or 0.044 AU. During the mission, the solar intensity ranges from one to about 500 times AM0. This requires a power system to operate over nearly three orders of magnitude of incident intensity.
Author
SOLAR ARRAYS; OPERATING TEMPERATURE; PLANETARY ORBITS; SOLAR ENERGY; HIGH TEMPERATURE; SUN; SOLAR CELLS
20090004579 NASA Glenn Research Center, Cleveland, OH, United States
Forecasting Proximal Femur and Wrist Fracture Caused by a Fall to the Side during Space Exploration Missions to the Moon and Mars
Lewandowski, Beth E.; Myers, Jerry G.; Sulkowski, C.; Ruehl, K.; Licata, A.; September 29, 2008; In English; 59th International Astronautical Congress 2008, 29 Sep. - 3 Oct. 2008, Glasgow, Scotland, United Kingdom; Original contains color and black and white illustrations
Contract(s)/Grant(s): WBS 444543.01.02.01
Report No.(s): Paper ID 1494; E_16843; Copyright; Avail.: CASI: A03, Hardcopy
The possibility of bone fracture in space is a concern due to the negative impact it could have on a mission. The Bone Fracture Risk Module (BFxRM) developed at the NASA Glenn Research Center is a statistical simulation that quantifies the probability of bone fracture at specific skeletal locations for particular activities or events during space exploration missions. This paper reports fracture probability predictions for the proximal femur and wrist resulting from a fall to the side during an extravehicular activity (EVA) on specific days of lunar and Martian exploration missions. The risk of fracture at the proximal femur on any given day of the mission is small and fairly constant, although it is slightly greater towards the end of the mission, due to a reduction in proximal femur bone mineral density (BMD). The risk of wrist fracture is greater than the risk of hip fracture and there is an increased risk on Mars since it has a higher gravitational environment than the moon. The BFxRM can be used to help manage the risk of bone fracture in space as an engineering tool that is used during mission operation and resource planning.
Author
BONES; MUSCULOSKELETAL SYSTEM; BONE MINERAL CONTENT; FEMUR; EXTRAVEHICULAR ACTIVITY; FRACTURING; WRIST
20090004580 NASA Glenn Research Center, Cleveland, OH, United States
Effect of Microscopic Damage Events on Static and Ballistic Impact Strength of Triaxial Braid Composites
Littell, Justin D.; Binienda, Wieslaw K.; Arnold, William A.; Roberts, Gary d.; Goldberg, Robert K.; October 20, 2008; In English; 4th International Confrence on Composites Testing and Model Identification, 20-22 Oct. 2008, Dayton, OH, United States; Original contains color and black and white illustrations
Contract(s)/Grant(s): WBS 698259.02.07.03.04.01
Report No.(s): E-16844; Copyright; Avail.: CASI: A03, Hardcopy
In previous work, the ballistic impact resistance of triaxial braided carbon/epoxy composites made with large flat tows (12k and 24k) was examined by impacting 2 X2 X0.125" composite panels with gelatin projectiles. Several high strength, intermediate modulus carbon fibers were used in combination with both untoughened and toughened matrix materials. A wide range of penetration thresholds were measured for the various fiber/matrix combinations. However, there was no clear relationship between the penetration threshold and the properties of the constituents. During some of these experiments high speed cameras were used to view the failure process, and full-field strain measurements were made to determine the strain at the onset of failure. However, these experiments provided only limited insight into the microscopic failure processes responsible for the wide range of impact resistance observed. In order to investigate potential microscopic failure processes in more detail, quasi-static tests were performed in tension, compression, and shear. Full-field strain measurement techniques were used to identify local regions of high strain resulting from microscopic failures. Microscopic failure events near the specimen surface, such as splitting of fiber bundles in surface plies, were easily identified. Subsurface damage, such as fiber fracture or fiber bundle splitting, could be identified by its effect on in-plane surface strains. Subsurface delamination could be detected as an out-of-plane deflection at the surface. Using this data, failure criteria could be established at the fiber tow level for use in analysis. An analytical formulation was developed to allow the microscopic failure criteria to be used in place of macroscopic properties as input to simulations performed using the commercial explicit finite element code, LS-DYNA. The test methods developed to investigate microscopic failure will be presented along with methods for determining local failure criteria that can be used in analysis. Results of simulations performed using LS-DYNA will be presented to illustrate the capabilities and limitations for simulating failure during quasi-static deformation and during ballistic impact of large unit cell size triaxial braid composites.
Author
BRAIDED COMPOSITES; COMPOSITE STRUCTURES; CARBON FIBERS; EPOXY MATRIX COMPOSITES; STATIC DEFORMATION; DELAMINATING; IMPACT STRENGTH; MATRIX MATERIALS
20090004581 NASA Glenn Research Center, Cleveland, OH, United States
Evaluation of COTS Electronic Parts for Extreme Temperature Use in NASA Missions
Patterson, Richard L.; Hammoud, Ahmad; Elbuluk, Malik; July 28, 2008; In English; International Energy Conversion Engineering Conference (IECEC), 28-30 Jul. 2008, Cleveland, OH, United States; Original contains color and black and white illustrations
Contract(s)/Grant(s): NNC06BA07B
Report No.(s): E-16849; AIAA Paper 2008-5650; Copyright; Avail.: CASI: A02, Hardcopy
Electronic systems capable of extreme temperature operation are required for many future NASA space exploration missions where it is desirable to have smaller, lighter, and less expensive spacecraft and probes. Presently, spacecraft on-board electronics are maintained at about room temperature by use of thermal control systems. An Extreme Temperature Electronics Program at the NASA Glenn Research Center focuses on development of electronics suitable for space exploration missions. The effects of exposure to extreme temperatures and thermal cycling are being investigated for commercial-off-the-shelf components as well as for components specially developed for harsh environments. An overview of this program along with selected data is presented.
Author
COMMERCIAL OFF-THE-SHELF PRODUCTS; TEMPERATURE EFFECTS; ELECTRONICS; THERMAL CYCLING TESTS; SPACE EXPLORATION; TEMPERATURE CONTROL
20090004582 NASA Glenn Research Center, Cleveland, OH, United States
Silicon-On-Insulator (SOI) Devices and Mixed-Signal Circuits for Extreme Temperature Applications
Patterson, Richard; Hammoud, Ahmad; Elbuluk, Malik; June 15, 2008; In English; 39th IEEE Power Electronics Specialists Conference, 15-19 Jun. 2008, Rhodes, Greece; Original contains color and black and white illustrations
Contract(s)/Grant(s): WBS 939904.01.03.02.01
Report No.(s): E-16850; Copyright; Avail.: CASI: A02, Hardcopy
Electronic systems in planetary exploration missions and in aerospace applications are expected to encounter extreme temperatures and wide thermal swings in their operational environments. Electronics designed for such applications must, therefore, be able to withstand exposure to extreme temperatures and to perform properly for the duration of the missions. Electronic parts based on silicon-on-insulator (SOI) technology are known, based on device structure, to provide faster switching, consume less power, and offer better radiation-tolerance compared to their silicon counterparts. They also exhibit reduced current leakage and are often tailored for high temperature operation. However, little is known about their performance at low temperature. The performance of several SOI devices and mixed-signal circuits was determined under extreme temperatures, cold-restart, and thermal cycling. The investigations were carried out to establish a baseline on the functionality and to determine suitability of these devices for use in space exploration missions under extreme temperatures. The experimental results obtained on selected SOI devices are presented and discussed in this paper.
Author
SOI (SEMICONDUCTORS); TEMPERATURE EFFECTS; THERMAL CYCLING TESTS; RADIATION TOLERANCE; HIGH TEMPERATURE; AEROSPACE ENGINEERING
20090004613 NASA Goddard Space Flight Center, Greenbelt, MD, United States
Analyzing the Core Flight Software (CFS) with SAVE
Ganesan, Dharmalingam; Lindvall, Mikael; McComas, David; November 13, 2008; In English; Flight Software Workshop 2008 (FSW-08), 13-14 Nov. 2008, Laurel, MD, United States; Original contains color illustrations
Contract(s)/Grant(s): NNG05GE77G
Copyright; Avail.: CASI: A03, Hardcopy
This viewgraph presentation describes the SAVE tool and it's application to Core Flight Software (CFS). The contents include: 1) Fraunhofer-a short intro; 2) Context of this Collaboration; 3) CFS-Core Flight Software?; 4) The SAVE Tool; 5) Applying SAVE to CFS -A few example analyses; and 6) Goals.
CASI
SOFTWARE ENGINEERING; COMPUTER SYSTEMS DESIGN; APPLICATION PROGRAMMING INTERFACE; ARCHITECTURE (COMPUTERS); SYSTEMS INTEGRATION
20090004620 NASA Marshall Space Flight Center, Huntsville, AL, United States
Lessons in Systems Engineering: The SSME Weight Growth History
Ryan, Richard; August 21, 2008; In English; NASA APPL JSC Center forum on Systems Engineering, 21 Aug. 2008, Houston, TX, United States; Original contains color and black and white illustrations
No Copyright; Avail.: CASI: A03, Hardcopy
Avail Online: http://hdl.handle.net/2060/20090004620
This viewgraph presentation describes the Space Shuttle Main Engine (SSME) weight growth history and lessons learned from SSME weight imbalances.
CASI
LESSONS LEARNED; SPACE SHUTTLE MAIN ENGINE; SYSTEMS ENGINEERING; ROCKET ENGINE DESIGN; WEIGHT ANALYSIS
Additions to the NASA Aeronautics and Space Database as of 02/05/2009
20090004672 NASA Glenn Research Center, Cleveland, OH, United States
Thermoelectric Properties of Self Assembled TiO2/SnO2 Nanocomposites
Dynys, Fred; Sayir, Ali; Sehirlioglu, Alp; May 26, 2008; In English; European Materials Resource Society Conference, 26-30 May 2008, Strasbourg, France; Original contains color illustrations
Contract(s)/Grant(s): WBS 138494.04.02.01
Report No.(s): E-16834; Copyright; Avail.: CASI: A03, Hardcopy
Recent advances in improving efficiency of thermoelectric materials are linked to nanotechnology. Thermodynamically driven spinodal decomposition was utilized to synthesize bulk nanocomposites. TiO2/SnO2 system exhibits a large spinodal region, ranging from 15 to 85 mole % TiO2. The phase separated microstructures are stable up to 1400 C. Semiconducting TiO2/SnO2 powders were synthesized by solid state reaction between TiO2 and SnO2. High density samples were fabricated by pressureless sintering. Self assemble nanocomposites were achieved by annealing at 1000 to 1350 C. X-ray diffraction reveal phase separation of (Ti(x)Sn(1-x))O2 type phases. The TiO2/SnO2 nanocomposites exhibit n-type behavior; a power factor of 70 W/mK2 at 1000 C has been achieved with penta-valent doping. Seebeck, thermal conductivity, electrical resistivity and microstructure will be discussed in relation to composition and doping.
Author
NANOCOMPOSITES; THERMOELECTRICITY; X RAY DIFFRACTION; ANNEALING; MICROSTRUCTURE; NANOTECHNOLOGY; POWDER (PARTICLES); THERMAL CONDUCTIVITY; TITANIUM OXIDES
20090004673 NASA Glenn Research Center, Cleveland, OH, United States
Performance of the THS4302 and the Class V Radiation-Tolerant THS4304-SP Silicon Germanium Wideband Amplifiers at Extreme Temperatures
Patterson, Richard L.; Elbuluk, Malik; Hammoud, Ahmad; VanKeuls, Frederick W.; [2009]; In English; Original contains color and black and white illustrations
Contract(s)/Grant(s): NNC06BA07BWBS 939904.11.03.01
Copyright; Avail.: CASI: A01, Hardcopy
This report discusses the performance of silicon germanium, wideband gain amplifiers under extreme temperatures. The investigated devices include Texas Instruments THS4304-SP and THS4302 amplifiers. Both chips are manufactured using the BiCom3 process based on silicon germanium technology along with silicon-on-insulator (SOI) buried oxide layers. The THS4304-SP device was chosen because it is a Class V radiation-tolerant (150 kRad, TID silicon), voltage-feedback operational amplifier designed for use in high-speed analog signal applications and is very desirable for NASA missions. It operates with a single 5 V power supply [1]. It comes in a 10-pin ceramic flatpack package, and it provides balanced inputs, low offset voltage and offset current, and high common mode rejection ratio. The fixed-gain THS4302 chip, which comes in a 16-pin leadless package, offers high bandwidth, high slew rate, low noise, and low distortion [2]. Such features have made the amplifier useful in a number of applications such as wideband signal processing, wireless transceivers, intermediate frequency (IF) amplifier, analog-to-digital converter (ADC) preamplifier, digital-to-analog converter (DAC) output buffer, measurement instrumentation, and medical and industrial imaging.
Author
ANALOG TO DIGITAL CONVERTERS; SOI (SEMICONDUCTORS); SILICON; GERMANIUM; TEMPERATURE EFFECTS; FEEDBACK AMPLIFIERS; LOW NOISE; TRANSMITTER RECEIVERS; OPERATIONAL AMPLIFIERS
20090004674 NASA Glenn Research Center, Cleveland, OH, United States
Performance of High Temperature Operational Amplifier, Type LM2904WH, under Extreme Temperatures
Patterson, Richard; Hammoud, Ahmad; Elbuluk, Malik; [2008]; In English; Original contains color and black and white illustrations
Contract(s)/Grant(s): NNC06BA07BWBS 939904.11.03.01
Report No.(s): E-16846; Copyright; Avail.: CASI: A01, Hardcopy
Operation of electronic parts and circuits under extreme temperatures is anticipated in NASA space exploration missions as well as terrestrial applications. Exposure of electronics to extreme temperatures and wide-range thermal swings greatly affects their performance via induced changes in the semiconductor material properties, packaging and interconnects, or due to incompatibility issues between interfaces that result from thermal expansion/contraction mismatch. Electronics that are designed to withstand operation and perform efficiently in extreme temperatures would mitigate risks for failure due to thermal stresses and, therefore, improve system reliability. In addition, they contribute to reducing system size and weight, simplifying its design, and reducing development cost through the elimination of otherwise required thermal control elements for proper ambient operation. A large DC voltage gain (100 dB) operational amplifier with a maximum junction temperature of 150 C was recently introduced by STMicroelectronics [1]. This LM2904WH chip comes in a plastic package and is designed specifically for automotive and industrial control systems. It operates from a single power supply over a wide range of voltages, and it consists of two independent, high gain, internally frequency compensated operational amplifiers. Table I shows some of the device manufacturer s specifications.
Author
HIGH TEMPERATURE; TEMPERATURE EFFECTS; OPERATIONAL AMPLIFIERS; SEMICONDUCTORS (MATERIALS); THERMAL STRESSES; CIRCUITS; CHIPS; ELECTRIC POTENTIAL; TEMPERATURE CONTROL
20090004675 NASA Glenn Research Center, Cleveland, OH, United States
Performance of MEMS Silicon Oscillator, ASFLM1, under Wide Operating Temperature Range
Patterson, Richard L.; Hammoud, Ahmad; [2008]; In English; Original contains color and black and white illustrations
Contract(s)/Grant(s): NNC06BA07BWBS 939904.11.03.01
Report No.(s): E-16847; Copyright; Avail.: CASI: A02, Hardcopy
Over the last few years, MEMS (Micro-Electro-Mechanical Systems) resonator-based oscillators began to be offered as commercial-off-the-shelf (COTS) parts by a few companies [1-2]. These quartz-free, miniature silicon devices could compete with the traditional crystal oscillators in providing the timing (clock function) for many digital and analog electronic circuits. They 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, cover a wide frequency range (1 MHz to 125 MHz), and are specified, depending on the grade, for extended temperature operation from -40 C to +85 C. The small size of the MEMS oscillators along with their reliability and thermal stability make them 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 ABRACON Corporation MEMS silicon oscillator chip, type ASFLM1, under extreme temperatures.
Author
DIGITAL ELECTRONICS; THERMAL CYCLING TESTS; MICROELECTROMECHANICAL SYSTEMS; OSCILLATORS; ANALOG CIRCUITS; COMMERCIAL OFF-THE-SHELF PRODUCTS; SILICON
20090004676 NASA Glenn Research Center, Cleveland, OH, United States
Extreme High and Low Temperature Operation of the Silicon-On-Insulator Type CHT-OPA Operational Amplifier
Patterson, Richard; Hammoud, Ahmad; Elbuluk, Malik; January 11, 2008; In English; Original contains color and black and white illustrations
Contract(s)/Grant(s): NNC06BA07BWBS 939904.01.03.02.01
Report No.(s): E-16848; Copyright; Avail.: CASI: A02, Hardcopy
A new operational amplifier chip based on silicon-on-insulator technology was evaluated for potential use in extreme temperature environments. The CHT-OPA device is a low power, precision operational amplifier with rail-to-rail output swing capability, and it is rated for operation between -55 C and +225 C. A unity gain inverting circuit was constructed utilizing the CHT-OPA chip and a few passive components. The circuit was evaluated in the temperature range from -190 C to +200 C in terms of signal gain and phase shift, and supply current. The investigations were carried out to determine suitability of this device for use in space exploration missions and aeronautic applications under wide temperature incursion. Re-restart capability at extreme temperatures, i.e. power switched on while the device was soaked at extreme temperatures, was also investigated. In addition, the effects of thermal cycling under a wide temperature range on the operation of this high performance amplifier were determined. The results from this work indicate that this silicon-on-insulator amplifier chip maintained very good operation between +200 C and -190 C. The limited thermal cycling had no effect on the performance of the amplifier, and it was able to re-start at both -190 C and +200 C. In addition, no physical degradation or packaging damage was introduced due to either extreme temperature exposure or thermal cycling. The good performance demonstrated by this silicon-on-insulator operational amplifier renders it a potential candidate for use in space exploration missions or other environments under extreme temperatures. Additional and more comprehensive characterization is, however, required to establish the reliability and suitability of such devices for long term use in extreme temperature applications.
Author
HIGH TEMPERATURE; LOW TEMPERATURE; OPERATIONAL AMPLIFIERS; SOI (SEMICONDUCTORS); TECHNOLOGY UTILIZATION
20090004677 NASA Glenn Research Center, Cleveland, OH, United States
Electronic Components for use in Extreme Temperature Aerospace Applications
Patterson, Richard L.; Hammoud, Ahmad; Elbuluk, Malik; February 11, 2008; In English; 12th International Components for Military and Space Electronics Conference (CMSE 08), 11-14 Feb. 2008, San Diego, CA, United States; Original contains color and black and white illustrations
Contract(s)/Grant(s): WBS 939904.01.03.02.01
Report No.(s): E-16851; Copyright; Avail.: CASI: A03, Hardcopy
Electrical power management and control systems designed for use in planetary exploration missions and deep space probes require electronics that are capable of efficient and reliable operation under extreme temperature conditions. Space-based infra-red satellites, all-electric ships, jet engines, electromagnetic launchers, magnetic levitation transport systems, and power facilities are also typical examples where the electronics are expected to be exposed to harsh temperatures and to operate under severe thermal swings. Most commercial-off-the-shelf (COTS) devices are not designed to function under such extreme conditions and, therefore, new parts must be developed or the conventional devices need to be modified. For example, spacecraft operating in the cold environment of deep space carry a large number of radioisotope heating units in order to maintain the surrounding temperature of the on-board electronics at approximately 20 C. At the other end, built-in radiators and coolers render the operation of electronics possible under hot conditions. These thermal measures lead to design complexity, affect development costs, and increase size and weight. Electronics capable of operation at extreme temperatures, thus, will not only tolerate the hostile operational environment, but also make the overall system efficient, more reliable, and less expensive. The Extreme Temperature Electronics Program at the NASA Glenn Research Center focuses on research and development of electronics suitable for applications in the aerospace environment and deep space exploration missions. Research is being conducted on devices, including COTS parts, for potential use under extreme temperatures. These components include semiconductor switching devices, passive devices, DC/DC converters, operational amplifiers, and oscillators. An overview of the program will be presented along with some experimental findings.
Author
AEROSPACE ENGINEERING; AEROSPACE ENVIRONMENTS; ELECTRONIC EQUIPMENT; TEMPERATURE EFFECTS; THERMAL STRESSES; EXTRATERRESTRIAL ENVIRONMENTS; SPACECRAFT ELECTRONIC EQUIPMENT
20090004679 NASA Glenn Research Center, Cleveland, OH, United States
Progress Towards III-V Photovoltaics on Flexible Substrates
McNatt, Jeremiah S.; Pal, AnnaMaria T.; Clark, Eric B.; Sayir, Ali; Raffaelle, Ryne P.; Bailey, Christopher G.; Hubbard, Seth M.; Maurer, William F.; Fritzemeier, Les; July 28, 2008; In English; 6th International Energy Conversion Engineering Conference (IECEC), 28-30 Jul. 2008, Cleveland, OH, United States; Original contains color illustrations
Contract(s)/Grant(s): WBS 698671.01.03.54
Report No.(s): E-16853; Copyright; Avail.: CASI: A01, Hardcopy
Presented here is the recent progress of the NASA Glenn Research Center OMVPE group's efforts in the development of high efficiency thin-film polycrystalline III-V photovoltaics on optimum substrates. By using bulk polycrystalline germanium (Ge) films, devices of high efficiency and low mass will be developed and incorporated onto low-cost flexible substrates. Our progress towards the integration of high efficiency polycrystalline III-V devices and recrystallized Ge films on thin metal foils is discussed.
Author
PHOTOVOLTAIC CONVERSION; VAPOR PHASE EPITAXY; RECRYSTALLIZATION; POLYCRYSTALS; METAL FOILS; GERMANIUM; ORGANOMETALLIC COMPOUNDS
20090004682 NASA Glenn Research Center, Cleveland, OH, United States
Precipitation Model Validation in 3rd Generation Aeroturbine Disc Alloys
Olson, G. B.; Jou, H.-J.; Jung, J.; Sebastian, J. T.; Misra, A.; Locci, I.; Hull, D.; Septembert 14, 2008; In English; 11th International Superalloys 2008, 14-18 Sep. 2008, Champion, PAu1, FROM; Original contains black and white illustrations
Contract(s)/Grant(s): NNC07CB01CWBS 698259.02.07.03
Report No.(s): E-16858; Copyright; Avail.: CASI: A02, Hardcopy
In support of application of the DARPA-AIM methodology to the accelerated hybrid thermal process optimization of 3rd generation aeroturbine disc alloys with quantified uncertainty, equilibrium and diffusion couple experiments have identified available fundamental thermodynamic and mobility databases of sufficient accuracy. Using coherent interfacial energies quantified by Single-Sensor DTA nucleation undercooling measurements, PrecipiCalc(TM) simulations of nonisothermal precipitation in both supersolvus and subsolvus treated samples show good agreement with measured gamma particle sizes and compositions. Observed longterm isothermal coarsening behavior defines requirements for further refinement of elastic misfit energy and treatment of the parallel evolution of incoherent precipitation at grain boundaries.
Author
MATHEMATICAL MODELS; NUCLEATION; SUPERCOOLING; TURBINES; PRECIPITATION MEASUREMENT; NICKEL ALLOYS
20090004683 NASA Glenn Research Center, Cleveland, OH, United States
Effect of Upper-Cycle Temperature on the Load-Biased, Strain-Temperature Response of NiTi
Padula, Santo, II; Vaidyanathan, Raj; Gaydosh, Darrell; Noebe, Ronald; Bigelow, Glen; Garg, Anita; September 21, 2008; In English; The International Conference on Shape Memory and Superelastic Technologies (SMST) 2008, 21-25 sEP. 2008, Stresa, Italy; Original contains color illustrations
Contract(s)/Grant(s): WBS 561581.02.08.03.15.02
Report No.(s): E-16859; Copyright; Avail.: CASI: A03, Hardcopy
Over the past decade, interest in shape memory alloy based actuators has increased as the primary benefits of these solid-state devices have become more apparent. However, much is still unknown about the characteristic behavior of these materials when used in actuator applications. Recently we have shown that the maximum temperature reached during thermal cycling under isobaric conditions could significantly affect the observed mechanical response of NiTi (55 wt% Ni), especially the amount of transformation strain available for actuation and thus work output. This investigation extends that original work to ascertain whether further increases in the upper-cycle temperature would produce additional improvement in the work output of the material, which has a stress-free Af of 113 oC, and to determine the optimum cyclic conditions. Thus, isobaric, thermal-cycle experiments were conducted in the aforementioned alloy at various stress levels from 50-300 MPa using upper-cycle temperatures of 165, 200, 230, 260, 290, 320 and 350 oC. The data indicated that the amount of applied stress influenced the transformation strain available in the system, as would be expected. However, the maximum temperature reached during the thermal excursion also plays a role in determining the transformation strain, with the maximum transformation strain being developed by thermal cycling to 290 oC. In situ, neutron diffraction showed that the differences in transformation strain were related to differences in martensite texture within the microstructure when cycling to different upper-cycle temperatures. Hence, understanding this effect is important to optimizing the operation of SMA-based actuators and could lead to new methods for processing and training shape memory alloys for optimal performance.
Author
THERMAL CYCLING TESTS; STRESS-STRAIN RELATIONSHIPS; NICKEL ALLOYS; TITANIUM ALLOYS; LOADS (FORCES); SHAPE MEMORY ALLOYS; NEUTRON DIFFRACTION
20090004684 NASA Glenn Research Center, Cleveland, OH, United States
NASA's Evolutionary Xenon Thruster: The NEXT Ion Propulsion System for Solar System Exploration
Pencil, Eric J.; Benson, Scott W.; June 2008; In English; Original contains color and black and white illustrations
Contract(s)/Grant(s): WBS 346620.01.03.01
Report No.(s): E-16860; No Copyright; Avail.: CASI: A03, Hardcopy
Avail Online: http://hdl.handle.net/2060/20090004684
This viewgraph presentation reviews NASA s Evolutionary Xenon Thruster (NEXT) Ion Propulsion system. The NEXT project is developing a solar electric ion propulsion system. The NEXT project is advancing the capability of ion propulsion to meet NASA robotic science mission needs. The NEXT system is planned to significantly improve performance over the state of the art electric propulsion systems, such as NASA Solar Electric Propulsion Technology Application Readiness (NSTAR). The status of NEXT development is reviewed, including information on the NEXT Thruster, the power processing unit, the propellant management system (PMS), the digital control interface unit, and the gimbal. Block diagrams NEXT system are presented. Also a review of the lessons learned from the Dawn and NSTAR systems is provided. In summary the NEXT project activities through 2007 have brought next-generation ion propulsion technology to a sufficient maturity level.
CASI
ELECTRIC PROPULSION; ION ENGINES; ION PROPULSION; PROPULSION SYSTEM PERFORMANCE; SOLAR ELECTRIC PROPULSION
20090004685 NASA Glenn Research Center, Cleveland, OH, United States
NASA's Evolutionary Xenon Thruster (NEXT) Ion Propulsion System Information Summary
Pencil, Eirc S.; Benson, Scott W.; August 2008; In English; Original contains color illustrations
Contract(s)/Grant(s): WBS 346620.01.03.01
Report No.(s): E-16861; No Copyright; Avail.: CASI: A03, Hardcopy
Avail Online: http://hdl.handle.net/2060/20090004685
This document is a guide to New Frontiers mission proposal teams. The document describes the development and status of the NASA's Evolutionary Xenon Thruster (NEXT) ion propulsion system (IPS) technology, its application to planetary missions, and the process anticipated to transition NEXT to the first flight mission.
Derived from text
ION PROPULSION; XENON; THRUSTORS; FABRICATION; SYSTEMS ENGINEERING
20090004686 NASA Glenn Research Center, Cleveland, OH, United States
An Overview of Recent Phased Array Measurements at NASA Glenn
Podboy, Gary G.; September 23, 2008; In English; TWG Meeting, 23-24 Sep. 2008, Williamsburg, VA, United States; Original contains color and black and white illustrations
Contract(s)/Grant(s): WBS 561581.02.08.03.18.02
Report No.(s): E-16862; No Copyright; Avail.: CASI: A03, Hardcopy
Avail Online: http://hdl.handle.net/2060/20090004686
A review of measurements made at the NASA Glenn Research Center using an OptiNAV Array 48 phased array system is provided. Data were acquired on a series of round convergent and convergent-divergent nozzles using the Small Hot Jet Acoustic Rig. Tests were conducted over a range of jet operating conditions, including subsonic and supersonic and cold and hot jets. Phased array measurements were also acquired on a Williams International FJ44 engine. These measurements show how the noise generated by the engine is split between the inlet-radiated and exhaust-radiated components. The data also show inlet noise being reflected off of the inflow control device used during the test.
Author
PHASED ARRAYS; CONVERGENT-DIVERGENT NOZZLES; CONVERGENT NOZZLES; JET FLOW
20090004687 NASA Glenn Research Center, Cleveland, OH, United States
SDR/STRS Flight Experiment and the Role of SDR-Based Communication and Navigation Systems
Reinhart, Richard C.; February 25, 2008; In English; IDGA 6th Annual Software Radio Summit, 25-28 Feb. 2008, Vienna, VA, United States; Original contains color illustrations
Contract(s)/Grant(s): WBS 439432.04.07.0
Report No.(s): E-16867; No Copyright; Avail.: CASI: A03, Hardcopy
Avail Online: http://hdl.handle.net/2060/20090004687
This presentation describes an open architecture SDR (software defined radio) infrastructure, suitable for space-based radios and operations, entitled Space Telecommunications Radio System (STRS). SDR technologies will endow space and planetary exploration systems with dramatically increased capability, reduced power consumption, and less mass than conventional systems, at costs reduced by vigorous competition, hardware commonality, dense integration, minimizing the impact of parts obsolescence, improved interoperability, and software re-use. To advance the SDR architecture technology and demonstrate its applicability in space, NASA is developing a space experiment of multiple SDRs each with various waveforms to communicate with NASA s TDRSS satellite and ground networks, and the GPS constellation. An experiments program will investigate S-band and Ka-band communications, navigation, and networking technologies and operations.
Author
RADIO COMMUNICATION; ARCHITECTURE (COMPUTERS); ULTRAHIGH FREQUENCIES; TDR SATELLITES; SUPERHIGH FREQUENCIES; SATELLITE NETWORKS; RADIO EQUIPMENT; GLOBAL POSITIONING SYSTEM
20090004693 NASA Glenn Research Center, Cleveland, OH, United States
Doping of BiScO3-PbTiO3 Ceramics for Enhanced Properties
Sehirlioglu, Alp; Sayir, Ali; Dynys, Fred; October 05, 2008; In English; Materials Science and Technology Meeting ASM/ACERS, 5-9 Oct. 2008, Pittsburgh, PA, United States; Original contains color and black and white illustrations
Contract(s)/Grant(s): AFOSR FA-9550-06.1-0260WBS 984754.02.07.03.16.04
Report No.(s): E-16871; Copyright; Avail.: CASI: A03, Hardcopy
High-temperature piezoelectrics are a key technology for aeronautics and aerospace applications such as fuel modulation to increase the engine efficiency and decrease emissions. The principal challenge for the insertion of piezoelectric materials is the limitation on upper use temperature which is due to low Curie-Temperature (T(sub c) and increasing electrical conductivity. BiScO3 -PbTiO3 (BS-PT) system is a promising candidate for improving the operating temperature for piezoelectric actuators due to its high TC (>400 C). Effects of Zr and Mn doping of the BS-PT ceramics have been studied and all electrical and electromechanical properties for Sc-deficient and Ti-deficient BS- PT ceramics are reported as a function of electrical field and temperature. Donor doping with Zr and Mn (in Sc deficient compositions) increased the DC-resistivity and decreased tan at all temperatures. Resulting ceramics exhibited saturated hysteresis loops with low losses and showed no dependence on the applied field (above twice the coercive field) and measurement frequency.
Author
PIEZOELECTRICITY; HIGH TEMPERATURE; CERAMICS; EXHAUST EMISSION; ELECTRICAL PROPERTIES; COMBUSTION PRODUCTS; ACTUATORS
20090004695 NASA Glenn Research Center, Cleveland, OH, United States
Liquid Methane/Liquid Oxygen Propellant Conditioning Feed System (PCFS) Test Rigs
Skaff, A.; Grasl, S.; Nguyen, C.; Hockenberry S.; Schubert, J.; Arrington, L.; Vasek, T.; December 08, 2008; In English; JANNAF 3rd Spacecraft Propulsion Joint Subcommittee Meeting, 8-12 Dec. 2008, Orland, FL, United States; Original contains color illustrations
Contract(s)/Grant(s): NNCO5CA95C
Report No.(s): E-16872; Copyright; Avail.: CASI: A03, Hardcopy
As part of their Propulsion and Cryogenic Advanced Development (PCAD) program, NASA has embarked upon an effort to develop chemical rocket engines which utilize non-toxic, cryogenic propellants such as liquid oxygen (LO2) and liquid methane (LCH4). This effort includes the development and testing of a 100 lbf Reaction Control Engine (RCE) that will be used to evaluate the performance of a LO2/LCH4 rocket engine over a broad range of propellant temperatures and pressures. This testing will take place at NASA-Glenn Research Center's (GRC) Research Combustion Laboratory (RCL) test facility in Cleveland, OH, and is currently scheduled to begin in late 2008. While the initial tests will be performed at sea level, follow-on testing will be performed at NASA-GRC's Altitude Combustion Stand (ACS) for altitude testing. In support of these tests, Sierra Lobo, Inc. (SLI) has designed, developed, and fabricated two separate portable propellant feed systems under the Propellant Conditioning and Feed System (PCFS) task: one system for LCH4, and one for LO2. These systems will be capable of supplying propellants over a large range of conditions from highly densified to several hundred pounds per square inch (psi) saturated. This paper presents the details of the PCFS design and explores the full capability of these propellant feed systems.
Author
METHANE; LIQUID OXYGEN; PROPELLANTS; CHEMICAL PROPULSION; CRYOGENIC ROCKET PROPELLANTS; FEED SYSTEMS; ROCKET ENGINES; LIQUEFIED GASES; COMBUSTION
20090004702 NASA Langley Research Center, Hampton, VA, United States
Fluorescence Imaging and Streamline Visualization of Hypersonic Flow over Rapid Prototype Wind-Tunnel Models
Danehy, Paul M.; Alderfer, David W.; Inman, Jennifer A.; Berger, Karen T.; Buck, Gregory M.; Schwartz, Richard J.; [2008]; In English; Original contains color and black and white illustrations
Contract(s)/Grant(s): WBS 599489.02.07.07.06.02
Report No.(s): LF99-5899; Copyright; Avail.: CASI: A03, Hardcopy
Reentry models for use in hypersonic wind tunnel tests were fabricated using a stereolithography apparatus. These models were produced in one day or less, which is a significant time savings compared to the manufacture of ceramic or metal models. The models were tested in the NASA Langley Research Center 31-Inch Mach 10 Air Tunnel. Only a few of the models survived repeated tests in the tunnel, and several failure modes of the models were identified. Planar laser-induced fluorescence (PLIF) of nitric oxide (NO) was used to visualize the flowfields in the wakes of these models. Pure NO was either seeded through tubes plumbed into the model or via a tube attached to the strut holding the model, which provided localized addition of NO into the model s wake through a porous metal cylinder attached to the end of the tube. Models included several 2- inch diameter Inflatable Reentry Vehicle Experiment (IRVE) models and 5-inch diameter Crew Exploration Vehicle (CEV) models. Various model configurations and NO seeding methods were used, including a new streamwise visualization method based on PLIF. Virtual Diagnostics Interface (ViDI) technology, developed at NASA Langley Research Center, was used to visualize the data sets in post processing. The use of calibration "dotcards" was investigated to correct for camera perspective and lens distortions in the PLIF images.
Author
WIND TUNNEL MODELS; LITHOGRAPHY; REENTRY VEHICLES; WIND TUNNEL TESTS; MATHEMATICAL MODELS; LAMINAR FLOW; LASER INDUCED FLUORESCENCE; HYPERSONIC WIND TUNNELS; IMAGING TECHNIQUES; FLOW VISUALIZATION
20090004704 NASA Langley Research Center, Hampton, VA, United States
Analytic Formulation and Numerical Implementation of an Acoustic Pressure Gradient Prediction
Lee, Seongkyu; Brentner, Kenneth S.; Farassat, F.; Morris, Philip J.; April 24, 2008; In English
Contract(s)/Grant(s): NNL05AD50PWBS 561581.02.07.07
Copyright; Avail.: CASI: A03, Hardcopy
Two new analytical formulations of the acoustic pressure gradient have been developed and implemented in the PSU-WOPWOP rotor noise prediction code. The pressure gradient can be used to solve the boundary condition for scattering problems and it is a key aspect to solve acoustic scattering problems. The first formulation is derived from the gradient of the Ffowcs Williams-Hawkings (FW-H) equation. This formulation has a form involving the observer time differentiation outside the integrals. In the second formulation, the time differentiation is taken inside the integrals analytically. This formulation avoids the numerical time differentiation with respect to the observer time, which is computationally more efficient. The acoustic pressure gradient predicted by these new formulations is validated through comparison with available exact solutions for a stationary and moving monopole sources. The agreement between the predictions and exact solutions is excellent. The formulations are applied to the rotor noise problems for two model rotors. A purely numerical approach is compared with the analytical formulations. The agreement between the analytical formulations and the numerical method is excellent for both stationary and moving observer cases.
Author
ANALYSIS (MATHEMATICS); NUMERICAL DIFFERENTIATION; ACOUSTIC SCATTERING; PRESSURE GRADIENTS; NOISE PREDICTION; FFOWCS WILLIAMS-HAWKINGS EQUATION; BOUNDARY CONDITIONS; SOUND PRESSURE; ROTOR AERODYNAMICS
Additions to the NASA Aeronautics and Space Database as of 02/06/2009
20090004864 NASA Glenn Research Center, Cleveland, OH, United States
SBIR/STTR Programs
Stegeman, James D.; Comstock, Douglas; November 12, 2008; In English; National SBIR Conference, 14 Nov. 2008, Hartford, CT, United States; Original contains color illustrations
Contract(s)/Grant(s): WBS 128636.01.03.01
Report No.(s): E-16873; No Copyright; Avail.: CASI: A03, Hardcopy
Avail Online: http://hdl.handle.net/2060/20090004864
This presentation provides an overview of the NASA mission and overviews of both the Innovative Partnerships Program (IPP) and Small Business Innovation Research (SBIR) programs and how they relate to each other and to the NASA mission. Examples are provided concerning NASA technology needs and how the SBIR program has not only enabled technology development to meet those needs, but has also facilitated the infusion of that technology into the NASA mission.
Author
NASA PROGRAMS; RESEARCH AND DEVELOPMENT; TECHNOLOGY ASSESSMENT
20090004866 NASA Glenn Research Center, Cleveland, OH, United States
Lunar Dust Characterization Activity at GRC
Street, Kenneth W.; November 18, 2008; In English; NASA Lunar Dust Filtration and Separations Workshop, 18 Nov. 2008, Cleveland, OH, United States; Original contains color and black and white illustrations
Contract(s)/Grant(s): WBS 936374.03.01.03
Report No.(s): E-16874; No Copyright; Avail.: CASI: A03, Hardcopy
Avail Online: http://hdl.handle.net/2060/20090004866
The fidelity of lunar simulants as compared to actual regolith is evaluated using Figures of Merit (FOM) which are based on four criteria: Particle Size, Particle Shape, Composition, and Density of the bulk material. In practice, equipment testing will require other information about both the physical properties (mainly of the dust fraction) and composition as a function of particle size. At Glenn Research Center (GRC) we are involved in evaluating a number of simulant properties of consequence to testing of lunar equipment in a relevant environment, in order to meet Technology Readiness Level (TRL) 6 criteria. Bulk regolith has been characterized for many decades, but surprisingly little work has been done on the dust fraction (particles less than 20 micrometers in diameter). GRC is currently addressing the information shortfall by characterizing the following physical properties: Particle Size Distribution, Adhesion, Abrasivity, Surface Energy, Magnetic Susceptibility, Tribocharging and Surface Chemistry/Reactivity. Since some of these properties are also dependent on the size of the particles we have undertaken the construction of a six stage axial cyclone particle separator to fractionate dust into discrete particle size distributions for subsequent evaluation of these properties. An introduction to this work and progress to date will be presented.
Author
CHARACTERIZATION; LUNAR DUST; REGOLITH; LUNAR GEOLOGY; LUNAR ENVIRONMENT
20090004878 NASA Glenn Research Center, Cleveland, OH, United States
Some Expected Characteristics of Lunar Dust: A Geological View Applied to Engineering
Street, Kenneth W.; Schrader, Christian M.; Rickman, Doug; October 05, 2008; In English; Geological Society of America Meeting, 9 Oct. 2008, Houston, TX, United States; Original contains color and black and white illustrations
Contract(s)/Grant(s): WBS 092837.04.02.01.03
Report No.(s): E-16875; No Copyright; Avail.: CASI: A03, Hardcopy
Avail Online: http://hdl.handle.net/2060/20090004878
Compared to the Earth the geologic nature of the lunar regolith is quite distinct. Even though similar minerals exist on the Earth and Moon, they may have very different properties due to the absence of chemical modification in the lunar environment. The engineering properties of the lunar regolith reflect aspects of the parent rock and the consequences of hypervelocity meteor bombardment. On scales relevant to machinery and chemical processing for In-Situ Resource Utilization, ISRU (such as water production), the lunar regolith compositional range is much more restricted than terrestrial material. This fact impacts predictions of properties required by design engineers for constructing equipment for lunar use. In this paper two examples will be covered. 1) Abrasion is related to hardness and hardness is a commonly measured property for both minerals and engineering materials. Although different hardness scales are routinely employed for minerals and engineering materials, a significant amount of literature is available relating the two. As one example, we will discuss how to relate hardness to abrasion for the design of lunar equipment. We also indicate how abundant the various mineral phases are and typical size distributions for lunar regolith which will impact abrasive nature. 2) Mineral characteristics that may seem trivial to the non-geologist or material scientist may have significant bearing on ISRU processing technologies. As a second example we discuss the impact of traces of F-, Cl-, and OH-, H2O, CO2, and sulfur species which can radically alter melting points and the corrosive nature of reaction products thereby significantly changing bulk chemistry and associated processing technologies. For many engineering uses, a simulant s fidelity to bulk lunar regolith chemistry may be insufficient. Therefore, simulant users need to engage in continuing dialogue with simulant developers and geoscientists.
Author
LUNAR ENVIRONMENT; LUNAR DUST; LUNAR ROCKS; MINERALOGY; SIZE DISTRIBUTION; GEOLOGY; ABRASIVES
20090004883 NASA Langley Research Center, Hampton, VA, United States
Benchmark Analysis of Pion Contribution from Galactic Cosmic Rays
Aghara, Sukesh K.; Blattnig, Steve R.; Norbury, John W.; Singleterry, Robert C., Jr.; December 2008; In English; Original contains color and black and white illustrations
Contract(s)/Grant(s): WBS 651549.02.07.01
Report No.(s): NASA/TP-2008-215556; L-19400; Copyright; Avail.: CASI: A03, Hardcopy
Shielding strategies for extended stays in space must include a comprehensive resolution of the secondary radiation environment inside the spacecraft induced by the primary, external radiation. The distribution of absorbed dose and dose equivalent is a function of the type, energy and population of these secondary products. A systematic verification and validation effort is underway for HZETRN, which is a space radiation transport code currently used by NASA. It performs neutron, proton and heavy ion transport explicitly, but it does not take into account the production and transport of mesons, photons and leptons. The question naturally arises as to what is the contribution of these particles to space radiation. The pion has a production kinetic energy threshold of about 280 MeV. The Galactic cosmic ray (GCR) spectra, coincidentally, reaches flux maxima in the hundreds of MeV range, corresponding to the pion production threshold. We present results from the Monte Carlo code MCNPX, showing the effect of lepton and meson physics when produced and transported explicitly in a GCR environment.
Author
GALACTIC COSMIC RAYS; PIONS; EXTRATERRESTRIAL RADIATION; RADIATION DOSAGE; RADIATION SHIELDING; RADIATION TRANSPORT; MONTE CARLO METHOD
20090004893 NASA Glenn Research Center, Cleveland, OH, United States
Model Attitude and Deformation Measurements at the NASA Glenn Research Center
Woike, Mark R.; January 07, 2008; In English; 46th AIAA Model Attitude and Deformation Working Group Meeting, 7-10 Jan. 2008, Reno, NV, United States; Original contains black and white illustrations
Contract(s)/Grant(s): WBS 122711.03.06.03.01
Report No.(s): E-16877; No Copyright; Avail.: CASI: A03, Hardcopy
Avail Online: http://hdl.handle.net/2060/20090004893
The NASA Glenn Research Center is currently participating in an American Institute of Aeronautics and Astronautics (AIAA) sponsored Model Attitude and Deformation Working Group. This working group is chartered to develop a best practices document dealing with the measurement of two primary areas of wind tunnel measurements, 1) model attitude including alpha, beta and roll angle, and 2) model deformation. Model attitude is a principle variable in making aerodynamic and force measurements in a wind tunnel. Model deformation affects measured forces, moments and other measured aerodynamic parameters. The working group comprises of membership from industry, academia, and the Department of Defense (DoD). Each member of the working group gave a presentation on the methods and techniques that they are using to make model attitude and deformation measurements. This presentation covers the NASA Glenn Research Center s approach in making model attitude and deformation measurements.
Author
ATTITUDE (INCLINATION); DEFORMATION; WIND TUNNEL TESTS; SUPERSONIC WIND TUNNELS; WIND TUNNEL MODELS; AERONAUTICS
20090004895 Jet Propulsion Lab., California Inst. of Tech., Pasadena, CA, United States
Commercial Sensor Survey Fiscal Year 2008 Compendium Radiation Test Report
Becker, Heidi N.; Dolphin, Michael D.; Thorbourn, Dennis O.; Alexander, James W.; Salomon, Phil M.; October 2008; In English; Original contains color and black and white illustrations
Contract(s)/Grant(s): NAS7-03001WBS 939904.01.11.30; JPL Proj. 102197
Report No.(s): JPL Publication 08-26; Copyright; Avail.: CASI: A03, Hardcopy
Avail Online: http://dx.doi.org/2014/41025
The NASA Electronic Parts and Packaging (NEPP) Program Sensor Technology Commercial Sensor Survey task is geared toward benefiting future NASA space missions with low-cost, short-duty-cycle, visible-wavelength imaging needs. Such applications could include imaging for educational outreach purposes or short surveys of spacecraft, planetary, or lunar surfaces. Under the task, inexpensive commercial grade CMOS sensors were surveyed in fiscal year 2007 (FY07) and three sensors were selected for total ionizing dose (TID) and displacement damage dose (DDD) tolerance testing. The selected sensors had to meet selection criteria chosen to support small, low-mass cameras that produce good resolution color images. These criteria were discussed in detail in [1], and are provided again in Appendix 1 of this document. This compendium provides results for all radiation testing performed in FY08 on the Micron and OmniVision sensors that were selected in FY07 for radiation tolerance testing
Author
RADIATION TOLERANCE; RADIATION EFFECTS; MEASURING INSTRUMENTS
20090004912 ENSCO, Inc., Cocoa Beach, FL, United States
Completion of the Edward Air Force Base Statistical Guidance Wind Tool
Dreher, Joseph G.; October 2008; In English; Original contains color illustrations
Contract(s)/Grant(s): NNK06MA70C
Report No.(s): NASA/CR-2008-214751; Copyright; Avail.: CASI: A03, Hardcopy
The goal of this task was to develop a GUI using EAFB wind tower data similar to the KSC SLF peak wind tool that is already in operations at SMG. In 2004, MSFC personnel began work to replicate the KSC SLF tool using several wind towers at EAFB. They completed the analysis and QC of the data, but due to higher priority work did not start development of the GUI. MSFC personnel calculated wind climatologies and probabilities of 10-minute peak wind occurrence based on the 2-minute average wind speed for several EAFB wind towers. Once the data were QC'ed and analyzed the climatologies were calculated following the methodology outlined in Lambert (2003). The climatologies were calculated for each tower and month, and then were stratified by hour, direction (10" sectors), and direction (45" sectors)/hour. For all climatologies, MSFC calculated the mean, standard deviation and observation counts of the Zminute average and 10-minute peak wind speeds. MSFC personnel also calculated empirical and modeled probabilities of meeting or exceeding specific 10- minute peak wind speeds using PDFs. The empirical PDFs were asymmetrical and bounded on the left by the 2- minute average wind speed. They calculated the parametric PDFs by fitting the GEV distribution to the empirical distributions. Parametric PDFs were calculated in order to smooth and interpolate over variations in the observed values due to possible under-sampling of certain peak winds and to estimate probabilities associated with average winds outside the observed range. MSFC calculated the individual probabilities of meeting or exceeding specific 10- minute peak wind speeds by integrating the area under each curve. The probabilities assist SMG forecasters in assessing the shuttle FR for various Zminute average wind speeds. The A M ' obtained the processed EAFB data from Dr. Lee Bums of MSFC and reformatted them for input to Excel PivotTables, which allow users to display different values with point-click-drag techniques. The GUI was created from the PivotTables using VBA code. It is run through a macro within Excel and allows forecasters to quickly display and interpret peak wind climatology and probabilities in a fast-paced operational environment. The GUI was designed to look and operate exactly the same as the KSC SLF tool since SMG forecasters were already familiar with that product. SMG feedback was continually incorporated into the GUI ensuring the end product met their needs. The final version of the GUI along with all climatologies, PDFs, and probabilities has been delivered to SMG and will be put into operational use.
Author
GRAPHICAL USER INTERFACE; WIND MEASUREMENT; CLIMATOLOGY; WIND VELOCITY; WIND (METEOROLOGY); FORECASTING; PROBABILITY THEORY
20090004981 Colorado Univ., Boulder, CO United States
Mounting system for optical frequency reference cavities
Notcutt, Mark, Inventor; Hall, John L., Inventor; Ma, Long-Sheng, Inventor; December 30, 2008; In English
Contract(s)/Grant(s): NAG5-10368
Patent Info.: August 25, 2006US-Patent-7,469,454; US-Patent-Appl-SN-11/510,269
No Copyright; Avail.: CASI: A02, Hardcopy
Avail Online: http://hdl.handle.net/2060/20090004981
A technique for reducing the vibration sensitivity of laser-stabilizing optical reference cavities is based upon an improved design and mounting method for the cavity, wherein the cavity is mounted vertically. It is suspended at one plane, around the spacer cylinder, equidistant from the mirror ends of the cavity. The suspension element is a collar of an extremely low thermal expansion coefficient material, which surrounds the spacer cylinder and contacts it uniformly. Once the collar has been properly located, it is cemented in place so that the spacer cylinder is uniformly supported and does not have to be squeezed at all. The collar also includes a number of cavities partially bored into its lower flat surface, around the axial bore. These cavities are support points, into which mounting base pins will be inserted. Hence the collar is supported at a minimum of three points.
Official Gazette of the U.S. Patent and Trademark Office
MOUNTING; OPTICAL RESONATORS; SENSITIVITY; VIBRATION DAMPING; LASER APPLICATIONS; LASER CAVITIES
20090004982 NASA, Washington, DC United States
Magnetostrictive valve assembly
Richard, James A., Inventor; December 30, 2008; In English
Patent Info.: September 1, 2006US-Patent-7,469,878; US-Patent-Appl-SN-11/518,733
No Copyright; Avail.: CASI: A01, Hardcopy
Avail Online: http://hdl.handle.net/2060/20090004982
A magnetostrictive valve assembly includes a housing that defines a passage with a seat being formed therein. A magnetically-biased and axially-compressed magnetostrictive assembly slidingly fitted in the passage is configured as a hollow and open-ended conduit adapted to support a flow of a fluid therethrough. Current-carrying coil(s) disposed about the passage in the region of the magnetostrictive assembly generate a magnetic field in the passage when current flows through the coil(s). A hollow valve body with side ports is coupled on one end thereof to an axial end of the magnetostrictive assembly. The other end of the valve body is designed to seal with the seat formed in the housing's passage when brought into contact therewith.
Official Gazette of the U.S. Patent and Trademark Office
MAGNETOSTRICTION; VALVES; ROCKET ENGINES
20090004983 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; December 30, 2008; In English
Contract(s)/Grant(s): NAS7-1407
Patent Info.: March 9, 2004US-Patent-7,470,478; US-Patent-Appl-SN-10/797,625
No Copyright; Avail.: CASI: A03, Hardcopy
Avail Online: http://hdl.handle.net/2060/20090004983
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.
Official Gazette of the U.S. Patent and Trademark Office
ELECTRODES; FEED SYSTEMS; FUEL CELLS; METHYL ALCOHOL
20090004984 Columbia Univ., New York, NY United States
Cross reactive arrays of three-way junction sensors for steroid determination
Stojanovic, Milan N., Inventor; Landry, Donald, Inventor; Nikic, Dragan B., Inventor; December 30, 2008; In English
Contract(s)/Grant(s): NAS2-02039
Patent Info.: October 14, 2005US-Patent-7,470,516; US-Patent-Appl-SN-11/251,496
No Copyright; Avail.: CASI: A08, Hardcopy
Avail Online: http://hdl.handle.net/2060/20090004984
This invention provides analyte sensitive oligonucleotide compositions for detecting and analyzing analytes in solution, including complex solutions using cross reactive arrays of analyte sensitive oligonucleotide compositions.
Official Gazette of the U.S. Patent and Trademark Office
DETECTION; OLIGONUCLEOTIDES; REACTIVITY; STEROIDS
Additions to the NASA Aeronautics and Space Database as of 02/09/2009
20090004998 NASA Johnson Space Center, Houston, TX, United States
Human Adaptation to Space: Space Physiology and Countermeasures
Fogarty, Jennifer; [2009]; In English; NASA Human Health and Performance Technology, 15 Jan. 2009, Houston, TX, United States; Original contains color illustrations
No Copyright; Avail.: CASI: A03, Hardcopy
Avail Online: http://hdl.handle.net/2060/20090004998
This viewgraph presentation reviews human physiological responses to spaceflight, and the countermeasures taken to prevent adverse effects of manned space flight. The topics include: 1) Human Spaceflight Experience; 2) Human Response to Spaceflight; 3) ISS Expeditions 1-16; 4) Countermeasure; and 5) Biomedical Data;
CASI
AEROSPACE MEDICINE; HUMAN TOLERANCES; MANNED SPACE FLIGHT; PHYSIOLOGICAL RESPONSES; SPACE ADAPTATION SYNDROME; INTERNATIONAL SPACE STATION
20090005021 NASA Glenn Research Center, Cleveland, OH, United States
Estimating the Need for Medical Intervention due to Sleep Disruption on the International Space Station
Myers, Jerry G.; Lewandowski, Beth E.; Brooker, John E.; Hurst, S. R.; Mallis, Melissa M.; Caldwell, J. Lynn; September 29, 2008; In English; Original contains color and black and white illustrations
Contract(s)/Grant(s): WBS 444543.01.02.01
Report No.(s): E-16856; Paper ID:1499; Copyright; Avail.: CASI: A03, Hardcopy
During ISS and shuttle missions, difficulties with sleep affect more than half of all US crews. Mitigation strategies to help astronauts cope with the challenges of disrupted sleep patterns can negatively impact both mission planning and vehicle design. The methods for addressing known detrimental impacts for some mission scenarios may have a substantial impact on vehicle specific consumable mass or volume or on the mission timeline. As part of the Integrated Medical Model (IMM) task, NASA Glenn Research Center is leading the development of a Monte Carlo based forecasting tool designed to determine the consumables required to address risks related to sleep disruption. The model currently focuses on the International Space Station and uses an algorithm that assembles representative mission schedules and feeds this into a well validated model that predicts relative levels of performance, and need for sleep (SAFTE Model, IBR Inc). Correlation of the resulting output to self-diagnosed needs for hypnotics, stimulants, and other pharmaceutical countermeasures, allows prediction of pharmaceutical use and the uncertainty of the specified prediction. This paper outlines a conceptual model for determining a rate of pharmaceutical utilization that can be used in the IMM model for comparison and optimization of mitigation methods with respect to all other significant medical needs and interventions.
Author
INTERNATIONAL SPACE STATION; SLEEP; SPACE SHUTTLE MISSIONS; AEROSPACE MEDICINE; HUMAN FACTORS ENGINEERING
20090005024 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.; November 18, 2008; In English; NASA Seals and Secondary Flows Symposium, 18 Nov. 2008, Cleveland, OH, United States; Original contains color and black and white illustrations
Contract(s)/Grant(s): WBS 561581.02.08.03.15.02
Report No.(s): E-16864; No Copyright; Avail.: CASI: A03, Hardcopy
Avail Online: http://hdl.handle.net/2060/20090005024
Low leakage, non-contacting finger seals have potential to reduce gas turbine engine specific fuel consumption by 2 to 3 percent and to reduce direct operating costs by increasing the time between engine overhauls. A non-contacting finger seal with concentric lift-pads operating adjacent to a test rotor with herringbone grooves was statically tested at 300, 533, and 700 K inlet air temperatures at pressure differentials up to 576 kPa. Leakage flow factors were approximately 70 percent less than state-of-the-art labyrinth seals. Leakage rates are compared to first order predictions. Initial spin tests at 5000 rpm, 300 K inlet air temperature and pressure differentials to 241 kPa produced no measurable wear.
Author
LABYRINTH SEALS; ROTORS; SECONDARY FLOW; MATHEMATICAL MODELS; SPIN TESTS; GAS TURBINE ENGINES
20090005033 NASA Goddard Space Flight Center, Greenbelt, MD, United States; NASA Goddard Space Flight Center, Greenbelt, MD, United States
Catching Up on State Transitions in Cygnus X-1
Boeck, Moritz; Hanke, Manfred; Wilms, Joern; Pirner, Stefan; Grinberg, Victoria; Markoff, Sera; Pottschmidt, Katja; Nowak, Michael A.; Pooley, Guy; September 2008; In English; 7th Microquasar Workshop: Microquasars and Beyond, 1-5 Sep. 2008, Izmir, Turkey; Original contains color and black and white illustrations
Contract(s)/Grant(s): NNG06EO90A; DLR 50OR0801
Copyright; Avail.: CASI: A01, Hardcopy
In 2005 February we observed Cygnus X-1 over a period of 10 days quasi-continuously with the Rossi X-ray Timing Explorer and the Ryle telescope. We present the results of the spectral and timing analysis on a timescale of 90 min and show that the behavior of Cyg X-1 is similar to that found during our years long monitoring campaign. As a highlight we present evidence for a full transition from the hard to the soft state that happened during less than three hours. The observation provided a more complete picture of a state transition than before, especially concerning the evolution of the time lags, due to unique transition coverage and analysis with high time resolution.
Author
CYGNUS CONSTELLATION; X RAY SOURCES; SPECTRUM ANALYSIS
20090005034 NASA Goddard Space Flight Center, Greenbelt, MD, United States
Highly Structured Wind in Vela X-1
Kreykenbohm, Ingo; Wilms, Joern; Kretschmar, Peter; Torrejon, Jose Miguel; Pottschmidt, Katja; Hanke, Manfred; Santangelo, Andrea; Ferrigno, Carlo; Staubert, Ruediger; September 08, 2008; In English; 7th INTEGRAL Workshop, 8-11 Sep. 2008, Copenhagen, Denmark; Original contains color and black and white illustrations
Contract(s)/Grant(s): NNG06EO90A
Copyright; Avail.: CASI: A03, Hardcopy
We present an in-depth analysis of the spectral and temporal behavior of a long almost uninterrupted INTEGRAL observation of Vela X-1 in Nov/Dec 2003. In addition to an already high activity level, Vela X-1 exhibited several very intense flares with a maximum intensity of more than 5 Crab in the 20 40 keV band. Furthermore Vela X-1 exhibited several off states where the source became undetectable with ISGRI. We interpret flares and off states as being due to the strongly structured wind of the optical companion: when Vela X-1 encounters a cavity in the wind with strongly reduced density, the flux will drop, thus potentially triggering the onset of the propeller effect which inhibits further accretion, thus giving rise to the off states. The required drop in density to trigger the propeller effect in Vela X-1 is of the same order as predicted by theoretical papers for the densities in the OB star winds. The same structured wind can give rise to the giant flares when Vela X-1 encounters a dense blob in the wind. Further temporal analysis revealed that a short lived QPO with a period of 6800 sec is present. The part of the light curve during which the QPO is present is very close to the off states and just following a high intensity state, thus showing that all these phenomena are related.
Author
X RAY BINARIES; STELLAR WINDS
20090005035 NASA Goddard Space Flight Center, Greenbelt, MD, United States
Multi-Satellite Observations of Cygnus X-1 to Study the Focused Wind and Absorption Dips
Hanke, Manfred; Wilms, Joern; Boeck, Moritz; Nowak, Michael A.; Schultz, Norbert S.; Pottschmidt, Katja; Lee, Julia C.; September 2008; In English; 7th Microquasar Worksho, 1-5 Sep. 2008, Izmir, Turkey; Original contains color and black and white illustrations
Contract(s)/Grant(s): NNG06EO90A; 50OR0701
Copyright; Avail.: CASI: A02, Hardcopy
High-mass X-ray binary systems are powered by the stellar wind of their donor stars. The X-ray state of Cygnus X-1 is correlated with the properties of the wind which defines the environment of mass accretion. Chandra-HETGS observations close to orbital phase 0 allow for an analysis of the photoionzed stellar wind at high resolution, but because of the strong variability due to soft X-ray absorption dips, simultaneous multi-satellite observations are required to track and understand the continuum, too. Besides an earlier joint Chandra and RXTE observation, we present first results from a recent campaign which represents the best broad-band spectrum of Cyg X-1 ever achieved: On 2008 April 18/19 we observed this source with XMM-Newton, Chandra, Suzaku, RXTE, INTEGRAL, Swift, and AGILE in X- and gamma-rays, as well as with VLA in the radio. After superior conjunction of the black hole, we detect soft X-ray absorption dips likely due to clumps in the focused wind covering greater than or equal to 95% of the X-ray source, with column densities likely to be of several 10(exp 23) cm(exp -2), which also affect photon energies above 20 keV via Compton scattering.
Author
CYGNUS CONSTELLATION; SATELLITE OBSERVATION; STELLAR WINDS; X RAY ABSORPTION
20090005036 NASA Goddard Space Flight Center, Greenbelt, MD, United States
Modelling a Simultaneous Radio/X-Ray Flare from Cyg X-1
Leventis, Konstantinos; Markoff, Sera; Wilsm, Joern; Nowak, Michael A.; Maitra, Dipankar; Pottschmidt, Katja; Pooley, Guy G.; Kreykenbohm, Ingo; Rotschild, Richard E.; September 2008; In English; 7th Microquasar Workshop: Microquasars and Beyond, 1-5 Sep. 2008, Izmir, Turkey; Original contains color and black and white illustrations
Contract(s)/Grant(s): NNG06EO90A
Copyright; Avail.: CASI: A01, Hardcopy
The long-term monitoring campaign of Cyg X-1 has provided the detection of the first simultaneous radio/X-ray flare seen from that source. We investigate the physical characteristics of the event in terms of emission from a homogeneous, expanding blob of pair-plasma, superimposed on a baseline flux in both bands. We find that while the radio flare can be reconstructed under various configurations of a cooling blob, continuous (re)acceleration of particles inside the jet is necessary to sustain X-ray emission at the levels implied by the data, for the observed duration. We present major results of the modelling and discuss implications for the role of microquasar jets.
Author
CYGNUS CONSTELLATION; RADIO EMISSION; FLARES; ASTRONOMICAL MODELS
20090005037 NASA Goddard Space Flight Center, Greenbelt, MD, United States
Automatic Extraction of Planetary Image Features
Troglio, G.; LeMoigne, J.; Moser, G.; Serpico, S. B.; Benediktsson, J. A.; [2009]; In English; Third International Conference on Space Mission Challenges for Information Technology (SMC-IT 2009), 19-23 Jul. 2009, Pasadena, CA, United States; Original contains color illustrations
Copyright; Avail.: CASI: A01, Hardcopy
With the launch of several Lunar missions such as the Lunar Reconnaissance Orbiter (LRO) and Chandrayaan-1, a large amount of Lunar images will be acquired and will need to be analyzed. Although many automatic feature extraction methods have been proposed and utilized for Earth remote sensing images, these methods are not always applicable to Lunar data that often present low contrast and uneven illumination characteristics. In this paper, we propose a new method for the extraction of Lunar features (that can be generalized to other planetary images), based on the combination of several image processing techniques, a watershed segmentation and the generalized Hough Transform. This feature extraction has many applications, among which image registration.
Author
IMAGE PROCESSING; DATA ACQUISITION; PATTERN RECOGNITION; PATTERN REGISTRATION; ALGORITHMS; LUNAR EXPLORATION
20090005038 NASA Goddard Space Flight Center, Greenbelt, MD, United States
Global Land Data Assimilation System (GLDAS) Products, Services and Application from NASA Hydrology Data and Information Services Center (HDISC)
Fang, Hongliang; Beaudoing, Hiroko K.; Rodell, matthew; Teng, William L.; Vollmer, Bruce E.; [2009]; In English; ASPRS 2009 Annual Conference, 8-31 Mar. 2009, Baltimore, MD, United States; Original contains color and black and white illustrations
Copyright; Avail.: CASI: A02, Hardcopy
The Global Land Data Assimilation System (GLDAS) is generating a series of land surface state (e.g., soil moisture and surface temperature) and flux (e.g., evaporation and sensible heat flux) products simulated by four land surface models (CLM, Mosaic, Noah and VIC). These products are now accessible at the Hydrology Data and Information Services Center (HDISC), a component of the NASA Goddard Earth Sciences Data and Information Services Center (GES DISC). Current data holdings include a set of 1.0 degree resolution data products from the four models, covering 1979 to the present; and a 0.25 degree data product from the Noah model, covering 2000 to the present. The products are in Gridded Binary (GRIB) format and can be accessed through a number of interfaces. Users can search the products through keywords and perform on-the-fly spatial and parameter subsetting and format conversion of selected data. More advanced visualization, access and analysis capabilities will be available in the future. The long term GLDAS data are used to develop climatology of water cycle components and to explore the teleconnections of droughts and pluvial.
Author
LAND MANAGEMENT; EARTH SCIENCES; DATA ACQUISITION; DATA INTEGRATION; INFORMATION SYSTEMS; CLIMATOLOGY; HYDROLOGY
20090005039 NASA Goddard Space Flight Center, Greenbelt, MD, United States
Mechanical Overview of the International X-Ray Observatory
Robinson, David W.; McClelland, Ryan S.; [2009]; In English; 2009 IEEE Aerospace Conference, 7-14 Mar. 2009, Big Sky, MT, United States; Original contains color and black and white illustrations
Copyright; Avail.: CASI: A02, Hardcopy
The International X-ray Observatory (IXO) is a new collaboration between NASA, ESA, and JAXA which is under study for launch in 2020. IXO will be a large 6600 kilogram Great Observatory-class mission which will build upon the legacies of the Chandra and XMM-Newton X-ray observatories. It combines elements from NASA's Constellation-X program and ESA's XEUS program. The observatory will have a 20-25 meter focal length, which necessitates the use of a deployable instrument module. Currently the project is actively trading configurations and layouts of the various instruments and spacecraft components. This paper will provide a snapshot of the latest observatory configuration under consideration and summarize the observatory from the mechanical engineering perspective.
Author
ASTRONOMICAL OBSERVATORIES; SPACECRAFT CONFIGURATIONS; MECHANICAL ENGINEERING
Additions to the NASA Aeronautics and Space Database as of 02/10/2009
20090005099 NASA Johnson Space Center, Houston, TX, United States
Solid State Light Evaluation in the U.S. Lab Mockup
Maida, James c.; Bowen, Charles K.; Wheelwright, Chuck; January 09, 2009; In English; Original contains color and black and white illustrations
Copyright; Avail.: CASI: A03, Hardcopy
This document constitutes the publication of work performed by the Space Human Factors Laboratory (mail code SF5 at the time) at the Johnson Space Center (JSC) in the months of June and July of 2000. At that time, the Space Human Factors Laboratory was part of the Space Human Factors Branch in the Flight Projects Division of the Space and Life Directorate. This report was originally to be a document for internal consumption only at JSC as it was seen to be only preliminary work for the further development of solid state illumination for general lighting on future space vehicles and the International Space Station (ISS). Due to funding constraints, immediate follow-on efforts were delayed and the need for publication of this document was overcome by other events. However, in recent years and with the development and deployment of a solid state light luminaire prototype on ISS, the time was overdue for publishing this information for general distribution and reference. Solid state lights (SSLs) are being developed to potentially replace the general luminaire assemblies (GLAs) currently in service in the International Space Station (ISS) and included in designs of modules for the ISS. The SSLs consist of arrays of light emitting diodes (LEDs), small solid state electronic devices that produce visible light in proportion to the electrical current flowing through them. Recent progressive advances in electrical power-to-light conversion efficiency in LED technology have allowed the consideration of LEDs as replacements for incandescent and fluorescent light sources in many circumstances, and their inherent advantages in ruggedness, reliability, and life expectancy make them attractive for applications in spacecraft. One potential area of application for the SSLs in the U.S. Laboratory Module of the ISS. This study addresses the suitability of the SSLs as replacements for the GLAs in this application.
Derived from text
INTERNATIONAL SPACE STATION; LIGHT SOURCES; SOLID STATE DEVICES; HUMAN FACTORS ENGINEERING; LIGHT ADAPTATION
20090005100 Jet Propulsion Lab., California Inst. of Tech., Pasadena, CA, United States
Radiation Tests of Highly Scaled High Density Commercial Nonvolatile Flash Memories
Irom, Farokh; Nguyen, Duc N.; December 2008; In English; Original contains color and black and white illustrations
Contract(s)/Grant(s): NAS7-03001Proj. 102197
Report No.(s): JPL Publication 08-27; Copyright; Avail.: CASI: A03, Hardcopy
We tested the advanced commercial high density 8 Gb NAND flash memory from Samsung with heavy ions. We also tested the advanced commercial NOR flash memory from Spansion. The general conclusion is that the SEU and SEFI cross section is smaller than the older generation of flash memories. Another observation is a new high current phenomenon in the high density NAND and NOR flash memories. This high current phenomenon is destructive for Samsung NAND flash memory during READ and PROGRAM modes and during PROGRAM mode for Spansion NOR flash. The results in this report show that the high current phenomenon in scaled devices is a complex problem that is not fully understood. Processing details and oxide defects appear to play a role in gate rupture, and the differences in experimental observations by different groups may be because of difference in semiconductor processing. More work needs to be done to increase the level of understanding as well as how it may affect highly scaled commercial devices. The high current spikes phenomenon is on verge of becoming a serious problem as scaling continues and the transistors sizes become comparable to ion track widths.
Author
COMPUTER STORAGE DEVICES; ELECTRONIC EQUIPMENT; TEST FACILITIES; MEMORY (COMPUTERS); RADIATION
Additions to the NASA Aeronautics and Space Database as of 02/12/2009
20090005167 NASA Dryden Flight Research Center, Edwards, CA, United States
X-48B Flight Research Progress Overview
Risch, Tim; Cosentino, Gary; Regan, Chris; Kisska, Michael; Princen, Norman; January 05, 2009; In English; 47th AIAA Aerospace Sciences Meeting, 5-8 Jan. 2009, Orlando, FL., United States; Original contains color and black and white illustrations
Copyright; Avail.: CASI: A03, Hardcopy
Program Objectives; I. Assess stability & control characteristics of a BWB class vehicle in free-flight conditions: a) Assess dynamic interaction of control surfaces; b) Assess control requirements to accommodate asymmetric thrust; c) Assess stability and controllability about each axis at a range of flight conditions II. Assess flight control algorithms designed to provide desired flight characteristics: a) Assess control surface allocation and blending; b) Assess edge of envelope protection schemes; c) Assess takeoff and landing characteristics; d) Test experimental control laws and control design methods. III. Evaluate prediction and test methods for BWB class vehicles: a) Correlate flight measurements with ground-based predictions and measurements.
Author
AERODYNAMIC CHARACTERISTICS; BLENDED-WING-BODY CONFIGURATIONS; CONTROL THEORY; IN-FLIGHT MONITORING; PREDICTION ANALYSIS TECHNIQUES; FLIGHT CONTROL
20090005170 Jet Propulsion Lab., California Inst. of Tech., Pasadena, CA, United States
Distribution Automation Applications of Fiber Optics
Kirkham, Harold; Johnston, Alan; Friend, Heather; October 15, 2008; In English; Original contains black and white illustrations
Contract(s)/Grant(s): NAS7-03001; DE-AI01-79ET 29372 (Mod. A009)
Report No.(s): Jpl Publication 89-10, Rev A; No Copyright; Avail.: CASI: A06, Hardcopy
Avail Online: http://hdl.handle.net/2060/20090005170
Motivations for interest and research in distribution automation are discussed. The communication requirements of distribution automation are examined, and shown to exceed the capabilities of power line carrier, radio and telephone systems. A fiber-optic-based communication system is described that is co-located with the distribution system and that could satisfy the data rate and reliability requirements. A cost comparison shows that it could be constructed at a cost that is similar to that of a power line carrier system. The requirements for fiber optic sensors for distribution automation are discussed. The design of a data link suitable for optically-powered electronic sensing is presented. Empirical results are given. A modeling technique that has been used to understand the reflections of guided light from a variety of surfaces is described. An optical position indicator design is discussed. Systems aspects of distribution automation are discussed, in particular the lack of interface, communications and data standards. The economics of distribution automation are examined.
Author
FIBER OPTICS; AUTOMATION; ECONOMICS; ELECTRIC POWER
20090005178 NASA Glenn Research Center, Cleveland, OH, United States
Testing of a Microwave Blade Tip Clearance Sensor at the NASA Glenn Research Center
Woike, Mark R.; Roeder, James W.; Hughes, Christopher E.; Bencic, Timothy J.; January 05, 2009; In English; 47th AIAA Aerosciences Conference, 5-8 Jan. 2009, Orlando, FL, United States; Original contains color and black and white illustrations
Contract(s)/Grant(s): WBS 984754.02.07.03.13.06
Report No.(s): E-16826; No Copyright; Avail.: CASI: A03, Hardcopy
Avail Online: http://hdl.handle.net/2060/20090005178
The development of new active tip clearance control and structural health monitoring schemes in turbine engines and other types of rotating machinery requires sensors that are highly accurate and can operate in a high temperature environment. The use of a microwave sensor to acquire blade tip clearance and tip timing measurements is being explored at the NASA Glenn Research Center. The microwave blade tip clearance sensor works on principles that are very similar to a short range radar system. The sensor sends a continuous microwave signal towards a target and measures the reflected signal. The phase difference of the reflected signal is directly proportional to the distance between the sensor and the target being measured. This type of sensor is beneficial in that it has the ability to operate at extremely high temperatures and is unaffected by contaminants that may be present in turbine engines. The use of microwave sensors for this application is a new concept. Techniques on calibrating the sensors along with installation effects are not well quantified as they are for other sensor technologies. Developing calibration techniques and evaluating installation effects are essential in using these sensors to make tip clearance and tip timing measurements. As a means of better understanding these issues, the microwave sensors were used on a bench top calibration rig, a large axial vane fan, and a turbofan. Background on the microwave tip clearance sensor, an overview of their calibration, and the results from their use on the axial vane fan and the turbofan will be presented in this paper.
Author
BLADE TIPS; MICROWAVE SENSORS; TURBINE ENGINES; CLEARANCES; TIME MEASUREMENT; CONTAMINANTS; HIGH TEMPERATURE ENVIRONMENTS; ACTIVE CONTROL; CALIBRATING
20090005179 Lockheed Martin Engineering and Science Services, Hampton, VA, United States
Characterization of Solid Polymers, Ceramic Gap Filler, and Closed-Cell Polymer Foam Using Low-Load Test Methods
Herring, Helen M.; December 2008; In English; Original contains color and black and white illustrations
Contract(s)/Grant(s): NNL07AA00BTask NNL07AM74T; WBS-510505.03.07.01.07
Report No.(s): NASA/CR-2008-215538; LF99-7926; Copyright; Avail.: CASI: A03, Hardcopy
Various solid polymers, polymer-based composites, and closed-cell polymer foam are being characterized to determine their mechanical properties, using low-load test methods. The residual mechanical properties of these materials after environmental exposure or extreme usage conditions determines their value in aerospace structural applications. In this experimental study, four separate polymers were evaluated to measure their individual mechanical responses after thermal aging and moisture exposure by dynamic mechanical analysis. A ceramic gap filler, used in the gaps between the tiles on the Space Shuttle, was also tested, using dynamic mechanical analysis to determine material property limits during flight. Closed-cell polymer foam, used for the Space Shuttle External Tank insulation, was tested under low load levels to evaluate how the foam's mechanical properties are affected by various loading and unloading scenarios.
Author
MECHANICAL PROPERTIES; CERAMICS; FILLERS; FOAMS; POLYMERS; AGING (MATERIALS); LOAD TESTS; STRUCTURAL DESIGN; TEMPERATURE EFFECTS
20090005180 NASA Dryden Flight Research Center, Edwards, CA, United States
Tests and Techniques for Characterizing and Modeling X-43A Electromechanical Actuators
Lin, Yohan; Baumann, Ethan; Bose, David M.; Beck, Roger; Jenney, Gavin; December 2008; In English; Original contains color and black and white illustrations
Report No.(s): NASA/TM-2008-214637; H-2819; DFRC-434; Copyright; Avail.: CASI: A05, Hardcopy
A series of tests were conducted on the electromechanical actuators of the X-43A research vehicle in preparation for the Mach 7 and 10 hypersonic flights. The tests were required to help validate the actuator models in the simulation and acquire a better understanding of the installed system characteristics. Static and dynamic threshold, multichannel crosstalk, command-to-surface timing, free play, voltage regeneration, calibration, frequency response, compliance, hysteretic damping, and aircraft-in-the-loop tests were performed as part of this effort. This report describes the objectives, configurations, and methods for those tests, as well as the techniques used for developing second-order actuator models from the test results. When the first flight attempt failed because of actuator problems with the launch vehicle, further analysis and model enhancements were performed as part of the return-to-flight activities. High-fidelity models are described, along with the modifications that were required to match measurements taken from the research vehicle. Problems involving the implementation of these models into the X-43A simulation are also discussed. This report emphasizes lessons learned from the actuator testing, simulation modeling, and integration efforts for the X-43A hypersonic research vehicle.
Author
ACTUATORS; FREQUENCY RESPONSE; HYPERSONIC VEHICLES; X-45 AIRCRAFT; RESEARCH VEHICLES; ELECTROMECHANICAL DEVICES; PROVING
20090005181 NASA Dryden Flight Research Center, Edwards, CA, United States
Ground/Flight Correlation of Aerodynamic Loads with Structural Response
Mangalam, Arun S.; Davis, Mark C.; January 05, 2009; In English; 47th AIAA Aerospace Sciences Meeting and Exhibit, 5-8 Jan. 2009, Orlando, FL, United States; Original contains color illustrations
Report No.(s): DFRC-835; Copyright; Avail.: CASI: A03, Hardcopy
Ground and flight tests provide a basis and methodology for in-flight characterization of the aerodynamic and structural performance through the monitoring of the fluid-structure interaction. The NF-15B flight tests of the Intelligent Flight Control System program provided a unique opportunity to test the correlation of aerodynamic loads with points of flow attaching and detaching from the surface, which are also known as flow bifurcation points, as observed in a previous wind tunnel test performed at the U.S. Air Force Academy (Colorado Springs, Colorado). Moreover, flight tests, along with the subsequent unsteady aerodynamic tests in the NASA Transonic Dynamics Tunnel (TDT), provide a basis using surface flow sensors as means of assessing the aeroelastic performance of flight vehicles. For the flight tests, the NF-15B tail was instrumented with hot-film sensors and strain gages for measuring root-bending strains. This data were gathered via selected sideslip maneuvers performed at level flight and subsonic speeds. The aerodynamic loads generated by the sideslip maneuver resulted in a structural response, which were then compared with the hot-film sensor signals. The hot-film sensor signals near the stagnation region were found to be highly correlated with the root-bending strains. For the TDT tests, a flexible wing section developed under the U.S. Air Force Research Lab SensorCraft program was instrumented with strain gages, accelerometers, and hot-film sensors at two span stations. The TDT tests confirmed the correlation between flow bifurcation points and the wing structural response to tunnel-generated gusts. Furthermore, as the wings structural modes were excited by the gusts, a gradual phase change between the flow bifurcation point and the structural mode occurred during a resonant condition.
Author
AERODYNAMIC LOADS; FLIGHT TESTS; GROUND TESTS; UNSTEADY AERODYNAMICS; STRAIN GAGES
20090005183 NASA Johnson Space Center, Houston, TX, United States
Impact Histories of Vesta and Vestoids inferred from Howardites, Eucrites, and Diogenites
Scott, E. R. D.; Bogard, D. D.; Bottke, W. F.; Taylor, G. J.; Greenwood, R. C.; Franchi, I. A.; Keil, K.; Moskovitz, N. A.; Nesvorny, D.; [2009]; In English; 40th Lunar Planetary Conference, 23-27 Mar. 2009, Houston, TX, United States; Original contains color illustrations
Copyright; Avail.: CASI: A01, Hardcopy
The parent body of the howardites, eucrites and diogenites (HEDs) is thought to be asteroid (4) Vesta [1]. However, several eucrites have now been recognized, like NWA 011 and Ibitira, with major element compositions and mineralogy like normal eucrites but with different oxygen isotope compositions and minor element concentrations suggesting they are not from the same body [2, 3]. The discoveries of abnormal eucrites and V-type asteroids that are probably not from Vesta [see 4] raise the question whether the HEDs with normal oxygen isotopes are coming from Vesta [3]. To address this issue and understand more about the evolution of Vesta in preparation for the arrival of the Dawn spacecraft, we integrate fresh insights from Ar-Ar dating and oxygen isotope analyses of HEDs, radiometric dating of differentiated meteorites, as well as dynamical and astronomical studies of Vesta, the Vesta asteroid family (i.e., the Vestoids), and other V-type asteroids.
Author
VESTA ASTEROID; METEORITES; ASTEROIDS; ACHONDRITES; CHRONOLOGY; METEORITIC COMPOSITION
20090005184 NASA Johnson Space Center, Houston, TX, United States
A Process for Comparing Dynamics of Distributed Space Systems Simulations
Cures, Edwin Z.; Jackson, Albert A.; Morris, Jeffery C.; [2009]; In English; Joint 2009 Spring Simkulation Interoperability Workshop (SIW), 23-27 Mar. 2009, San DIego, CA, United States
Copyright; Avail.: CASI: A03, Hardcopy
The paper describes a process that was developed for comparing the primary orbital dynamics behavior between space systems distributed simulations. This process is used to characterize and understand the fundamental fidelities and compatibilities of the modeling of orbital dynamics between spacecraft simulations. This is required for high-latency distributed simulations such as NASA s Integrated Mission Simulation and must be understood when reporting results from simulation executions. This paper presents 10 principal comparison tests along with their rationale and examples of the results. The Integrated Mission Simulation (IMSim) (formerly know as the Distributed Space Exploration Simulation (DSES)) is a NASA research and development project focusing on the technologies and processes that are related to the collaborative simulation of complex space systems involved in the exploration of our solar system. Currently, the NASA centers that are actively participating in the IMSim project are the Ames Research Center, the Jet Propulsion Laboratory (JPL), the Johnson Space Center (JSC), the Kennedy Space Center, the Langley Research Center and the Marshall Space Flight Center. In concept, each center participating in IMSim has its own set of simulation models and environment(s). These simulation tools are used to build the various simulation products that are used for scientific investigation, engineering analysis, system design, training, planning, operations and more. Working individually, these production simulations provide important data to various NASA projects.
Author
AEROSPACE SYSTEMS; SYSTEMS ENGINEERING; COMPUTERIZED SIMULATION; COMPLEX SYSTEMS
20090005185 NASA Johnson Space Center, Houston, TX, United States; United Space Alliance, Houston, TX, United States
Hubble Servicing Challenges Drive Innovation of Shuttle Rendezvous Techniques
Goodman, John L.; Walker, Stephen R.; January 31, 2009; In English; 32nd Annual AAS Guidance and Control Conference, 31 Jan. - 4 Feb. 2009, Breckenridge, CO, United States; Original contains color and black and white illustrations
Report No.(s): AAS 09-013; Copyright; Avail.: CASI: A03, Hardcopy
Hubble Space Telescope (HST) servicing, performed by Space Shuttle crews, has contributed to what is arguably one of the most successful astronomy missions ever flown. Both nominal and contingency proximity operations techniques were developed to enable successful servicing, while lowering the risk of damage to HST systems, and improve crew safety. Influencing the development of these techniques were the challenges presented by plume impingement and HST performance anomalies. The design of both the HST and the Space Shuttle was completed before the potential of HST contamination and structural damage by shuttle RCS jet plume impingement was fully understood. Relative navigation during proximity operations has been challenging, as HST was not equipped with relative navigation aids. Since HST reached orbit in 1990, proximity operations design for servicing missions has evolved as insight into plume contamination and dynamic pressure has improved and new relative navigation tools have become available. Servicing missions have provided NASA with opportunities to gain insight into servicing mission design and development of nominal and contingency procedures. The HST servicing experiences and lessons learned are applicable to other programs that perform on-orbit servicing and rendezvous, both human and robotic.
Author
HUBBLE SPACE TELESCOPE; MAINTENANCE; SPACEBORNE TELESCOPES; ROBOTICS; NAVIGATION AIDS; DYNAMIC PRESSURE; SPACECREWS; SPACE SHUTTLES
20090005186 NASA Dryden Flight Research Center, Edwards, CA, United States
CFD Analysis of Nozzle Jet Plume Effects on Sonic Boom Signature
Bui, Trong T.; January 05, 2009; In English; 47th AIAA Aerospace Sciences Meeting, 5-8 Jan. 2009, Orlando, FL, FROM; Original contains color and black and white illustrations
Report No.(s): DFRC-843; AIAA Paper 2009-1054; No Copyright; Avail.: CASI: A03, Hardcopy
Avail Online: http://hdl.handle.net/2060/20090005186
An axisymmetric full Navier-Stokes computational fluid dynamics study is conducted to examine nozzle exhaust jet plume effects on the sonic boom signature of a supersonic aircraft. A simplified axisymmetric nozzle geometry, representative of the nozzle on the NASA Dryden NF-15B Lift and Nozzle Change Effects on Tail Shock research airplane, is considered. The computational fluid dynamics code is validated using available wind-tunnel sonic boom experimental data. The effects of grid size, spatial order of accuracy, grid type, and flow viscosity on the accuracy of the predicted sonic boom pressure signature are quantified. Grid lines parallel to the Mach wave direction are found to give the best results. Second-order accurate upwind methods are required as a minimum for accurate sonic boom simulations. The highly underexpanded nozzle flow is found to provide significantly more reduction in the tail shock strength in the sonic boom N-wave pressure signature than perfectly expanded and overexpanded nozzle flows. A tail shock train in the sonic boom signature is observed for the highly underexpanded nozzle flow. Axisymmetric computational fluid dynamics simulations show the flow physics inside the F-15 nozzle to be nonisentropic and complex. Although the one-dimensional isentropic nozzle plume results look reasonable, they fail to capture the sonic boom shock train in the highly underexpanded nozzle flow.
Author
COMPUTATIONAL FLUID DYNAMICS; PLUMES; NOZZLE FLOW; GAS JETS; SONIC BOOMS; SIGNATURES; NOZZLE GEOMETRY; COMPUTATIONAL GRIDS
20090005210 Eltron Research, Inc., Boulder, CO United States
Polymer composites containing nanotubes
Bley, Richard A., Inventor; August 12, 2008; In English
Contract(s)/Grant(s): NAS9-00116; NAS9-00028
Patent Info.: August 25, 2004US-Patent-7,411,019; US-Patent-Appl-SN-10/927,628
No Copyright; Avail.: CASI: A03, Hardcopy
Avail Online: http://hdl.handle.net/2060/20090005210
The present invention relates to polymer composite materials containing carbon nanotubes, particularly to those containing singled-walled nanotubes. The invention provides a polymer composite comprising one or more base polymers, one or more functionalized m-phenylenevinylene-2,5-disubstituted-p-phenylenevinylene polymers and carbon nanotubes. The invention also relates to functionalized m-phenylenevinylene-2,5-disubstituted-p-phenylenevinylene polymers, particularly to m-phenylenevinylene-2,5-disubstituted-p-phenylenevinylene polymers having side chain functionalization, and more particularly to m-phenylenevinylene-2,5-disubstituted-p-phenylenevinylene polymers having olefin side chains and alkyl epoxy side chains. The invention further relates to methods of making polymer composites comprising carbon nanotubes.
Official Gazette of the U.S. Patent and Trademark Office
CARBON NANOTUBES; COMPOSITE MATERIALS; POLYMER MATRIX COMPOSITES; POLYMERS
20090005211 NASA, Washington, DC United States
Guidance and control for an autonomous soaring UAV
Allen, Michael J., Inventor; October 7, 2008; In English
Patent Info.: March 23, 2006US-Patent-7,431,243; US-Patent-Appl-SN-11/277,325
No Copyright; Avail.: CASI: A03, Hardcopy
Avail Online: http://hdl.handle.net/2060/20090005211
The present invention provides a practical method for UAVs to take advantage of thermals in a manner similar to piloted aircrafts and soaring birds. In general, the invention is a method for a UAV to autonomously locate a thermal and be guided to the thermal to greatly improve range and endurance of the aircraft.
Official Gazette of the U.S. Patent and Trademark Office
AUTONOMY; SOARING; AIRCRAFT GUIDANCE; PILOTLESS AIRCRAFT; UNMANNED AIRCRAFT SYSTEMS; AIR CURRENTS
20090005212 SunPower, Inc., Athens, OH United States
Pulse tube cooler having 1/4 wavelength resonator tube instead of reservoir
Gedeon, David R., Inventor; October 14, 2008; In English
Contract(s)/Grant(s): NAS5-02021
Patent Info.: August 23, 2005US-Patent-7,434,409; US-Patent-Appl-SN-11/209,984
No Copyright; Avail.: CASI: A02, Hardcopy
Avail Online: http://hdl.handle.net/2060/20090005212
An improved pulse tube cooler having a resonator tube connected in place of a compliance volume or reservoir. The resonator tube has a length substantially equal to an integer multiple of 1/4 wavelength of an acoustic wave in the working gas within the resonator tube at its operating frequency, temperature and pressure. Preferably, the resonator tube is formed integrally with the inertance tube as a single, integral tube with a length approximately 1/2 of that wavelength. Also preferably, the integral tube is spaced outwardly from and coiled around the connection of the regenerator to the pulse tube at a cold region of the cooler and the turns of the coil are thermally bonded together to improve heat conduction through the coil.
Official Gazette of the U.S. Patent and Trademark Office
CRYOGENIC COOLING; CRYOGENIC EQUIPMENT; CRYOGENICS; RESONATORS
Additions to the NASA Aeronautics and Space Database as of 02/13/2009
20090005237 International Trade Bridge, Inc., Beavercreek, OH, United States; NASA Kennedy Space Center, Cocoa Beach, FL, United States
Final Report on NASA Portable Laser Coating Removal Systems Field Demonstrations and Testing
Rothgeb, Matthew J; McLaughlin, Russell L.; May 2008; In English; CD-ROM contains full text document in PDF format
Contract(s)/Grant(s): NNH06CC40C
Report No.(s): NASA/CR-2008-214752; Copyright; Avail.: CASI: C01, CD-ROM: A04, Hardcopy
Processes currently used throughout the National Aeronautics and Space Administration (NASA) to remove corrosion and coatings from structures, ground service equipment, small parts and flight components result in waste streams consisting of toxic chemicals, spent media blast materials, and waste water. When chemicals are used in these processes they are typically high in volatile organic compounds (VOC) and are considered hazardous air pollutants (HAP). When blast media is used, the volume of hazardous waste generated is increased significantly. Many of the coatings historically used within NASA contain toxic metals such as hexavalent chromium, and lead. These materials are highly regulated and restrictions on worker exposure continue to increase. Most recently the Occupational Safety and Health Administration (OSHA) reduced the permissible exposure limit (PEL) for hexavalent chromium (CrVI) from 52 to 5 micrograms per cubic meter of air as an 8-hour time-weighted average. Hexavalent chromium is found in numerous pretreatment and primer coatings used within the Space Shuttle Program. In response to the need to continue to protect assets within the agency and the growing concern over these new regulations, NASA is researching different ways to continue the required maintenance of both facility and flight equipment in a safe, efficient, and environmentally preferable manner. The use of laser energy to prepare surfaces for a variety of processes, such as corrosion and coating removal, weld preparation, and non destructive evaluation (NDE) is a relatively new application of the technology that has been proven to be environmentally preferable and in many cases less labor intensive than currently used removal methods. The novel process eliminates VOCs and blast media and captures the removed coatings with an integrated vacuum system. This means that the only waste generated are the coatings that are removed, resulting in an overall cleaner process. The development of a Portable Laser Coating Removal System (PLCRS) started as the goal of a Joint Group on Pollution Prevention (JG-PP) project, led by the Air Force, where several types of lasers in several configurations were thoroughly evaluated. Following this project, NASA decided to evaluate the best performers on processes and coatings specific to the agency. Laser systems used during this project were all of a similar design, between 40 and 500 Watts, most of which had integrated vacuum systems in order to collect materials removed from substrate surfaces during operation.
Derived from text
COATING; CORROSION; POLLUTION CONTROL; LASERS; PORTABLE EQUIPMENT; AIR POLLUTION
20090005240 NASA Johnson Space Center, Houston, TX, United States
Reliability of Strength Testing using the Advanced Resistive Exercise Device and Free Weights
English, Kirk L.; Loehr, James A.; Laughlin, Mitzi A.; Lee, Stuart M. C.; Hagan, R. Donald; [2008]; In English; Original contains color and black and white illustrations
Copyright; Avail.: CASI: A03, Hardcopy
The Advanced Resistive Exercise Device (ARED) was developed for use on the International Space Station as a countermeasure against muscle atrophy and decreased strength. This investigation examined the reliability of one-repetition maximum (1RM) strength testing using ARED and traditional free weight (FW) exercise. Methods: Six males (180.8 +/- 4.3 cm, 83.6 +/- 6.4 kg, 36 +/- 8 y, mean +/- SD) who had not engaged in resistive exercise for at least six months volunteered to participate in this project. Subjects completed four 1RM testing sessions each for FW and ARED (eight total sessions) using a balanced, randomized, crossover design. All testing using one device was completed before progressing to the other. During each session, 1RM was measured for the squat, heel raise, and deadlift exercises. Generalizability (G) and intraclass correlation coefficients (ICC) were calculated for each exercise on each device and were used to predict the number of sessions needed to obtain a reliable 1RM measurement (G . 0.90). Interclass reliability coefficients and Pearson's correlation coefficients (R) also were calculated for the highest 1RM value (1RM9sub peak)) obtained for each exercise on each device to quantify 1RM relationships between devices.
Author
CORRELATION COEFFICIENTS; PHYSICAL EXERCISE; MUSCLES; PERFORMANCE TESTS; MUSCULAR STRENGTH
20090005244 NASA Goddard Space Flight Center, Greenbelt, MD, United States
GFO and JASON Altimeter Engineering Assessment Report. Update: GFO--Acceptance to December 27, 2007, JASON--Acceptance to December 26, 2007. Version 1: June 2008
Conger, A. M.; Hancock, D. W.; Hayne, G. S.; Brooks, R. L.; September 2008; In English; Original contains color and black and white illustrations
Contract(s)/Grant(s): NNG06HX14C
Report No.(s): NASA/TM-2008-209984/Ver.1/Vol.10; 200802408; Copyright; Avail.: CASI: A09, Hardcopy
The purpose of this document is to present and document GEOSAT Follow-On (GFO) performance analyses and results. This is the eighth Assessment Report since the initial report. This report extends the performance assessment since acceptance to 27 December 2007. Since launch, a variety of GFO performance studies have been performed: Appendix A provides an accumulative index of those studies. We began the inclusion of analyses of the JASON altimeter after the end of the Topographic Experiment (TOPEX) mission. Prior to this, JASON and TOPEX were compared during our assessment of theTOPEX altimeter. With the end of the TOPEX mission, we developed methods to report on JASON as it relates to GFO.
Author
GEOSAT SATELLITES; ALTIMETERS; LAUNCHING
Additions to the NASA Aeronautics and Space Database as of 02/16/2009
20090005254 Boeing Co., Chicago, IL United States
Parametrically disciplined operation of a vibratory gyroscope
Shcheglov, Kirill V., Inventor; Hayworth, Ken J., Inventor; Challoner, A. Dorian, Inventor; Peay, Chris S., Inventor; October 14, 2008; In English
Contract(s)/Grant(s): NAS7-1402
Patent Info.: July 29, 2005US-Patent-7,437,253; US-Patent-Appl-SN-11/192,759
No Copyright; Avail.: CASI: A03, Hardcopy
Avail Online: http://hdl.handle.net/2060/20090005254
Parametrically disciplined operation of a symmetric nearly degenerate mode vibratory gyroscope is disclosed. A parametrically-disciplined inertial wave gyroscope having a natural oscillation frequency in the neighborhood of a sub-harmonic of an external stable clock reference is produced by driving an electrostatic bias electrode at approximately twice this sub-harmonic frequency to achieve disciplined frequency and phase operation of the resonator. A nearly symmetric parametrically-disciplined inertial wave gyroscope that can oscillate in any transverse direction and has more than one bias electrostatic electrode that can be independently driven at twice its oscillation frequency at an amplitude and phase that disciplines its damping to zero in any vibration direction. In addition, operation of a parametrically-disciplined inertial wave gyroscope is taught in which the precession rate of the driven vibration pattern is digitally disciplined to a prescribed non-zero reference value.
Official Gazette of the U.S. Patent and Trademark Office
PARAMETERIZATION; GYROSCOPES; VIBRATION
20090005255 Honeywell International, Inc., Morristown, NJ United States
Systems and methods for self-synchronized digital sampling
Samson, Jr., John R., Inventor; October 14, 2008; In English
Contract(s)/Grant(s): NAS8-01140
Patent Info.: November 1, 2005US-Patent-7,437,272; US-Patent-Appl-SN-11/264,566
No Copyright; Avail.: CASI: A02, Hardcopy
Avail Online: http://hdl.handle.net/2060/20090005255
Systems and methods for self-synchronized data sampling are provided. In one embodiment, a system for capturing synchronous data samples is provided. The system includes an analog to digital converter adapted to capture signals from one or more sensors and convert the signals into a stream of digital data samples at a sampling frequency determined by a sampling control signal; and a synchronizer coupled to the analog to digital converter and adapted to receive a rotational frequency signal from a rotating machine, wherein the synchronizer is further adapted to generate the sampling control signal, and wherein the sampling control signal is based on the rotational frequency signal.
Official Gazette of the U.S. Patent and Trademark Office
DATA SAMPLING; SYNCHRONISM; PULSE COMMUNICATION
20090005801 SunPower, Inc., Athens, OH United States
Multi-stage pulse tube cryocooler with acoustic impedance constructed to reduce transient cool down time and thermal loss
Gedeon, David R., Inventor; Wilson, Kyle B., Inventor; October 21, 2008; In English
Contract(s)/Grant(s): NAS5-02021
Patent Info.: August 23, 2005US-Patent-7,437,878; US-Patent-Appl-SN-11/209,983
No Copyright; Avail.: CASI: A02, Hardcopy
Avail Online: http://hdl.handle.net/2060/20090005801
The cool down time for a multi-stage, pulse tube cryocooler is reduced by configuring at least a portion of the acoustic impedance of a selected stage, higher than the first stage, so that it surrounds the cold head of the selected stage. The surrounding acoustic impedance of the selected stage is mounted in thermally conductive connection to the warm region of the selected stage for cooling the acoustic impedance and is fabricated of a high thermal diffusivity, low thermal radiation emissivity material, preferably aluminum.
Official Gazette of the U.S. Patent and Trademark Office
ACOUSTIC IMPEDANCE; CRYOGENIC COOLING; FABRICATION; LOSSES; THERMAL DIFFUSIVITY
20090005802 NASA, Washington, DC United States
Actuator operated microvalves
Okojie, Robert S., Inventor; October 21, 2008; In English
Patent Info.: August 26, 2005US-Patent-7,438,030; US-Patent-Appl-SN-11/213,604
No Copyright; Avail.: CASI: A03, Hardcopy
Avail Online: http://hdl.handle.net/2060/20090005802
An actuator operated microvalve and the method of making same is disclosed and claimed. The microvalve comprises a SiC housing which includes a first lower portion and a second upper portion. The lower portion of the SiC housing includes a passageway therethrough, a microvalve seat, and a moveable SiC diaphragm. The SiC diaphragm includes a centrally located boss and radially extending corrugations which may be sinusoidally shaped. The boss of the SiC diaphragm moves and modulates in a range of positions between a closed position wherein the boss interengages said microvalve seat prohibiting communication of fluid through the passageway and a fully open position when the boss is spaced apart from the seat at its maximum permitting communication of fluid through said passageway. The actuator includes a SiC top plate affixed to the boss of the diaphragm and a first electrode and the second upper portion of the SiC housing further includes a second electrode.
Official Gazette of the U.S. Patent and Trademark Office
ACTUATORS; VALVES; SILICON CARBIDES
20090005852 NASA Kennedy Space Center, Cocoa Beach, FL, United States
Volume Averaged Height Integrated Radar Reflectivity (VAHIRR) Cost-Benefit Analysis
Bauman, William H., III; October 2008; In English; Original contains color illustrations
Contract(s)/Grant(s): NNK06MA70C
Report No.(s): NASA/CR-2008-214753; Copyright; Avail.: CASI: A03, Hardcopy
Lightning Launch Commit Criteria (LLCC) are designed to prevent space launch vehicles from flight through environments conducive to natural or triggered lightning and are used for all U.S. government and commercial launches at government and civilian ranges. They are maintained by a committee known as the NASA/USAF Lightning Advisory Panel (LAP). The previous LLCC for anvil cloud, meant to avoid triggered lightning, have been shown to be overly restrictive. Some of these rules have had such high safety margins that they prohibited flight under conditions that are now thought to be safe 90% of the time, leading to costly launch delays and scrubs. The LLCC for anvil clouds was upgraded in the summer of 2005 to incorporate results from the Airborne Field Mill (ABFM) experiment at the Eastern Range (ER). Numerous combinations of parameters were considered to develop the best correlation of operational weather observations to in-cloud electric fields capable of rocket triggered lightning in anvil clouds. The Volume Averaged Height Integrated Radar Reflectivity (VAHIRR) was the best metric found. Dr. Harry Koons of Aerospace Corporation conducted a risk analysis of the VAHIRR product. The results indicated that the LLCC based on the VAHIRR product would pose a negligible risk of flying through hazardous electric fields. Based on these findings, the Kennedy Space Center Weather Office is considering seeking funding for development of an automated VAHIRR algorithm for the new ER 45th Weather Squadron (45 WS) RadTec 431250 weather radar and Weather Surveillance Radar-1988 Doppler (WSR-88D) radars. Before developing an automated algorithm, the Applied Meteorology Unit (AMU) was tasked to determine the frequency with which VAHIRR would have allowed a launch to safely proceed during weather conditions otherwise deemed "red" by the Launch Weather Officer. To do this, the AMU manually calculated VAHIRR values based on candidate cases from past launches with known anvil cloud LLCC violations. An automated algorithm may be developed if the analyses from past launches show VAHIRR would have provided a significant cost benefit by allowing a launch to proceed. The 45 WS at the ER and 30th Weather Squadron (30 WS) at the Western Range provided the AMU with launch weather summaries from past launches that were impacted by LLCC. The 45 WS provided summaries from 14 launch attempts and the 30 WS fkom 5. The launch attempts occurred between December 2001 and June 2007. These summaries helped the AMU determine when the LLCC were "red" due to anvil cloud. The AMU collected WSR-88D radar reflectivity, cloud-to-ground lightning strikes, soundings and satellite imagery. The AMU used step-by-step instructions for calculating VAHIRR manually as provided by the 45 WS. These instructions were used for all of the candidate cases when anvil cloud caused an LLCC violation identified in the launch weather summaries. The AMU evaluated several software programs capable of visualizing radar data so that VAHIRR could be calculated and chose GR2Analyst from Gibson Ridge Software, LLC. Data availability and lack of detail from some launch weather summaries permitted analysis of six launch attempts from the ER and none from the WR. The AMU did not take into account whether or not other weather LCC violations were occurring at the same time as the anvil cloud LLCC since the goal of this task was to determine how often VAHIRR provided relief to the anvil cloud LLCC at any time during several previous launch attempts. Therefore, in the statistics presented in this report, it is possible that even though VAHIRR provided relief to the anvil cloud LLCC, other weather LCC could have been violated not permitting the launch to proceed. The results of this cost-benefit analysis indicated VAHIRR provided relief from the anvil cloud LLCC between about 15% and 18% of the time for varying 5-minute time periods based on summaries fkom six launch attempts and would have allowed launch to proceed that were otherwise "NO GO" due to the anvil cloud LLCC if the T-0 time occurred during the anvil cloud LLCC violations.
Derived from text
FLIGHT CONDITIONS; LIGHTNING; REFLECTANCE; SPACECRAFT LAUNCHING; WEATHER FORECASTING; METEOROLOGICAL RADAR; LAUNCH WINDOWS
20090005854 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; October 21, 2008; In English
Patent Info.: February 2, 2007US-Patent-7,438,264; US-Patent-Appl-SN-11/670,781
No Copyright; Avail.: CASI: A03, Hardcopy
Avail Online: http://hdl.handle.net/2060/20090005854
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.In one embodiment, a vehicle used for carrying out the method of this invention comprises an ejection module, which includes the robot, and a de-orbit module. Once servicing is completed by the robot, the ejection module separates from the de-orbit module, leaving the de-orbit module attached to the satellite for de-orbiting the same at a future time. Upon separation, the ejection module can either de-orbit itself or rendezvous with another satellite for servicing. The ability to de-orbit a spacecraft further allows the opportunity to direct the landing of the spent satellite in a safe location away from population centers, such as the ocean.
Official Gazette of the U.S. Patent and Trademark Office
AUTONOMY; ORBITAL RENDEZVOUS; ROBOTICS; SPACECRAFT MAINTENANCE; SPACECRAFT REENTRY
20090005855 NASA, Washington, DC United States
Simplified night sky display system
Castellano, Timothy P., Inventor; October 21, 2008; In English
Patent Info.: January 18, 2006US-Patent-7,438,422; US-Patent-Appl-SN-11/340,816
No Copyright; Avail.: CASI: A02, Hardcopy
Avail Online: http://hdl.handle.net/2060/20090005855
A portable structure, simply constructed with inexpensive and generally lightweight materials, for displaying a selected portion of the night sky and selected planets, satellites, comets and other astronomically observable objects that are visually perceptible within that portion of the night sky. The structure includes a computer having stored signals representing the observable objects, an image projector that converts and projects the stored signals as visually perceptible images, a first curvilinear light-reflecting surface to receive and reflect the visually perceptible images, and a second curvilinear surface to receive and display the visually perceptible images reflected from the first surface. The images may be motionless or may move with passage of time. In one embodiment, the structure includes an inflatable screen surface that receives gas in an enclosed volume, supports itself without further mechanical support, and optionally self-regulates pressure of the received gas within the enclosed volume.
Official Gazette of the U.S. Patent and Trademark Office
DISPLAY DEVICES; NIGHT SKY; PROJECTORS; PLANETARIUMS; ASTRONOMICAL MODELS
20090005856 City Univ. of New York, NY United States
Tetravalent chromium doped laser materials and NIR tunable lasers
Alfano, Robert R., Inventor; Petricevic, Vladimir, Inventor; Bykov, Alexey, Inventor; October 21, 2008; In English
Contract(s)/Grant(s): NCC1-03009
Patent Info.: December 7, 2005US-Patent-7,440,480; US-Patent-Appl-SN-11/295,749
No Copyright; Avail.: CASI: A03, Hardcopy
Avail Online: http://hdl.handle.net/2060/20090005856
A method is described to improve and produce purer Cr.sup.4+-doped laser materials and lasers with reduced co-incorporation of chromium in any other valence states, such as Cr.sup.3+, Cr.sup.2+, Cr.sup.5+, and Cr.sup.6+. The method includes: 1) certain crystals of olivine structure with large cation (Ca) in octahedral sites such as Cr.sup.4+:Ca.sub.2GeO.sub.4, Cr.sup.4+:Ca.sub.2SiO.sub.4, Cr.sup.4+:Ca.sub.2Ge.sub.xSi.sub.1-xO.sub.4 (where 0<x<1), and/or 2) high-temperature solution growth techniques that enable the growth of the crystals below the temperature of polymorphic transitions by using low melting point solvent based on oxide, fluoride and/or chloride compounds. Purer Cr.sup.4+-doped laser materials are characterized by a relatively high concentration of Cr.sup.4+-lasing ion in crystalline host that makes these materials suitable for compact high power (thin disk/wedge) NIR laser applications.
Official Gazette of the U.S. Patent and Trademark Office
ADDITIVES; CHROMIUM; LASER MATERIALS; LASERS; TUNABLE LASERS
20090005857 International Trade Bridge, Inc., Cocoa Beach, FL, United States; International Trade Bridge, Inc., Beavercreek, OH, United States; NASA Kennedy Space Center, Cocoa Beach, FL, United States
Final Report on Portable Laser Coating Removal Systems Field Demonstrations and Testing
Rothgeb, Matthew J.; McLaughlin, Russell L.; May 2008; In English; Original contains color and black and white illustrations
Contract(s)/Grant(s): NNH06CC40C
Report No.(s): NASA CR-2008-214754; NASA.PROJ.PLCRS.FTR.MR.01May08.F; Copyright; Avail.: CASI: A04, Hardcopy
Processes currently used throughout the National Aeronautics and Space Administration (NASA) to remove corrosion and coatings from structures, ground service equipment and small components results in waste streams consisting of toxic chemicals, spent media blast materials, and waste water. When chemicals are used in these processes they are typically high in volatile organic compounds (VOC) and are considered hazardous air pollutants (HAP). When blast media is used, the volume of hazardous waste generated is increased significantly. Many of the coatings historically used within NASA contain toxic metals such as hexavalent chromium, and lead. These materials are highly regulated and restrictions on worker exposure continue to increase. Most recently the EPA reduced the permissible exposure limit (PEL) for hexavalent chromium. The new standard lowers OSHA's PEL for hexavalent chromium from 52 to 5 micrograms of Cr(V1) per cubic meter of air as an 8-hour time-weighted average. Hexavalent chromium is found in the pretreatment and primer coatings used within the Shuttle Program. In response to the need to continue to protect assets within the agency and the growing concern over these new regulations, NASA is researching different ways to continue the required maintenance of both facility and flight equipment in a safe, efficient and environmentally preferable manner. The use of laser energy to remove prepare surfaces for a variety of processes, such as corrosion and coating removal, weld preparation and non destructive evaluation is a relatively new technology that has shown itself to be environmentally preferable and in many cases less labor intensive than currently used removal methods. The development of a Portable Laser Coating Removal System (PLCRS) started as the goal of a Joint Group on Pollution Prevention (JG-PP) project, led by the Air Force, where several types of lasers in several configurations were thoroughly evaluated. Following this project, NASA decided to evaluate the best performers on processes and coatings specific to the agency. Laser systems used during this project were all of a similar design, most of which had integrated vacuum systems in order to collect materials removed from substrate surfaces during operation. Due to the fact that the technology lends itself to a bide variety of processes, several site demonstrations were organized in order to allow for greater evaluation of the laser systems across NASA. The project consisted of an introductory demonstration and a more in-depth evaluation at Wright-Patterson Air Force Base. Additionally, field demonstrations occurred at Glenn Research Center and Kennedy Space Center. During these demonstrations several NASA specific applications were evaluated, including the removal of coatings within Orbiter tile cavities and Teflon from Space Shuttle Main Engine gaskets, removal of heavy grease from Solid Rocket Booster components and the removal of coatings on weld lines for Shuttle and general ground service equipment for non destructive evaluation (NDE). In addition, several general industry applications such as corrosion removal, structural coating removal, weld-line preparation and surface cleaning were evaluated. This included removal of coatings and corrosion from surfaces containing lead-based coatings and applications similar to launch-structure maintenance and Crawler maintenance. During the project lifecycle, an attempt was made to answer process specific concerns and questions as they arose. Some of these initially unexpected questions concerned the effects lasers might have on substrates used on flight equipment including strength, surface re-melting, substrate temperature and corrosion resistance effects. Additionally a concern was PPE required for operating such a system including eye, breathing and hearing protection. Most of these questions although not initially planned, were fully explored as a part of this project. Generally the results from tesng were very positive. Corrosion was effectively removed from steel, but less successfully from aluminum alloys. Coatings were able to be removed, with varying results, generally dark, matte and thin coatings were easier to remove. Steel and aluminum panels were able to be cleaned for welding, with no known deleterious effects and weld-lines were able to have coatings removed in critical areas for NDE while saving time as compared to other methods.
Derived from text
CORROSION; LASERS; MAINTENANCE; LASER APPLICATIONS; PAINT REMOVAL
20090005858 Kentucky Univ., Lexington, KY United States
System and technique for retrieving depth information about a surface by projecting a composite image of modulated light patterns
Hassebrook, Laurence G., Inventor; Lau, Daniel L., Inventor; Guan, Chun, Inventor; October 21, 2008; In English
Contract(s)/Grant(s): NCC5-222
Patent Info.: May 21, 2003US-Patent-7,440,590; US-Patent-Appl-SN-10/444,033
No Copyright; Avail.: CASI: A03, Hardcopy
Avail Online: http://hdl.handle.net/2060/20090005858
A technique, associated system and program code, for retrieving depth information about at least one surface of an object. Core features include: projecting a composite image comprising a plurality of modulated structured light patterns, at the object; capturing an image reflected from the surface; and recovering pattern information from the reflected image, for each of the modulated structured light patterns. Pattern information is preferably recovered for each modulated structured light pattern used to create the composite, by performing a demodulation of the reflected image. Reconstruction of the surface can be accomplished by using depth information from the recovered patterns to produce a depth map/mapping thereof. Each signal waveform used for the modulation of a respective structured light pattern, is distinct from each of the other signal waveforms used for the modulation of other structured light patterns of a composite image; these signal waveforms may be selected from suitable types in any combination of distinct signal waveforms, provided the waveforms used are uncorrelated with respect to each other. The depth map/mapping to be utilized in a host of applications, for example: displaying a 3-D view of the object; virtual reality user-interaction interface with a computerized device; face--or other animal feature or inanimate object--recognition and comparison techniques for security or identification purposes; and 3-D video teleconferencing/telecollaboration.
Official Gazette of the U.S. Patent and Trademark Office
IMAGE PROCESSING; PATTERN RECOGNITION; PHOTOMAPPING; IMAGE CLASSIFICATION; IMAGE ANALYSIS
20090005860 California Inst. of Tech., Pasadena, CA United States
Single mode whispering-gallery-mode resonator
Savchenkov, Anatoliy, Inventor; Strekalov, Dmitry V., Inventor; Matsko, Andrey B., Inventor; Ilchenko, Vladimir, Inventor; Maleki, Lutfollah, Inventor; October 21, 2008; In English
Patent Info.: November 17, 2005US-Patent-7,440,651; US-Patent-Appl-SN-11/282,160
No Copyright; Avail.: CASI: A03, Hardcopy
Avail Online: http://hdl.handle.net/2060/20090005860
Whispering-gallery-mode (WGM) resonators configured to support only a single whispering gallery mode.
Official Gazette of the U.S. Patent and Trademark Office
RESONATORS; WHISPERING GALLERY MODES; Q FACTORS; RESONANT VIBRATION
20090005863 California Inst. of Tech., Pasadena, CA United States
Organic fuel cell methods and apparatus
Vamos, Eugene, Inventor; Surampudi, Subbarao, Inventor; Narayanan, Sekharipuram R., Inventor; Frank, Harvey A., Inventor; Halpert, Gerald, Inventor; Olah, George A., Inventor; Prakash, G. K. Surya, Inventor; November 4, 2008; In English
Patent Info.: May 27, 2004US-Patent-7,445,859; US-Patent-Appl-SN-10/857,587
No Copyright; Avail.: CASI: A03, Hardcopy
Avail Online: http://hdl.handle.net/2060/20090005863
A liquid organic, fuel cell is provided which employs a solid electrolyte membrane. An organic fuel, such as a methanol/water mixture, is circulated past an anode of a cell while oxygen or air is circulated past a cathode of the cell. The cell solid electrolyte membrane is preferably fabricated from Nafion.TM.. Additionally, a method for improving the performance of carbon electrode structures for use in organic fuel cells is provided wherein a high surface-area carbon particle/Teflon.TM.-binder structure is immersed within a Nafion.TM./methanol bath to impregnate the electrode with Nafion.TM.. A method for fabricating an anode for use in a organic fuel cell is described wherein metal alloys are deposited onto the electrode in an electro-deposition solution containing perfluorooctanesulfonic acid. A fuel additive containing perfluorooctanesulfonic acid for use with fuel cells employing a sulfuric acid electrolyte is also disclosed. New organic fuels, namely, trimethoxymethane, dimethoxymethane, and trioxane are also described for use with either conventional or improved fuel cells.
Official Gazette of the U.S. Patent and Trademark Office
CELL ANODES; CELL CATHODES; METHYL ALCOHOL; BIOCHEMICAL FUEL CELLS
20090005864 California Univ., Oakland, CA United States
Fluid control structures in microfluidic devices
Mathies, Richard A., Inventor; Grover, William H., Inventor; Skelley, Alison, Inventor; Lagally, Eric, Inventor; Liu, Chung N., Inventor; November 4, 2008; In English
Contract(s)/Grant(s): NAG5-9659
Patent Info.: December 29, 2003US-Patent-7,445,926; US-Patent-Appl-SN-10/750,533
No Copyright; Avail.: CASI: A03, Hardcopy
Avail Online: http://hdl.handle.net/2060/20090005864
Methods and apparatus for implementing microfluidic analysis devices are provided. A monolithic elastomer membrane associated with an integrated pneumatic manifold allows the placement and actuation of a variety of fluid control structures, such as structures for pumping, isolating, mixing, routing, merging, splitting, preparing, and storing volumes of fluid. The fluid control structures can be used to implement a variety of sample introduction, preparation, processing, and storage techniques.
Official Gazette of the U.S. Patent and Trademark Office
CONTROL EQUIPMENT; ELASTOMERS; MICROFLUIDIC DEVICES; MICROINSTRUMENTATION; MEMBRANES
Additions to the NASA Aeronautics and Space Database as of 02/17/2009
20090005939 NASA Dryden Flight Research Center, Edwards, CA, United States
X-48B Flight Test Progress Overview
Risch, Timoth K.; Cosentino, Gary B.; Regan, Christopher D.; Kisska, Michael; Princen, Norman; January 05, 2009; In English; 47th AIAA Aerospace Sciences Meeting, 5-8 Jan. 2009, Orlando, Fl, United States; Original contains color and black and white illustrations
Copyright; Avail.: CASI: A03, Hardcopy
The results of a series of 39 flight tests of the X-48B Low Speed Vehicle (LSV) performed at the NASA Dryden Flight Research Center from July 2007 through December 2008 are reported here. The goal of these tests is to evaluate the aerodynamic and controls and dynamics performance of the subscale LSV aircraft, eventually leading to the development of a control system for a full-scale vehicle. The X-48B LSV is an 8.5%-scale aircraft of a potential, full-scale Blended Wing Body (BWB) type aircraft and is flown remotely from a ground control station using a computerized flight control system located onboard the aircraft. The flight tests were the first two phases of a planned three-phase research program aimed at ascertaining the flying characteristics of this type of aircraft. The two test phases reported here are: 1) envelope expansion, during which the basic flying characteristics of the airplane were examined, and 2) parameter identification, stalls, and engine-out testing, during which further information on the aircraft performance was obtained and the airplane was tested to the limits of controlled flight. The third phase, departure limiter assaults, has yet to be performed. Flight tests in two different wing leading edge configurations (slats extended and slats retracted) as well as three weight and three center of gravity positions were conducted during each phase. Data gathered in the test program included measured airplane performance parameters such as speed, acceleration, and control surface deflections along with qualitative flying evaluations obtained from pilot and crew observations. Flight tests performed to-date indicate the aircraft exhibits good handling qualities and performance, consistent with pre-flight simulations.
Author
BLENDED-WING-BODY CONFIGURATIONS; FLIGHT TESTS; GENERAL OVERVIEWS; FULL SCALE TESTS; SUBSONIC AIRCRAFT
20090005944 NASA Dryden Flight Research Center, Edwards, CA, United States
Design and Calibration of a Flowfield Survey Rake for Inlet Flight Research
Flynn, Darin C.; Ratnayake, Nalin A.; Frederick, Michael; January 05, 2009; In English; 47th AIAA Aerospace Sciences Meeting and Exhibit, 5 Jan. 2009, Orlando, Fl, United States; Original contains color and black and white illustrations
No Copyright; Avail.: CASI: A03, Hardcopy
Avail Online: http://hdl.handle.net/2060/20090005944
The Propulsion Flight Test Fixture at the NASA Dryden Flight Research Center is a unique test platform available for use on NASA's F-15B aircraft, tail number 836, as a modular host for a variety of aerodynamics and propulsion research. For future flight data from this platform to be valid, more information must be gathered concerning the quality of the airflow underneath the body of the F-15B at various flight conditions, especially supersonic conditions. The flow angularity and Mach number must be known at multiple locations on any test article interface plane for measurement data at these locations to be valid. To determine this prerequisite information, flight data will be gathered in the Rake Airflow Gauge Experiment using a custom-designed flowfield rake to probe the airflow underneath the F-15B at the desired flight conditions. This paper addresses the design considerations of the rake and probe assembly, including the loads and stress analysis using analytical methods, computational fluid dynamics, and finite element analysis. It also details the flow calibration procedure, including the completed wind-tunnel test and posttest data reduction, calibration verification, and preparation for flight-testing.
Author
FLOW DISTRIBUTION; SURVEYS; WIND TUNNEL TESTS; ENGINE INLETS; COMPUTATIONAL FLUID DYNAMICS; CALIBRATING
20090005948 NASA Goddard Space Flight Center, Greenbelt, MD, United States
Evolution of Web Services in EOSDIS: Search and Order Metadata Registry (ECHO)
Mitchell, Andrew; Ramapriyan, Hampapuram; Lowe, Dawn; [2009]; In English
No Copyright; Avail.: CASI: A01, Hardcopy
Avail Online: http://hdl.handle.net/2060/20090005948
During 2005 through 2008, NASA defined and implemented a major evolutionary change in it Earth Observing system Data and Information System (EOSDIS) to modernize its capabilities. This implementation was based on a vision for 2015 developed during 2005. The EOSDIS 2015 Vision emphasizes increased end-to-end data system efficiency and operability; increased data usability; improved support for end users; and decreased operations costs. One key feature of the Evolution plan was achieving higher operational maturity (ingest, reconciliation, search and order, performance, error handling) for the NASA s Earth Observing System Clearinghouse (ECHO). The ECHO system is an operational metadata registry through which the scientific community can easily discover and exchange NASA's Earth science data and services. ECHO contains metadata for 2,726 data collections comprising over 87 million individual data granules and 34 million browse images, consisting of NASA s EOSDIS Data Centers and the United States Geological Survey's Landsat Project holdings. ECHO is a middleware component based on a Service Oriented Architecture (SOA). The system is comprised of a set of infrastructure services that enable the fundamental SOA functions: publish, discover, and access Earth science resources. It also provides additional services such as user management, data access control, and order management. The ECHO system has a data registry and a services registry. The data registry enables organizations to publish EOS and other Earth-science related data holdings to a common metadata model. These holdings are described through metadata in terms of datasets (types of data) and granules (specific data items of those types). ECHO also supports browse images, which provide a visual representation of the data. The published metadata can be mapped to and from existing standards (e.g., FGDC, ISO 19115). With ECHO, users can find the metadata stored in the data registry and then access the data either directly online or through a brokered order to the data archive organization. ECHO stores metadata from a variety of science disciplines and domains, including Climate Variability and Change, Carbon Cycle and Ecosystems, Earth Surface and Interior, Atmospheric Composition, Weather, and Water and Energy Cycle. ECHO also has a services registry for community-developed search services and data services. ECHO provides a platform for the publication, discovery, understanding and access to NASA s Earth Observation resources (data, service and clients). In their native state, these data, service and client resources are not necessarily targeted for use beyond their original mission. However, with the proper interoperability mechanisms, users of these resources can expand their value, by accessing, combining and applying them in unforeseen ways.
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EOS DATA AND INFORMATION SYSTEM; METADATA; WEB SERVICES; ECOSYSTEMS; EARTH SCIENCES
20090005960 NASA Goddard Space Flight Center, Greenbelt, MD, United States
The NASA NEESPI Data Portal to Support Studies of Climate and Environmental Changes in Non-Boreal Europe
Shen, Suhung; Leptoukh, Gregory; Loboda, Tatiana; Csiszar, Ivan; Romanov, Peter; Gerasimov, Irina; August 23, 2008; In English; NATO Advance Workshop: "Regional Aspects of Climate-Terrestrial-Hydrologic Interactions in Eastern Europe" (NEESPI Regional Non-boreal Europe Meeting), 23028 Aug. 2008, Odessa, Ukraine; Original contains color and black and white illustrations
Contract(s)/Grant(s): NNH05ZDA001N-ACCESS
Copyright; Avail.: CASI: A03, Hardcopy
NASA NEESPI (Northern Eurasia Earth Science Partnership Initiative) data portal is a NASA funded project that focuses on collecting satellite remote sensing data, providing tools, information, and services in support of NEESPI scientific objectives (Leptoukh, et al., 2007). The data can be accessed online through anonymous ftp, through an advanced data searching and ordering system Mirador that uses keywords to find data quickly in a Google-like interface, and through the Goddard Interactive Online Visualization ANd aNalysis Infrastructure (Giovanni). The portal provides preprocessed data from different satellite sensors and numerical models to the same spatial and temporal resolution and the same projection so that the data can be used easily to perform inter-comparison or relationship studies. In addition, it provides parameter and spatially subsetted data for regional studies. Studies of regional carbon, hydrology, aerosols in non-boreal Europe and their interactions with global climate are very challenging research topics. The NASA NEESPI data portal makes many satellite data available for such studies, including information on land cover types, fire, vegetation index, aerosols, land surface temperature, soil moisture, precipitation, snow/ice, and other parameters. This paper will introduce the features and products available in the system, focusing on the online data 1 tool, Giovanni NEESPI. An example that explores different data through Giovanni NEESPI in temperate region of non-boreal Europe will be presented.
Author
CLIMATOLOGY; EARTH SCIENCES; ASIA; EUROPE; MATHEMATICAL MODELS; REMOTE SENSING
20090005965 NASA Goddard Space Flight Center, Greenbelt, MD, United States
cFE/CFS (Core Flight Executive/Core Flight System)
Wildermann, Charles P.; November 13, 2008; In English; Flight Software Workshop 2008, 13-14 Nov. 2008, Laurel, MD, United States; Original contains color illustrations
No Copyright; Avail.: CASI: A02, Hardcopy
Avail Online: http://hdl.handle.net/2060/20090005965
This viewgraph presentation describes in detail the requirements and goals of the Core Flight Executive (cFE) and the Core Flight System (CFS). The Core Flight Software System is a mission independent, platform-independent, Flight Software (FSW) environment integrating a reusable core flight executive (cFE). The CFS goals include: 1) Reduce time to deploy high quality flight software; 2) Reduce project schedule and cost uncertainty; 3) Directly facilitate formalized software reuse; 4) Enable collaboration across organizations; 5) Simplify sustaining engineering (AKA. FSW maintenance); 6) Scale from small instruments to System of Systems; 7) Platform for advanced concepts and prototyping; and 7) Common standards and tools across the branch and NASA wide.
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SOFTWARE ENGINEERING; SPACE FLIGHT; COMPUTER PROGRAMS; FLIGHT CONTROL; SYSTEMS INTEGRATION; OPERATING SYSTEMS (COMPUTERS)
20090005967 NASA Goddard Space Flight Center, Greenbelt, MD, United States
Modern Era Retrospective Restrospective-Analysis for Research and Applications (MERRA) Data and Services at the GES DISC
Berrick, Stephen W.; Shen, Suhung; Ostrenga, Dana; December 15, 2008; In English; American Geophysical Union Meeting, 15-19 Dec. 2008, San Francisco, CA, United States; Original contains color illustrations
Copyright; Avail.: CASI: A01, Hardcopy
The Modern Era Retrospective-analysis for Research and Applications (MERRA) dataset is a NASA satellite era, 30 year (1979 - present), reanalysis using the Goddard Earth Observing System Data Assimilation System, Version 5 (GEOS-5). The project, run out of NASA's Global Modeling and Assimilation Office at Goddard Space Flight Center, provides the science and application communities with a state-of-the-art global analysis with emphasis on improved estimates of the hydrological cycle over a broad range of weather and climate time scales. MERRA products are generated as a long-term synthesis that places the NASA EOS suite of observations in a climate context. The MERRA analysis is performed at a horizontal resolution of 2/3 longitude x 1/2 latitude (540x361 global gridpoints) with observational analyses every 6 hours. The MERRA output data will include 3 dimensional state fields for every 6 hourly analysis cycle on 42 pressure levels (or 72 terrain following model coordinate levels) from the surface through the stratosphere. Several data products are specifically designed to support chemistry and stratosphere transport modeling. The 2 dimensional surface and atmospheric diagnostics (numbering 259) are being stored on the native grid at 1 hourly intervals. These include radiation and vertical integrals of the atmosphere for water and energy budget studies and also surface diagnostics where the diurnal cycle is important. The one hourly surface and near surface data product will also facilitate research on the integrated analysis of Earth system observations in the land, ocean and cryosphere. The MERRA products are archived and distributed by the Goddard Earth Sciences Data and Information Services Center (GES DISC) through its Modeling DISC Web (MDISC) portal. Multiple data access methods and services are available for MERRA data through MDISC: (1) Mirador offers a quick, comprehensive search of MERRA and all GES DISC archived data holdings, allowing searches on keywords, location names or latitude/longitude box, and date/time, with responses within a few seconds. (2) Giovanni is a GES DISC developed Web application that provides data visualization and analysis online. Giovanni features popular visualizations such as latitude-longitude maps, animations, cross sections, profiles, time series, etc. and some basic statistical analysis functions such as scatter plots and correlation coefficient maps. Users are able to download results in several different formats, including Google Earth. (3) On-the-fly parameter subsetting of data within a spatial/temporal window is provided through a simple select and click Web page. (4) MERRA data are also available via OPeNDAP, GrADS Data Server (GDS) and can be converted to netCDF on the fly.
Author
DATA SYSTEMS; EARTH SCIENCES; INFORMATION SYSTEMS; SYSTEMS INTEGRATION; SCIENTIFIC VISUALIZATION
20090005968 NASA Goddard Space Flight Center, Greenbelt, MD, United States
Provenance in Data Interoperability for Multi-Sensor Intercomparison
Lynnes, Chris; Leptoukh, Greg; Berrick, Steve; Shen, Suhung; Prados, Ana; Fox, Peter; Yang, Wenli; Min, Min; Holloway, Dan; Enloe, Yonsook; December 15, 2008; In English; American Geophysical Union Meeting, 15-19 Dec. 2008, San Francisco, CA, United States; Original contains color illustrations
Copyright; Avail.: CASI: A01, Hardcopy
As our inventory of Earth science data sets grows, the ability to compare, merge and fuse multiple datasets grows in importance. This requires a deeper data interoperability than we have now. Efforts such as Open Geospatial Consortium and OPeNDAP (Open-source Project for a Network Data Access Protocol) have broken down format barriers to interoperability; the next challenge is the semantic aspects of the data. Consider the issues when satellite data are merged, cross-calibrated, validated, inter-compared and fused. We must match up data sets that are related, yet different in significant ways: the phenomenon being measured, measurement technique, location in space-time or quality of the measurements. If subtle distinctions between similar measurements are not clear to the user, results can be meaningless or lead to an incorrect interpretation of the data. Most of these distinctions trace to how the data came to be: sensors, processing and quality assessment. For example, monthly averages of satellite-based aerosol measurements often show significant discrepancies, which might be due to differences in spatio- temporal aggregation, sampling issues, sensor biases, algorithm differences or calibration issues. Provenance information must be captured in a semantic framework that allows data inter-use tools to incorporate it and aid in the intervention of comparison or merged products. Semantic web technology allows us to encode our knowledge of measurement characteristics, phenomena measured, space-time representation, and data quality attributes in a well-structured, machine-readable ontology and rulesets. An analysis tool can use this knowledge to show users the provenance-related distrintions between two variables, advising on options for further data processing and analysis. An additional problem for workflows distributed across heterogeneous systems is retrieval and transport of provenance. Provenance may be either embedded within the data payload, or transmitted from server to client in an out-of-band mechanism. The out of band mechanism is more flexible in the richness of provenance information that can be accomodated, but it relies on a persistent framework and can be difficult for legacy clients to use. We are prototyping the embedded model, incorporating provenance within metadata objects in the data payload. Thus, it always remains with the data. The downside is a limit to the size of provenance metadata that we can include, an issue that will eventually need resolution to encompass the richness of provenance information required for daata intercomparison and merging.
Author
INTEROPERABILITY; EARTH SCIENCES; METADATA; MULTISENSOR APPLICATIONS; COMPUTER NETWORKS
20090005969 NASA Goddard Space Flight Center, Greenbelt, MD, United States
Semantic Web Data Discovery of Earth Science Data at NASA Goddard Earth Sciences Data and Information Services Center (GES DISC)
Hegde, Mahabaleshwara; Strub, Richard F.; Lynnes, Christopher S.; Fang, Hongliang; Teng, William; December 15, 2008; In English; American Geophysical Union Conference, 15-19 Dec. 2008, San Francisco, CA, United States; Original contains color illustrations
Copyright; Avail.: CASI: A01, Hardcopy
Mirador is a web interface for searching Earth Science data archived at the NASA Goddard Earth Sciences Data and Information Services Center (GES DISC). Mirador provides keyword-based search and guided navigation for providing efficient search and access to Earth Science data. Mirador employs the power of Google's universal search technology for fast metadata keyword searches, augmented by additional capabilities such as event searches (e.g., hurricanes), searches based on location gazetteer, and data services like format converters and data sub-setters. The objective of guided data navigation is to present users with multiple guided navigation in Mirador is an ontology based on the Global Change Master directory (GCMD) Directory Interchange Format (DIF). Current implementation includes the project ontology covering various instruments and model data. Additional capabilities in the pipeline include Earth Science parameter and applications ontologies.
Author
WORLD WIDE WEB; EARTH SCIENCES; INFORMATION SYSTEMS; SEMANTICS; METADATA
20090005971 NASA Goddard Space Flight Center, Greenbelt, MD, United States
Spectroscopy using the Hadamard Transform V2
Fixsen, D. J.; Greenhouse, M. A.; MacKenty, J. W.; Mather, J. C.; January 18, 2009; In English; SPIE Meeting, 18-22 Jan. 2009, San Jose, CA, United States; Original contains poor quality, truncated or crooked pages
Copyright; Avail.: CASI: A03, Hardcopy
The IRMOS (infrared multiobject spectrometer) is an imaging dispersive spectrometer, with a micromirror array to select desired objects. In standard operation, the mirrors are "opened" in patterns such that the resulting spectra do not overlap on the detector. The IRMOS can also be operated in a Hadamard mode, in which the spectra are allowed to overlap, but are modulated by opening the mirrors in many combinations. This mode enables the entire field of view to be observed with the same sensitivity as in the standard mode if the uncertainty is dominated by the detector read noise. We explain the concept and discuss the benefits with an example observation of the Orion Trapezium using the 2.1 m telescope at Kitt Peak National Observatory.
Author
INFRARED SPECTROMETERS; SPECTROSCOPY; TRANSFORMATIONS (MATHEMATICS); MATHEMATICAL MODELS
20090005976 NASA Glenn Research Center, Cleveland, OH, United States
Analysis of Bonded Joints Between the Facesheet and Flange of Corrugated Composite Panels
Yarrington, Phillip W.; Collier, Craig S.; Bednarcyk, Brett A.; December 2008; In English; 49th Structures, Structural Dynamics, and Materials Conference (SDM), 7-10 Apr. 2008, Schaumburg, IL, United States; Original contains color and black and white illustrations
Contract(s)/Grant(s): WBS 645846.02.07.03.03.02
Report No.(s): NASA/TM-2008-215438; AIAA Paper-2008-2092; E-16608; Copyright; Avail.: CASI: A03, Hardcopy
This paper outlines a method for the stress analysis of bonded composite corrugated panel facesheet to flange joints. The method relies on the existing HyperSizer Joints software, which analyzes the bonded joint, along with a beam analogy model that provides the necessary boundary loading conditions to the joint analysis. The method is capable of predicting the full multiaxial stress and strain fields within the flange to facesheet joint and thus can determine ply-level margins and evaluate delamination. Results comparing the method to NASTRAN finite element model stress fields are provided illustrating the accuracy of the method.
Author
BONDED JOINTS; STRESS ANALYSIS; LAMINATES; COMPOSITE STRUCTURES; FINITE ELEMENT METHOD; STRESS DISTRIBUTION; STRESS-STRAIN RELATIONSHIPS
20090005977 NASA Glenn Research Center, Cleveland, OH, United States
Space Telecommunications Radio System (STRS) Definitions and Acronyms
Briones, Janette C.; Handler, Louis M.; Johnson, Sandra K.; Nappier, Jennifer; Gnepp, Steven; Kacpura, Thomas J.; Reinhart, Richard C.; Hall, Charles S.; Mortensen, Dale; December 2008; In English
Contract(s)/Grant(s): WBS 439432.04.07.01
Report No.(s): NASA/TM-2008-215445; E-16637; Copyright; Avail.: CASI: A03, Hardcopy
Software-defined radio is a relatively new technology area, and industry consensus on terminology is not always consistent. Confusion exists when the various organizations and standards bodies define different radio terms associated with the actual amount of reconfigurability of the radios. The Space Telecommunications Radio System (STRS) Definitions and Acronyms Document provides the readers of the STRS documents a common understanding of the terminology used and how they will be applied to the STRS architecture.
Author
TELECOMMUNICATION; RADIO EQUIPMENT; SOFTWARE ENGINEERING; SPACE COMMUNICATION
20090005991 NASA Glenn Research Center, Cleveland, OH, United States
A Novel Multiscale Physics Based Progressive Failure Methodology for Laminated Composite Structures
Pineda, Evan J.; Waas, Anthony M.; Bednarcyk, Brett A.; Collier, Craig S.; Yarrington, Phillip W.; December 2008; In English; Original contains color illustrations
Contract(s)/Grant(s): NNL07AA29CWBS 984754.02.07.03.16.05
Report No.(s): NASA/TM-2008-215448; E-16644; Copyright; Avail.: CASI: A03, Hardcopy
A variable fidelity, multiscale, physics based finite element procedure for predicting progressive damage and failure of laminated continuous fiber reinforced composites is introduced. At every integration point in a finite element model, progressive damage is accounted for at the lamina-level using thermodynamically based Schapery Theory. Separate failure criteria are applied at either the global-scale or the microscale in two different FEM models. A micromechanics model, the Generalized Method of Cells, is used to evaluate failure criteria at the micro-level. The stress-strain behavior and observed failure mechanisms are compared with experimental results for both models.
Author
MICROMECHANICS; FINITE ELEMENT METHOD; FIBER COMPOSITES; LAMINATES; STRESS-STRAIN RELATIONSHIPS; FAILURE; COMPOSITE STRUCTURES
20090005992 NASA Glenn Research Center, Cleveland, OH, United States
Current Methods for Modeling and Simulating Icing Effects on Aircraft Performance, Stability and Control
Ralvasky, Thomas P.; Barnhart, Billy P.; Lee, Sam; December 2008; In English; Atmospheric Flight Mechanics Conference and Exhibit, 18-21 Aug. 2008, Honolulu, HI, United States; Original contains black and white illustrations
Contract(s)/Grant(s): WBS 457280.02.07.03.02
Report No.(s): NASA/TM-2008-215453; AIAA-Paper-2008-6204; E-16643; Copyright; Avail.: CASI: A03, Hardcopy
Icing alters the shape and surface characteristics of aircraft components, which results in altered aerodynamic forces and moments caused by air flow over those iced components. The typical effects of icing are increased drag, reduced stall angle of attack, and reduced maximum lift. In addition to the performance changes, icing can also affect control surface effectiveness, hinge moments, and damping. These effects result in altered aircraft stability and control and flying qualities. Over the past 80 years, methods have been developed to understand how icing affects performance, stability and control. Emphasis has been on wind tunnel testing of two-dimensional subscale airfoils with various ice shapes to understand their effect on the flow field and ultimately the aerodynamics. This research has led to wind tunnel testing of subscale complete aircraft models to identify the integrated effects of icing on the aircraft system in terms of performance, stability, and control. Data sets of this nature enable pilot in the loop simulations to be performed for pilot training, or engineering evaluation of system failure impacts or control system design.
Author
AIRCRAFT ICING; FLIGHT CHARACTERISTICS; SIMULATION; AERODYNAMIC FORCES; AIRCRAFT CONTROL; ANGLE OF ATTACK
20090005994 NASA Glenn Research Center, Cleveland, OH, United States
Processing and Preparation of Advanced Stirling Convertors for Extended Operation at NASA Glenn Research Center
Oriti, Salvatore M.; Cornell, Peggy A.; December 2008; In English; Sixth International Energy Conversion Engineering Conference (IECEC), 28-30 Jul. 2008, Cleveland, OH, United States; Original contains color and black and white illustrations
Contract(s)/Grant(s): WBS 138494.04.01.01
Report No.(s): NASA/TM-2008-215454; E-16645; No Copyright; Avail.: CASI: A03, Hardcopy
Avail Online: http://hdl.handle.net/2060/20090005994
The U.S. Department of Energy (DOE), Lockheed Martin Space Company (LMSC), Sunpower Inc., and NASA Glenn Research Center (GRC) have been developing an Advanced Stirling Radioisotope Generator (ASRG) for use as a power system on space science missions. This generator will make use of the free-piston Stirling convertors to achieve higher conversion efficiency than currently available alternatives. NASA GRC is supporting the development of the ASRG by providing extended operation of several Sunpower Inc. Advanced Stirling Convertors (ASCs). In the past year and a half, eight ASCs have operated in continuous, unattended mode in both air and thermal vacuum environments. Hardware, software, and procedures were developed to prepare each convertor for extended operation with intended durations on the order of tens of thousands of hours. Steps taken to prepare a convertor for long-term operation included geometry measurements, thermocouple instrumentation, evaluation of working fluid purity, evacuation with bakeout, and high purity charge. Actions were also taken to ensure the reliability of support systems, such as data acquisition and automated shutdown checkouts. Once a convertor completed these steps, it underwent short-term testing to gather baseline performance data before initiating extended operation. These tests included insulation thermal loss characterization, low-temperature checkout, and full-temperature and power demonstration. This paper discusses the facilities developed to support continuous, unattended operation, and the processing results of the eight ASCs currently on test.
Author
STIRLING CYCLE; ENERGY CONVERSION EFFICIENCY; DEGASSING; COMPUTER PROGRAMS
20090005995 NASA Glenn Research Center, Cleveland, OH, United States
NASA Glenn Research Center's Materials International Space Station Experiments (MISSE 1-7)
deGroh, Kim K.; Banks, Bruce a.; Dever, Joyce A.; Jaworske, Donald A.; Miller, Sharon K.; Sechkar, Edward A.; Panko, Scott R.; December 2008; In English; International Symposium on SM/MPAC and SEED Experiments, 10-11 Mar. 2008, Tsukuba, Japan; Original contains color and black and white illustrations
Contract(s)/Grant(s): WBS 698671.01.03.51
Report No.(s): NASA/TM-2008-215482; E-16690; Copyright; Avail.: CASI: A03, Hardcopy
NASA Glenn Research Center (Glenn) has 39 individual materials flight experiments (>540 samples) flown as part of the Materials International Space Station Experiment (MISSE) to address long duration environmental durability of spacecraft materials in low Earth orbit (LEO). MISSE is a series of materials flight experiments consisting of trays, called Passive Experiment Carriers (PECs) that are exposed to the space environment on the exterior of the International Space Station (ISS). MISSE 1-5 have been successfully flown and retrieved and were exposed to the space environment from one to four years. MISSE 6A & 6B were deployed during the STS-123 shuttle mission in March 2008, and MISSE 7A & 7B are being prepared for launch in 2009. The Glenn MISSE experiments address atomic oxygen (AO) effects such as erosion and undercutting of polymers, AO scattering, stress effects on AO erosion, and in-situ AO fluence monitoring. Experiments also address solar radiation effects such as radiation induced polymer shrinkage, stress effects on radiation degradation of polymers, and radiation degradation of indium tin oxide (ITO) coatings and spacesuit fabrics. Additional experiments address combined AO and solar radiation effects on thermal control films, paints and cermet coatings. Experiments with Orion Crew Exploration Vehicle (CEV) seals and UltraFlex solar array materials are also being flown. Several experiments were designed to provide ground-facility to in-space calibration data thus enabling more accurate in-space performance predictions based on ground-laboratory testing. This paper provides an overview of Glenn s MISSE 1-7 flight experiments along with a summary of results from Glenn s MISSE 1 & 2 experiments.
Author
INTERNATIONAL SPACE STATION; SOLAR RADIATION; RADIATION EFFECTS; AEROSPACE ENVIRONMENTS; LOW EARTH ORBITS; EROSION
20090005996 NASA Glenn Research Center, Cleveland, OH, United States
The Effect of Simulated Lunar Dust on the Absorptivity, Emissivity, and Operating Temperature on AZ-93 and Ag/FEP Thermal Control Surfaces
Gaier, James R.; Siamidis, John; Panko, Scott R.; Rogers, Kerry J.; Larkin, Elizabeth M. G.; December 2008; In English; Original contains color and black and white illustrations
Contract(s)/Grant(s): WBS 936374.04.08.03
Report No.(s): NASA/TM-2008-215492; E-16723; Copyright; Avail.: CASI: A03, Hardcopy
JSC-1AF lunar simulant has been applied to AZ-93 and AgFEP thermal control surfaces on aluminum or composite substrates in a simulated lunar environment. The temperature of these surfaces was monitored as they were heated with a solar simulator and cooled in a 30 K coldbox. Thermal modeling was used to determine the absorptivity ( ) and emissivity ( ) of the thermal control surfaces in both their clean and dusted states. Then, a known amount of power was applied to the samples while in the coldbox and the steady state temperatures measured. It was found that even a submonolayer of simulated lunar dust can significantly degrade the performance of both white paint and second-surface mirror type thermal control surfaces under these conditions. Contrary to earlier studies, dust was found to affect as well as . Dust lowered the emissivity by as much as 16 percent in the case of AZ-93, and raised it by as much as 11 percent in the case of AgFEP. The degradation of thermal control surface by dust as measured by / rose linearly regardless of the thermal control coating or substrate, and extrapolated to degradation by a factor 3 at full coverage by dust. Submonolayer coatings of dust were found to not significantly change the steady state temperature at which a shadowed thermal control surface will radiate.
Author
LUNAR DUST; LUNAR ENVIRONMENT; LUNAR SOIL; ABSORPTIVITY; EMISSIVITY; OPERATING TEMPERATURE; THERMAL CONTROL COATINGS; CONTROL SURFACES
Additions to the NASA Aeronautics and Space Database as of 02/18/2009
20090006099 NASA, Washington, DC United States
Laser fresnel distance measuring system and method
Campbell, Jonathan W., Inventor; Lehner, David L., Inventor; Smalley, Larry L., Inventor; Smith, legal representative, Molly C., Inventor; Sanders, Alvin J., Inventor; Earl, Dennis Duncan, Inventor; Allison, Stephen W., Inventor; Smith, Kelly L., Inventor; November 4, 2008; In English
Patent Info.: September 18, 2006US-Patent-7,446,860; US-Patent-Appl-SN-11/527,648
No Copyright; Avail.: CASI: A02, Hardcopy
Avail Online: http://hdl.handle.net/2060/20090006099
A method and system for determining range to a target are provided. A beam of electromagnetic energy is transmitted through an aperture in an opaque screen such that a portion of the beam passes through the aperture to generate a region of diffraction that varies as a function of distance from the aperture. An imaging system is focused on a target plane in the region of diffraction with the generated image being compared to known diffraction patterns. Each known diffraction pattern has a unique value associated therewith that is indicative of a distance from the aperture. A match between the generated image and at least one of the known diffraction patterns is indicative of a distance between the aperture and target plane.
Official Gazette of the U.S. Patent and Trademark Office
DISTANCE MEASURING EQUIPMENT; LASERS; FRESNEL INTEGRALS
20090006100 Ohio Aerospace Inst., Cleveland, OH United States
Method for the growth of large low-defect single crystals
Powell, J. Anthony, Inventor; Neudeck, Philip G., Inventor; Trunek, Andrew J., Inventor; Spry, David J., Inventor; November 11, 2008; In English
Patent Info.: December 2, 2006US-Patent-7,449,065; US-Patent-Appl-SN-11/633,111
No Copyright; Avail.: CASI: A03, Hardcopy
Avail Online: http://hdl.handle.net/2060/20090006100
A method and the benefits resulting from the product thereof are disclosed for the growth of large, low-defect single-crystals of tetrahedrally-bonded crystal materials. The process utilizes a uniquely designed crystal shape whereby the direction of rapid growth is parallel to a preferred crystal direction. By establishing several regions of growth, a large single crystal that is largely defect-free can be grown at high growth rates. This process is particularly suitable for producing products for wide-bandgap semiconductors, such as SiC, GaN, AlN, and diamond. Large low-defect single crystals of these semiconductors enable greatly enhanced performance and reliability for applications involving high power, high voltage, and/or high temperature operating conditions.
Official Gazette of the U.S. Patent and Trademark Office
DEFECTS; SINGLE CRYSTALS; CRYSTAL DEFECTS; CRYSTAL GROWTH
20090006101
Model-based fault detection and isolation for intermittently active faults with application to motion-based thruster fault detection and isolation for spacecraft
Wilson, Edward, Inventor; November 11, 2008; In English
Contract(s)/Grant(s): NAS2-00065
Patent Info.: May 6, 2004US-Patent-7,451,021; US-Patent-Appl-SN-10/841,675
No Copyright; Avail.: CASI: A03, Hardcopy
Avail Online: http://hdl.handle.net/2060/20090006101
The present invention is a method for detecting and isolating fault modes in a system having a model describing its behavior and regularly sampled measurements. The models are used to calculate past and present deviations from measurements that would result with no faults present, as well as with one or more potential fault modes present. Algorithms that calculate and store these deviations, along with memory of when said faults, if present, would have an effect on the said actual measurements, are used to detect when a fault is present. Related algorithms are used to exonerate false fault modes and finally to isolate the true fault mode. This invention is presented with application to detection and isolation of thruster faults for a thruster-controlled spacecraft. As a supporting aspect of the invention, a novel, effective, and efficient filtering method for estimating the derivative of a noisy signal is presented.
Official Gazette of the U.S. Patent and Trademark Office
FAULT DETECTION; ISOLATION; MATHEMATICAL MODELS
20090006102 Illinois Univ., Urbana, IL United States
Method for fabricating a microscale anemometer
Liu, Chang, Inventor; Chen, Jack, Inventor; November 18, 2008; In English
Contract(s)/Grant(s): NAG5-8781
Patent Info.: May 18, 2005US-Patent-7,451,537; US-Patent-Appl-SN-11/132,144
No Copyright; Avail.: CASI: A03, Hardcopy
Avail Online: http://hdl.handle.net/2060/20090006102
Method for fabricating a microscale anemometer on a substrate. A sacrificial layer is formed on the substrate, and a metal thin film is patterned to form a sensing element. At least one support for the sensing element is patterned. The sacrificial layer is removed, and the sensing element is lifted away from the substrate by raising the supports, thus creating a clearance between the sensing element and the substrate to allow fluid flow between the sensing element and the substrate. The supports are raised preferably by use of a magnetic field applied to magnetic material patterned on the supports.
Official Gazette of the U.S. Patent and Trademark Office
FABRICATION; ANEMOMETERS; METHODOLOGY; MICROBALANCES
20090006104 NASA, Washington, DC United States
Re-entry vehicle shape for enhanced performance
Brown, James L., Inventor; Garcia, Joseph A., Inventor; Prabhu, Dinesh K., Inventor; October 7, 2008; In English
Patent Info.: November 1, 2005US-Patent-7,431,242; NASA-Case-ARC-15606-1; US-Patent-Appl-SN-11/265,324
No Copyright; Avail.: CASI: A03, Hardcopy
Avail Online: http://hdl.handle.net/2060/20090006104
A convex shell structure for enhanced aerodynamic performance and/or reduced heat transfer requirements for a space vehicle that re-enters an atmosphere. The structure has a fore-body, an aft-body, a longitudinal axis and a transverse cross sectional shape, projected on a plane containing the longitudinal axis, that includes: first and second linear segments, smoothly joined at a first end of each the first and second linear segments to an end of a third linear segment by respective first and second curvilinear segments; and a fourth linear segment, joined to a second end of each of the first and second segments by curvilinear segments, including first and second ellipses having unequal ellipse parameters. The cross sectional shape is non-symmetric about the longitudinal axis. The fourth linear segment can be replaced by a sum of one or more polynomials, trigonometric functions or other functions satisfying certain constraints.
Official Gazette of the U.S. Patent and Trademark Office
REENTRY VEHICLES; AERODYNAMIC CHARACTERISTICS; AFTERBODIES; AIRCRAFT PERFORMANCE
20090006336 NASA, Washington, DC United States
Integrator Circuitry for Single Channel Radiation Detector
Holland, Samuel D., Inventor; Delaune, Paul B., Inventor; Turner, Kathryn M., Inventor; August 12, 2008; In English
Patent Info.: May 31, 2006US-Patent-7,411,198; US-Patent-Appl-SN-11/421,174
No Copyright; Avail.: CASI: A03, Hardcopy
Avail Online: http://hdl.handle.net/2060/20090006336
Input circuitry is provided for a high voltage operated radiation detector to receive pulses from the detector having a rise time in the range of from about one nanosecond to about ten nanoseconds. An integrator circuit, which utilizes current feedback, receives the incoming charge from the radiation detector and creates voltage by integrating across a small capacitor. The integrator utilizes an amplifier which closely follows the voltage across the capacitor to produce an integrator output pulse with a peak value which may be used to determine the energy which produced the pulse. The pulse width of the output is stretched to approximately 50 to 300 nanoseconds for use by subsequent circuits which may then use amplifiers with lower slew rates.
Official Gazette of the U.S. Patent and Trademark Office
INTEGRATORS; CIRCUITS; RADIATION DETECTORS
20090006374 Massachusetts Inst. of Tech., Boston, MA United States
Dielectric Elastomer Actuated Systems and Methods
Dubowsky, Steven, Inventor; Hafez, Moustapha, Inventor; Lichter, Matthew, Inventor; Weiss, Peter, Inventor; Wingert, Andreas, Inventor; August 12, 2008; In English
Patent Info.: November 8, 2002US-Patent-7,411,331; US-Patent-Appl-SN-10/291,217
No Copyright; Avail.: CASI: A03, Hardcopy
Avail Online: http://hdl.handle.net/2060/20090006374
The system of the present invention includes an actuator having at least two electrodes, an elastomeric dielectric film disposed between the two electrodes, and a frame attached to the elastomeric dielectric film. The frame provides a linear actuation force characteristic over a displacement range. The displacement range is preferably the stroke of the actuator. The displacement range can be about 5 mm and greater. Further, the frame can include a plurality of configurations, for example, at least a rigid members coupled to a flexible member wherein the frame provides an elastic restoring force. In preferred embodiments, the rigid member can be, but is not limited to, curved beams, parallel beams, rods and plates. In a preferred embodiment the actuator can further include a passive element disposed between two flexible members such as, for example, links to tune a stiffness characteristic of the actuator. The passive element can be a bi-stable element. Further, the actuator can include a plurality of layers of the elastomeric dielectric film integrated into the frame. The elastomeric film can be made of different materials such as, for example, acrylic, silicone and latex.
Official Gazette of the U.S. Patent and Trademark Office
DIELECTRICS; ELASTOMERS; ACTUATORS
20090006476 NASA, Washington, DC United States
Interferometric Polarization Control
Chuss, David T., Inventor; Wollack, Edward J., Inventor; Moseley, Samuel H., Inventor; Novak, Giles A., Inventor; August 12, 2008; In English
Patent Info.: June 20, 2006US-Patent-7,412,175; US-Patent-Appl-SN-11/425,352
No Copyright; Avail.: CASI: A03, Hardcopy
Avail Online: http://hdl.handle.net/2060/20090006476
A signal conditioning module provides a polarimeter capability in a photometric system. The module may include multiple variable delay polarization modulators. Each modulator may include an input port, and a first arm formed to include a first reflector and first rooftop mirror arranged in opposed relationship. The first reflector may direct an input radiation signal to the first rooftop mirror. Each modulator also may include an output port and a second arm formed to include a second reflector and second rooftop mirror arranged in opposed relationship. The second reflector can guide a signal from the second rooftop mirror towards the output port to provide an output radiation signal. A beamsplitting grid may be placed between the first reflector and the first rooftop mirror, and also between the second reflector and the second rooftop mirror. A translation apparatus can provide adjustment relative to optical path length vis-a-vis the first arm, the second arm and the grid.
Official Gazette of the U.S. Patent and Trademark Office
POLARIMETERS; INTERFEROMETRY; PHOTOMETRY; POLARIZATION; SIGNAL PROCESSING; ASTRONOMICAL POLARIMETRY
20090006515 General Electric Co., Schenectady, NY United States
Electron Beam Welding to Join Gamma Titanium Aluminide Articles
Kelly, Thomas Joseph, Inventor; August 19, 2008; In English
Contract(s)/Grant(s): NAS3-26385
Patent Info.: November 20, 2002US-Patent-7,413,620; US-Patent-Appl-SN-10/301,767
No Copyright; Avail.: CASI: A02, Hardcopy
Avail Online: http://hdl.handle.net/2060/20090006515
A method is provided for welding two gamma titanium aluminide articles together. The method includes preheating the two articles to a welding temperature of from about 1700 F to about 2100 F, thereafter electron beam welding the two articles together at the welding temperature and in a welding vacuum to form a welded structure, and thereafter annealing the welded structure at an annealing temperature of from about 1800 F to about 2200 F, to form a joined structure.
Official Gazette of the U.S. Patent and Trademark Office
ELECTRON BEAM WELDING; TITANIUM ALUMINIDES
20090006534 Honeywell International, Inc., Morristown, NJ United States
Multiple Miniature Avionic Displays
Rye, Jeffrey M., Inventor; Dorneich, Michael C., Inventor; Gannon, Aaron J., Inventor; August 19, 2008; In English
Contract(s)/Grant(s): NAS1-00107; NAS1-00107
Patent Info.: April 28, 2005US-Patent-7,414,543; US-Patent-Appl-SN-11/116,971
No Copyright; Avail.: CASI: A02, Hardcopy
Avail Online: http://hdl.handle.net/2060/20090006534
A display screen for displaying multiple sets of information is provided. In one embodiment, an aviation display screen includes a main window and a plurality of miniature windows. The main window is adapted to illustrate one set of information. Each miniature window is adapted to display a set of avionic information. The avionic display is further adapted to toggle a select set of avionic information in one of the miniature windows into the main window.
Official Gazette of the U.S. Patent and Trademark Office
AVIONICS; DISPLAY DEVICES; SCREENS; MINIATURIZATION
20090006537 NASA, Washington, DC United States
Interferometric Rayleigh Scattering Measurement System
Bivolaru, Daniel, Inventor; Danehy, Paul M., Inventor; Lee, Joseph W., Inventor; August 19, 2008; In English
Patent Info.: August 1, 2006US-Patent-7,414,708; NASA-Case-LAR-17235-1; US-Patent-Appl-SN-11/461,569
No Copyright; Avail.: CASI: A03, Hardcopy
Avail Online: http://hdl.handle.net/2060/20090006537
A method and apparatus for performing simultaneous multi-point measurements of multiple velocity components in a gas flow is described. Pulses of laser light are directed to a measurement region of unseeded gas to produce Rayleigh or Mie scattered light in a plurality of directions. The Rayleigh or Mie scattered light is collected from multiple directions and combined in a single collimated light beam. The Rayleigh or Mie scattered light is then mixed together with a reference laser light before it is passed through a single planar Fabry-Perot interferometer for spectral analysis. At the output of the interferometer, a high-sensitivity CCD camera images the interference fringe pattern. This pattern contains the spectral and spatial information from both the Rayleigh scattered light and the reference laser light. Interferogram processing software extracts and analyzes spectral profiles to determine the velocity components of the gas flow at multiple points in the measurement region. The Rayleigh light rejected by the interferometer is recirculated to increase the accuracy and the applicability of the method for measurements at high temperatures without requiring an increase in the laser energy.
Official Gazette of the U.S. Patent and Trademark Office
GAS FLOW; FLOW VELOCITY; FLOW MEASUREMENT; VELOCITY MEASUREMENT; INTERFEROMETERS; INTERFEROMETRY; RAYLEIGH SCATTERING
20090006538 NASA, Washington, DC United States
Ad Hoc Selection of Voice over Internet Streams
Macha, Mitchell G., Inventor; Bullock, John T., Inventor; August 19, 2008; In English
Patent Info.: October 24, 2002US-Patent-7,415,005; US-Patent-Appl-SN-10/283,354
No Copyright; Avail.: CASI: A03, Hardcopy
Avail Online: http://hdl.handle.net/2060/20090006538
A method and apparatus for a communication system technique involving ad hoc selection of at least two audio streams is provided. Each of the at least two audio streams is a packetized version of an audio source. A data connection exists between a server and a client where a transport protocol actively propagates the at least two audio streams from the server to the client. Furthermore, software instructions executable on the client indicate a presence of the at least two audio streams, allow selection of at least one of the at least two audio streams, and direct the selected at least one of the at least two audio streams for audio playback.
Official Gazette of the U.S. Patent and Trademark Office
COMMUNICATION NETWORKS; SITUATIONAL AWARENESS; INTERNETS; AUDIO DATA; PLAYBACKS; VOICE DATA PROCESSING
20090006539 Intellectual Assets. LLC, Lake Tahoe, NV United States
Surveillance System and Method having an Adaptive Sequential Probability Fault Detection Test
Bickford, Randall L., Inventor; Herzog, James P., Inventor; August 19, 2008; In English
Contract(s)/Grant(s): NAS8-98027
Patent Info.: July 24, 2006US-Patent-7,415,382; US-Patent-Appl-SN-11/492,329
No Copyright; Avail.: CASI: A03, Hardcopy
Avail Online: http://hdl.handle.net/2060/20090006539
System and method providing surveillance of an asset such as a process and/or apparatus by providing training and surveillance procedures that numerically fit a probability density function to an observed residual error signal distribution that is correlative to normal asset operation and then utilizes the fitted probability density function in a dynamic statistical hypothesis test for providing improved asset surveillance.
Official Gazette of the U.S. Patent and Trademark Office
FAULT DETECTION; ARTIFICIAL INTELLIGENCE; STATISTICAL TESTS; NUMERICAL ANALYSIS
Additions to the NASA Aeronautics and Space Database as of 02/19/2009
20090006592 NASA, Washington, DC United States
Torsional Magnetorheological Device
Arnold, Steven M., Inventor; Penney, Nicholas, Inventor; August 26, 2008; In English
Patent Info.: October 23, 2003US-Patent-7,416,062; NASA-Case-LEW-17510-1; US-Patent-Appl-SN-10/693,853
No Copyright; Avail.: CASI: A03, Hardcopy
Avail Online: http://hdl.handle.net/2060/20090006592
A magnetorheological device comprising a housing having a divider within the housing is disclosed and claimed. A rotary impeller having two paddles is rotatably mounted within the housing. The rotary impeller sealingly engages the divider and the paddles in combination with the divider forms a first chamber and a second chamber. Magnetorheological fluid resides in the chambers and a passageway interconnects the first and second chambers. A coil surrounds a portion of the passageway such that when energized the magnetorheological fluid solidifies plugging the passageway. As the impeller rotates, it pushes the incompressible fluid against the divider in the housing and the plug in the passageway and retards and/or stops the motion of the impeller.
Official Gazette of the U.S. Patent and Trademark Office
MECHANICAL DEVICES; DAMPERS; MAGNETIC MATERIALS; SEALS (STOPPERS); ROTORS; TORSION; RHEOLOGY; MAGNETORHEOLOGICAL FLUIDS
20090006593 Toledo Univ., OH United States
Circuit with a Switch for Charging a Battery in a Battery Capacitor Circuit
Stuart, Thomas A., Inventor; Ashtiani, Cyrus N., Inventor; August 26, 2008; In English
Contract(s)/Grant(s): NAG3-2709
Patent Info.: October 12, 2005US-Patent-7,417,407; US-Patent-Appl-SN-11/249,048
No Copyright; Avail.: CASI: A03, Hardcopy
Avail Online: http://hdl.handle.net/2060/20090006593
A circuit for charging a battery combined with a capacitor includes a power supply adapted to be connected to the capacitor, and the battery. The circuit includes an electronic switch connected to the power supply. The electronic switch is responsive to switch between a conducting state to allow current and a non-conducting state to prevent current flow. The circuit includes a control device connected to the switch and is operable to generate a control signal to continuously switch the electronic switch between the conducting and non-conducting states to charge the battery.
Official Gazette of the U.S. Patent and Trademark Office
CIRCUITS; ELECTRIC SWITCHES; ELECTRIC BATTERIES; CHARGING; CAPACITORS; ELECTRICAL ENGINEERING
20090006594 NASA, Washington, DC United States
Dual Expander Cycle Rocket Engine with an Intermediate, Closed-cycle Heat Exchanger
Greene, William D., Inventor; September 2, 2008; In English
Patent Info.: June 30, 2005US-Patent-7,418,814; NASA-Case-MFS-32214-1; US-Patent-Appl-SN-11/172,666
No Copyright; Avail.: CASI: A02, Hardcopy
Avail Online: http://hdl.handle.net/2060/20090006594
A dual expander cycle (DEC) rocket engine with an intermediate closed-cycle heat exchanger is provided. A conventional DEC rocket engine has a closed-cycle heat exchanger thermally coupled thereto. The heat exchanger utilizes heat extracted from the engine's fuel circuit to drive the engine's oxidizer turbomachinery.
Official Gazette of the U.S. Patent and Trademark Office
ROCKET ENGINES; THERMODYNAMIC CYCLES; CLOSED CYCLES; HEAT EXCHANGERS; ROCKET ENGINE DESIGN
20090006595 NASA, Washington, DC United States
Cable Tensiometer for Aircraft
Nunnelee, Mark, Inventor; September 16, 2008; In English
Patent Info.: September 4, 2007US-Patent-7,424,832; NASA-Case-DRC-007041; US-Patent-Appl-SN-11/849,843
No Copyright; Avail.: CASI: A02, Hardcopy
Avail Online: http://hdl.handle.net/2060/20090006595
The invention is a cable tensiometer that can be used on aircraft for real-time, in-flight cable tension measurements. The invention can be used on any aircraft cables with high precision. The invention is extremely light-weight, hangs on the cable being tested and uses a dual bending beam design with a high mill-volt output to determine tension.
Official Gazette of the U.S. Patent and Trademark Office
CABLES; WIRE; TENSIOMETERS; CABLE FORCE RECORDERS; MECHANICAL MEASUREMENT; AIRCRAFT SAFETY
20090006596 California Inst. of Tech., Pasadena, CA United States
Carbon nanotube switches for memory, RF communications and sensing applications, and methods of making the same
Kaul, Anupama B., Inventor; Wong, Eric W., Inventor; Baron, Richard L., Inventor; Epp, Larry, Inventor; November 4, 2008; In English
Contract(s)/Grant(s): NAS7-1407
Patent Info.: September 19, 2006US-Patent-7,446,044; US-Patent-Appl-SN-11/523,273
No Copyright; Avail.: CASI: A03, Hardcopy
Avail Online: http://hdl.handle.net/2060/20090006596
Switches having an in situ grown carbon nanotube as an element thereof, and methods of fabricating such switches. A carbon nanotube is grown in situ in mechanical connection with a conductive substrate, such as a heavily doped silicon wafer or an SOI wafer. The carbon nanotube is electrically connected at one location to a terminal. At another location of the carbon nanotube there is situated a pull electrode that can be used to elecrostatically displace the carbon nanotube so that it selectively makes contact with either the pull electrode or with a contact electrode. Connection to the pull electrode is sufficient to operate the device as a simple switch, while connection to a contact electrode is useful to operate the device in a manner analogous to a relay. In various embodiments, the devices disclosed are useful as at least switches for various signals, multi-state memory, computational devices, and multiplexers.
Official Gazette of the U.S. Patent and Trademark Office
CARBON NANOTUBES; COMMUNICATION EQUIPMENT; COMPUTER STORAGE DEVICES; ELECTRODES; FABRICATION; SWITCHES; NANOTECHNOLOGY
20090006597 National Inst. of Aerospace Associates, Hampton, VA United States
Hybrid piezoelectric energy harvesting transducer system
Xu, Tian-Bing, Inventor; Jiang, Xiaoning, Inventor; Su, Ji, Inventor; Rehrig, Paul W., Inventor; Hackenberger, Wesley S., Inventor; November 4, 2008; In English
Contract(s)/Grant(s): NCC1-02043
Patent Info.: July 13, 2006US-Patent-7,446,459; NASA-Case-LAR-17169-1; US-Patent-Appl-SN-11/486,200
No Copyright; Avail.: CASI: A02, Hardcopy
Avail Online: http://hdl.handle.net/2060/20090006597
A hybrid piezoelectric energy harvesting transducer system includes: (a) first and second symmetric, pre-curved piezoelectric elements mounted separately on a frame so that their concave major surfaces are positioned opposite to each other; and (b) a linear piezoelectric element mounted separately on the frame and positioned between the pre-curved piezoelectric elements. The pre-curved piezoelectric elements and the linear piezoelectric element are spaced from one another and communicate with energy harvesting circuitry having contact points on the frame. The hybrid piezoelectric energy harvesting transducer system has a higher electromechanical energy conversion efficiency than any known piezoelectric transducer.
Official Gazette of the U.S. Patent and Trademark Office
CIRCUITS; ELECTROMECHANICS; PIEZOELECTRIC TRANSDUCERS; PIEZOELECTRICITY; ELECTRICITY
Additions to the NASA Aeronautics and Space Database as of 02/20/2009
20090006600 Georgia Tech Research Corp., Atlanta, GA United States
Stagnation point reverse flow combustor
Zinn, Ben T., Inventor; Neumeier, Yedidia, Inventor; Seitzman, Jerry M., Inventor; Jagoda, Jechiel, Inventor; Weksler, Yoav, Inventor; September 16, 2008; In English
Contract(s)/Grant(s): NCC3-982
Patent Info.: August 26, 2004US-Patent-7,425,127; US-Patent-Appl-SN-10/927,205
No Copyright; Avail.: CASI: A03, Hardcopy
Avail Online: http://hdl.handle.net/2060/20090006600
A method for combusting a combustible fuel includes providing a vessel having an opening near a proximate end and a closed distal end defining a combustion chamber. A combustible reactants mixture is presented into the combustion chamber. The combustible reactants mixture is ignited creating a flame and combustion products. The closed end of the combustion chamber is utilized for directing combustion products toward the opening of the combustion chamber creating a reverse flow of combustion products within the combustion chamber. The reverse flow of combustion products is intermixed with combustible reactants mixture to maintain the flame.
Official Gazette of the U.S. Patent and Trademark Office
COMBUSTION CHAMBERS; COMBUSTION; STAGNATION POINT; REVERSED FLOW
20090006601 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; September 16, 2008; In English
Contract(s)/Grant(s): NAS7-1407
Patent Info.: September 1, 2004US-Patent-7,425,384; US-Patent-Appl-SN-10/932,521
No Copyright; Avail.: CASI: A03, Hardcopy
Avail Online: http://hdl.handle.net/2060/20090006601
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.
Official Gazette of the U.S. Patent and Trademark Office
FEED SYSTEMS; FUEL CELLS; METHYL ALCOHOL; ELECTRODES
20090006603 California Inst. of Tech., Pasadena, CA United States
Method for implementation of back-illuminated CMOS or CCD imagers
Pain, Bedabrata, Inventor; September 16, 2008; In English
Patent Info.: September 13, 2005US-Patent-7,425,460; US-Patent-Appl-SN-11/226,902
No Copyright; Avail.: CASI: A03, Hardcopy
Avail Online: http://hdl.handle.net/2060/20090006603
A method for implementation of back-illuminated CMOS or CCD imagers. An oxide layer buried between silicon wafer and device silicon is provided. The oxide layer forms a passivation layer in the imaging structure. A device layer and interlayer dielectric are formed, and the silicon wafer is removed to expose the oxide layer.
Official Gazette of the U.S. Patent and Trademark Office
CHARGE COUPLED DEVICES; CMOS; ILLUMINATING; IMAGING TECHNIQUES; SILICON
20090006604 NASA, Washington, DC United States
Synthesis of asymmetric tetracarboxylic acids and corresponding dianhydrides
Chuang, Chun-Hua, Inventor; September 16, 2008; In English
Patent Info.: March 18, 2006US-Patent-7,425,650; US-Patent-Appl-SN-11/378,553
No Copyright; Avail.: CASI: A03, Hardcopy
Avail Online: http://hdl.handle.net/2060/20090006604
This invention relates to processes for preparing asymmetrical biphenyl tetracarboxylic acids and the corresponding asymmetrical dianhydrides, namely 2,3,3',4'-biphenyl dianhydride (a-BPDA), 2,3,3',4'-benzophenone dianhydride (a-BTDA) and 3,4'-methylenediphthalic anhydride (-MDPA). By cross-coupling reactions of reactive metal substituted o-xylenes or by cross-coupling o-xylene derivatives in the presence of catalysts, this invention specifically produces asymmetrical biphenyl intermediates that are subsequently oxidized or hydrolyzed and oxidized to provide asymmetric biphenyl tetracarboxylic acids in comparatively high yields. These asymmetrical biphenyl tetracarboxylic acids are subsequently converted to the corresponding asymmetrical dianhydrides without contamination by symmetrical biphenyl dianhydrides.
Official Gazette of the U.S. Patent and Trademark Office
ANHYDRIDES; ASYMMETRY; POLYPHENYLS; CARBOXYLIC ACIDS; CARBOXYL GROUP
20090006605 Science Applications International Corp., Washington, DC, United States; NASA Goddard Space Flight Center, Greenbelt, MD, United States
An Enhanced Global Precipitation Measurement (GPM) Validation Network Prototype
Schwaller, Matthew R.; Morris, K. Robert; [2009]; In English; European Geosciences Union General Assembly, 19 - 24 Apr. 2009, Vienna, Austria
Contract(s)/Grant(s): NNG06HX03C
Copyright; Avail.: CASI: A01, Hardcopy
A Validation Network (VN) prototype is currently underway that compares data from the Precipitation Radar (PR) instrument on NASA's Tropical Rainfall Measuring Mission (TRMM) satellite to similar measurements from the U.S. national network of operational weather radars. This prototype is being conducted as part of the ground validation activities of NASA's Global Precipitation Measurement (GPM) mission. GPM will carry a Dual-frequency Precipitation Radar instrument (DPR) with similar characteristics to the TRMM PR. The purpose of the VN is to identify and resolve significant discrepancies between the U.S. national network of ground radar (GR) observations and satellite observations. The ultimate goal of such comparisons is to understand and resolve the first order variability and bias of precipitation retrievals in different meteorological/hydrological regimes at large scales. This paper presents a description of, and results from, an improved algorithm for volume matching and comparison of PR and ground radar observations.
Derived from text
PRECIPITATION MEASUREMENT; METEOROLOGICAL RADAR; DATA RETRIEVAL; PROTOTYPES; TRMM SATELLITE; INTERCALIBRATION; ALGORITHMS
20090006607 NASA, Washington, DC United States
Gas composition sensing using carbon nanotube arrays
Li, Jing, Inventor; Meyyappan, Meyya, Inventor; September 23, 2008; In English
Patent Info.: August 5, 2005US-Patent-7,426,848; NASA-Case-ARC-15460-1; US-Patent-Appl-SN-11/203,576
No Copyright; Avail.: CASI: A02, Hardcopy
Avail Online: http://hdl.handle.net/2060/20090006607
A method and system for estimating one, two or more unknown components in a gas. A first array of spaced apart carbon nanotubes (''CNTs'') is connected to a variable pulse voltage source at a first end of at least one of the CNTs. A second end of the at least one CNT is provided with a relatively sharp tip and is located at a distance within a selected range of a constant voltage plate. A sequence of voltage pulses {V(t.sub.n)}.sub.n at times t=t.sub.n (n=1, . . . , N1; N1.gtoreq.3) is applied to the at least one CNT, and a pulse discharge breakdown threshold voltage is estimated for one or more gas components, from an analysis of a curve I(t.sub.n) for current or a curve e(t.sub.n) for electric charge transported from the at least one CNT to the constant voltage plate. Each estimated pulse discharge breakdown threshold voltage is compared with known threshold voltages for candidate gas components to estimate whether at least one candidate gas component is present in the gas. The procedure can be repeated at higher pulse voltages to estimate a pulse discharge breakdown threshold voltage for a second component present in the gas.
Official Gazette of the U.S. Patent and Trademark Office
CARBON NANOTUBES; GAS ANALYSIS; GAS COMPOSITION; THRESHOLD VOLTAGE; ELECTRIC POTENTIAL
20090006609 NASA, Washington, DC United States
Interphase for ceramic matrix composites reinforced by non-oxide ceramic fibers
DiCarlo, James A., Inventor; Bhatt, Ramakrishna, Inventor; Morscher, Gregory N., Inventor; Yun, Hee-Mann, Inventor; September 23, 2008; In English
Patent Info.: June 24, 2003US-Patent-7,427,428; NASA-Case-LEW-17240-1; US-Patent-Appl-SN-10/601,657
No Copyright; Avail.: CASI: A03, Hardcopy
Avail Online: http://hdl.handle.net/2060/20090006609
A ceramic matrix composite material is disclosed having non-oxide ceramic fibers, which are formed in a complex fiber architecture by conventional textile processes; a thin mechanically weak interphase material, which is coated on the fibers; and a non-oxide or oxide ceramic matrix, which is formed within the interstices of the interphase-coated fiber architecture. During composite fabrication or post treatment, the interphase is allowed to debond from the matrix while still adhering to the fibers, thereby providing enhanced oxidative durability and damage tolerance to the fibers and the composite material.
Official Gazette of the U.S. Patent and Trademark Office
CERAMIC FIBERS; CERAMIC MATRIX COMPOSITES; OXIDES
20090006611 QorTek, Inc., Williamsport, PA United States
Thin, nearly wireless adaptive optical device
Knowles, Gareth, Inventor; Hughes, Eli, Inventor; September 30, 2008; In English
Contract(s)/Grant(s): NAS5-03014
Patent Info.: September 10, 2007US-Patent-7,429,113; US-Patent-Appl-SN-11/900,088
No Copyright; Avail.: CASI: A03, Hardcopy
Avail Online: http://hdl.handle.net/2060/20090006611
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; ADAPTIVE OPTICS; OPTICAL MATERIALS
20090006631 NASA Goddard Space Flight Center, Greenbelt, MD, United States
Malaria Modeling and Surveillance in Thailand and Indonesia
Kiang, Richard; Adimi, Farida; Soebiyanto, Radina; September 29, 2008; In English; ICTM2008, 29 Sep. - 3 Oct. 2008, Jeju, Korea, Republic of; Original contains color illustrations
No Copyright; Avail.: CASI: A02, Hardcopy
Avail Online: http://hdl.handle.net/2060/20090006631
This viewgraph presentation reviews the modeling of malaria transmission in Thailand and Indonesia to assist in the understanding and reducing the incidence of the deadly disease. Satellite observations are being integrated into this work, and this is described herein.
CASI
INDONESIA; PARASITIC DISEASES; SATELLITE OBSERVATION; THAILAND; METEOROLOGICAL PARAMETERS
20090006635 NASA Goddard Space Flight Center, Greenbelt, MD, United States
Reusing Information Management Services for Recommended Decadal Study Missions to Facilitate Aerosol and Cloud Studies
Kempler, Steve; Alcott, Gary; Lynnes, Chris; Leptoukh, Greg; Vollmer, Bruce; Berrick, Steve; December 15, 2008; In English; American Geophysical Union Meeting, 15-19 Dec. 2008, San Francisco, CA, United States; Original contains color illustrations
No Copyright; Avail.: CASI: A01, Hardcopy
Avail Online: http://hdl.handle.net/2060/20090006635
NASA Earth Sciences Division (ESD) has made great investments in the development and maintenance of data management systems and information technologies, to maximize the use of NASA generated Earth science data. With information management system infrastructure in place, mature and operational, very small delta costs are required to fully support data archival, processing, and data support services required by the recommended Decadal Study missions. This presentation describes the services and capabilities of the Goddard Space Flight Center (GSFC) Earth Sciences Data and Information Services Center (GES DISC) and the reusability for these future missions. The GES DISC has developed a series of modular, reusable data management components currently in use. They include data archive and distribution (Simple, Scalable, Script-based, Science [S4] Product Archive aka S4PA), data processing (S4 Processor for Measurements aka S4PM), data search (Mirador), data browse, visualization, and analysis (Giovanni), and data mining services. Information management system components are based on atmospheric scientist inputs. Large development and maintenance cost savings can be realized through their reuse in future missions.
Author
AEROSOLS; EARTH SCIENCES; INFORMATION MANAGEMENT; CLOUDS (METEOROLOGY); PERIODIC VARIATIONS; ECOSYSTEMS
20090006636 NASA Goddard Space Flight Center, Greenbelt, MD, United States
A-Train Data Depot (ATDD)
Smith, Peter M.; Kempler, Steven; Leptoukh, Gregory; Savtchenko, Andrey; Kummerer, Robert; Gopolan, Arun; December 15, 2008; In English; American Geophysical Union Meeting, 15-19 Dec. 2008, San Francisco, CA, United States; Original contains color illustrations
No Copyright; Avail.: CASI: A01, Hardcopy
Avail Online: http://hdl.handle.net/2060/20090006636
ATDD is a web based tool which provides collocated data and display products for a number of A-train instruments Cloudsat, Calipso, OMI, AIRS, MODIS, MLS, POLDER-3, and ECWMF model data. Products provided include Clouds, Aerosols, Water Vapor, Temperatures and trace gases. All input data is online and in HDF4, HDF5 format. Display products include curtain images, horizontal strips, line plot overlays, and GE kmz files. Sample products are shown for two type of events. Hurricane event, Norbert, Oct 8, 2008 and a dust storm event over the Arabian Sea, Nov 13-14, 2008.
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HURRICANES; DATA; DATA PRODUCTS; IMAGE PROCESSING; SATELLITE IMAGERY; WEB SERVICES; ON-LINE SYSTEMS; DUST STORMS
20090006637 NASA Goddard Space Flight Center, Greenbelt, MD, United States
SWCX Emission from the Helium Focusing Cone - Model to Data Comparison
Koutroumpa, D.; Collier, M. R.; Kuntz, K. D.; Lallement, R.; Snowden, Steven L.; [2009]; In English; Original contains poor quality, truncated or crooked pages
Copyright; Avail.: CASI: A03, Hardcopy
A model for heliospheric solar wind charge exchange (SWCX) X-ray emission is applied to a series of XMM-Newton observations of the interplanetary focusing cone of interstellar helium. The X-ray data are from three coupled observations of the South Ecliptic Pole (SEP, to observe the cone) and the Hubble Deep Field-North (HDFN. to monitor global variations of the SWCX emission due to variations in the solar wind) from the period 24 November to 15 December 2003. There is good qualitative agreement between the model predictions and thc data with the maximum SWCX flux observed at an ecliptic longitude of approx. 72deg, consistent with the central longitude of the He cone. We observe a total excess of 2.1 +/- 1.3 LU in the O VII line and 2.0 +/- 0.9 LU in the 0 VIII line. However. the SWCX emission model, which was adjusted for solar wind conditions appropriate for late 2003, predicts an excess from the He cone of only 0.5 LU and 0.2 LU, respectively, in the O VII and O VIII lines. We discuss thc model to data comparison and provide possible explanations for the discrepancies. We also qualitatively reexamine our SWCX n~ocicl predictions in the 1/4 keV band with data from the ROSAT All-Sky Survey towards the North and South Ecliptic Poles, when the He cone was probably first detected in soft X-rays.
Author
SOLAR WIND; HELIOSPHERE; CHARGE EXCHANGE; WIND VELOCITY; WIND DIRECTION; INTERSTELLAR GAS; HELIUM
20090006638 NASA Goddard Space Flight Center, Greenbelt, MD, United States
Accurate Satellite-Derived Estimates of Tropospheric Ozone Radiative Forcing
Joiner, Joanna; Schoeberl, Mark R.; Vasilkov, Alexander P.; Oreopoulos, Lazaros; Platnick, Steven; Livesey, Nathaniel J.; Levelt, Pieternel F.; December 05, 2008; In English; Original contains black and white illustrations
Contract(s)/Grant(s): NNG06HX18CDE-FG02-07ER64354
Copyright; Avail.: CASI: A03, Hardcopy
Estimates of the radiative forcing due to anthropogenically-produced tropospheric O3 are derived primarily from models. Here, we use tropospheric ozone and cloud data from several instruments in the A-train constellation of satellites as well as information from the GEOS-5 Data Assimilation System to accurately estimate the instantaneous radiative forcing from tropospheric O3 for January and July 2005. We improve upon previous estimates of tropospheric ozone mixing ratios from a residual approach using the NASA Earth Observing System (EOS) Aura Ozone Monitoring Instrument (OMI) and Microwave Limb Sounder (MLS) by incorporating cloud pressure information from OMI. Since we cannot distinguish between natural and anthropogenic sources with the satellite data, our estimates reflect the total forcing due to tropospheric O3. We focus specifically on the magnitude and spatial structure of the cloud effect on both the shortand long-wave radiative forcing. The estimates presented here can be used to validate present day O3 radiative forcing produced by models.
Author
OZONE; SATELLITE OBSERVATION; TROPOSPHERE; EARTH OBSERVING SYSTEM (EOS)
20090006640 NASA Goddard Space Flight Center, Greenbelt, MD, United States
The TRMM Multi-Satellite Precipitation Analysis (TMPA)
Huffman, George J.; Adler, Robert F.; Bolvin, David T.; Nelkin, Eric J.; December 2008; In English; Original contains color and black and white illustrations
Copyright; Avail.: CASI: A03, Hardcopy
The Tropical Rainfall Measuring Mission (TRMM) Multi-satellite Precipitation Analysis (TMPA) is intended to provide a "best" estimate of quasi-global precipitation from the wide variety of modern satellite-borne precipitation-related sensors. Estimates are provided at relatively fine scales (0.25degx0.25deg, 3-hourly) in both real and post-real time to accommodate a wide range of researchers. However, the errors inherent in the finest scale estimates are large. The most successful use of the TMPA data is when the analysis takes advantage of the fine-scale data to create time/space averages appropriate to the user s application. We review the conceptual basis for the TMPA, summarize the processing sequence, and focus on two new activities. First, a recent upgrade to the real-time version incorporates several additional satellite data sources and employs monthly climatological adjustments to approximate the bias characteristics of the research quality post-real-time product. Second, an upgrade of the research quality post-real-time TMPA from Version 6 to Version 7 (in beta test at press time) is designed to provide a variety of improvements that increase the list of input data sets and correct several issues. Future enhancements for the TMPA will include improved error estimation, extension to higher latitudes, and a shift to a Lagrangian time interpolation scheme.
Author
TRMM SATELLITE; RAIN; PRECIPITATION (METEOROLOGY); ESTIMATES; CLIMATOLOGY; ERROR ANALYSIS; LAGRANGIAN FUNCTION; REAL TIME OPERATION
20090006641 NASA Goddard Space Flight Center, Greenbelt, MD, United States
Applications of TRMM-based Multi-Satellite Precipitation Estimation for Global Runoff Simulation: Prototyping a Global Flood Monitoring System
Hong, Yang; Adler, Robert F.; Huffman, George J.; Pierce, Harold; November 26, 2008; In English; Original contains color and black and white illustrations
Copyright; Avail.: CASI: A03, Hardcopy
Advances in flood monitoring/forecasting have been constrained by the difficulty in estimating rainfall continuously over space (catchment-, national-, continental-, or even global-scale areas) and flood-relevant time scale. With the recent availability of satellite rainfall estimates at fine time and space resolution, this paper describes a prototype research framework for global flood monitoring by combining real-time satellite observations with a database of global terrestrial characteristics through a hydrologically relevant modeling scheme. Four major components included in the framework are (1) real-time precipitation input from NASA TRMM-based Multi-satellite Precipitation Analysis (TMPA); (2) a central geospatial database to preprocess the land surface characteristics: water divides, slopes, soils, land use, flow directions, flow accumulation, drainage network etc.; (3) a modified distributed hydrological model to convert rainfall to runoff and route the flow through the stream network in order to predict the timing and severity of the flood wave, and (4) an open-access web interface to quickly disseminate flood alerts for potential decision-making. Retrospective simulations for 1998-2006 demonstrate that the Global Flood Monitor (GFM) system performs consistently at both station and catchment levels. The GFM website (experimental version) has been running at near real-time in an effort to offer a cost-effective solution to the ultimate challenge of building natural disaster early warning systems for the data-sparse regions of the world. The interactive GFM website shows close-up maps of the flood risks overlaid on topography/population or integrated with the Google-Earth visualization tool. One additional capability, which extends forecast lead-time by assimilating QPF into the GFM, also will be implemented in the future.
Author
TRMM SATELLITE; HYDROLOGY MODELS; FLOODS; FORECASTING; EARLY WARNING SYSTEMS; RAIN
20090006642 NASA Goddard Space Flight Center, Greenbelt, MD, United States
Lossless Astronomical Image Compression and the Effects of Random Noise
Pence, William; [2009]; In English; Original contains black and white illustrations
Copyright; Avail.: CASI: A03, Hardcopy
In this paper we compare a variety of modern image compression methods on a large sample of astronomical images. We begin by demonstrating from first principles how the amount of noise in the image pixel values sets a theoretical upper limit on the lossless compression ratio of the image. We derive simple procedures for measuring the amount of noise in an image and for quantitatively predicting how much compression will be possible. We then compare the traditional technique of using the GZIP utility to externally compress the image, with a newer technique of dividing the image into tiles, and then compressing and storing each tile in a FITS binary table structure. This tiled-image compression technique offers a choice of other compression algorithms besides GZIP, some of which are much better suited to compressing astronomical images. Our tests on a large sample of images show that the Rice algorithm provides the best combination of speed and compression efficiency. In particular, Rice typically produces 1.5 times greater compression and provides much faster compression speed than GZIP. Floating point images generally contain too much noise to be effectively compressed with any lossless algorithm. We have developed a compression technique which discards some of the useless noise bits by quantizing the pixel values as scaled integers. The integer images can then be compressed by a factor of 4 or more. Our image compression and uncompression utilities (called fpack and funpack) that were used in this study are publicly available from the HEASARC web site.Users may run these stand-alone programs to compress and uncompress their own images.
Author
RANDOM NOISE; COMPRESSING; DATA COMPRESSION; ASTRONOMY; PIXELS; FLOATING POINT ARITHMETIC; IMAGE PROCESSING
Additions to the NASA Aeronautics and Space Database as of 02/23/2009
20090006653 NASA Goddard Space Flight Center, Greenbelt, MD, United States
Pair-Starved Pulsar Magnetospheres
Muslimov, Alex G.; Harding, Alice K.; [2009]; In English; Original contains poor quality, truncated or crooked pages
Copyright; Avail.: CASI: A03, Hardcopy
We propose a simple analytic model for the innermost (within the light cylinder of canonical radius, approx. c/Omega) structure of open-magnetic-field lines of a rotating neutron star (NS) with relativistic outflow of charged particles (electrons/positrons) and arbitrary angle between the NS spin and magnetic axes. We present the self-consistent solution of Maxwell's equations for the magnetic field and electric current in the pair-starved regime where the density of electron-positron plasma generated above the pulsar polar cap is not sufficient to completely screen the accelerating electric field and thus establish thee E . B = 0 condition above the pair-formation front up to the very high altitudes within the light cylinder. The proposed mode1 may provide a theoretical framework for developing the refined model of the global pair-starved pulsar magnetosphere.
Author
PULSAR MAGNETOSPHERES; NEUTRON STARS; MATHEMATICAL MODELS; RELATIVISTIC PARTICLES; ELECTRIC FIELDS; MAGNETIC FIELDS; POLAR CAPS; PULSARS
Additions to the NASA Aeronautics and Space Database as of 02/24/2009
20090006689 NASA Johnson Space Center, Houston, TX, United States
HRP Integrated Research Plan Analysis
Elliott, Todd; [2009]; In English; Original contains color and black and white illustrations
Copyright; Avail.: CASI: A03, Hardcopy
The charts, that are the totality of this document, presents tasks, duration of the tasks, the start and finish of the tasks, and subtasks. Also presented are PERT charts that display the beginning, external milestones, and end points for the tasks, and sub tasks.
CASI
MANAGEMENT PLANNING; HUMAN RESOURCES; RESEARCH MANAGEMENT; PROJECT PLANNING; SCHEDULING
20090006691 NASA Johnson Space Center, Houston, TX, United States
Orbital Debris Quarterly News, Vol. 13, No. 1
Liou, J.-C., Editor; Shoots, Debi, Editor; January 2009; In English; Original contains color and black and white illustrations
Contract(s)/Grant(s): NNJ05HI05C
Report No.(s): JSC-17604; Copyright; Avail.: CASI: A03, Hardcopy
Topics discussed include: new debris from a decommissioned satellite with a nuclear power source; debris from the destruction of the Fengyun-1C meteorological satellite; quantitative analysis of the European Space Agency's Automated Transfer Vehicle 'Jules Verne' reentry event; microsatellite impact tests; solar cycle 24 predictions and other long-term projections and geosynchronus (GEO) environment for the Orbital Debris Engineering Model (ORDEM2008). Abstracts from the NASA Orbital Debris Program Office, examining satellite reentry risk assessments and statistical issues for uncontrolled reentry hazards, are also included.
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SPACE DEBRIS; RISK ASSESSMENT; HAZARDS; AEROSPACE SAFETY
20090006694 NASA Johnson Space Center, Houston, TX, United States
Renal Stone Risk During Spaceflight: Assessment and Countermeasure Validation
Pietrzyk, Robert A.; Whitson, Peggy A.; Sams, Clarence F.; Jones, Jeffery A.; Smith, Scott M.; February 2, 2009; In English; NASA Human Research Program Investigators' Meeting, 2-4 Feb. 2009, Houston, TX, United States; Original contains color illustrations
Report No.(s): JSC-17672; Copyright; Avail.: CASI: A03, Hardcopy
This viewgraph presentation describes the risks of renal stone formation in manned space flight. The contents include: 1) Risk; 2) Evidence; 3) Nephrolithiasis -A Multifactorial Disease; 4) Symptoms/signs; 5) Urolithiasis and Stone Passage; 6) Study Objectives; 7) Subjects; 8) Methods; 9) Investigation Results; 10) Potassium Citrate; 11) Calcium Balance; 12) Case Study; 13) Significant Findings; 14) Risk Mitigation Strategies and Recommended Actions; and 15) Future Potential.
CASI
COUNTERMEASURES; MANNED SPACE FLIGHT; RISK; RENAL FUNCTION; AEROSPACE MEDICINE; KIDNEYS
20090006695 NASA Goddard Space Flight Center, Greenbelt, MD, United States
Is the Universe More Transparent to Gamma Rays than Previously Thought?
Stecker, Floyd W.; Scully, Sean T.; [2009]; In English; Original contains black and white illustrations
Copyright; Avail.: CASI: A03, Hardcopy
The MAGIC collaboration has recently reported the detection of the strong gamma-ray blazar 3C279 during a 1-2 day flare. They have used their spectral observations to draw conclusions regarding upper limits on the opacity of the Universe to high energy gamma-rays and, by implication, upper limits on the extragalactic mid-infrared background radiation. In this paper we examine the effect of gamma-ray absorption by the extragalactic infrared radiation on intrinsic spectra for this blazar and compare our results with the observational data on 3C279. We find agreement with our previous results, contrary to the recent assertion of the MAGIC group that the Universe is more transparent to gamma-rays than our calculations indicate. Our analysis indicates that in the energy range between approx. 80 and approx. 500 GeV, 3C279 has a best-fit intrinsic spectrum with a spectral index approx. 1.78 using our fast evolution model and approx. 2.19 using our baseline model. However, we also find that spectral indices in the range of 1.0 to 3.0 are almost as equally acceptable as the best fit spectral indices. Assuming the same intrinsic spectral index for this flare as for the 1991 flare from 3C279 observed by EGRET, viz., 2.02, which lies between our best fit indeces, we estimate that the MAGIC flare was approx.3 times brighter than the EGRET flare observed 15 years earlier.
Author
BACKGROUND RADIATION; GAMMA RAYS; RADIATION SPECTRA; TRANSPARENCE; GAMMA RAY TELESCOPES; GAMMA RAY OBSERVATORY; BRIGHTNESS; BLAZARS
20090006701 NASA Goddard Space Flight Center, Greenbelt, MD, United States
NASA SSA for Robotic Missions
Newman, Lauri K.; January 14, 2009; In English; JFCC-Space Control Group Meeting, 14 Jan. 2009, Colorado Springs, Co, United States; Original contains color illustrations
No Copyright; Avail.: CASI: A03, Hardcopy
Avail Online: http://hdl.handle.net/2060/20090006701
This viewgraph presentation reviews NASA's Space Situational Awareness (SSA) activities as preparation for robotic missions and Goddard's role in this work. The presentation includes the preparations that Goddard Space Flight Center (GSFC) has made to provide consolidated space systems protection indluding consolidating GSFC support for Orbit Debris analysis, conjunction assessment and collision avoidance, commercial and foreign support, and protection of GSFC managed missions.
CASI
NASA PROGRAMS; ROBOTICS; SITUATIONAL AWARENESS; AEROSPACE ENVIRONMENTS
20090006702 NASA Johnson Space Center, Houston, TX, United States
Hydrogen Hazards Assessment Protocol (HHAP): Approach and Methodology
Woods, Stephen; [2009]; In English; Original contains color and black and white illustrations
No Copyright; Avail.: CASI: A03, Hardcopy
Avail Online: http://hdl.handle.net/2060/20090006702
This viewgraph presentation reviews the approach and methodology to develop a assessment protocol for hydrogen hazards. Included in the presentation are the reasons to perform hazards assessment, the types of hazard assessments that exist, an analysis of hydrogen hazards, specific information about the Hydrogen Hazards Assessment Protocol (HHAP). The assessment is specifically tailored for hydrogen behavior. The end product of the assesment is a compilation of hazard, mitigations and associated factors to facilitate decision making and achieve the best practice.
CASI
HAZARDS; HYDROGEN; HAZARDOUS MATERIALS; RISK ASSESSMENT; SAFETY MANAGEMENT; RISK MANAGEMENT
20090006720 NASA Goddard Space Flight Center, Greenbelt, MD, United States
Development, Qualification and Integration of the Optical Fiber Array Assemblies for the Lunar Reconnaissance Orbiter
Ott, Melanie N.; Switzer, Robert; Chuska, Richard; LaRocca, Frank; Thomas, William Joe; Macmurphy, Shawn; August 10, 2008; In English; SPIE Optics + Photonics 2008, 10 - 14 Aug. 2008, California, United States; Original contains black and white illustrations
Copyright; Avail.: CASI: A03, Hardcopy
The NASA Goddard Fiber Optics Team in the Electrical Engineering Division of the Applied Engineering and Technology Directorate, designed, developed and integrated the space flight optical fiber array hardware for the Lunar Reconnaissance Orbiter (LRO). The two new assemblies that were designed and manufacturing at GSFC for the LRO exist in configurations that are unique in the world for the application of ranging and LIDAR. Described here is an account of the journey and the lessons learned from design to integration for the Lunar Orbiter Laser Altimeter and the Laser Ranging Application on the LRO.
Author
OPTICAL FIBERS; LUNAR ORBITER; ELECTRICAL ENGINEERING; LASER ALTIMETERS; FIBER OPTICS; OPTICAL RADAR; RANGEFINDING; RECONNAISSANCE
20090006723 NASA Goddard Space Flight Center, Greenbelt, MD, United States
Applications of Optical Fiber Assemblies in Harsh Environments, the Journey Past, Present and Future
Ott, Melanie N.; LaRocca, Frank; Thomas, William Joe; Switzer, Robert; Chuska, Richard; Macmurphy, Shawn; August 10, 2008; In English; SPIE Optics + Photonics 2008, 10 - 14 Aug. 2008, California, United States; Original contains black and white illustrations
Copyright; Avail.: CASI: A03, Hardcopy
Over the past ten years, NASA has studied the effects of harsh environments on optical fiber assemblies for communication systems, lidar systems, and science missions. The culmination of this has resulted in recent technologies that are unique and tailored to meeting difficult requirements under challenging performance constraints. This presentation will focus on the past mission applications of optical fiber assemblies including; qualification information, lessons learned and new technological advances that will enable the road ahead.
Author
OPTICAL FIBERS; TELECOMMUNICATION; OPTICAL RADAR; CONNECTORS
20090006725 NASA Goddard Space Flight Center, Greenbelt, MD, United States; MEI Technologies, Inc., Seabrook, MD, United States
Fiber Optic Cable Thermal Preparation to Ensure Stable Operation
Thoames Jr, William J.; Chuska, Rick F.; LaRocca, Frank V.; Switzer, Robert C.; Macmurphy, Shawn L.; Ott, Melanie N.; August 10, 2008; In English; SPIE Optics + Photonics 2008, 10 - 14 Aug. 2008, California, United States; Original contains black and white illustrations
Copyright; Avail.: CASI: A03, Hardcopy
Fiber optic cables are widely used in modern systems that must provide stable operation during exposure to changing environmental conditions. For example, a fiber optic cable on a satellite may have to reliably function over a temperature range of -50 C up to 125 C. While the system requirements for a particular application will dictate the exact method by which the fibers should be prepared, this work will examine multiple ruggedized fibers prepared in different fashions and subjected to thermal qualification testing. The data show that if properly conditioned the fiber cables can provide stable operation, but if done incorrectly, they will have large fluctuations in transmission.
Author
FIBER OPTICS; PERFORMANCE TESTS; TEMPERATURE EFFECTS; THERMAL STABILITY
20090006729 NASA Goddard Space Flight Center, Greenbelt, MD, United States; MEI Technologies, Inc., Seabrook, MD, United States
Vibration Performance Comparison Study on Current Fiber Optic Connector Technologies
Ott, Melanie N.; Thomes Jr., William J.; LaRocca, Frank V.; Switzer, Robert C.; Chuska, Rick F.; Macmurphy, Shawn L.; August 10, 2008; In English; SPIE Optics + Photonics 2008, 10 - 14 Aug. 2008, California, United States; Original contains black and white illustrations
Copyright; Avail.: CASI: A03, Hardcopy
Fiber optic cables are increasingly being used in harsh environments where they are subjected to vibration. Understanding the degradation in performance under these conditions is essential for integration of the fibers into the given application. System constraints oftentimes require fiber optic connectors so subsystems can be removed or assembled as needed. In the present work, various types of fiber optic connectors were monitored in-situ during vibration testing to examine the transient change in optical transmission and the steady-state variation following the event. Inspection of the fiber endfaces and connectors was performed at chosen intervals throughout the testing.
Author
FIBER OPTICS; VIBRATION; CONNECTORS; DEGRADATION; LIGHT TRANSMISSION
20090006758 NASA Johnson Space Center, Houston, TX, United States
Liquid Oxygen Rotating Friction Ignition Testing of Aluminum and Titanium with Monel and Inconel for Rocket Engine Propulsion System Contamination Investigation
Peralta, S.; Rosales, Keisa R.; Stoltzfus, Joel M.; [2009]; In English; G04 Twelfth International Symposium on Flammability and Sensitivity of Materials in Oxygen-Enriched Atmospheres, 7 - 9 Oct. 2009, Berlin, Germany; Original contains color and black and white illustrations
Copyright; Avail.: CASI: A03, Hardcopy
Metallic contaminant was found in the liquid oxygen (LOX) pre-valve screen of the shuttle main engine propulsion system on two orbiter vehicles. To investigate the potential for an ignition, NASA Johnson Space Center White Sands Test Facility performed (modified) rotating friction ignition testing in LOX. This testing simulated a contaminant particle in the low-pressure oxygen turbo pump (LPOTP) and the high-pressure oxygen turbo pump (HPOTP) of the shuttle main propulsion system. Monel(R) K-500 and Inconel(R) 718 samples represented the LPOTP and HPOTP materials. Aluminum foil tape and titanium foil represented the contaminant particles. In both the Monel(R) and Inconel(R) material configurations, the aluminum foil tape samples did not ignite after 30 s of rubbing. In contrast, all of the titanium foil samples ignited regardless of the rubbing duration or material configuration. However, the titanium foil ignitions did not propagate to the Monel and Inconel materials.
Author
CONTAMINANTS; CONTAMINATION; IGNITION; INCONEL (TRADEMARK); SPACE SHUTTLE MAIN ENGINE; MONEL (TRADEMARK); FUEL CONTAMINATION; ROCKET ENGINES
20090006763 NASA Johnson Space Center, Houston, TX, United States
International Space Station Science Research Accomplishments during the Assembly Years: An Analysis of Results from 2000-2008
Evans, Cynthia A.; Robinson, Julie A.; Tate-Brown, Judy; Thumm, Tracy; Crespo-Richey, Jessica; Baumann, David; Rhatigan, Jennifer; [2009]; In English; Original contains color and black and white illustrations
Report No.(s): NASA/TP-2009-213146-REVA; 17592; No Copyright; Avail.: CASI: A12, Hardcopy
Avail Online: http://hdl.handle.net/2060/20090006763
The International Space Station (ISS) celebrated ten years of operations in November 2008. Today, the ISS is more than a human outpost in low Earth orbit. It is also an international science laboratory hosting state-of-the-art scientific facilities that support fundamental and applied research across the range of physical and biological sciences. The launch of the first ISS element in 1998, the Russian Zarya module, was a highly visible milestone for international cooperation in human exploration. Later, when the first international crew that included Bill Shepard, Sergei Krikalev, and Yuri Gidzenko moved into the ISS to establish a continuous human presence in space, a new, global chapter in the history of human spaceflight was opened. As of this writing, 18 multinational crews comprising 52 astronauts and cosmonauts have called the ISS their home and workplace since November 2000. Dozens more have visited and assisted construction and science activities. While the ISS did not support permanent human crews during the first two years of operations (November 1998 to November 2000), it hosted a few early science experiments months before the first international crew took up residence. Since that time and simultaneous with the complicated task of ISS construction and overcoming impacts from the tragic Columbia accident science returns from the ISS have been growing at a steady pace. From Expedition 0 through 15, 138 experiments have been operated on the ISS, supporting research for hundreds of ground-based investigators from the U.S. and international partners. Many experiments are carried forward over several ISS increments, allowing for additional experimental runs and data collection. This report focuses on the experimental results collected to date, including scientific publications from studies based on operational data. Today, NASA's priorities for research aboard the ISS center on understanding human health during long-duration missions, researching effective countermeasures for long-duration crewmembers, and researching and testing new technologies that can be used for future exploration crews and spacecraft. Most research also supports new understandings, methods or applications relevant to life on Earth, such as understanding effective protocols to protect against loss of bone density or better methods for producing stronger metal alloys. Experiment results have already been used in applications as diverse as the manufacture of solar cell and insulation materials for new spacecraft and the verification of complex numerical models for behavior of fluids in fuel tanks.
Author
INTERNATIONAL SPACE STATION; LIFE SCIENCES; MATHEMATICAL MODELS; SPACEBORNE EXPERIMENTS; TECHNOLOGY UTILIZATION
Additions to the NASA Aeronautics and Space Database as of 02/25/2009
20090006787 White Sands Test Facility, Las Cruces, NM, United States
Investigation, Analysis, and Testing of Self-contained Oxygen Generators
Keddy, Christopher P.; Haas, Jon P.; Starritt, Larry; December 10, 2008; In English; Original contains color and black and white illustrations
Report No.(s): JSC-17515; WSTF-IR-1129-001-08; No Copyright; Avail.: CASI: A05, Hardcopy
Avail Online: http://hdl.handle.net/2060/20090006787
Self Contained Oxygen Generators (SCOGs) have widespread use in providing emergency breathing oxygen in a variety of environments including mines, submarines, spacecraft, and aircraft. These devices have definite advantages over storing of gaseous or liquid oxygen. The oxygen is not generated until a chemical briquette containing a chlorate or perchlorate oxidizer and a solid metallic fuel such as iron is ignited starting a thermal decomposition process allowing gaseous oxygen to be produced. These devices are typically very safe to store, easy to operate, and have primarily only a thermal hazard to the operator that can be controlled by barriers or furnaces. Tens of thousands of these devices are operated worldwide every year without major incident. This report examines the rare case of a SCOG whose behavior was both abnormal and lethal. This particular type of SCOG reviewed is nearly identical to a flight qualified version of SCOG slated for use on manned space vehicles. This Investigative Report is a compilation of a NASA effort in conjunction with other interested parties including military and aerospace to understand the causes of the particular SCOG accident and what preventative measures can be taken to ensure this incident is not repeated. This report details the incident and examines the root causes of the observed SCOG behavior from forensic evidence. A summary of chemical and numerical analysis is provided as a background to physical testing of identical SCOG devices. The results and findings of both small scale and full scale testing are documented on a test-by-test basis along with observations and summaries. Finally, conclusions are presented on the findings of this investigation, analysis, and testing along with suggestions on preventative measures for any entity interested in the safe use of these devices.
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OXYGEN; LIFE SUPPORT SYSTEMS; PERFORMANCE TESTS; FAILURE ANALYSIS; ACCIDENT PREVENTION
20090006791 NASA Johnson Space Center, Houston, TX, United States
Determination of Pass/Fail Criteria for Promoted Combustion Testing
Sparks, Kyle M.; Stoltzfus, Joel M.; Steinberg, Theodore A.; Lynn, David; [2009]; In English; 12th International Symposium on Flammability and Sensitivity, 7-9 Oct. 2009, Berlin, Germany, FROM; Original contains color illustrations
Report No.(s): JSC-17608; Copyright; Avail.: CASI: A03, Hardcopy
Promoted ignition testing is used to determine the relative flammability of metal rods in oxygen-enriched atmospheres. In these tests, a promoter is used to ignite each metal rod to start the sample burning. Experiments were performed to better understand the promoted ignition test by obtaining insight into the effect a burning promoter has on the preheating of a test sample. Test samples of several metallic materials were prepared and coupled to fast-responding thermocouples along their length. Various ignition promoters were used to ignite the test samples. The thermocouple measurements and test video was synchronized to determine temperature increase with respect to time and length along each test sample. A recommended length of test sample that must be consumed to be considered a flammable material was determined based on the preheated zone measured from these tests. This length was determined to be 30 mm (1.18 in.). Validation of this length and its rationale are presented.
Author
IGNITION TEMPERATURE; HEAT OF COMBUSTION; OXYGEN; COMBUSTION; FLAMMABILITY; IGNITION
20090006792 NASA Johnson Space Center, Houston, TX, United States
Decontaminating Solar Wind Samples with the Genesis Ultra-Pure Water Megasonic Wafer Spin Cleaner
Calaway, Michael J.; Rodriquez, M. C.; Allton, J. H.; Stansbery, E. K.; [2009]; In English; 40th Lunar and Planetary Science Conference, 23-27 Mar. 2009, Woodlands, TX, United States; Original contains color illustrations
Copyright; Avail.: CASI: A01, Hardcopy
The Genesis sample return capsule, though broken during the landing impact, contained most of the shattered ultra-pure solar wind collectors comprised of silicon and other semiconductor wafers materials. Post-flight analysis revealed that all wafer fragments were littered with surface particle contamination from spacecraft debris as well as soil from the impact site. This particulate contamination interferes with some analyses of solar wind. In early 2005, the Genesis science team decided to investigate methods for removing the surface particle contamination prior to solar wind analysis.
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DECONTAMINATION; SAMPLE RETURN MISSIONS; SOLAR WIND; WAFERS; WATER
20090006794 NASA Johnson Space Center, Houston, TX, United States
Status of Reconstruction of Fragmented Diamond-on-Silicon Collector From Genesis Spacecraft Solar Wind Concentrator
Rodriquez, Melissa C.; Calaway, M. C.; McNamara, K. M.; Hittle, J. D.; [2009]; In English; 40th Lunar and Planetary Science Conference, 23-27 Mar. 2009, Woodlands, TX, United States; Original contains color and black and white illustrations
Copyright; Avail.: CASI: A01, Hardcopy
In addition to passive solar wind collector surfaces, the Genesis Discovery Mission science canister had on board an electrostatic concave mirror for concentrating the solar wind ions, known as the concentrator . The 30-mm-radius collector focal point (the target) was comprised of 4 quadrants: two of single crystal SiC, one of polycrystalline 13C diamond and one of diamond-like-carbon (DLC) on a silicon substrate. [DLC-on-silicon is also sometimes referenced as Diamond-on-silicon, DOS.] Three of target quadrants survived the hard landing intact, but the DLC-on-silicon quadrant fractured into numerous pieces (Fig. 1). This abstract reports the status of identifying the DLC target fragments and reconstructing their original orientation.
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CARBON; DIAMONDS; FRAGMENTS; GENESIS MISSION; SILICON; SOLAR WIND; CONCENTRATORS
20090006804 NASA Johnson Space Center, Houston, TX, United States
Food Mass Reduction Trade Study
Perchonok, Michele H.; Stoklosa, Adam M.; Feb. 2, 2009; In English; HRP Investigators' Workshop, 2-4 Feb. 2009, League City, TX, United States; Original contains color illustrations
Report No.(s): JSC-17653; Copyright; Avail.: CASI: A01, Hardcopy
Future long duration manned space flights beyond low earth orbit will require the food system to remain safe, acceptable, and nutritious while efficiently balancing appropriate vehicle resources such as mass, volume, power, water, and crewtime. Often, this presents a challenge since maintaining the quality of the food system can result in a higher mass and volume. The Orion vehicle is significantly smaller than the Shuttle vehicle and the International Space Station and the mass and volume available for food is limited. Therefore, the food team has been challenged to reduce the mass of the packaged food from 1.82 kg per person per day to 1.14 kg per person per day. Past work has concentrated on how to reduce the mass of the packaging which contributes to about 15% of the total mass of the packaged food system. Designers have also focused on integrating and optimizing the Orion galley equipment as a system to reduce mass. To date, there has not been a significant effort to determine how to reduce the food itself. The objective of this project is to determine how the mass and volume of the packaged food can be reduced while maintaining caloric and hydration requirements. The following tasks are the key elements to this project: (1) Conduct further analysis of the ISS Standard Menu to determine moisture, protein, carbohydrate, and fat levels. (2) Conduct trade studies to determine how to bring the mass of the food system down. Trade studies may include removing the water of the total food system and/or increasing the fat content. (3) Determine the preferred method for delivery of the new food (e.g. bars, or beverages) and the degree of replacement. (4) Determine whether there are commercially available products that meet the requirements. By the end of this study, an estimate of the mass and volume savings will be provided to the Constellation Program. In addition, if new technologies need to be developed to achieve the mass savings, the technologies, timeline, and budget will be identified at the end of the project.
Author
CONSTELLATION PROGRAM; LONG DURATION SPACE FLIGHT; MANNED SPACE FLIGHT; WEIGHT REDUCTION; FOOD PRODUCTION (IN SPACE); SPACE FLIGHT FEEDING; SPACE RATIONS
20090006806 NASA Johnson Space Center, Houston, TX, United States
Lunar Navigation Architecture Design Considerations
D'Souza, Christopher; Getchius, Joel; Holt, Greg; Moreau, Michael; [2009; In English; 32nd Annual AAS Guidance and Control Conference, 31 Jan. - 4 Feb. 2009, Breckenridge, Co, United States; Original contains color and black and white illustrations
Contract(s)/Grant(s): WBS 544423.02.36.15.10
Report No.(s): JSC-17617; Copyright; Avail.: CASI: A03, Hardcopy
The NASA Constellation Program is aiming to establish a long-term presence on the lunar surface. The Constellation elements (Orion, Altair, Earth Departure Stage, and Ares launch vehicles) will require a lunar navigation architecture for navigation state updates during lunar-class missions. Orion in particular has baselined earth-based ground direct tracking as the primary source for much of its absolute navigation needs. However, due to the uncertainty in the lunar navigation architecture, the Orion program has had to make certain assumptions on the capabilities of such architectures in order to adequately scale the vehicle design trade space. The following paper outlines lunar navigation requirements, the Orion program assumptions, and the impacts of these assumptions to the lunar navigation architecture design. The selection of potential sites was based upon geometric baselines, logistical feasibility, redundancy, and abort support capability. Simulated navigation covariances mapped to entry interface flightpath- angle uncertainties were used to evaluate knowledge errors. A minimum ground station architecture was identified consisting of Goldstone, Madrid, Canberra, Santiago, Hartebeeshoek, Dongora, Hawaii, Guam, and Ascension Island (or the geometric equivalent).
Author
CONSTELLATION PROGRAM; LUNAR SURFACE; LAUNCH VEHICLES; FLIGHT PATHS; NAVIGATION; GROUND STATIONS
20090006808 NASA Johnson Space Center, Houston, TX, United States
NASA Product Peer Review Process
Jenks, Ken; [2009]; In English; NASA PM Challenge 2009, 24-29 Feb. 2009, Daytona Beach, FL, United States; Original contains color illustrations
Report No.(s): JSC-17618; No Copyright; Avail.: CASI: A03, Hardcopy
Avail Online: http://hdl.handle.net/2060/20090006808
This viewgraph presentation describes NASA's product peer review process. The contents include: 1) Inspection/Peer Review at NASA; 2) Reasons for product peer reviews; 3) Different types of peer reviews; and 4) NASA requirements for peer reviews. This presentation also includes a demonstration of an actual product peer review.
CASI
NASA PROGRAMS; PROJECT MANAGEMENT; MANNED SPACE FLIGHT; SYSTEMS ENGINEERING
20090006821 NASA Johnson Space Center, Houston, TX, United States
Human Factors in Training
Barshi, Immanuel; Byrne, Vicky; Arsintescu, Lucia; Connell, Erin; Sandor, Aniko; [2009]; In English; NASA Human Research Program Investigators' Meeting, 2-4 Feb. 2009, League City, TX, United States; Original contains color illustrations
Report No.(s): JSC-17696; Copyright; Avail.: CASI: A01, Hardcopy
Future space missions will be significantly longer than current shuttle missions and new systems will be more complex than current systems. Increasing communication delays between crews and Earth-based support means that astronauts need to be prepared to handle the unexpected on their own. As crews become more autonomous, their potential span of control and required expertise must grow to match their autonomy. It is not possible to train for every eventuality ahead of time on the ground, or to maintain trained skills across long intervals of disuse. To adequately prepare NASA personnel for these challenges, new training approaches, methodologies, and tools are required. This research project aims at developing these training capabilities. By researching established training principles, examining future needs, and by using current practices in space flight training as test beds, both in Flight Controller and Crew Medical domains, this research project is mitigating program risks and generating templates and requirements to meet future training needs. Training efforts in Fiscal Year 08 (FY08) strongly focused on crew medical training, but also began exploring how Space Flight Resource Management training for Mission Operations Directorate (MOD) Flight Controllers could be integrated with systems training for optimal Mission Control Center (MCC) operations. The Training Task addresses Program risks that lie at the intersection of the following three risks identified by the Project: (1) Risk associated with poor task design (2) Risk of error due to inadequate information (3) Risk associated with reduced safety and efficiency due to poor human factors design
Author
ASTRONAUT TRAINING; HUMAN FACTORS ENGINEERING; PROCEDURES; RISK; LONG DURATION SPACE FLIGHT; INTERPLANETARY FLIGHT; CONSTELLATION PROGRAM
20090006826 NASA Johnson Space Center, Houston, TX, United States
Early Petrogenesis and Late Impact(?) Metamorphism on the GRA 06128/9 Parent Body
Nyquist, Laurence E.; Shih, C.-Y.; Reese, Y. D.; [2009]; In English; 40th Lunar Planetary Conference, 23-27 Mar. 2009, Houston, TX, United States; Original contains color and black and white illustrations
Copyright; Avail.: CASI: A01, Hardcopy
Initial studies of GRA06128 and GRA06129 (hereafter GRA 8 and GRA 9) suggested that these alkalic meteorites represent partial melts of a parent body of approximately chondritic composition. A SM-147-Nd-143 isochron age of 4.545 +/- 0.087 Ga was found for GRA 8, but plagioclase (oligoclase) plus whole rock and leachate samples gave an apparent secondary age of approximately 3.5 Ga. The approximately 4.54 Ga age was interpreted to be the crystallization age of GRA 8; the approximately 3.5 Ga as an upper limit to a time of metamorphism. Here we extend Sm-Nd and Rb-Sr analyses to GRA 9.
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CHONDRITES; PETROGENESIS; METEORITIC COMPOSITION; GEOCHRONOLOGY; METEORITE PARENT BODIES; METAMORPHISM (GEOLOGY)
20090006828 NASA Johnson Space Center, Houston, TX, United States
Isotopic Evidence for a Martian Regolith Component in Martian Meteorites
Rao, M. N.; Nyquist, L. E.; Bogard, D. D.; Garrison, D. H.; Sutton, S.; [2009]; In English; 40th Lunar Planetary Science Conferece, 23-27 Mar. 2009, Houston, TX, United States; Original contains color and black and white illustrations
Copyright; Avail.: CASI: A01, Hardcopy
Noble gas measurements in gas-rich impact-melt (GRIM) glasses in EET79001 shergottite showed that their elemental and isotopic composition is similar to that of the Martian atmosphere [1-3]. The GRIM glasses contain large amounts of Martian atmospheric gases. Those measurements further suggested that the Kr isotopic composition of Martian atmosphere is approximately similar to that of solar Kr. The (80)Kr(sub n) - (80)Kr(sub M) mixing ratio in the Martian atmosphere reported here is approximately 3%. These neutron-capture reactions presumably occurred in the glass-precursor regolith materials containing Sm- and Br- bearing mineral phases near the EET79001/ Shergotty sites on Mars. The irradiated materials were mobilized into host rock voids either during shock-melting or possibly by earlier aeolian / fluvial activity.
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MARS ATMOSPHERE; METEORITIC COMPOSITION; PLANETARY GEOLOGY; REGOLITH; SHERGOTTITES; METEORITE PARENT BODIES; SNC METEORITES
Additions to the NASA Aeronautics and Space Database as of 02/26/2009
20090006855 NASA Goddard Space Flight Center, Greenbelt, MD, United States
Reviewing E(sub peak) Relations with Swift and Suzaku Data
Krimm, Hans A.; Yamaoka, Kazutaka; Ohno, Masanori; Sakamoto, Takanori; Sato, Goro; Sugita, Satoshi; Tashiro, Makoto; Hara, R.; Tanaka, H.; Ohmori, M.; Yamauchi, M.; [2008]; In English; Original contains black and white illustrations
Contract(s)/Grant(s): NNG06EO90A
Copyright; Avail.: CASI: A02, Hardcopy
In recent years several authors have derived correlations between gamma-ray burst (GRB) spectral peak energy (E(sub peak)) and either isotropic-equivalent radiated energy (E(sub iso)) or peak luminosity (L(sub iso)). Since these relationships are controversial, but could provide redshift estimators, it is important to determine whether bursts detected by Swift exhibit the same correlations. Swift has greatly added to the number of GRBs for which redshifts are known and hence E(sub iso) and L(sub iso) could be calculated. However, for most bursts it is not possible to adequately constrain E(sub peak) with Swift data alone since most GRBs have E(sub peak) above the energy range (15-50 keV) of the Swift Burst Alert Telescope (BAT). Therefore we have analyzed the spectra of 78 bursts (31 with redshift) which were detected by both Swift/BAT and the Suzaku Wide-band All-sky Monitor (WAM), which covers the energy range 50-5000 keV. For most bursts in this sample we can precisely determine E(sub peak) and for bursts with known redshift we can compare how the E(sub peak) relations for the Swift/Suzaku sample compare to earlier published results. Keywords: gamma rays: bursts
Author
SWIFT OBSERVATORY; GAMMA RAY BURSTS; BROADBAND; CORRELATION; LUMINOSITY; RED SHIFT
20090006863 NASA Goddard Space Flight Center, Greenbelt, MD, United States
Space-Based Ornithology - Studying Bird Migration and Environmental Change in North America
Smith, James A.; Deppe, Jill L.; September 15, 2008; In English; Original contains black and white illustrations
Copyright; Avail.: CASI: A02, Hardcopy
Natural fluctuations in the availability of critical stopover sites coupled with anthropogenic destruction of wetlands, land-use change, and anticipated losses due to climate change present migratory birds with a formidable challenge. Space based technology in concert with bird migration modeling and geographical information analysis yields new opportunities to shed light on the distribution and movement of organisms on the planet and their sensitivity to human disturbances and environmental changes. At the NASA Goddard Space Flight Center, we are creating ecological forecasting tools for science and application users to address the consequences of loss of wetlands, flooding, drought or other natural disasters such as hurricanes on avian biodiversity and bird migration. We use an individual-based bird biophysical migration model, driven by remotely sensed land surface data, climate and hydrologic data, and biological field observations to study migratory bird responses to environmental change in North America. Simulation allows us to study bird migration across multiple scales and can be linked to mechanistic processes describing the time and energy budget states of migrating birds. We illustrate our approach by simulating the spring migration of pectoral sandpipers from the Gulf of Mexico to Alaska. Mean stopover length and trajectory patterns are consistent with field observations.
Author
BIRDS; NORTH AMERICA; REMOTE SENSING; EARTH ENVIRONMENT; CLIMATE CHANGE
20090006866 NASA Goddard Space Flight Center, Greenbelt, MD, United States
Maritime Aerosol Network (MAN) as a Component of AERONET
Smirnov, A.; Holben, B. N.; Slutsker, I.; Giles, D. M.; McClain, C. R.; Eck, T. F.; Sakerin, S. M.; Macke, A.; Croot, P.; Zibordi, G.; Quinn, P. K.; et al.; [2008]; In English; To be published in Journal of Geophysical Research - Atmospheres, FROM, FROM, FROM; Original contains black and white illustrations
Copyright; Avail.: CASI: A03, Hardcopy
The World Ocean produces a large amount of natural aerosols that have all impact on the Earth's albedo and climate. Sea-salt is the major contributor to aerosol optical depth over the oceans. [Mahowald et al. 2006; Chin et al. 2002; Satheesh et al. 1999; Winter and Chylek, 1997] and therefore affects the radiative balance over the ocean through the direct [Haywood et al. 1999] and indirect aerosol effect [O'Dowd et al. 1999]. Aerosols over the oceans (produced marine and advected from land sources) are important for various atmospheric processes [Lewis and Schwartz, 2004] and remote sensing studies [Gordon, 1997].
Author
OCEAN SURFACE; REMOTE SENSING; AEROSOLS; CLIMATE; OPTICAL THICKNESS; OCEANS
20090006875 NASA Goddard Space Flight Center, Greenbelt, MD, United States
Fiber Amplifier Report for NEPP 2008
Thomes, Joe; Ott, Melanie; LaRocca, Frank; Chuska, Rick; Switzer, Rob; April 2008; In English; Original contains color illustrations
No Copyright; Avail.: CASI: A02, Hardcopy
Avail Online: http://hdl.handle.net/2060/20090006875
Ongoing qualification activities of LiNbO3 modulators. Passive (unpumped) radiation testing of Er-, Yb-, and Er/Yb-doped fibers: a) Yb-doped fibers exhibit higher radiation resistance than Er-doped fibers; b) Er/Yb co-doped fibers exhibit largest radiation resistance. Active (pumped) radiation testing of Yb-doped fibers conducted at NASA GSFC: a) Typical decay behavior observed; b) No comparison could be made to other fibers due to problems with test setup. Development of new high power fiber terminations.
Author
DOPED CRYSTALS; RADIATION TOLERANCE; MODULATORS; YTTRIUM
20090006878 NASA Goddard Space Flight Center, Greenbelt, MD, United States
A Smoking Gun in the Carina Nebula
Hamaguchi, Kenji; Corcoran, Michael F.; Ezoe, Yuichiro; Townsley, Leisa; Broos, Patrick; Gruendl, Robert; Vaidya, Kaushar; White, Stephen M.; Petre, Rob; Chu, You-Hua; February 27, 2009; In English; Original contains black and white illustrations
Contract(s)/Grant(s): NNG06EO90A; CAN 03-OSS-02
Copyright; Avail.: CASI: A03, Hardcopy
The Carina Nebula is one of thc youngest, most active sites of massive star formation in our Galaxy. In this nebula, we have discovered a bright X-ray source that has persisted for approx.30 years. The soft X-ray spectrum. consistent with kT approx.130 eV blackbody radiation with mild extinction, and no counterpart in the near- and mid-infrared wavelengths indicate that it is a, approx. 10(exp 6)-year-old neutron star housed in the Carina Nebula. Current star formation theory does not suggest that the progenitor of the neutron star and massive stars in the Carina Nebula, in particular (eta)Car, are coeval. This result demonstrates that the Carina Nebula experienced at least two major episodes of massive star formation. The neutron star would be responsible for remnants of high energy activity seen in multiple wavelengths.
Author
MASSIVE STARS; NEUTRON STARS; NEBULAE; STAR FORMATION; X RAY SOURCES; ACTIVE SITES (CHEMISTRY); BLACK BODY RADIATION; INFRARED SPECTRA
Additions to the NASA Aeronautics and Space Database as of 02/27/2009
20090006885 NASA Johnson Space Center, Houston, TX, United States
Understanding the Activation and Solution Properties of Lunar Dust for Future Lunar Habitation
Wallace, William T.; Jeevarajan, Antony S.; [2009]; In English; Lunar and Planetary Science Conference, 23-27 Mar. 2009, Woodlands, TX, United States; Original contains color and black and white illustrations
Copyright; Avail.: CASI: A01, Hardcopy
The decision to return humans to the moon by 2020 makes it imperative to understand the effects of lunar dust on human and mechanical systems.( Bush 2004; Gaier 2005; Mendell 2005) During the Apollo missions, dust was found to cause numerous problems for various instruments and systems. Additionally, the dust may have caused health issues for some of the astronauts.(Gaier 2005; Rowe 2007) It is necessary, therefore, for studies to be carried out in a variety of disciplines in order to mitigate the effects of the dust as completely as possible. Due to the lack of an atmosphere, there is nothing to protect the lunar soil from ultraviolet radiation, solar wind, and meteorite impacts. These processes could all serve to "activate" the soil, or produce reactive surface species. In order to understand the possible toxic effects of the reactive dust, it is necessary to "reactivate" the dust, as samples returned during the Apollo missions were exposed to the atmosphere of the Earth. We have used grinding and exposure to UV radiation in order to mimic some of the processes occurring on the lunar surface. To monitor the reactivity of the dust, we have measured the ability of the dust to produce hydroxyl radicals in solution. These radicals have been measured using a novel fluorescent technique developed in our laboratory,(Wallace et al. 2008) as well as using electron paramagnetic resonance (EPR).
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LUNAR SURFACE; ULTRAVIOLET RADIATION; RADIATION DOSAGE; LUNAR SOIL; ELECTRON PARAMAGNETIC RESONANCE; TOXICITY; LUNAR DUST; MOON
20090006886 NASA Johnson Space Center, Houston, TX, United States
Spacecraft Internal Acoustic Environment Modeling
Chu, S. Reynold; Allen, Chris; Feb. 2, 2009; In English; HRP Investigators' Workshop, 2-4 Feb. 2009, League City, TX, United States; Original contains color illustrations
Report No.(s): JSC-17648; No Copyright; Avail.: CASI: A01, Hardcopy
Avail Online: http://hdl.handle.net/2060/20090006886
The objective of the project is to develop an acoustic modeling capability, based on commercial off-the-shelf software, to be used as a tool for oversight of the future manned Constellation vehicles. The use of such a model will help ensure compliance with acoustic requirements. Also, this project includes modeling validation and development feedback via building physical mockups and conducting acoustic measurements to compare with the predictions.
Author
ACOUSTIC MEASUREMENT; DIMENSIONAL MEASUREMENT; SPACECRAFT ENVIRONMENTS; CONSTELLATIONS
20090006887 NASA Johnson Space Center, Houston, TX, United States
Thermostabilized Shelf Life Study
Perchonok, Michele H.; Catauro, Patricia M.; [2009]; In English; HRP Investigators' Workshop, 2-4 Feb. 2009, League City, TX, United States; Original contains color illustrations
Report No.(s): JSC-17649; No Copyright; Avail.: CASI: A01, Hardcopy
Avail Online: http://hdl.handle.net/2060/20090006887
The objective of this project is to determine the shelf life end-point of various food items by means of actual measurement or mathematical projection. The primary goal of the Advanced Food Technology Project in these long duration exploratory missions is to provide the crew with a palatable, nutritious and safe food system while minimizing volume, mass, and waste. The Mars missions could be as long as 2.5 years with the potential of the food being positioned prior to the crew arrival. Therefore, it is anticipated that foods that are used during the Mars missions will require a 5 year shelf life. Shelf life criteria are safety, nutrition, and acceptability. Any of these criteria can be the limiting factor in determining the food's shelf life. Due to the heat sterilization process used for the thermostabilized food items, safety will be preserved as long as the integrity of the package is maintained. Nutrition and acceptability will change over time. Since the food can be the sole source of nutrition to the crew, a significant loss in nutrition may determine when the shelf life endpoint has occurred. Shelf life can be defined when the food item is no longer acceptable. Acceptability can be defined in terms of appearance, flavor, texture, or aroma. Results from shelf life studies of the thermostabilized food items suggest that the shelf life of the foods range from 0 months to 8 years, depending on formulation.
Author
MARS MISSIONS; SERVICE LIFE; STORAGE STABILITY; THERMAL STABILITY
20090006888 NASA Johnson Space Center, Houston, TX, United States
Comparative Packaging Study
Perchonok, Michele H.; Oziomek, Thomas V.; Feb. 2, 2009; In English; HRP Investigators' Workshop, 2-4 Feb. 2009, League City, TX, United States; Original contains color illustrations
Report No.(s): JSC-17650; Copyright; Avail.: CASI: A01, Hardcopy
Future long duration manned space flights beyond low earth orbit will require the food system to remain safe, acceptable and nutritious. Development of high barrier food packaging will enable this requirement by preventing the ingress and egress of gases and moisture. New high barrier food packaging materials have been identified through a trade study. Practical application of this packaging material within a shelf life test will allow for better determination of whether this material will allow the food system to meet given requirements after the package has undergone processing. The reason to conduct shelf life testing, using a variety of packaging materials, stems from the need to preserve food used for mission durations of several years. Chemical reactions that take place during longer durations may decrease food quality to a point where crew physical or psychological well-being is compromised. This can result in a reduction or loss of mission success. The rate of chemical reactions, including oxidative rancidity and staling, can be controlled by limiting the reactants, reducing the amount of energy available to drive the reaction, and minimizing the amount of water available. Water not only acts as a media for microbial growth, but also as a reactant and means by which two reactants may come into contact with each other. The objective of this study is to evaluate three packaging materials for potential use in long duration space exploration missions.
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LONG DURATION SPACE FLIGHT; MANNED SPACE FLIGHT; PACKAGING; SPACE MISSIONS; FOOD PRODUCTION (IN SPACE)
20090006889 NASA Johnson Space Center, Houston, TX, United States
Effect of Processing and Subsequent Storage on Nutrition
Perchonok, Michele H.; Feb. 2, 2009; In English; Human Research Program Investigators' Workshop (HRP), 2-4 Feb. 2009, League City, TX, United States; Original contains color illustrations
Report No.(s): JSC-17652; No Copyright; Avail.: CASI: A01, Hardcopy
Avail Online: http://hdl.handle.net/2060/20090006889
This viewgraph presentation includes the following objectives: 1) To determine the effects of thermal processing, freeze drying, irradiation, and storage time on the nutritional content of food; 2) To evaluate the nutritional content of the food items currently used on the International Space Station and Shuttle; and 3) To determine if there is a need to institute countermeasures. (This study does not seek to address the effect of processing on nutrients in detail, but rather aims to place in context the overall nutritional status at the time of consumption).
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NUTRITION; INTERNATIONAL SPACE STATION; FOOD PROCESSING; STORAGE; SPACE FLIGHT FEEDING
20090006892 NASA Johnson Space Center, Houston, TX, United States
Integrated Immune Experiment
Crucian, Brian; Feb. 2, 2009; In English; Human Research Program Investigators' Workshop, 2-4 Feb. 2009, League City, TX, United States; Original contains color illustrations
Copyright; Avail.: CASI: A03, Hardcopy
This viewgraph presentation reviews NASA's Integrated Immune Experiment. The objectives include: 1) Address significant lack of data regarding immune status during flight; 2) Replace several recent immune studies with one comprehensive study that will include in-flight sampling; 3) Determine the in-flight status of immunity, physiological stress, viral immunity/reactivation; 4) Determine the clinical risk related to immune dysregulation for exploration class spaceflight; and 5) Determine the appropriate monitoring strategy for spaceflight-associated immune dysfunction, that could be used for the evaluation of countermeasures.
CASI
SPACEBORNE EXPERIMENTS; MANNED SPACE FLIGHT; AEROSPACE MEDICINE; IMMUNOLOGY
20090006895 NASA Langley Research Center, Hampton, VA, United States
Guidance and Control Software Project Data - Volume 2: Development Documents
Hayhurst, Kelly J., Editor; December 2008; In English; Original contains black and white illustrations
Contract(s)/Grant(s): WBS 457280.02.07.07.06.02
Report No.(s): NASA/TM-2008-215551; L-19549; LF99-8041; Copyright; Avail.: CASI: A17, Hardcopy
The Guidance and Control Software (GCS) project was the last in a series of software reliability studies conducted at Langley Research Center between 1977 and 1994. The technical results of the GCS project were recorded after the experiment was completed. Some of the support documentation produced as part of the experiment, however, is serving an unexpected role far beyond its original project context. Some of the software used as part of the GCS project was developed to conform to the RTCA/DO-178B software standard, "Software Considerations in Airborne Systems and Equipment Certification," used in the civil aviation industry. That standard requires extensive documentation throughout the software development life cycle, including plans, software requirements, design and source code, verification cases and results, and configuration management and quality control data. The project documentation that includes this information is open for public scrutiny without the legal or safety implications associated with comparable data from an avionics manufacturer. This public availability has afforded an opportunity to use the GCS project documents for DO-178B training. This report provides a brief overview of the GCS project, describes the 4-volume set of documents and the role they are playing in training, and includes the development documents from the GCS project.
Author
SOFTWARE RELIABILITY; SOFTWARE ENGINEERING; COMPUTER PROGRAMMING; CONFIGURATION MANAGEMENT; PROVING
20090006896 NASA Langley Research Center, Hampton, VA, United States
Appendix A: Guidance and Control Software Development Specification
Withers, B. Edward; Bechler, Bernice; Guidance and Control Software Project Data - Volume 2: Development Documents; December 2008; pp. A-1 - A-11; In English
Copyright; Avail.: CASI: A06, Hardcopy
The Guidance and Control Software (GCS) represents the Viking lander (ref. A.20) onboard navigational software. The purpose of this software is to: 1.) provide guidance and engine control of the vehicle (shown in Figure A.1.1) during its terminal phase of descent onto a surface and 2.) communicate sensory information about the vehicle and its descent to some other receiving device. A typical descent trajectory is shown in Figure A.1.2. The initialization of the GCS starts the sensing of vehicle altitude. When a predefined engine ignition altitude is sensed by the altimeter radar, the GCS begins guidance and control of the vehicle. The axial engines are ignited; while the axial engines are warming up, the parachute remains connected to the vehicle. During this engine warm-up phase, the aerodynamics of the parachute dictate the trajectory followed by the vehicle. Vehicle attitude is maintained by firing the engines in a throttled-down condition. Once the main engines become hot, the parachute is released and the GCS performs an attitude correction maneuver and then follows a controlled acceleration descent until a predetermined velocity-altitude contour is crossed (see Figure A.5.1). The GCS then attempts to maintain the descent of the vehicle along this predetermined velocity-altitude contour. The vehicle descends along this contour until a predefined engine shut off altitude is reached or touchdown is sensed. After all engines are shut off, the vehicle free-falls to the surface.
Author
SPECIFICATIONS; VIKING LANDER SPACECRAFT; DESCENT TRAJECTORIES; COMPUTER PROGRAMMING; NAVIGATION; GUIDANCE (MOTION); SOFTWARE ENGINEERING; ATTITUDE (INCLINATION); AIRBORNE/SPACEBORNE COMPUTERS
20090006897 NASA Langley Research Center, Hampton, VA, United States
Appendix B: Design Description for the Pluto Implementation of the Guidance and Control Software
Morris, Philip; Angellatta, Rob; Guidance and Control Software Project Data - Volume 2: Development Documents; December 2008; pp. B-1 - B-14; In English
Copyright; Avail.: CASI: A07, Hardcopy
This document contains a detailed description of the Pluto software design. The Pluto software design fully encompasses all software requirements as presented in the GCS Guidance and Control Software Development Specification (ref. B.3) defining a GCS implementation. The Pluto design provides full and complete software design specifications suitable for coding a GCS implementation.
Author
DESIGN ANALYSIS; SOFTWARE ENGINEERING; COMPUTER PROGRAMMING
20090006898 NASA Langley Research Center, Hampton, VA, United States
Appendix C: Source Code for the Pluto Implementation of the Guidance and Control Software
Morris, Philip; Guidance and Control Software Project Data - Volume 2: Development Documents; December 2008; pp. C-1 - C-9; In English
Copyright; Avail.: CASI: A05, Hardcopy
This document contains the source code for the Pluto implementation of the Guidance and control software.
Author
SOFTWARE ENGINEERING; COMPUTER PROGRAMS; GUIDANCE (MOTION)
20090006907 NASA Johnson Space Center, Houston, TX, United States
Constellation Training Facility Support
Flores, Jose M.; November 20, 2008; In English; Constellatoin Training Facility Support, 20 Nov. 2008, Houston, TX, United States; Original contains color illustrations
Copyright; Avail.: CASI: A03, Hardcopy
The National Aeronautics and Space Administration is developing the next set of vehicles that will take men back to the moon under the Constellation Program. The Constellation Training Facility (CxTF) is a project in development that will be used to train astronauts, instructors, and flight controllers on the operation of Constellation Program vehicles. It will also be used for procedure verification and validation of flight software and console tools. The CxTF will have simulations for the Crew Exploration Vehicle (CEV), Crew Module (CM), CEV Service Module (SM), Launch Abort System (LAS), Spacecraft Adapter (SA), Crew Launch Vehicle (CLV), Pressurized Cargo Variant CM, Pressurized Cargo Variant SM, Cargo Launch Vehicle, Earth Departure Stage (EDS), and the Lunar Surface Access Module (LSAM). The Facility will consist of part-task and full-task trainers, each with a specific set of mission training capabilities. Part task trainers will be used for focused training on a single vehicle system or set of related systems. Full task trainers will be used for training on complete vehicles and all of its subsystems. Support was provided in both software development and project planning areas of the CxTF project. Simulation software was developed for the hydraulic system of the Thrust Vector Control (TVC) of the ARES I launch vehicle. The TVC system is in charge of the actuation of the nozzle gimbals for navigation control of the upper stage of the ARES I rocket. Also, software was developed using C standards to send and receive data to and from hand controllers to be used in CxTF cockpit simulations. The hand controllers provided movement in all six rotational and translational axes. Under Project Planning & Control, support was provided to the development and maintenance of integrated schedules for both the Constellation Training Facility and Missions Operations Facilities Division. These schedules maintain communication between projects in different levels. The CxTF support provided is one that requires continuous maintenance since the project is still on initial development phases.
Author
CONSTELLATION PROGRAM; TRAINING DEVICES; SOFTWARE ENGINEERING; LUNAR SURFACE; SERVICE MODULES; PROJECT PLANNING
20090006920 NASA Johnson Space Center, Houston, TX, United States
Determination of Time Required for Materials Exposed to Oxygen to Return to Reduced Flammability
Harper, Susana; Hirsch, David; Smith, Sarah; [2009]; In English; Sixth International Workshop On Dosimetry For Radiation Processing, 4 - 9 Oct. 2009, Ettlingen, Germany; Original contains color and black and white illustrations
Report No.(s): JSC-17607; No Copyright; Avail.: CASI: A03, Hardcopy
Avail Online: http://hdl.handle.net/2060/20090006920
Increased material flammability due to exposure to high oxygen concentrations is a concern from both a safety and operational perspective. Localized, high oxygen concentrations can occur when exiting a higher oxygen concentration environment due to material saturation, as well as oxygen entrapment between barrier materials. Understanding of oxygen diffusion and permeation and its correlation to flammability risks can reduce the likelihood of fires while improving procedures as NASA moves to longer missions with increased extravehicular activities in both spacecraft and off-Earth habitats. This paper examines the time required for common spacecraft materials exposed to oxygen to return to reduced flammability after removal from the increased oxygen concentration environment. Specifically, NASA-STD-6001A maximum oxygen concentration testing and ASTM F-1927 permeability testing were performed on Nomex 4 HT90-40, Tiburon 5 Surgical Drape, Cotton, Extravehicular Mobility Unit (EMU) Liquid-Cooled Ventilation Garment, EMU Thermal Comfort Undergarment, EMU Mosite Foam with Spandex Covering, Advanced Crew Escape Suit (ACES) Outer Cross-section, ACES Liquid Cooled Garment (LCG), ACES O2 Hose Material, Minicel 6 Polyethylene Foam, Minicel Polyethylene Foam with Nomex Covering, Pyrell Polyurethane Foam, and Zotek 7 F-30 Foam.
Author
FLAMMABILITY; GARMENTS; OXYGEN; EXTRAVEHICULAR ACTIVITY; RISK; SAFETY
20090006922 NASA Johnson Space Center, Houston, TX, United States
NASA Space Flight Human System Standard
Conolly, Janis; Feb. 2, 2009; In English; NASA Human Research Program Investigators' Workshop, 2-4 Feb. 2009, League City, TX, United States; Original contains color illustrations
Report No.(s): JSC-17697; No Copyright; Avail.: CASI: A01, Hardcopy
Avail Online: http://hdl.handle.net/2060/20090006922
This viewgraph presentation describes what is involved in the NASA space flight human system standard.
Derived from text
NASA SPACE PROGRAMS; MANNED SPACE FLIGHT; STANDARDS; HUMAN FACTORS ENGINEERING
20090006927 NASA Johnson Space Center, Houston, TX, United States
Ar-Ar Impact Heating Ages of Eucrites and Timing of the LHB
Bogard, Donald; Garrison, Daniel; [2009]; In English; 40th Lunar Planetary Science Conference, 23-27 Mar. 2009, Houston, TX, United States; Original contains color and black and white illustrations
Report No.(s): JSC-17610; Copyright; Avail.: CASI: A01, Hardcopy
Eucrites and howardites, more than most meteorite types, show extensive impact resetting of their Ar-39-Ar-40 (K-Ar) ages approximately equal to 3.4-4.1 Ga ago, and many specimens show some disturbance of other radiometry chronometers as well. Bogard (1995) argued that this age resetting occurred on Vesta and was produced by the same general population of objects that produced many of the lunar impact basins. The exact nature of the lunar late heavy bombardment (LHB or 'cataclysm') remains controversial, but the timing is similar to the reset ages of eucrites. Neither the beginning nor ending time of the lunar LHB is well constrained. Comparison of Ar-Ar ages of brecciated eucrites with data for the lunar LHB can resolve both the origin of these impactors and the time period over which they were delivered to the inner solar system. This abstract reports some new Ar-Ar age data for eucrites, obtained since the authors' 1995 and 2003 papers.
Derived from text
METEORITES; ARGON ISOTOPES; GEOCHRONOLOGY; RADIOACTIVE AGE DETERMINATION; LUNAR SURFACE; METEORITE COLLISIONS; HEATING
Additions to the NASA Aeronautics and Space Database as of 03/03/2009
20090006949 NASA Johnson Space Center, Houston, TX, United States
Genesis Solar Wind Array Collector Cataloging Status
Burkett, P.J.; Rodriguez, M.C.; Calaway, M.C.; Allton, J.H.; [2009]; In English; 40th Lunar and Planetary Science Conference, 23 - 27 Mar. 2009, Texas, United States; Original contains color illustrations
Report No.(s): JSC-17626; Copyright; Avail.: CASI: A01, Hardcopy
Genesis solar wind array collectors were fractured upon landing hard in Utah in 2004. The fragments were retrieved from the damaged canister, imaged, repackaged and shipped to the Johnson Space Center curatorial facility [1]. As of January 2009, the collection consists of 3460 samples. Of these, 442 are comprised into "multiple" sample groupings, either affixed to adhesive paper (177) or collected in jars (17), culture trays (87), or sets of polystyrene vials (161). A focused characterization task was initiated in May 2008 to document the largest samples in the collection. The task consisted of two goals: to document sapphire based fragments greater than 2 cm in one dimension, and to document silicon based fragments greater than 1 cm in one direction.
Author
SOLAR WIND; GENESIS MISSION; FRAGMENTS; SAMPLERS; CHARACTERIZATION; ACCUMULATORS; AEROSOLS
20090006950 NASA Johnson Space Center, Houston, TX, United States
Rb-Sr and Sm-Nd Studies of Olivine-Phyric Shergottites RBT 04262 and LAR 06319: Isotopic Evidence for Relationship to Enriched Basaltic Shergottites
Nyquist, L.E.; Shih, C.-Y.; Reese, Y.; [2009]; In English; 40th Lunar Planetary Conference, 23 - 27 Mar. 2009, Texas, United States; Original contains color and black and white illustrations
Report No.(s): JSC-17636; Copyright; Avail.: CASI: A01, Hardcopy
RBT 04262 and LAR 06319 are two Martian meteorites recently discovered in Antarctica. Both contain abundant olivines, and were classified as olivine-phyric shergottites. A detailed petrographic study of RBT 04262 suggested it should be reclassified as a lherzolitic shergottite. However, the moderately LREE-depleted REE distribution pattern indicated that it is closely related to enriched basaltic shergottites like Shergotty, Zagami, Los Angeles, etc. In earlier studies of a similarly olivinephyric shergottite NWA 1068 which contains 21% modal olivine, it was shown that it probably was produced from an enriched basaltic shergottite magma by olivine accumulation . As for LAR 06319, recent petrographic studies suggested that it is different from either lherzolitic shergottites or the highly LREE-depleted olivine-phyric shergottites. We performed Rb-Sr and Sm-Nd isotopic analyses on RBT 04262 and LAR 06319 to determine their crystallization ages and Sr and Nd isotopic signatures, and to better understand the petrogenetic relationships between them and other basaltic, lherzolitic and depleted olivine-phyric shergottites.
Derived from text
ISOTOPIC LABELING; METEORITIC COMPOSITION; OLIVINE; PETROGRAPHY; SHERGOTTITES; SNC METEORITES
20090006953 NASA Langley Research Center, Hampton, VA, United States
Guidance and Control Software Project Data - Volume 1: Planning Documents
Hayhurst, Kelly J., Editor; December 2008; In English; Original contains black and white illustrations
Contract(s)/Grant(s): WBS 457280.02.07.07.06.02
Report No.(s): NASA/TM-2008-215550; L-19548; LF99-8040; Copyright; Avail.: CASI: A08, Hardcopy
The Guidance and Control Software (GCS) project was the last in a series of software reliability studies conducted at Langley Research Center between 1977 and 1994. The technical results of the GCS project were recorded after the experiment was completed. Some of the support documentation produced as part of the experiment, however, is serving an unexpected role far beyond its original project context. Some of the software used as part of the GCS project was developed to conform to the RTCA/DO-178B software standard, "Software Considerations in Airborne Systems and Equipment Certification," used in the civil aviation industry. That standard requires extensive documentation throughout the software development life cycle, including plans, software requirements, design and source code, verification cases and results, and configuration management and quality control data. The project documentation that includes this information is open for public scrutiny without the legal or safety implications associated with comparable data from an avionics manufacturer. This public availability has afforded an opportunity to use the GCS project documents for DO-178B training. This report provides a brief overview of the GCS project, describes the 4-volume set of documents and the role they are playing in training, and includes the planning documents from the GCS project.
Author
SOFTWARE ENGINEERING; COMPUTER PROGRAMMING; SOFTWARE RELIABILITY; CONFIGURATION MANAGEMENT
20090006954 NASA Langley Research Center, Hampton, VA, United States
Appendix A: Plan for Software Aspects of Certification for the Guidance and Control Software Project
Hayhurst, Kelly J.; Guidance and Control Software Project Data - Volume 1: Planning Documents; December 2008; pp. A-1 - A-1; In English
Copyright; Avail.: CASI: A03, Hardcopy
As stated in section 11.1 of the Requirements and Technical Concepts for Aviation RTCA/DO-178B guidelines, "Software Considerations in Airborne Systems and Equipment Certification," (ref. A.1) the Plan for Software Aspects of Certification for a project is the primary means used by the certification authority, namely the Federal Aviation Administration (FAA), for determining whether an applicant is proposing a software life cycle that is commensurate with the rigor required for the level of software being developed. To this extent, this document contains an overview of the Guidance and Control Software (GCS) Project including: a) an overview of the guidance and control application, b) statement of certification considerations, c) discussion of the software development plan, including the software life cycle processes and corresponding data, and d) the project milestones and schedule. In an effort to increase our understanding of software, NASA Langley Research Center has conducted a series of experiments over the past twenty years to generate data to help characterize the software development process (ref. A.2). With an increased understanding of the failure behavior of software, improved methods for producing reliable software and assessing reliability can be developed. The current experiment, the GCS project, was started originally in 1985 at the Research Triangle Institute (RTI) (ref. A.3) to: (1) collect data on the faults that occur during the software life cycle, (2) collect data on faults that occur in operational guidance and control software, and (3) make observations on the effectiveness of life cycle processes that complies with the DO-178B guidelines. To do this, the GCS project involves the development of two separate implementations of the GCS where the life cycle activities comply with the RTCA DO- 178B guidelines. This document presents an overview of the software life cycle activities for this project and discusses why various development decisions were made, especially with respect to the experimental nature of this project. Details concerning the integral development processes are contained in the Software Verification Plan, Software Configuration Management Plan, and Software Quality Assurance Plan. The following section gives a general overview of the GCS project.
Author
CERTIFICATION; COMPUTER PROGRAMS; MANAGEMENT PLANNING; SOFTWARE RELIABILITY; SOFTWARE ENGINEERING
20090006955 NASA Langley Research Center, Hampton, VA, United States
Appendix B: Software Development Standards for the Guidance and Control Software Project
Hayhurst, Kelly J.; Becher, Bernice; Guidance and Control Software Project Data - Volume 1: Planning Documents; December 2008; pp. B-1 - B-5; In English
Copyright; Avail.: CASI: A04, Hardcopy
According to the Requirements and Technical Concepts for Aviation RTCA/DO-178B document entitled Software Considerations in Airborne Systems and Equipment Certification (ref. B.2), the purpose of the software development standards is to "define the rules and constraints for the software development process." To that extent, this document contains the Guidance and Control Software (GCS) project standards for the development of the software requirements, software design, and implemented code. These standards include constraints and rules on defining the software requirements, and designing and coding the software. These standards, along with the software requirements, will set the basis for evaluating actual project results with expected results. This document also contains other project standards including communication protocol among the project participants and problem and action reporting procedures. It is hoped that this document will serve as a handbook for the project participants, especially those individuals responsible for the design and coding of the software. All project participants are expected to become familiar with and follow the standards set forth in this document. To provide a basis for understanding the various project standards and procedures, the following section gives an overview of the GCS project and the software development process.
Author
COMPUTER PROGRAMMING; STANDARDS; SOFTWARE ENGINEERING; COMPUTER PROGRAMS; CERTIFICATION; CODING
20090006956 NASA Langley Research Center, Hampton, VA, United States
Appendix E: Software Quality Assurance Plan for the Guidance and Control Software Project
Hayhurst, Kelly J.; Guidance and Control Software Project Data - Volume 1: Planning Documents; December 2008; pp. E-1 - E-1; In English
Copyright; Avail.: CASI: A03, Hardcopy
As described in the Requirements and Technical Concepts for Aviation RTCA/DO-178B guidelines, "Software Considerations in Airborne Systems and Equipment Certification," (ref. E.1) the Software Quality Assurance (SQA) process provides evidence that the software life cycle processes satisfy their objectives and that the resultant software conforms to its requirements. The primary means that SQA provides this evidence is by assuring that the software life cycle processes are performed in compliance with the approved software plans and standards. For the Guidance and Control Software (GCS) project, three objectives of SQA process (as given in Table A-9 of Annex A in DO-178B) are to be obtained: a) that software development processes and integral processes comply with approved software plans and standards, b) that the transition criteria for the software life cycle processes are satisfied, and c) that a conformity review of the software product is conducted. In conducting the SQA process, two other objectives are to be obtained. First, deficiencies in the development and integral processes and project artifacts are to be detected, evaluated, tracked and resolved. Second, assurance is to be provided that the software products and software life cycle data conform to certification requirements. This plan defines the means by which these software quality assurance process objectives will be satisfied. In compliance with section 11.5 of DO-178B, this document contains the following: a) a description of the SQA environment, b) a statement of the SQA authority, responsibility, and independence, c) a description of the SQA activities, d) the transition criteria for entering the SQA process, e) the timing of the SQA activities, and f) a definition of the SQA records to be produced.
Author
SOFTWARE ENGINEERING; COMPUTER PROGRAMS; CERTIFICATION; COMPUTER PROGRAMMING
20090006957 NASA Langley Research Center, Hampton, VA, United States
Appendix C: Software Verification Plan for the Guidance and Control Software Project
Quach, Patrick; Taylor, Debbie; Guidance and Control Software Project Data - Volume 1: Planning Documents; December 2008; pp. C-1 - C-2; In English
Copyright; Avail.: CASI: A03, Hardcopy
This document is the Software Verification Plan for the Guidance and Control Software (GCS) project. The plan details verification activities to be conducted to satisfy DO-178B criteria for software verification and discusses issues important to the verification process. The procedures and processes will be applied to all implementations of GCS. Software verification activities serve as "filters" for the development process. These activities are independent from the development process, but effect the development process because each step of the development processes that produces an artifact will initiate a verification activity. As defined in Paragraph 6 of DO-178B (ref. C.2), software verification is a technical assessment of the results of the software development process as well as an assessment of the verification process. Two methods for verification addressed in this document are reviews/analysis, and testing. Other activities that support these methods will also be addressed as well as issues and considerations involved. The following is a brief description of topics covered in this document. The Overview of Verification Activities section describes the composition and organization of each implementation team as well as the independence established for verification purposes. This is followed by the Verification Methods section which outlines the review procedures for the design and code artifacts. The following section describes the test coverage and testing strategy required by DO-178B and to be used to verify executables against the GCS Specification. The GCS Specification will serve as the Software Requirements Data for this project. The Verification Environment section briefly describes the tools to be used during the verification process and the programs developed to support verification activities. The hardware platform on which those activities will be carried out will also be described. The Transition Criteria section gives objectives to be met for each step in the verification process before proceeding to the next step. Lastly, the Reverification Guidelines describe procedures to be followed to verify an artifact after a correction has been made to the artifact.
Author
PROGRAM VERIFICATION (COMPUTERS); SOFTWARE ENGINEERING; COMPUTER PROGRAMMING; PROVING
20090006958 NASA Langley Research Center, Hampton, VA, United States
Appendix D: Software Configuration Management Plan for the Guidance and Control Software Project
Smith, Laura J.; Hayhurst, Kelly J.; Guidance and Control Software Project Data - Volume 1: Planning Documents; December 2008; pp. D-1 - D-3; In English
Copyright; Avail.: CASI: A03, Hardcopy
According to the RTCA/DO-178B "Software Considerations in Airborne Systems and Equipment Certification", configuration management is the "process of identifying and defining the configuration items of a system, controlling the release and change of these items throughout the software life cycle, recording and reporting the status of configuration items and change requests, and verifying the completeness and correctness of configuration items" (ref. D.2). This configuration management plan establishes the methods to be used to achieve the objectives of the software configuration management (SCM) process throughout the software life cycle for the Guidance and Control Software (GCS) project in accordance with the DO-178B guidelines. Specifically, this document provides a description of the SCM environment that will be used throughout the GCS project (including the methods, tools, standards, and procedures) and a description of the SCM activities in the software life cycle. As described in Subsection 7.1 of the DO-178B guidelines, the SCM process, along with the other software life cycle processes, assists in meeting the following general objectives for the certification authority: a) provide a defined and controlled configuration of the software throughout the software life cycle; b) provide the ability to consistently replicate the executable object code or to regenerate it if needed; c) provide control of process inputs and outputs during the software life cycle that ensures consistency and repeatability of process activities; d) provide a known point for review, assessing status, and change control by establishing baselines for configuration items; e) provide controls that ensure problems receive attention and changes are recorded, approved, and implemented; f) provide evidence of approval for the software; g) aid the assessment of the software product compliance with requirements; and h) ensure that secure physical archiving, recovery and control are maintained for the configuration items.
Author
CONFIGURATION MANAGEMENT; COMPUTER PROGRAMS; CERTIFICATION; MANAGEMENT PLANNING; SOFTWARE ENGINEERING; COMPUTER PROGRAMMING
20090006959 NASA Langley Research Center, Hampton, VA, United States
Guidance and Control Software Project Data - Volume 3: Verification Documents
Hayhurst, Kelly J., Editor; December 2008; In English; Original contains black and white illustrations
Contract(s)/Grant(s): WBS 457280.02.07.07.06.02
Report No.(s): NASA/TM-2008-215552; L-19550; LF99-8042; Copyright; Avail.: CASI: A16, Hardcopy
The Guidance and Control Software (GCS) project was the last in a series of software reliability studies conducted at Langley Research Center between 1977 and 1994. The technical results of the GCS project were recorded after the experiment was completed. Some of the support documentation produced as part of the experiment, however, is serving an unexpected role far beyond its original project context. Some of the software used as part of the GCS project was developed to conform to the RTCA/DO-178B software standard, "Software Considerations in Airborne Systems and Equipment Certification," used in the civil aviation industry. That standard requires extensive documentation throughout the software development life cycle, including plans, software requirements, design and source code, verification cases and results, and configuration management and quality control data. The project documentation that includes this information is open for public scrutiny without the legal or safety implications associated with comparable data from an avionics manufacturer. This public availability has afforded an opportunity to use the GCS project documents for DO-178B training. This report provides a brief overview of the GCS project, describes the 4-volume set of documents and the role they are playing in training, and includes the verification documents from the GCS project.
Author
COMPUTER PROGRAMMING; SOFTWARE ENGINEERING; SOFTWARE RELIABILITY; PROVING
20090006960 NASA Langley Research Center, Hampton, VA, United States
Appendix C: Review Records for the Pluto Implementation of the Guidance and Control Software
Hayhurst, Kelly J.; Guidance and Control Software Project Data - Volume 3: Verification Documents; December 2008; pp. C-1 - C-11; In English
Copyright; Avail.: CASI: A06, Hardcopy
Review records are included for the Pluto implementation of the guidance and control software.
Author
GUIDANCE (MOTION); COMPUTER PROGRAMS; COMPUTER PROGRAMMING; RECORDS; SOFTWARE ENGINEERING
20090006961 NASA Langley Research Center, Hampton, VA, United States
Appendix D: Test Results Logs for the Pluto Implementation of the Guidance and Control Software
Quach, Cuong C.; Guidance and Control Software Project Data - Volume 3: Verification Documents; December 2008; pp. D-1 - D-4; In English
Copyright; Avail.: CASI: A03, Hardcopy
Test results logs are included for the Pluto implementation of the guidance and control software.
Author
COMPUTER PROGRAMS; RECORDS; COMPUTER PROGRAMMING; SOFTWARE ENGINEERING
20090006962 NASA Langley Research Center, Hampton, VA, United States
Appendix B: Software Verification Results for the PLUTO Implementation of the Guidance and Control Software
Quach, Cuong C.; Guidance and Control Software Project Data - Volume 3: Verification Documents; December 2008; pp. B-1 - B-5; In English
Copyright; Avail.: CASI: A04, Hardcopy
The purpose of this document, as described in Section 11.14 of DO-178B, is to provide details about the results of software verification activities conducted for the PLUTO implementation of the Guidance and Control Software (GCS). As stated in other documents, the GCS project adheres to the DO-178B guidelines for Level A software. Accordingly, specific verification activities have been described in the Software Verification Plan, and Software Verification Cases and Procedures documents. This document gives the results of each of those activities as carried out on the Pluto implementation. As stated in the Software Verification Plan, verification activities conducted for Pluto encompass two groups: 1) Review and analysis of artifacts from the Design and Coding processes, and 2) Development and execution of test cases. The review and analysis of the Pluto design and source code are performed following the procedure established in the Software Verification Cases and Procedures document. Test case development as well as test case execution are also performed in accordance with procedures described in that document. The three sections below are the main thrust of this document and describe the design review, code review, and test case execution results.
Author
PROGRAM VERIFICATION (COMPUTERS); PROVING; DESIGN ANALYSIS; CODING
20090006963 NASA Langley Research Center, Hampton, VA, United States
Appendix A: Software Verification Cases and Procedures for the Guidance and Control Software Project
Quach, Cuong C.; Taylor, Debbie; Guidance and Control Software Project Data - Volume 3: Verification Documents; December 2008; pp. A-1 - A-13; In English
Copyright; Avail.: CASI: A07, Hardcopy
The purpose of this document, as described in Section 11.13 of Requirements and Technical Concepts for Aviation RTCA/DO-178B, "Software Considerations in Airborne Systems and Equipment Certification" (ref. A.2), is to provide details about how software verification process activities are to be implemented for the Guidance and Control Software (GCS) project. As stated in the preface, the development and verification of this software strictly follows guidelines described in DO-178B. This document focuses on review and analysis as well as testing methods. In particular, this document will provide details on procedures for conducting reviews and analysis, describe the test cases that meet Level A requirements, and test procedures to use for verification. Methods adopted for tracking test cases as well as accounting for test coverage will also be discussed. As stated in the Software Verification Plan, GCS verification activities are independent from the development process. The development process produces artifacts that must undergo some level of verification as described in DO-178B. Figure A.1 gives an overview of verification activities for the GCS project and how they are related to the development processes.
Author
PROGRAM VERIFICATION (COMPUTERS); COMPUTER PROGRAMS; SOFTWARE ENGINEERING; PROVING
20090006964 NASA Langley Research Center, Hampton, VA, United States
Guidance and Control Software Project Data - Volume 4: Configuration Management and Quality Assurance Documents
Hayhurst, Kelly J., Editor; December 2008; In English; Original contains black and white illustrations
Contract(s)/Grant(s): WBS 457280.02.07.07.06.02
Report No.(s): NASA/TM-2008-215553; L-19551; LF99-8043; No Copyright; Avail.: CASI: A18, Hardcopy
Avail Online: http://hdl.handle.net/2060/20090006964
The Guidance and Control Software (GCS) project was the last in a series of software reliability studies conducted at Langley Research Center between 1977 and 1994. The technical results of the GCS project were recorded after the experiment was completed. Some of the support documentation produced as part of the experiment, however, is serving an unexpected role far beyond its original project context. Some of the software used as part of the GCS project was developed to conform to the RTCA/DO-178B software standard, "Software Considerations in Airborne Systems and Equipment Certification," used in the civil aviation industry. That standard requires extensive documentation throughout the software development life cycle, including plans, software requirements, design and source code, verification cases and results, and configuration management and quality control data. The project documentation that includes this information is open for public scrutiny without the legal or safety implications associated with comparable data from an avionics manufacturer. This public availability has afforded an opportunity to use the GCS project documents for DO-178B training. This report provides a brief overview of the GCS project, describes the 4-volume set of documents and the role they are playing in training, and includes configuration management and quality assurance documents from the GCS project.
Author
SOFTWARE ENGINEERING; SOFTWARE RELIABILITY; COMPUTER PROGRAMMING; CONFIGURATION MANAGEMENT; PROVING
20090006965 NASA Langley Research Center, Hampton, VA, United States
Appendix E: Problem Reports for the Pluto Implementation of the Guidance and Control Software Project
Guidance and Control Software Project Data - Volume 4: Configuration Management and Quality Assurance Documents; December 2008; pp. E-1 - E-13; In English
No Copyright; Avail.: CASI: A07, Hardcopy
Avail Online: http://hdl.handle.net/2060/20090006965
The Teamwork balance operation indicates the existence of errors in the Pluto design. In accordance with the Software Design Standards, the Pluto design is to be modified such that the Teamwork balance operation indicates an absence of errors. A Teamwork balance report is included.
Author
SOFTWARE ENGINEERING; ERRORS; DESIGN ANALYSIS; COMPUTER PROGRAMS
20090006966 NASA Langley Research Center, Hampton, VA, United States
Appendix F: Support Documentation Change Reports for the Guidance and Control Software Project
Hayhurst, Kelly; Guidance and Control Software Project Data - Volume 4: Configuration Management and Quality Assurance Documents; December 2008; pp. F-1 - F-16; In English
No Copyright; Avail.: CASI: A08, Hardcopy
Avail Online: http://hdl.handle.net/2060/20090006966
Documentation change reports are included for th eguidance and control software project.
Author
COMPUTER PROGRAMS; DOCUMENTATION; SOFTWARE ENGINEERING; GUIDANCE (MOTION)
20090006967 NASA Langley Research Center, Hampton, VA, United States
Appendix A: Appendix A: Software Accomplishment Summary for the Guidance and Control Software Project
Hayhurst, Kelly J.; Guidance and Control Software Project Data - Volume 4: Configuration Management and Quality Assurance Documents; December 2008; pp. A-1 - A-2; In English
No Copyright; Avail.: CASI: A03, Hardcopy
Avail Online: http://hdl.handle.net/2060/20090006967
The Guidance and Control Software (GCS) project is a research effort to investigate the faults that occur in the development and operation of software, especially software applications that conform to the Requirements and Technical Concepts for Aviation RTCA/DO-178B guidelines, "Software Considerations in Airborne Systems and Equipment Certification." To this extent, this project involved the production of two separate implementations of the GCS for the purpose of (1) collecting data on the faults that occur during the software development process, (2) collecting data on faults that occur in operational guidance and control software, and (3) making observations on the effectiveness of a development process that complies with the DO-178B guidelines. The GCS project was started originally in 1985 at the Research Triangle Institute (RTI) (ref. A.1) with the development of the specification document for the guidance and control software application. The development of each of the two implementations described in this document started from a common specification of the requirements for the GCS (referred to as the GCS specification) and proceeded independently through the development of the design and code. Each GCS implementation was designed to run in conjunction with a software simulator that provides input to the implementation based on an expected usage distribution in the operational environment, provides response modeling for the guidance and control application, and receives data from the implementation. The GCS simulator is designed to allow an experimenter to run one or more implementations in a multitasking environment and collect data on the comparison of the results from multiple implementations. Certain constraints were incorporated in the GCS specification and project standards (especially standards regarding communication protocol) due to the nature of the GCS project.
Author
SOFTWARE ENGINEERING; GUIDANCE (MOTION); COMPUTER PROGRAMMING; SPECIFICATIONS; DATA ACQUISITION; DATA PROCESSING
20090006968 NASA Langley Research Center, Hampton, VA, United States
Appendix C: Configuration Management Records for the Guidance and Control Software Project
Smith, Laura; Hayhurst, Kelly J.; Guidance and Control Software Project Data - Volume 4: Configuration Management and Quality Assurance Documents; December 2008; pp. C-1 - C-3; In English
No Copyright; Avail.: CASI: A03, Hardcopy
Avail Online: http://hdl.handle.net/2060/20090006968
This document contains the records of changes made to the life cycle data placed under configuration control in compliance with the Configuration Management Plan for the Guidance and Control Software project. items. Each table gives the configuration management library name for that item, the date and action that was taken, the element(s) affected, the requester, and remarks. A Support Documentation Change Report that has been logged by the Software Quality Assurance (SQA) representative provides that authority necessary to change the support documentation, including the plans and procedures documents. A Problem Report that has been logged by the SQA representative provides the authority necessary to revise any of the development products (requirements, design, and code). Each reservation of a configuration item should correspond to one change report. The change report should be noted in the remarks section of each table.
Author
CONFIGURATION MANAGEMENT; MANAGEMENT PLANNING; COMPUTER PROGRAMS
20090006969 NASA Langley Research Center, Hampton, VA, United States
Appendix D: Software Quality Assurance Records for the Guidance and Control Software Project
Hayhurst, Kelly J.; Guidance and Control Software Project Data - Volume 4: Configuration Management and Quality Assurance Documents; December 2008; pp. D-1 - D-2; In English
No Copyright; Avail.: CASI: A03, Hardcopy
Avail Online: http://hdl.handle.net/2060/20090006969
As described in the Radio Technical Commission for Aeronautics RTCA/DO-178B guidelines, "Software Considerations in Airborne Systems and Equipment Certification," (ref. D.1) the Software Quality Assurance (SQA) process provides evidence that the software life cycle processes satisfy their objectives and that the resultant software conforms to its requirements. The primary means that SQA provides this evidence is by assuring that the software life cycle processes are performed in compliance with the approved software plans and standards. The Software Quality Assurance Records for the GCS project consist of the reports from reviews that are held during each of the development processes and the status logs for all of the change reports for the project s life cycle data. An SQA report was produced at the closure of each development process for each of the two GCS implementations, Mercury and Pluto. The basic form of all the reports is an introduction followed by the overview of the review sessions and a listing of any problem reports that are issued. Each report documents the SQA approval for a particular stage of the implementation's development and contains an acceptance statement signed by the SQA representative as part of the report. For each of the GCS implementations, the following reports are included in this document: Preliminary Design Review Report, Design Review Report, and Test Completion Report for Integration. There is also a Test Readiness Review Report for Requirements-based Testing that was conducted at the start of the integration process. Because only one set of requirements-based test cases was developed for the project, the review of those cases was not implementation specific.
Author
COMPUTER PROGRAMS; SOFTWARE ENGINEERING; DESIGN ANALYSIS; COMPUTER PROGRAMMING; STANDARDS
20090006970 NASA Langley Research Center, Hampton, VA, United States
Appendix B: Software Configuration Index for the Guidance and Control Software Project
Smith, Laura J.; Hayhurst, Kelly J.; Guidance and Control Software Project Data - Volume 4: Configuration Management and Quality Assurance Documents; December 2008; pp. B-1 - B-2; In English
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Avail Online: http://hdl.handle.net/2060/20090006970
The Software Configuration Index (SCI) functions as a master list for the configuration of items under configuration control for the Guidance and Control Software (GCS) project. The Software Life Cycle Environment Configuration Index (SECI) identifies the configuration of the software life cycle environment. This document contains both the Software Configuration Index and the Software Life Cycle Environment Configuration Index as described in sections 11.16 and 11.15 of DO-178B, respectively. The Software Configuration Index identifies the configuration of the software product. The SCI should identify the following: a) the software product; b) executable object code; c) each source code component; d) software life cycle data; e) archive and release media; f) instructions for building the executable object code; g) procedures used to recover the software for regeneration, testing, or modification; h) reference to the Software Life Cycle Environment Configuration Index if packaged separately; and i) data integrity checks for the executable object code, if used.
Author
SOFTWARE ENGINEERING; COMPUTER PROGRAMMING; CONFIGURATION MANAGEMENT; PROGRAM VERIFICATION (COMPUTERS)
20090006971 NASA Johnson Space Center, Houston, TX, United States
Solubility of Sulfur in Shergottitic Silicate Melts Up to 0.8 GPA: Implications for S Contents of Shergottites
Righter, K.; Pando, K.M.; Danielson, L.; [2009]; In English; 40th Lunar Planetary Science Conference, 23 - 27 Mar. 2009, Texas, United States; Original contains color and black and white illustrations
Report No.(s): JSC-17662; Copyright; Avail.: CASI: A01, Hardcopy
Shergottites have high S contents (1300 to 4600 ppm; [1]), but it is unclear if they are sulfide saturated or under-saturated. This issue has fundamental implications for determining the long term S budget of the martian surface and atmosphere (from mantle degassing), as well as evolution of the highly siderophile elements (HSE) Au, Pd, Pt, Re, Rh, Ru, Ir, and Os, since concentrations of the latter are controlled by sulfide stability. Resolution of sulfide saturation depends upon temperature, pressure, oxygen fugacity (and FeO), and magma composition [2]. Expressions derived from experimental studies allow prediction of S contents, though so far they are not calibrated for shergottitic liquids [3-5]. We have carried out new experiments designed to test current S saturation models, and then show that existing calibrations are not suitable for high FeO and low Al2O3 compositions characteristic of shergottitic liquids. The new results show that existing models underpredict S contents of sulfide saturated shergottitic liquids by a factor of 2.
Author
SOLUBILITY; SHERGOTTITES; SULFUR; SILICATES; MARS SURFACE; MELTS (CRYSTAL GROWTH)
20090006972 NASA Johnson Space Center, Houston, TX, United States
Analysis of Moderately Siderophile Elements in Angrites: Implications for Core Formation of the Angrite Parent Body
Righter, K.; Shirai, N.; Irving, A.J.; [2009]; In English; 40th Lunar Planetary Science Conference, 23 - 27 Mar. 2009, Texas, United States; Original contains color and black and white illustrations
Report No.(s): JSC-17663; Copyright; Avail.: CASI: A01, Hardcopy
Angrites are an enigmatic group of achondrites, that constitute the largest group of basalts not affiliated with the Moon, Mars or Vesta (HEDs). Chemically, angrites are exceptionally refractory element- enriched (e.g., Al, Ca) and volatile element-depleted (e.g., Na and K) achondrites. Highly volatile siderophile and chalcophile elements (Zn, Ge and Se) may be less depleted than alkalis and Ga taken to imply a fractionation of plagiophile elements. Core formation on the angrite parent body (APB) is not well understood due to the dearth of moderately siderophile element (Ga, Ge, Mo, Sb, W) data for angrites, with the exception of Ni and Co [2]. In particular, there are no data for Mo abundances of angrites, while Sb and W abundances are reported for only 3 angrites, and have not always been determined on the same sample. The recent increase in angrite numbers (13) has greatly increased our knowledge of the compositional diversity of the angrite parent body (APB). In this study, we report new Co, Ni, Ga, Mo, Sb and W abundances for angrites by laser ablation inductively coupled plasma mass spectrometry (ICP-MS) in order to place constraints on core formation of the APB.
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ACHONDRITES; METEORITIC COMPOSITION; METEORITE PARENT BODIES; SIDEROPHILE ELEMENTS; PETROGRAPHY
20090006975 NASA Johnson Space Center, Houston, TX, United States
Chlorine Isotopes: As a Possible Tracer of Fluid/Bio-Activities on Mars and a Progress Report on Chlorine Isotope Analysis by TIMs
Nakamura, N.; Nyquist, L.E.; Reese, Y.; Shih, C-Y.; Numata, M.; Fujitani, T.; Okano, O.; [2009]; In English; Lunar and Planetary Science Conference, 23 - 27 Mar. 2009, Texas, United States; Original contains black and white illustrations
Report No.(s): JSC-17680; Copyright; Avail.: CASI: A01, Hardcopy
Significantly large mass fractionations between chlorine isotopes (Cl-35, Cl-37) have been reported for terrestrial materials including both geological samples and laboratory materials. Also, the chlorine isotopic composition can be used as a tracer for early solar system processes. Moreover, chlorine is ubiquitous on the Martian surface. Typical chlorine abundances in Gusev soils are approx.0.5 %. The global surface average chlorine abundance also is approx.0.5 %. Striking variations among outcrop rocks at Meridiani were reported with some chlorine abundances as high as approx.2%. Characterizing conditions under which chlorine isotopic fractionation may occur is clearly of interest to planetary science. Thus, we have initiated development of a chlorine isotopic analysis technique using TIMS at NASA-JSC. We present here a progress report on the current status of development at JSC and discuss the possible application of chlorine isotopic analysis to Martian meteorites in a search for fluid- and possibly biological activity on Mars.
Author
SNC METEORITES; CHLORINE; SOILS; ACTIVITY (BIOLOGY); GEOLOGY; MARS SURFACE
20090007462 Universities Space Research Association, Houston, TX, United States; NASA Johnson Space Center, Houston, TX, United States
Lunar Dust and Lunar Simulant Activation, Monitoring, Solution and Cellular Toxicity Properties
Wallace, William; Jeevarajan, A. S.; February 02, 2009; In English; Human Research Program Investigators Workshop, 2 - 4 Feb. 2009, League City, TX, United States; Original contains color and black and white illustrations
Report No.(s): JSC-17724; Copyright; Avail.: CASI: A01, Hardcopy
During the Apollo missions, many undesirable situations were encountered that must be mitigated prior to returning humans to the moon. Lunar dust (that part of the lunar regolith less than 20 microns in diameter) was found to produce several problems with mechanical equipment and could have conceivably produced harmful physiological effects for the astronauts. For instance, the abrasive nature of the dust was found to cause malfunctions of various joints and seals of the spacecraft and suits. Additionally, though efforts were made to exclude lunar dust from the cabin of the lunar module, a significant amount of material nonetheless found its way inside. With the loss of gravity correlated with ascent from the lunar surface, much of the finer fraction of this dust began to float and was inhaled by the astronauts. The short visits tothe Moon during Apollo lessened exposure to the dust, but the plan for future lunar stays of up to six months demands that methods be developed to minimize the risk of dust inhalation. The guidelines for what constitutes "safe" exposure will guide the development of engineering controls aimed at preventing the presence of dust in the lunar habitat. This work has shown the effects of grinding on the activation level of lunar dust, the changes in dissolution properties of lunar simulant, and the production of cytokines by cellular systems. Grinding of lunar dust leads to the production of radicals in solution and increased dissolution of lunar simulant in buffers of different pH. Additionally, ground lunar simulant has been shown to promote the production of IL-6 and IL-8, pro-inflammatory cytokines, by alveolar epithelial cells. These results provide evidence of the need for further studies on these materials prior to returning to the lunar surface.
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ASTRONAUTS; EXPOSURE; LUNAR DUST; PHYSIOLOGICAL EFFECTS; RESPIRATORY SYSTEM; BIOLOGICAL EFFECTS
20090007463 NASA Johnson Space Center, Houston, TX, United States
An Overview of Astronaut Photography
Stefanov, William L.; January 26, 2009; In English; Original contains color illustrations
Contract(s)/Grant(s): NNJ05HI05C
No Copyright; Avail.: CASI: A03, Hardcopy
Avail Online: http://hdl.handle.net/2060/20090007463
This viewgraph presentation gives a general overview of astronaut photography. The contents include: 1) The Data; and 2) Astronaut Training and Operations.
CASI
GENERAL OVERVIEWS; PHOTOGRAPHY; REMOTE SENSING; INTERNATIONAL SPACE STATION
20090007465 NASA Johnson Space Center, Houston, TX, United States
Prevention of Muscle Atrophy With Exercise Countermeasures: Where We are and Where We are Going
Ploutz, Snyder, Lori; January 29, 2009; In English; Original contains color and black and white illustrations
Report No.(s): JSC-17747; No Copyright; Avail.: CASI: A03, Hardcopy
Avail Online: http://hdl.handle.net/2060/20090007465
This viewgraph presentation reviews muscle atrophy, models for atrophy, exercise countermearures and muscle strength as it relates to muscle function.
CASI
ATROPHY; MUSCLES; MUSCULAR FUNCTION; PHYSICAL EXERCISE; ANIMAL MODELS; MUSCULOSKELETAL SYSTEM
20090007466 Universities Space Research Association, Houston, TX, United States; NASA Johnson Space Center, Houston, TX, United States
Probabilistic Risk Model for Organ Doses and Acute Health Effects of Astronauts on Lunar Missions
Kim, Myung-Hee Y.; Hu, Shaowen; Nounu, Hatem N.; Cucinotta, Francis A.; February 02, 2009; In English; Human Research Program Investigators Workshop, 2 - 4 Feb. 2009, League City, TX, FROM; Original contains color and black and white illustrations
Report No.(s): JSC-17753; Copyright; Avail.: CASI: A01, Hardcopy
Exposure to large solar particle events (SPEs) is a major concern during EVAs on the lunar surface and in Earth-to-Lunar transit. 15% of crew times may be on EVA with minimal radiation shielding. Therefore, an accurate assessment of SPE occurrence probability is required for the mission planning by NASA. We apply probabilistic risk assessment (PRA) for radiation protection of crews and optimization of lunar mission planning.
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ASTRONAUTS; LUNAR SURFACE; SPACE MISSIONS; ORGANS; RISK ASSESSMENT; HEALTH PHYSICS; PROBABILITY THEORY
20090007467 NASA Johnson Space Center, Houston, TX, United States
ARED (Advanced-Resistive Exercise Device) Update
Ploutz-Snyder, Lori; February 02, 2009; In English; Human Research Program Investigators Workshop, 2 - 4 Feb. 2009, League City, TX, United States; Original contains color illustrations
No Copyright; Avail.: CASI: A03, Hardcopy
Avail Online: http://hdl.handle.net/2060/20090007467
This viewgraph presentation describes ARED which is a new hardware exercise device for use on the International Space Station. Astronaut physiological adaptations, muscle parameters, and cardiovascular parameters are also reviewed.
CASI
ASTRONAUTS; INTERNATIONAL SPACE STATION; PHYSICAL EXERCISE; RESISTANCE; MUSCULOSKELETAL SYSTEM; PHYSIOLOGY
20090007469 NASA Langley Research Center, Hampton, VA, United States
Comparison of Radiation Transport Codes, HZETRN, HETC and FLUKA, Using the 1956 Webber SPE Spectrum
Heinbockel, John H.; Slaba, Tony C.; Blattnig, Steve R.; Tripathi, Ram K.; Townsend, Lawrence W.; Handler, Thomas; Gabriel, Tony A.; Pinsky, Lawrence S.; Reddell, Brandon; Clowdsley, Martha S.; Singleterry, Robert C.; Norbury, John W.; Badavi, Francis F.; Aghara, Sukesh K.; January 2009; In English; Original contains color illustrations
Contract(s)/Grant(s): NNL07AA36C; NNL07AA18CNNL06AA14AWBS 651549.02.07.01
Report No.(s): NASA/TP-2009-215560; LF99-8108; L-19555; Copyright; Avail.: CASI: A03, Hardcopy
Protection of astronauts and instrumentation from galactic cosmic rays (GCR) and solar particle events (SPE) in the harsh environment of space is of prime design of personal shielding, spacecraft, and mission planning. Early entry of radiation constraints into the design process enables optimal demands efficient and accurate tools that can be used by design engineers in every phase of an evolving space project. The radiation efficient tool for analyzing the shielding effectiveness of materials exposed to space radiation. In this paper, HZETRN is for a shield/target configuration comprised of a 20 g/sq cm Aluminum slab in front of a 30 to the February 1956 SPE, as modeled by the Webber spectrum. Neutron and proton fluence spectra, as well as dose and dose the water target. This study shows that there are many regions where HZETRN agrees with both for this shield/target configuration and the SPE environment. However, there are also regions where there are appreciable
Author
RADIATION TRANSPORT; SHIELDING; GALACTIC COSMIC RAYS; SOLAR FLARES; MISSION PLANNING; EXTRATERRESTRIAL RADIATION; PROTECTION
20090007473 NASA Marshall Space Flight Center, Huntsville, AL, United States
Developing a Material Strength Design Value Based on Compression after Impact Damage for the Ares I Composite Interstage
Nettles, A. T.; Jackson, J. R.; January 2009; In English; Original contains color and black and white illustrations
Report No.(s): NASA/TP-2009-215634; M-1248; No Copyright; Avail.: CASI: A04, Hardcopy
Avail Online: http://hdl.handle.net/2060/20090007473
The derivation of design values for compression after impact strength for two types of honeycomb sandwich structures are presented. The sandwich structures in this study had an aluminum core and composite laminate facesheets of either 16-ply quasi or 18-ply directional lay-ups. The results show that a simple power law curve fit to the data can be used to create A- and B-basis residual strength curves.
Author
HONEYCOMB STRUCTURES; METAL MATRIX COMPOSITES; SANDWICH STRUCTURES; RESIDUAL STRENGTH; LAMINATES; IMPACT DAMAGE; IMPACT STRENGTH
20090007493 National Inst. of Aerospace, Hampton, VA, United States; NASA Langley Research Center, Hampton, VA, United States; National Inst. of Aerospace, Hampton, VA, United States
Accuracy of Gradient Reconstruction on Grids with High Aspect Ratio
Thomas, James; December 2008; In English; Original contains color and black and white illustrations
Report No.(s): NIA Report No. 2008-12; LF99-8199; No Copyright; Avail.: CASI: A03, Hardcopy
Avail Online: http://hdl.handle.net/2060/20090007493
Gradient approximation methods commonly used in unstructured-grid finite-volume schemes intended for solutions of high Reynolds number flow equations are studied comprehensively. The accuracy of gradients within cells and within faces is evaluated systematically for both node-centered and cell-centered formulations. Computational and analytical evaluations are made on a series of high-aspect-ratio grids with different primal elements, including quadrilateral, triangular, and mixed element grids, with and without random perturbations to the mesh. Both rectangular and cylindrical geometries are considered; the latter serves to study the effects of geometric curvature. The study shows that the accuracy of gradient reconstruction on high-aspect-ratio grids is determined by a combination of the grid and the solution. The contributors to the error are identified and approaches to reduce errors are given, including the addition of higher-order terms in the direction of larger mesh spacing. A parameter GAMMA characterizing accuracy on curved high-aspect-ratio grids is discussed and an approximate-mapped-least-square method using a commonly-available distance function is presented; the method provides accurate gradient reconstruction on general grids. The study is intended to be a reference guide accompanying the construction of accurate and efficient methods for high Reynolds number applications
Author
APPROXIMATION; GRADIENTS; HIGH ASPECT RATIO; FINITE VOLUME METHOD; UNSTRUCTURED GRIDS (MATHEMATICS); ACCURACY
20090007494 NASA Langley Research Center, Hampton, VA, United States
Refined Zigzag Theory for Laminated Composite and Sandwich Plates
Tessler, Alexander; DiSciuva, Marco; Gherlone, Marco; January 2009; In English; Original contains black and white illustrations
Contract(s)/Grant(s): E57WBS 984754.02.07.07.15.04
Report No.(s): NASA/TP-2009-215561; L-19564; LF99-8200; Copyright; Avail.: CASI: A04, Hardcopy
A refined zigzag theory is presented for laminated-composite and sandwich plates that includes the kinematics of first-order shear deformation theory as its baseline. The theory is variationally consistent and is derived from the virtual work principle. Novel piecewise-linear zigzag functions that provide a more realistic representation of the deformation states of transverse-shear-flexible plates than other similar theories are used. The formulation does not enforce full continuity of the transverse shear stresses across the plate s thickness, yet is robust. Transverse-shear correction factors are not required to yield accurate results. The theory is devoid of the shortcomings inherent in the previous zigzag theories including shear-force inconsistency and difficulties in simulating clamped boundary conditions, which have greatly limited the accuracy of these theories. This new theory requires only C(sup 0)-continuous kinematic approximations and is perfectly suited for developing computationally efficient finite elements. The theory should be useful for obtaining relatively efficient, accurate estimates of structural response needed to design high-performance load-bearing aerospace structures.
Author
LAMINATES; SANDWICH STRUCTURES; FUNCTIONS (MATHEMATICS); KINEMATICS; PLATE THEORY; COMPOSITE STRUCTURES
20090007551 NASA Johnson Space Center, Houston, TX, United States
Antarctica Meta-Analysis: Psychosocial Factors Related to Long Duration Isolation and Confinement
Leveton, Lauren; Shea, Camille; Slack, Kelley J.; Keeton, Kathryn E.; Palinkas, Lawrence A.; February 02, 2009; In English; Human Research Program Investigators' Workshop, 2-4 Feb. 2009, League City, TX, United States; Original contains color illustrations
Report No.(s): JSC-17719; Copyright; Avail.: CASI: A01, Hardcopy
This meta-analysis is examining the psychological effects of wintering-over in Antarctica. As an isolated, confined, and extreme (ICE) environment, Antarctica provides invaluable opportunities to experience stressors more common to spaceflight than to the average person s everyday life. Increased prevalence of psychological symptoms, syndromes, and psychiatric disorders, as well as positive effects, are expected to be associated with various demographic and environmental factors. Implications for spaceflight are discussed. Findings from statistical review of the Antarctic articles will be shared.
Author
ANTARCTIC REGIONS; PSYCHOLOGICAL EFFECTS; SIGNS AND SYMPTOMS; ISOLATION; CONFINEMENT
Additions to the NASA Aeronautics and Space Database as of 03/04/2009
20090007555 NASA Johnson Space Center, Houston, TX, United States
Occupant Protection during Orion Crew Exploration Vehicle Landings
Gernhardt, Michael L.; Jones, J. A.; Granderson, B. K.; Somers, J. T.; February 02, 2009; In English; Human Research Program Investigators Workshop, 2 - 4 Feb. 2009, League City, TX, United States
Report No.(s): JSC-17729; JSC-17773; Copyright; Avail.: CASI: A01, Hardcopy
The constellation program is evaluating current vehicle design capabilities for nominal water landings and contingency land landings of the Orion Crew Exploration vehicle. The Orion Landing Strategy tiger team was formed to lead the technical effort for which associated activities include the current vehicle design, susceptibility to roll control and tip over, reviewing methods for assessing occupant injury during ascent / aborts /landings, developing an alternate seat/attenuation design solution which improves occupant protection and operability, and testing the seat/attenuation system designs to ensure valid results. The EVA physiology, systems and Performance (EPSP) project is leading the effort under the authority of the Tiger Team Steering committee to develop, verify, validate and accredit biodynamics models using a variety of crash and injury databases including NASCAR, Indy Car and military aircraft. The validated biodynamics models will be used by the Constellation program to evaluate a variety of vehicle, seat and restraint designs in the context of multiple nominal and off-nominal landing scenarios. The models will be used in conjunction with Acceptable Injury Risk definitions to provide new occupant protection requirements for the Constellation Program.
Author
CONSTELLATION PROGRAM; CREW EXPLORATION VEHICLE; RISK; SPACECRAFT LANDING; PROTECTION; COUNTERMEASURES
20090007598 NASA Langley Research Center, Hampton, VA, United States
Ablative Thermal Response Analysis Using the Finite Element Method
Dec John A.; Braun, Robert D.; January 05, 2009; In English; 47th AIAA Aerospace Sciences Meeting and Exhibit, 5-18 Jan. 2009, Orlando, FL, United States; Original contains color and black and white illustrations
Contract(s)/Grant(s): WBS 092837.04.01.04.08.04
Report No.(s): AIAA-Paper-2009-0259; LF99-7029; Copyright; Avail.: CASI: A03, Hardcopy
A review of the classic techniques used to solve ablative thermal response problems is presented. The advantages and disadvantages of both the finite element and finite difference methods are described. As a first step in developing a three dimensional finite element based ablative thermal response capability, a one dimensional computer tool has been developed. The finite element method is used to discretize the governing differential equations and Galerkin's method of weighted residuals is used to derive the element equations. A code to code comparison between the current 1-D tool and the 1-D Fully Implicit Ablation and Thermal Response Program (FIAT) has been performed.
Author
ABLATION; THERMAL ANALYSIS; FINITE ELEMENT METHOD; THERMODYNAMICS
20090007599 NASA Langley Research Center, Hampton, VA, United States
Multi-Dimensional, Inviscid Flux Reconstruction for Simulation of Hypersonic Heating on Tetrahedral Grids
Gnoffo, Peter A.; January 05, 2009; In English; 47th AIAA Aerospace Sciences Meeting and Exhibit, 5-8 Jan. 2009, Orlando, FL, United States; Original contains color and black and white illustrations
Contract(s)/Grant(s): WBS 599489.02.07.07.04.01
Report No.(s): AIAA-Paper-2009-0599; LF99-7070; No Copyright; Avail.: CASI: A03, Hardcopy
Avail Online: http://hdl.handle.net/2060/20090007599
The quality of simulated hypersonic stagnation region heating on tetrahedral meshes is investigated by using a three-dimensional, upwind reconstruction algorithm for the inviscid flux vector. Two test problems are investigated: hypersonic flow over a three-dimensional cylinder with special attention to the uniformity of the solution in the spanwise direction and hypersonic flow over a three-dimensional sphere. The tetrahedral cells used in the simulation are derived from a structured grid where cell faces are bisected across the diagonal resulting in a consistent pattern of diagonals running in a biased direction across the otherwise symmetric domain. This grid is known to accentuate problems in both shock capturing and stagnation region heating encountered with conventional, quasi-one-dimensional inviscid flux reconstruction algorithms. Therefore the test problem provides a sensitive test for algorithmic effects on heating. This investigation is believed to be unique in its focus on three-dimensional, rotated upwind schemes for the simulation of hypersonic heating on tetrahedral grids. This study attempts to fill the void left by the inability of conventional (quasi-one-dimensional) approaches to accurately simulate heating in a tetrahedral grid system. Results show significant improvement in spanwise uniformity of heating with some penalty of ringing at the captured shock. Issues with accuracy near the peak shear location are identified and require further study.
Author
HYPERSONIC FLOW; UNSTRUCTURED GRIDS (MATHEMATICS); TETRAHEDRONS; STAGNATION POINT; HEATING; HEAT FLUX
20090007600 NASA Langley Research Center, Hampton, VA, United States
Hypersonic Viscous Flow Over Large Roughness Elements
Chang, Chau-Lyan; Choudhari, Meelan M.; January 05, 2009; In English; 47th AIAA Aerospace Sciences Meeting and Exhibit, 5-08 Jan. 2009, Orlando, FL, United States; Original contains color and black and white illustrations
Contract(s)/Grant(s): WBS 526282.01.07.04.02
Report No.(s): AIAA-Paper-2009-0173; LF99-7074; No Copyright; Avail.: CASI: A03, Hardcopy
Avail Online: http://hdl.handle.net/2060/20090007600
Viscous flow over discrete or distributed surface roughness has great implications for hypersonic flight due to aerothermodynamic considerations related to laminar-turbulent transition. Current prediction capability is greatly hampered by the limited knowledge base for such flows. To help fill that gap, numerical computations are used to investigate the intricate flow physics involved. An unstructured mesh, compressible Navier-Stokes code based on the space-time conservation element, solution element (CESE) method is used to perform time-accurate Navier-Stokes calculations for two roughness shapes investigated in wind tunnel experiments at NASA Langley Research Center. It was found through 2D parametric study that at subcritical Reynolds numbers of the boundary layers, absolute instability resulting in vortex shedding downstream, is likely to weaken at supersonic free-stream conditions. On the other hand, convective instability may be the dominant mechanism for supersonic boundary layers. Three-dimensional calculations for a rectangular or cylindrical roughness element at post-shock Mach numbers of 4.1 and 6.5 also confirm that no self-sustained vortex generation is present.
Author
HYPERSONIC FLOW; VISCOUS FLOW; SURFACE ROUGHNESS; HYPERSONIC BOUNDARY LAYER; NUMERICAL ANALYSIS; COMPUTATIONAL FLUID DYNAMICS
20090007601 NASA Langley Research Center, Hampton, VA, United States
Stability Analysis of Roughness Array Wake in a High-Speed Boundary Layer
Choudhari, Meelan; Li, Fei; Edwards, Jack; January 04, 2009; In English; Original contains color and black and white illustrations
Contract(s)/Grant(s): FA9550-0701-0191
Report No.(s): AIAA-Paper-2009-0170; LF99-7075; Copyright; Avail.: CASI: A03, Hardcopy
Computations are performed to examine the effects of both an isolated and spanwise periodic array of trip elements on a high-speed laminar boundary layer, so as to identify the potential physical mechanisms underlying an earlier transition to turbulence as a result of the trip(s). In the context of a 0.333 scale model of the Hyper-X forebody configuration, the time accurate solution for an array of ramp shaped trips asymptotes to a stationary field at large times, indicating the likely absence of a strong absolute instability in the mildly separated flow due to the trips. A prominent feature of the wake flow behind the trip array corresponds to streamwise streaks that are further amplified in passing through the compression corner. Stability analysis of the streaks using a spatial, 2D eigenvalue approach reveals the potential for a strong convective instability that might explain the earlier onset of turbulence within the array wake. The dominant modes of streak instability are primarily sustained by the spanwise gradients associated with the streaks and lead to integrated logarithmic amplification factors (N factors) approaching 7 over the first ramp of the scaled Hyper-X forebody, and substantially higher over the second ramp. Additional computations are presented to shed further light on the effects of both trip geometry and the presence of a compression corner on the evolution of the streaks.
Author
FLOW STABILITY; WAKES; SURFACE ROUGHNESS; LAMINAR BOUNDARY LAYER; BOUNDARY LAYER TRANSITION; COMPUTATIONAL FLUID DYNAMICS
20090007602 NASA Langley Research Center, Hampton, VA, United States
CARS Temperature Measurements in a Combustion-Heated Supersonic Jet
Tedder, S. A.; Danehy, P. M.; Magnotti, G.; Cutler, A. D.; January 05, 2009; In English; 47th AIAA Aerospace Sciences Meeting and Exhibit Including The New Horizons Forum and Aerospace Exposition, 5-8 Jan. 2009, Orlando, FL, United States; Original contains color and black and white illustrations
Contract(s)/Grant(s): WBS 599489.02.07.07.06.02
Report No.(s): AIAA Paper 2009-524; LF99-7077; Copyright; Avail.: CASI: A03, Hardcopy
Measurements were made in a combustion-heated supersonic axi-symmetric free jet from a nozzle with a diameter of 6.35 cm using dual-pump Coherent Anti-Stokes Raman Spectroscopy (CARS). The resulting mean and standard deviation temperature maps are presented. The temperature results show that the gas temperature on the centerline remains constant for approximately 5 nozzle diameters. As the heated gas mixes with the ambient air further downstream the mean temperature decreases. The standard deviation map shows evidence of the increase of turbulence in the shear layer as the jet proceeds downstream and mixes with the ambient air. The challenges of collecting data in a harsh environment are discussed along with influences to the data. The yield of the data collected is presented and possible improvements to the yield is presented are discussed.
Author
RAMAN SPECTROSCOPY; HEAT OF COMBUSTION; SUPERSONIC JET FLOW; SUPERSONIC COMBUSTION; TEMPERATURE MEASUREMENT; COMPUTATIONAL FLUID DYNAMICS
20090007603 NASA Langley Research Center, Hampton, VA, United States
NASA Standard for Models and Simulations: Philosophy and Requirements Overview
Blattnig, St3eve R.; Luckring, James M.; Morrison, Joseph H.; Sylvester, Andre J.; Tripathi, Ram K.; Zang, Thomas A.; January 05, 2009; In English; 47th AIAA Aerospace Sciences Meeting and Exhibit, 5-8 Jan. 2009, Orlando, FL, United States; Original contains color illustrations
Contract(s)/Grant(s): WBS 510505.05.07.02.01
Report No.(s): LF99-7104; No Copyright; Avail.: CASI: A03, Hardcopy
Avail Online: http://hdl.handle.net/2060/20090007603
Following the Columbia Accident Investigation Board report, the NASA Administrator chartered an executive team (known as the Diaz Team) to identify those CAIB report elements with NASA-wide applicability and to develop corrective measures to address each element. One such measure was the development of a standard for the development, documentation, and operation of models and simulations. This report describes the philosophy and requirements overview of the resulting NASA Standard for Models and Simulations.
Author
NASA PROGRAMS; MODELS; SIMULATION; STANDARDS; AEROSPACE SAFETY
20090007604 NASA Langley Research Center, Hampton, VA, United States
Comparison of Node-Centered and Cell-Centered Unstructured Finite-Volume Discretizations Part 1 Viscous Fluxes
Diskin, Boris; Thomas, James L.; Nielsen, Eric J.; Nishikawa, Hiroaki; White, Jeffery A.; January 05, 2009; In English; 47th AIAA Aerospace Sciences Meeting and Exhibit, 5-8 Jan. 2009, Orlando, FL, United States; Original contains color and black and white illustrations
Contract(s)/Grant(s): WBS 525282.01.07.04.02
Report No.(s): LF99-7106; Copyright; Avail.: CASI: A03, Hardcopy
Discretization of the viscous terms in current finite-volume unstructured-grid schemes are compared using node-centered and cell-centered approaches in two dimensions. Accuracy and efficiency are studied for six nominally second-order accurate schemes: a node-centered scheme, cell-centered node-averaging schemes with and without clipping, and cell-centered schemes with unweighted, weighted, and approximately mapped least-square face gradient reconstruction. The grids considered range from structured (regular) grids to irregular grids composed of arbitrary mixtures of triangles and quadrilaterals, including random perturbations of the grid points to bring out the worst possible behavior of the solution. Two classes of tests are considered. The first class of tests involves smooth manufactured solutions on both isotropic and highly anisotropic grids with discontinuous metrics, typical of those encountered in grid adaptation. The second class concerns solutions and grids varying strongly anisotropically over a curved body, typical of those encountered in high-Reynolds number turbulent flow simulations. Results from the first class indicate the face least-square methods, the node-averaging method without clipping, and the node-centered method demonstrate second-order convergence of discretization errors with very similar accuracies per degree of freedom. The second class of tests are more discriminating. The node-centered scheme is always second order with an accuracy and complexity in linearization comparable to the best of the cell-centered schemes. In comparison, the cell-centered node-averaging schemes are less accurate, have a higher complexity in linearization, and can fail to converge to the exact solution when clipping of the node-averaged values is used. The cell-centered schemes using least-square face gradient reconstruction have more compact stencils with a complexity similar to the complexity of the node-centered scheme. For simulations on highly anisotropic curved grids, the least-square methods have to be amended either by introducing a local mapping of the surface anisotropy or modifying the scheme stencil to reflect the direction of strong coupling.
Author
UNSTRUCTURED GRIDS (MATHEMATICS); FINITE VOLUME METHOD; DISCRETIZATION (MATHEMATICS); VISCOUS FLOW; COMPUTATIONAL FLUID DYNAMICS
20090007605 NASA Langley Research Center, Hampton, VA, United States
Recent Enhancements To The FUN3D Flow Solver For Moving-Mesh Applications
Biedron, Robert T,; Thomas, James L.; January 05, 2009; In English; 47th AIAA Aerospace Sciences Meeting and Exhibit, 5-8 Jan. 2009, Orlando, FL, United States; Original contains color and black and white illustrations
Contract(s)/Grant(s): WBS 526282.01.07.04.02
Report No.(s): LF99-7107; No Copyright; Avail.: CASI: A03, Hardcopy
Avail Online: http://hdl.handle.net/2060/20090007605
An unsteady Reynolds-averaged Navier-Stokes solver for unstructured grids has been extended to handle general mesh movement involving rigid, deforming, and overset meshes. Mesh deformation is achieved through analogy to elastic media by solving the linear elasticity equations. A general method for specifying the motion of moving bodies within the mesh has been implemented that allows for inherited motion through parent-child relationships, enabling simulations involving multiple moving bodies. Several example calculations are shown to illustrate the range of potential applications. For problems in which an isolated body is rotating with a fixed rate, a noninertial reference-frame formulation is available. An example calculation for a tilt-wing rotor is used to demonstrate that the time-dependent moving grid and noninertial formulations produce the same results in the limit of zero time-step size.
Author
COMPUTATIONAL FLUID DYNAMICS; UNSTRUCTURED GRIDS (MATHEMATICS); COMPUTATIONAL GRIDS; NAVIER-STOKES EQUATION; REYNOLDS AVERAGING; FLOW GEOMETRY; SIMULATION
20090007606 NASA Langley Research Center, Hampton, VA, United States
Implementation of Radiation, Ablation, and Free Energy Minimization Modules for Coupled Simulations of Hypersonic Flow
Gnoffo, Peter A.; Johnston, Christopher O.; Thompson, Richard A.; January 05, 2009; In English; 47th AIAA Aerospace Sciences Meeting and Exhibit, 5-8 Jan. 2009, Orlando, FL, United States; Original contains color and black and white illustrations
Contract(s)/Grant(s): WBS 599489.02.07.07.04.01
Report No.(s): AIAA-Paper-2009-1399; LF99-7110; No Copyright; Avail.: CASI: A03, Hardcopy
Avail Online: http://hdl.handle.net/2060/20090007606
A description of models and boundary conditions required for coupling radiation and ablation physics to a hypersonic flow simulation is provided. Chemical equilibrium routines for varying elemental mass fraction are required in the flow solver to integrate with the equilibrium chemistry assumption employed in the ablation models. The capability also enables an equilibrium catalytic wall boundary condition in the non-ablating case. The paper focuses on numerical implementation issues using FIRE II, Mars return, and Apollo 4 applications to provide context for discussion. Variable relaxation factors applied to the Jacobian elements of partial equilibrium relations required for convergence are defined. Challenges of strong radiation coupling in a shock capturing algorithm are addressed. Results are presented to show how the current suite of models responds to a wide variety of conditions involving coupled radiation and ablation.
Author
NUMERICAL ANALYSIS; HYPERSONIC FLOW; SIMULATION; RADIATION; ABLATION; BOUNDARY CONDITIONS; MODELS
20090007607 NASA Langley Research Center, Hampton, VA, United States
Analysis of Compression Pad Cavities for the Orion Heatshield
Thompson, Richard A.; Lessard, Victor R.; Jentink, Thomas N.; Zoby, Ernest V.; January 05, 2009; In English; 47th AIAA Aerospace Sciences Meeting and Exhibit, 5-8 Jan. 2009, Orlando, FL, United States; Original contains color and black and white illustrations
Contract(s)/Grant(s): WBS 644423.02.39.04.10.03
Report No.(s): AIAA-Paper-2009-1525; LF99-7113; Copyright; Avail.: CASI: A03, Hardcopy
Current results of a program for analysis of the compression pad cavities on the Orion heatshield are reviewed. The program was supported by experimental tests, engineering modeling, and applied computations with an emphasis on the latter presented in this paper. The computational tools and approach are described along with calculated results for wind tunnel and flight conditions. Correlations of the computed results are shown which can produce a credible prediction of heating augmentation due to cavity disturbances. The models developed for use in preliminary design of the Orion heatshield are presented.
Author
HEAT SHIELDING; CAVITIES; CREW EXPLORATION VEHICLE; THERMAL ANALYSIS; COMPUTATIONAL FLUID DYNAMICS; THERMODYNAMICS
20090007608 NASA Langley Research Center, Hampton, VA, United States
Domain Decomposition By the Advancing-Partition Method for Parallel Unstructured Grid Generation
Pirzadeh, Shahyar Z.; Zagaris, George; January 05, 2009; In English; 47th AIAA Aerospace Sciences Meeting and Exhibit, 5-8 Jan. 2009, Orlando, FL, United States; Original contains color and black and white illustrations
Contract(s)/Grant(s): WBS 561581.02.08.07.20.02
Report No.(s): LF99-7126; Copyright; Avail.: CASI: A03, Hardcopy
A new method of domain decomposition has been developed for generating unstructured grids in subdomains either sequentially or using multiple computers in parallel. Domain decomposition is a crucial and challenging step for parallel grid generation. Prior methods are generally based on auxiliary, complex, and computationally intensive operations for defining partition interfaces and usually produce grids of lower quality than those generated in single domains. The new technique, referred to as "Advancing Partition," is based on the Advancing-Front method, which partitions a domain as part of the volume mesh generation in a consistent and "natural" way. The benefits of this approach are: 1) the process of domain decomposition is highly automated, 2) partitioning of domain does not compromise the quality of the generated grids, and 3) the computational overhead for domain decomposition is minimal. The new method has been implemented in NASA's unstructured grid generation code VGRID.
Author
UNSTRUCTURED GRIDS (MATHEMATICS); GRID GENERATION (MATHEMATICS); DECOMPOSITION; DOMAINS; COMPUTERS
20090007628 NASA Langley Research Center, Hampton, VA, United States
Enhancement of USM3D Unstructured Flow Solver for High-Speed High-Temperature Shear Flows
Pandya, Mohagna J.; Abdol-Hamid, Khaled S.; Frink, Neal T.; January 05, 2009; In English; 47th AIAA Aerospace Sciences Meeting and Exhibit, 5-8 Jan. 2009, Orlando, FL, United States; Original contains color and black and white illustrations
Contract(s)/Grant(s): WBS 136905.02.04.04.16.03
Report No.(s): LF99-7127; Copyright; Avail.: CASI: A03, Hardcopy
Large temperature and pressure fluctuations have a profound effect on turbulence development in transonic and supersonic jets. For high-speed, high-temperature jet flows, standard turbulence models lack the ability to predict the observed mixing rate of a shear layer. Several proposals to address this deficiency have been advanced in the literature to modify the turbulence transport equations in a variety of ways. In the present study, some of the most proven and simple modifications to two-equation turbulence models have been selected and implemented in NASA's USM3D tetrahedral Navier-Stokes flow solver. The modifications include the addition of compressibility correction and pressure dilatation terms in the turbulence transport equations for high-speed flows, and the addition of a simple modification to the Boussinesq's closure model coefficient for high-temperature jets. The efficacy of the extended models is demonstrated by comparison with experimental data for two supersonic axisymmetric jet test cases at design pressure ratio.
Author
TURBULENCE MODELS; THREE DIMENSIONAL MODELS; NUMERICAL ANALYSIS; COMPUTATIONAL FLUID DYNAMICS; NAVIER-STOKES EQUATION; SHEAR FLOW; UNSTRUCTURED GRIDS (MATHEMATICS)
20090007630 NASA Langley Research Center, Hampton, VA, United States
A Framework for Parallel Unstructured Grid Generation for Complex Aerodynamic Simulations
Zagaris, George; Pirzadeh, Shahyar Z.; Chrisochoides, Nikos; January 05, 2009; In English; 47th AIAA Aerospace Sciences Meeting and Exhibit, 5-8 Jan. 2009, Orlando, FL, United States; Original contains color and black and white illustrations
Contract(s)/Grant(s): NNL06AA02H; NNX07AM10HWBS 561581.02.08.07.20.02
Report No.(s): LF99-7128; Copyright; Avail.: CASI: A03, Hardcopy
A framework for parallel unstructured grid generation targeting both shared memory multi-processors and distributed memory architectures is presented. The two fundamental building-blocks of the framework consist of: (1) the Advancing-Partition (AP) method used for domain decomposition and (2) the Advancing Front (AF) method used for mesh generation. Starting from the surface mesh of the computational domain, the AP method is applied recursively to generate a set of sub-domains. Next, the sub-domains are meshed in parallel using the AF method. The recursive nature of domain decomposition naturally maps to a divide-and-conquer algorithm which exhibits inherent parallelism. For the parallel implementation, the Master/Worker pattern is employed to dynamically balance the varying workloads of each task on the set of available CPUs. Performance results by this approach are presented and discussed in detail as well as future work and improvements.
Author
UNSTRUCTURED GRIDS (MATHEMATICS); GRID GENERATION (MATHEMATICS); ARCHITECTURE (COMPUTERS); DISTRIBUTED MEMORY; MEMORY (COMPUTERS); DOMAINS; ALGORITHMS
20090007632 NASA Langley Research Center, Hampton, VA, United States
Interaction of Aircraft Wakes From Laterally Spaced Aircraft
Proctor, Fred H.; January 05, 2009; In English; 47th AIAA Aerospace Sciences Meeting and Exhibit, 5-8 Jan. 2009, Orlando, FL, United States; Original contains color and black and white illustrations
Contract(s)/Grant(s): WBS 305295.02.07.07.20
Report No.(s): LF99-7139; No Copyright; Avail.: CASI: A03, Hardcopy
Avail Online: http://hdl.handle.net/2060/20090007632
Large Eddy Simulations are used to examine wake interactions from aircraft on closely spaced parallel paths. Two sets of experiments are conducted, with the first set examining wake interactions out of ground effect (OGE) and the second set for in ground effect (IGE). The initial wake field for each aircraft represents a rolled-up wake vortex pair generated by a B-747. Parametric sets include wake interactions from aircraft pairs with lateral separations of 400, 500, 600, and 750 ft. The simulation of a wake from a single aircraft is used as baseline. The study shows that wake vortices from either a pair or a formation of B-747 s that fly with very close lateral spacing, last longer than those from an isolated B-747. For OGE, the inner vortices between the pair of aircraft, ascend, link and quickly dissipate, leaving the outer vortices to decay and descend slowly. For the IGE scenario, the inner vortices ascend and last longer, while the outer vortices decay from ground interaction at a rate similar to that expected from an isolated aircraft. Both OGE and IGE scenarios produce longer-lasting wakes for aircraft with separations less than 600 ft. The results are significant because concepts to increase airport capacity have been proposed that assume either aircraft formations and/or aircraft pairs landing on very closely spaced runways.
Author
WAKES; VORTICES; RUNWAYS; GROUND EFFECT (AERODYNAMICS); BOEING 747 AIRCRAFT; LARGE EDDY SIMULATION
20090007635 NASA Langley Research Center, Hampton, VA, United States
Synthetic Vision Systems
Prinzel, L.J.; Kramer, L.J.; [2009]; In English; Original contains color illustrations
Report No.(s): LF99-1309; No Copyright; Avail.: CASI: A03, Hardcopy
Avail Online: http://hdl.handle.net/2060/20090007635
A synthetic vision system is an aircraft cockpit display technology that presents the visual environment external to the aircraft using computer-generated imagery in a manner analogous to how it would appear to the pilot if forward visibility were not restricted. The purpose of this chapter is to review the state of synthetic vision systems, and discuss selected human factors issues that should be considered when designing such displays.
Author
AVIONICS; ENHANCED VISION; VISIBILITY; COCKPITS; DISPLAY DEVICES; NAVIGATION AIDS; FLIGHT OPERATIONS; AIRCRAFT SAFETY
20090007678 NASA Langley Research Center, Hampton, VA, United States
Hybrid Reynolds-Averaged/Large-Eddy Simulations of a Co-Axial Supersonic Free-Jet Experiment
Baurle, R. A.; Edwards, J. R.; et al.; January 05, 2009; In English; 47th AIAA Aerospace Sciences Meeting and Exhibit, 5-8 Jan. 2009, Orlando, FL, United States; Original contains color and black and white illustrations
Contract(s)/Grant(s): WBS 599489.02.07.07.03.02.01
Report No.(s): AIAA-Paper-2009-0129; LF99-7141; Copyright; Avail.: CASI: A03, Hardcopy
Reynolds-averaged and hybrid Reynolds-averaged/large-eddy simulations have been applied to a supersonic coaxial jet flow experiment. The experiment utilized either helium or argon as the inner jet nozzle fluid, and the outer jet nozzle fluid consisted of laboratory air. The inner and outer nozzles were designed and operated to produce nearly pressure-matched Mach 1.8 flow conditions at the jet exit. The purpose of the computational effort was to assess the state-of-the-art for each modeling approach, and to use the hybrid Reynolds-averaged/large-eddy simulations to gather insight into the deficiencies of the Reynolds-averaged closure models. The Reynolds-averaged simulations displayed a strong sensitivity to choice of turbulent Schmidt number. The baseline value chosen for this parameter resulted in an over-prediction of the mixing layer spreading rate for the helium case, but the opposite trend was noted when argon was used as the injectant. A larger turbulent Schmidt number greatly improved the comparison of the results with measurements for the helium simulations, but variations in the Schmidt number did not improve the argon comparisons. The hybrid simulation results showed the same trends as the baseline Reynolds-averaged predictions. The primary reason conjectured for the discrepancy between the hybrid simulation results and the measurements centered around issues related to the transition from a Reynolds-averaged state to one with resolved turbulent content. Improvements to the inflow conditions are suggested as a remedy to this dilemma. Comparisons between resolved second-order turbulence statistics and their modeled Reynolds-averaged counterparts were also performed.
Author
REYNOLDS AVERAGING; LARGE EDDY SIMULATION; SUPERSONIC JET FLOW; COAXIAL FLOW; COMPUTATIONAL FLUID DYNAMICS
20090007682 NASA Langley Research Center, Hampton, VA, United States
Evaluation of Fast-Time Wake Vortex Prediction Models
Proctor, Fred H.; Hamilton, David W.; January 05, 2009; In English; 47th AIAA Aerospace Sciences Meeting and Exhibit, 5-8 Jan. 2009, Orlando, FL, United States; Original contains color and black and white illustrations
Contract(s)/Grant(s): WBS 305295.02.07.07.20
Report No.(s): LF99-7143; Copyright; Avail.: CASI: A02, Hardcopy
Current fast-time wake models are reviewed and three basic types are defined. Predictions from several of the fast-time models are compared. Previous statistical evaluations of the APA-Sarpkaya and D2P fast-time models are discussed. Root Mean Square errors between fast-time model predictions and Lidar wake measurements are examined for a 24 hr period at Denver International Airport. Shortcomings in current methodology for evaluating wake errors are also discussed.
Author
AIRCRAFT WAKES; VORTICES; MODELS; AIR TRAFFIC CONTROL; AIRCRAFT APPROACH SPACING; AIRCRAFT SAFETY
20090007683 NASA Langley Research Center, Hampton, VA, United States
Local-in-Time Adjoint-Based Method for Optimal Control/Design Optimization of Unsteady Compressible Flows
Yamaleev, N. K.; Diskin, B.; Nielsen, E. J.; January 05, 2009; In English; 47th AIAA Aerospace Sciences Meeting and Exhibit, 5-8 Jan. 2009, Orlando, FL, United States; Original contains black and white illustrations
Contract(s)/Grant(s): WBS 984754.02.07.07.14.03
Report No.(s): LF99-7147; AIAA Paper 2009-1169; Copyright; Avail.: CASI: A03, Hardcopy
.We study local-in-time adjoint-based methods for minimization of ow matching functionals subject to the 2-D unsteady compressible Euler equations. The key idea of the local-in-time method is to construct a very accurate approximation of the global-in-time adjoint equations and the corresponding sensitivity derivative by using only local information available on each time subinterval. In contrast to conventional time-dependent adjoint-based optimization methods which require backward-in-time integration of the adjoint equations over the entire time interval, the local-in-time method solves local adjoint equations sequentially over each time subinterval. Since each subinterval contains relatively few time steps, the storage cost of the local-in-time method is much lower than that of the global adjoint formulation, thus making the time-dependent optimization feasible for practical applications. The paper presents a detailed comparison of the local- and global-in-time adjoint-based methods for minimization of a tracking functional governed by the Euler equations describing the ow around a circular bump. Our numerical results show that the local-in-time method converges to the same optimal solution obtained with the global counterpart, while drastically reducing the memory cost as compared to the global-in-time adjoint formulation.
Author
OPTIMAL CONTROL; DESIGN OPTIMIZATION; COST REDUCTION; UNSTEADY FLOW; TIME DEPENDENCE
20090007685 NASA Langley Research Center, Hampton, VA, United States
Turbulent Supersonic/Hypersonic Heating Correlations for Open and Closed Cavities
Everhart, Joel L.; Greene, Francis A.; January 05, 2009; In English; 47th AIAA Aerospace Sciences Meeting and Exhibit, 5-8 Jan. 2009, Orlando, FL, United States; Original contains color and black and white illustrations
Contract(s)/Grant(s): WBS 52628201070405
Report No.(s): LF99-7148; No Copyright; Avail.: CASI: A03, Hardcopy
Avail Online: http://hdl.handle.net/2060/20090007685
Supersonic/hypersonic laminar heating correlations that were developed for damage assessment analysis of atmospheric re-entry vehicles have been modified and extended to cover fully-turbulent conditions over rectangular cavity geometries that are aligned with the local velocity. Turbulent boundary layer properties were computationally determined and used to develop the cavity geometry parametrics and to correlate experimental closed cavity heating data to yield new relationships for the floor-averaged and centerline endwall peak-heating augmentation. With the form of the closed-cavity correlations established, historical data were used to develop new correlations for turbulent open-cavity heating.
Author
TURBULENT BOUNDARY LAYER; AERODYNAMIC HEATING; AEROTHERMODYNAMICS; CAVITY FLOW; IMPACT DAMAGE; DAMAGE ASSESSMENT; THERMAL PROTECTION; ATMOSPHERIC ENTRY
20090007687 NASA Langley Research Center, Hampton, VA, United States
2-D Circulation Control Airfoil Benchmark Experiments Intended for CFD Code Validation
Englar, Robert J.; Jones, Gregory S.; Allan, Brian G.; Lin, Johb C.; January 05, 2009; In English; 47th AIAA Aerospace Sciences Meeting and Exhibit, 5-8 Jan. 2009, Orlando, FL, United States; Original contains color and black and white illustrations
Contract(s)/Grant(s): WBS 561581.02.08.07.20.04
Report No.(s): AIAA-Paper-2009-902; LF99-7167; Copyright; Avail.: CASI: A03, Hardcopy
A current NASA Research Announcement (NRA) project being conducted by Georgia Tech Research Institute (GTRI) personnel and NASA collaborators includes the development of Circulation Control (CC) blown airfoils to improve subsonic aircraft high-lift and cruise performance. The emphasis of this program is the development of CC active flow control concepts for both high-lift augmentation, drag control, and cruise efficiency. A collaboration in this project includes work by NASA research engineers, whereas CFD validation and flow physics experimental research are part of NASA s systematic approach to developing design and optimization tools for CC applications to fixed-wing aircraft. The design space for CESTOL type aircraft is focusing on geometries that depend on advanced flow control technologies that include Circulation Control aerodynamics. The ability to consistently predict advanced aircraft performance requires improvements in design tools to include these advanced concepts. Validation of these tools will be based on experimental methods applied to complex flows that go beyond conventional aircraft modeling techniques. This paper focuses on recent/ongoing benchmark high-lift experiments and CFD efforts intended to provide 2-D CFD validation data sets related to NASA s Cruise Efficient Short Take Off and Landing (CESTOL) study. Both the experimental data and related CFD predictions are discussed.
Author
ACTIVE CONTROL; AERODYNAMICS; CIRCULATION CONTROL AIRFOILS; COMPUTATIONAL FLUID DYNAMICS; DESIGN OPTIMIZATION; DYNAMIC CONTROL; FLOW DISTRIBUTION; LIFT AUGMENTATION; DRAG
20090007688 NASA Langley Research Center, Hampton, VA, United States
Using Numerical Modeling to Simulate Space Capsule Ground Landings
Heymsfield, Ernie; Fasanella, Edwin L.; January 11, 2009; In English; Transportation Research Board 88th Annual Meeting, 11-15 Jan. 2009, Washington, DC, United States; Original contains color and black and white illustrations
Contract(s)/Grant(s): WBS 644423.04.31.04.40.43.20
Report No.(s): LF99-7336; Copyright; Avail.: CASI: A03, Hardcopy
Experimental work is being conducted at the National Aeronautics and Space Administration s (NASA) Langley Research Center (LaRC) to investigate ground landing capabilities of the Orion crew exploration vehicle (CEV). The Orion capsule is NASA s replacement for the Space Shuttle. The Orion capsule will service the International Space Station and be used for future space missions to the Moon and to Mars. To evaluate the feasibility of Orion ground landings, a series of capsule impact tests are being performed at the NASA Langley Landing and Impact Research Facility (LandIR). The experimental results derived at LandIR provide means to validate and calibrate nonlinear dynamic finite element models, which are also being developed during this study. Because of the high cost and time involvement intrinsic to full-scale testing, numerical simulations are favored over experimental work. Subsequent to a numerical model validated by actual test responses, impact simulations will be conducted to study multiple impact scenarios not practical to test. Twenty-one swing tests using the LandIR gantry were conducted during the June 07 through October 07 time period to evaluate the Orion s impact response. Results for two capsule initial pitch angles, 0deg and -15deg , along with their computer simulations using LS-DYNA are presented in this article. A soil-vehicle friction coefficient of 0.45 was determined by comparing the test stopping distance with computer simulations. In addition, soil modeling accuracy is presented by comparing vertical penetrometer impact tests with computer simulations for the soil model used during the swing tests.
Author
LANDING LOADS; CREW EXPLORATION VEHICLE; IMPACT LOADS; IMPACT TESTS; SPACE MISSIONS; MATHEMATICAL MODELS; MARS MISSIONS; DYNAMIC MODELS; COEFFICIENT OF FRICTION; COMPUTERIZED SIMULATION
20090007689 NASA Langley Research Center, Hampton, VA, United States
Atomistic Cohesive Zone Models for Interface Decohesion in Metals
Yamakov, Vesselin I.; Saether, Erik; Glaessgen, Edward H.; January 03, 2009; In English; 15th International Symposium, Plasticity 2009, 308 Jan. 2009, Saint Thomas, Virgin Islands (U.S.); Original contains black and white illustrations
Contract(s)/Grant(s): NCC1-02043WBS 698259.02.07.03.01
Report No.(s): LF99-7716; Copyright; Avail.: CASI: A01, Hardcopy
Using a statistical mechanics approach, a cohesive-zone law in the form of a traction-displacement constitutive relationship characterizing the load transfer across the plane of a growing edge crack is extracted from atomistic simulations for use within a continuum finite element model. The methodology for the atomistic derivation of a cohesive-zone law is presented. This procedure can be implemented to build cohesive-zone finite element models for simulating fracture in nanocrystalline or ultrafine grained materials.
Author
COHESION; METALS; STATISTICAL MECHANICS; LOADS (FORCES); EDGE CRACKS; CONTINUUM MODELING
20090007690 NASA Langley Research Center, Hampton, VA, United States
Blended-Wing-Body Low-Speed Flight Dynamics: Summary of Ground Tests and Sample Results
Vicroy, Dan D.; January 05, 2009; In English; 47th AIAA Aerospace Sciences Meeting and Exhibit, 5-8 Jan. 2009, Orlando, FL, United States; Original contains color and black and white illustrations
Contract(s)/Grant(s): WBS 561581.02.08.07.17
Report No.(s): AIAA-Paper-2009-0933; LF99-8176; No Copyright; Avail.: CASI: A02, Hardcopy
Avail Online: http://hdl.handle.net/2060/20090007690
A series of low-speed wind tunnel tests of a Blended-Wing-Body tri-jet configuration to evaluate the low-speed static and dynamic stability and control characteristics over the full envelope of angle of attack and sideslip are summarized. These data were collected for use in simulation studies of the edge-of-the-envelope and potential out-of-control flight characteristics. Some selected results with lessons learned are presented.
Author
BLENDED-WING-BODY CONFIGURATIONS; FLIGHT CHARACTERISTICS; STATIC STABILITY; WIND TUNNEL TESTS; ANGLE OF ATTACK; SIDESLIP
20090007692 NASA Langley Research Center, Hampton, VA, United States
Uncertainty Analysis for the Evaluation of a Passive Runway Arresting System
Deloach, Richard; Marlowe, Jill M.; Yager, Thomas J.; January 05, 2009; In English; 47th AIAA Aerospace Sciences Meeting and Exhibit, 5-8 Jan. 2009, Orlando, FL, United States; Original contains color and black and white illustrations
Contract(s)/Grant(s): WBS 526282.01.07.03
Report No.(s): AIAA-Paper-2009-1156; LF99-8190; Copyright; Avail.: CASI: A03, Hardcopy
This paper considers the stopping distance of an aircraft involved in a runway overrun incident when the runway has been provided with an extension comprised of a material engineered to induce high levels of rolling friction and drag. A formula for stopping distance is derived that is shown to be the product of a known formula for the case of friction without drag, and a dimensionless constant between 0 and 1 that quantifies the further reduction in stopping distance when drag is introduced. This additional quantity, identified as the Drag Reduction Factor, D, is shown to depend on the ratio of drag force to friction force experienced by the aircraft as it enters the overrun area. The specific functional form of D is shown to depend on how drag varies with speed. A detailed uncertainty analysis is presented which reveals how the uncertainty in estimates of stopping distance are influenced by experimental error in the force measurements that are acquired in a typical evaluation experiment conducted to assess candidate overrun materials.
Author
AIRCRAFT SAFETY; ARRESTING GEAR; RUNWAYS; STOPPING; FRICTION; DRAG REDUCTION; KINETIC ENERGY; ENERGY DISSIPATION; MATERIALS SELECTION; MATERIAL ABSORPTION; MATHEMATICAL MODELS
20090007697 NASA Langley Research Center, Hampton, VA, United States
The Development and Implementation of a Cryogenic Pressure Sensitive Paint System in the National Transonic Facility
Watkins, A. Neal; Leighty, Bradley D.; Lipford, William E.; Oglesby, Donald M.; Goodman, Kyle Z.; Goad, William K.; Goad, Linda R.; Massey, Edward A.; January 05, 2009; In English; 47th AIAA Aerospace Sciences Meeting and Exhibit, 5-8 Jan. 2009, Orlando, FL, United States; Original contains color and black and white illustrations
Contract(s)/Grant(s): WBS 561581.02.08.07.20.03
Report No.(s): LF99-8224; Copyright; Avail.: CASI: A02, Hardcopy
The Pressure Sensitive Paint (PSP) method was used to measure global surface pressures on a model at full-scale flight Reynolds numbers. In order to achieve these conditions, the test was carried out at the National Transonic Facility (NTF) operating under cryogenic conditions in a nitrogen environment. The upper surface of a wing on a full-span 0.027 scale commercial transport was painted with a porous PSP formulation and tested at 120K. Data was acquired at Mach 0.8 with a total pressure of 200 kPa, resulting in a Reynolds number of 65 x 106/m. Oxygen, which is required for PSP operation, was injected using dry air so that the oxygen concentration in the flow was approximately 1535 ppm. Results show qualitative agreement with expected results. This preliminary test is the first time that PSP has been successfully deployed to measure global surface pressures at cryogenic condition in the NTF. This paper will describe the system as installed, the results obtained from the test, as well as proposed upgrades and future tests.
Author
PRESSURE SENSITIVE PAINTS; POROSITY; REYNOLDS NUMBER; CRYOGENICS; TRANSONIC SPEED; WING SPAN; SURFACE PROPERTIES
20090007699 NASA Langley Research Center, Hampton, VA, United States
Spatially and Temporally Resolved Measurements of Velocity in a H2-air Combustion-Heated Supersonic Jet
Bivolaru, Daniel; Cutler, Andrew D.; Danehy, Paul M.; Gaffney, Richard L.; Baurle, Robert a.; January 05, 2009; In English; 47th AIAA Aerospace Sciences Meeting and Exhibit, 5-8 Jan. 2009, Orlando, Fl, United States; Original contains color and black and white illustrations
Contract(s)/Grant(s): WBS 599489.02.07.07.06.02
Report No.(s): LF99-8231; Copyright; Avail.: CASI: A02, Hardcopy
This paper presents simultaneous measurements at multiple points of two orthogonal components of flow velocity using a single-shot interferometric Rayleigh scattering (IRS) technique. The measurements are performed on a large-scale Mach 1.6 (Mach 5.5 enthalpy) H2-air combustion jet during the 2007 test campaign in the Direct Connect Supersonic Combustion Test facility at NASA Langley Research Center. The measurements are performed simultaneously with CARS (Coherent Anti-stokes Raman Spectroscopy) using a combined CARS-IRS instrument with a common path 9-nanosecond pulsed, injection-seeded, 532-nm Nd:YAG laser probe pulse. The paper summarizes the measurements of velocities along the core of the vitiated air flow as well as two radial profiles. The average velocity measurement near the centerline at the closest point from the nozzle exit compares favorably with the CFD calculations using the VULCAN code. Further downstream, the measured axial velocity shows overall higher values than predicted with a trend of convergence at further distances. Larger discrepancies are shown in the radial profiles.
Author
AIR FLOW; FLOW VELOCITY; VELOCITY MEASUREMENT; INTERFEROMETRY; RAYLEIGH SCATTERING; RAMAN SPECTROSCOPY; MEASURING INSTRUMENTS
20090007702 NASA Langley Research Center, Hampton, VA, United States
Blended-Wing-Body Transonic Aerodynamics: Summary of Ground Tests and Sample Results
Carter, Melissa B.; Vicroy, Dan D.; Patel, Dharmendra; January 05, 2009; In English; 47th AIAA Aerospace Sciences Meeting and Exhibit, 5-8 Jan. 2009, Orlando, Fl, United States; Original contains color and black and white illustrations
Contract(s)/Grant(s): WBS 561581.02.08.07.12.04
Report No.(s): LF99-8272; Copyright; Avail.: CASI: A03, Hardcopy
The Blended-Wing-Body (BWB) concept has shown substantial performance benefits over conventional aircraft configuration with part of the benefit being derived from the absence of a conventional empennage arrangement. The configuration instead relies upon a bank of trailing edge devices to provide control authority and augment stability. To determine the aerodynamic characteristics of the aircraft, several wind tunnel tests were conducted with a 2% model of Boeing's BWB-450-1L configuration. The tests were conducted in the NASA Langley Research Center's National Transonic Facility and the Arnold Engineering Development Center s 16-Foot Transonic Tunnel. Characteristics of the configuration and the effectiveness of the elevons, drag rudders and winglet rudders were measured at various angles of attack, yaw angles, and Mach numbers (subsonic to transonic speeds). The data from these tests will be used to develop a high fidelity simulation model for flight dynamics analysis and also serve as a reference for CFD comparisons. This paper provides an overview of the wind tunnel tests and examines the effects of Reynolds number, Mach number, pitch-pause versus continuous sweep data acquisition and compares the data from the two wind tunnels.
Author
BLENDED-WING-BODY CONFIGURATIONS; AERODYNAMIC CHARACTERISTICS; TRANSONIC SPEED; WIND TUNNEL TESTS; COMPUTATIONAL FLUID DYNAMICS; TRAILING EDGES; REYNOLDS NUMBER; CONTROL STABILITY; ANGLE OF ATTACK
20090007704 NASA Langley Research Center, Hampton, VA, United States
Some Activities of MISSE 6 Mission
Prasad, Narasimha S.; January 24, 2009; In English; SPIE Photonics West 2009, 24-29 Jan. 2009, San Jose, CA, United States; Original contains color and black and white illustrations
Contract(s)/Grant(s): WBS 736466.09.02.07.02.01
Report No.(s): Paper No. 7193-3; LF99-8319; No Copyright; Avail.: CASI: A02, Hardcopy
Avail Online: http://hdl.handle.net/2060/20090007704
The objective of the Materials International Space Station Experiment (MISSE) is to study the performance of novel materials when subjected to the synergistic effects of the harsh space environment for several months. In this paper, a few laser and optical elements from NASA Langley Research Center (LaRC) that have been flown on MISSE 6 mission will be discussed. These items were characterized and packed inside a ruggedized Passive Experiment Container (PEC) that resembles a suitcase. The PEC was tested for survivability due to launch conditions. Subsequently, the MISSE 6 PEC was transported by the STS-123 mission to International Space Station (ISS) on March 11, 2008. The astronauts successfully attached the PEC to external handrails and opened the PEC for long term exposure to the space environment. The plan is to retrieve the MISSE 6 PEC by STS-128 mission in August 2009.
Author
INTERNATIONAL SPACE STATION; SPACEBORNE EXPERIMENTS; LONG DURATION SPACE FLIGHT; RADIATION DOSAGE; RADIATION EFFECTS
20090007708 NASA Marshall Space Flight Center, Huntsville, AL, United States
Liquid Oxygen/Liquid Methane Ascent Main Engine Technology Development
Robinson, Joel W.; Stephenson, David D.; September 29, 2008; In English; 59th International Astronautical Conference, 29 Sep. - 03 Oct. 2008, Scotland, United Kingdom; Original contains black and white illustrations
Report No.(s): MSFC-2022; IAC-08-C4.1.02; No Copyright; Avail.: CASI: A02, Hardcopy
Avail Online: http://hdl.handle.net/2060/20090007708
The National Aeronautics & Space Administration (NASA) has identified Liquid Oxygen (LO2)/Liquid Methane (LCH4) as a potential propellant combination for future space vehicles based upon the Exploration Systems Architecture Study (ESAS). The technology is estimated to have higher performance and lower overall systems mass compared to existing hypergolic propulsion systems. The current application considering this technology is the lunar ascent main engine (AME). AME is anticipated to be an expendable, pressure-fed engine to provide ascent from the moon at the completion of a 210 day lunar stay. The engine is expected to produce 5,500 lbf (24,465 N) thrust with variable inlet temperatures due to the cryogenic nature of the fuel and oxidizer. The primary technology risks include establishing reliable and robust ignition in vacuum conditions, maximizing specific impulse, developing rapid start capability for the descent abort, providing the capability for two starts and producing a total engine bum time over 500 seconds. This paper will highlight the efforts of the Marshall Space Flight Center (MSFC) in addressing risk reduction activities for this technology.
Author
LIQUID OXYGEN; METHANE; LIQUEFIED GASES; HYPERGOLIC ROCKET PROPELLANTS; INLET TEMPERATURE; ENGINE DESIGN
20090007713 NASA Marshall Space Flight Center, Huntsville, AL, United States
Development and Utilization of Space Fission Power Systems
Houts, Michael; Mason, Lee S.; Palac, Donald T.; Harlow, Scott E.; September 09, 2008; In English; Space 2008, 9 - 12 Sep. 2008, California, United States; Original contains black and white illustrations
Report No.(s): MSFC-2026; Copyright; Avail.: CASI: A01, Hardcopy
Space fission power systems could enable advanced civilian space missions. Terrestrially, thousands of fission systems have been operated since 1942. In addition, the US flew a space fission system in 1965, and the former Soviet Union flew 33 such systems prior to the end of the Cold War. Modern design and development practices, coupled with 65 years of experience with terrestrial reactors, could enable the affordable development of space fission power systems for near-term planetary surface applications.
Author
SPACECRAFT POWER SUPPLIES; PLANETARY SURFACES; SPACE MISSIONS; FISSION
20090007714 NASA Marshall Space Flight Center, Huntsville, AL, United States; Boeing AS and T Phantom Works, Saint Louis, MO, United States
Evaluation of ARCAM Deposited Ti-6Al-4V
Slattery, Kevin; Slaughter, Blake; Speorl, Emily; Good, James; Gilley, Scott; McLemore, Carole; September 14, 2008; In English; 2nd South African International Aerospace Symposium, 14 - 16 Sep. 2008, Cape Town, South Africa; Original contains black and white illustrations
Report No.(s): MSFC-2027; Copyright; Avail.: CASI: A02, Hardcopy
A wide range of Metal Additive Manufacturing (MAM) technologies are becoming available. One of the challenges in using new technologies for aerospace systems is demonstrating that the process and system has the ability to manufacture components that meet the high quality requirements on a statistically significant basis. The widest-used system for small to medium sized components is the ARCAM system manufactured in Gothenburg, Sweden. This system features a 4kW electron-beam gun, and has a chamber volume of 250mm long x 250mm wide x 250mm to 400mm tall. This paper will describe the basis for the quality and consistency requirements, the experimental and evaluation procedures used for the evaluation, and an analysis of the results for Ti-6Al-4V.
Author
ADDITIVES; MANUFACTURING; TITANIUM ALLOYS; VANADIUM ALLOYS; ALUMINUM ALLOYS; ELECTRON BEAMS; AEROSPACE SYSTEMS
20090007715 NASA Marshall Space Flight Center, Huntsville, AL, United States
A Review of NASA's Radiation-Hardened Electronics for Space Environments Project
Keys, Andrew S.; Adams, James H.; Patrick, Marshall C.; Johnson, Michael A.; Cressler, John D.; September 09, 2008; In English; AIAA Space 2008, 9 - 11 Sep. 2008, California, United States
Report No.(s): MSFC-2028; Copyright; Avail.: CASI: A02, Hardcopy
NASA's Radiation Hardened Electronics for Space Exploration (RHESE) project develops the advanced technologies required to produce radiation hardened electronics, processors, and devices in support of the requirements of NASA's Constellation program. Over the past year, multiple advancements have been made within each of the RHESE technology development tasks that will facilitate the success of the Constellation program elements. This paper provides a brief review of these advancements, discusses their application to Constellation projects, and addresses the plans for the coming year.
Author
AEROSPACE ENVIRONMENTS; CONSTELLATION PROGRAM; FIELD-PROGRAMMABLE GATE ARRAYS; RADIATION EFFECTS; GERMANIUM; HARDNESS
Additions to the NASA Aeronautics and Space Database as of 03/05/2009
20090007740 NASA Langley Research Center, Hampton, VA, United States
Detection of Subsurface Material Separation in Shuttle Orbiter Slip-Side Joggle Region of the Wing Leading Edge using Infrared Imaging Data from Arc Jet Tests
Daryabeigi, Kamran; Walker, Sandra P.; January 26, 2009; In English; 33rd Annual Conference on Composites, Materials, and Structures, 26-29 Jan. 2009, Cocoa Beach, FL, United States; Original contains color and black and white illustrations
Contract(s)/Grant(s): WBS 510505.05.07.04.11
Report No.(s): LF99-7701; No Copyright; Avail.: CASI: A03, Hardcopy
Avail Online: http://hdl.handle.net/2060/20090007740
The objective of the present study was to determine whether infrared imaging (IR) surface temperature data obtained during arc-jet tests of Space Shuttle Orbiter s reinforced carbon-carbon (RCC) wing leading edge panel slip-side joggle region could be used to detect presence of subsurface material separation, and if so, to determine when separation occurs during the simulated entry profile. Recent thermostructural studies have indicated thermally induced interlaminar normal stress concentrations at the substrate/coating interface in the curved joggle region can result in local subsurface material separation, with the separation predicted to occur during approach to peak heating during reentry. The present study was an attempt to determine experimentally when subsurface material separations occur. A simplified thermal model of a flat RCC panel with subsurface material separation was developed and used to infer general surface temperature trends due to the presence of subsurface material separation. IR data from previously conducted arc-jet tests on three test specimens were analyzed: one without subsurface material separation either pre or post test, one with pre test separation, and one with separation developing during test. The simplified thermal model trend predictions along with comparison of experimental IR data of the three test specimens were used to successfully infer material separation from the arc-jet test data. Furthermore, for the test specimen that had developed subsurface material separation during the arc-jet tests, the initiation of separation appeared to occur during the ramp up to the peak heating condition, where test specimen temperature went from 2500 to 2800 F.
Author
SPACE SHUTTLE ORBITERS; WING PANELS; TEMPERATURE EFFECTS; INTERLAMINAR STRESS; INFRARED IMAGERY; STRESS CONCENTRATION; SURFACE TEMPERATURE; LEADING EDGES
20090007742 NASA Langley Research Center, Hampton, VA, United States
Integration of Engine, Plume, and CFD Analyses in Conceptual Design of Low-Boom Supersonic Aircraft
Li, Wu; Campbell, Richard; Geiselhart, Karl; Shields, Elwood; Nayani, Sudheer; Shenoy, Rajiv; January 05, 2009; In English; 47th AIAA Aerospace Sciences Meeting and Exhibit, 5-8 Jan. 2009, Orlando, FL, United States; Original contains color and black and white illustrations
Contract(s)/Grant(s): WBS 984754.02.07.07.12.03
Report No.(s): AIAA-Paper 2009-1171; LF99-7718; Copyright; Avail.: CASI: A03, Hardcopy
This paper documents an integration of engine, plume, and computational fluid dynamics (CFD) analyses in the conceptual design of low-boom supersonic aircraft, using a variable fidelity approach. In particular, the Numerical Propulsion Simulation System (NPSS) is used for propulsion system cycle analysis and nacelle outer mold line definition, and a low-fidelity plume model is developed for plume shape prediction based on NPSS engine data and nacelle geometry. This model provides a capability for the conceptual design of low-boom supersonic aircraft that accounts for plume effects. Then a newly developed process for automated CFD analysis is presented for CFD-based plume and boom analyses of the conceptual geometry. Five test cases are used to demonstrate the integrated engine, plume, and CFD analysis process based on a variable fidelity approach, as well as the feasibility of the automated CFD plume and boom analysis capability.
Author
PLUMES; COMPUTATIONAL FLUID DYNAMICS; SUPERSONIC AIRCRAFT; PROPULSION SYSTEM CONFIGURATIONS; SYSTEMS ANALYSIS
20090007743 NASA Langley Research Center, Hampton, VA, United States
High-Order Energy Stable WENO Schemes
Yamaleev, Nail K.; Carpenter, Mark H.; January 05, 2009; In English; 47th AIAA Aerospace Sciences Meeting and Exhibit, 5-8 Jan. 2009, Orlando, Fl, United States; Original contains black and white illustrations
Contract(s)/Grant(s): WBS 599489.02.07.07.04.03.01
Report No.(s): AIAA-Paper-2009-1135; LF99-7889; Copyright; Avail.: CASI: A03, Hardcopy
A third-order Energy Stable Weighted Essentially Non-Oscillatory (ESWENO) finite difference scheme developed by Yamaleev and Carpenter was proven to be stable in the energy norm for both continuous and discontinuous solutions of systems of linear hyperbolic equations. Herein, a systematic approach is presented that enables 'energy stable' modifications for existing WENO schemes of any order. The technique is demonstrated by developing a one-parameter family of fifth-order upwind-biased ESWENO schemes; ESWENO schemes up to eighth order are presented in the appendix. New weight functions are also developed that provide (1) formal consistency, (2) much faster convergence for smooth solutions with an arbitrary number of vanishing derivatives, and (3) improved resolution near strong discontinuities.
Author
ESSENTIALLY NON-OSCILLATORY SCHEMES; FINITE DIFFERENCE THEORY; HYPERBOLIC DIFFERENTIAL EQUATIONS; LINEAR EQUATIONS; STABILITY; NUMERICAL ANALYSIS
20090007744 NASA Langley Research Center, Hampton, VA, United States
Hybrid Wing Body Configuration System Studies
Nickol, Craig L.; McCullers, Arnie; January 05, 2009; In English; 47th AIAA Aerospace Sciences Meeting and Exhibit, 5-8 Jan. 2009, Orlando, FL, United States; Original contains color and black and white illustrations
Contract(s)/Grant(s): WBS 561581.02.08.07.13.05
Report No.(s): LF99-8168; Copyright; Avail.: CASI: A03, Hardcopy
The objective of this study was to develop a hybrid wing body (HWB) sizing and analysis capability, apply that capability to estimate the fuel burn potential for an HWB concept, and identify associated technology requirements. An advanced tube with wings concept was also developed for comparison purposes. NASA s Flight Optimization System (FLOPS) conceptual aircraft sizing and synthesis software was modified to enable the sizing and analysis of HWB concepts. The noncircular pressurized centerbody of the HWB concept was modeled, and several options were created for defining the outboard wing sections. Weight and drag estimation routines were modified to accommodate the unique aspects of an HWB configuration. The resulting capability was then utilized to model a proprietary Boeing blended wing body (BWB) concept for comparison purposes. FLOPS predicted approximately a 15 percent greater drag, mainly caused by differences in compressibility drag estimation, and approximately a 5 percent greater takeoff gross weight, mainly caused by the additional fuel required, as compared with the Boeing data. Next, a 777-like reference vehicle was modeled in FLOPS and calibrated to published Boeing performance data; the same mission definition was used to size an HWB in FLOPS. Advanced airframe and propulsion technology assumptions were applied to the HWB to develop an estimate for potential fuel burn savings from such a concept. The same technology assumptions, where applicable, were then applied to an advanced tube-with-wings concept. The HWB concept had a 39 percent lower block fuel burn than the reference vehicle and a 12 percent lower block fuel burn than the advanced tube-with-wings configuration. However, this fuel burn advantage is partially derived from assuming the high-risk technology of embedded engines with boundary-layer-ingesting inlets. The HWB concept does have the potential for significantly reduced noise as a result of the shielding advantages that are inherent with an over-body engine installation.
Author
BOUNDARY LAYERS; BLENDED-WING-BODY CONFIGURATIONS; AERODYNAMIC CONFIGURATIONS; FLIGHT OPTIMIZATION; TAKEOFF; WINGS
20090007745 NASA Langley Research Center, Hampton, VA, United States
An Overview of the State of the Art in Atomistic and Multiscale Simulation of Fracture
Saether, Erik; Yamakov, Vesselin; Phillips, Dawn R.; Glaessgen, Edward H.; February 2009; In English; Original contains color and black and white illustrations
Contract(s)/Grant(s): WBS 698259.02.07.07.03.01
Report No.(s): NASA/TM-2009-215564; LF99-8229; L-19581; Copyright; Avail.: CASI: A04, Hardcopy
The emerging field of nanomechanics is providing a new focus in the study of the mechanics of materials, particularly in simulating fundamental atomic mechanisms involved in the initiation and evolution of damage. Simulating fundamental material processes using first principles in physics strongly motivates the formulation of computational multiscale methods to link macroscopic failure to the underlying atomic processes from which all material behavior originates. This report gives an overview of the state of the art in applying concurrent and sequential multiscale methods to analyze damage and failure mechanisms across length scales.
Author
ATOMIC PHYSICS; DEGRADATION; MOLECULAR DYNAMICS; FINITE ELEMENT METHOD; ATOMS
20090007747 NASA Marshall Space Flight Center, Huntsville, AL, United States
Considerations Regarding the Development of an Environmental Control and Life Support System for Lunar Surface Applications
Bagdigian, Robert M.; September 24, 2008; In English; Department of Biological Sciences of the RAS, 24 - 27 Sep. 2008, Moscow, Russia; Original contains color and black and white illustrations
Report No.(s): MSFC-2031; No Copyright; Avail.: CASI: A03, Hardcopy
Avail Online: http://hdl.handle.net/2060/20090007747
NASA is engaged in early architectural analyses and trade studies aimed at identifying requirements, predicting performance and resource needs, characterizing mission constraints and sensitivities, and guiding technology development planning needed to conduct a successful human exploration campaign of the lunar surface. Conceptual designs and resource estimates for environmental control and life support systems (ECLSS) within pressurized lunar surface habitats and rovers have been considered and compared in order to support these lunar campaign studies. This paper will summarize those concepts and some of the more noteworthy considerations that will likely remain as key drivers in the evolution of the lunar surface ECLSS architecture.
Author
LUNAR SURFACE; LIFE SUPPORT SYSTEMS; ENVIRONMENTAL CONTROL; PERFORMANCE PREDICTION; TECHNOLOGICAL FORECASTING; MISSION PLANNING
20090007751 NASA Johnson Space Center, Houston, TX, United States; Draper (Charles Stark) Lab., Inc., Houston, TX, United States
Autonomous Optical Lunar Navigation
Zanetti, Renato; Crouse, Brian; D'souza, Chris; [2009]; In English; AAS Spaceflight Mechanic Conference, 8 - 12 Feb. 2009, Georgia, United States; Original contains color illustrations
Contract(s)/Grant(s): 644423.02.36.15.10 ORION
Report No.(s): JSC-17581; Copyright; Avail.: CASI: A01, Hardcopy
The performance of optical autonomous navigation is investigated for low lunar orbits and for high elliptical lunar orbits. Various options for employing the camera measurements are presented and compared. Strategies for improving navigation performance are developed and applied to the Orion vehicle lunar mission
Author
AUTONOMOUS NAVIGATION; OPTICAL EQUIPMENT; CAMERAS; LUNAR ORBITS; ELLIPTICAL ORBITS
20090007776 NASA Johnson Space Center, Houston, TX, United States
Ballistic Limit Equation for Single Wall Titanium
Ratliff, J. M.; Christiansen, Eric L.; Bryant, C.; [2009]; In English; 5th European Conference on Space Debris, 30 Mar. - 2 Apr. 2009, Darmstadt, Germany
Contract(s)/Grant(s): 510505.05.05.05.03
Report No.(s): JSC-17569; No Copyright; Avail.: CASI: A01, Hardcopy
Avail Online: http://hdl.handle.net/2060/20090007776
Hypervelocity impact tests and hydrocode simulations were used to determine the ballistic limit equation (BLE) for perforation of a titanium wall, as a function of wall thickness. Two titanium alloys were considered, and separate BLEs were derived for each. Tested wall thicknesses ranged from 0.5mm to 2.0mm. The single-wall damage equation of Cour-Palais [ref. 1] was used to analyze the Ti wall's shielding effectiveness. It was concluded that the Cour-Palais single-wall equation produced a non-conservative prediction of the ballistic limit for the Ti shield. The inaccurate prediction was not a particularly surprising result; the Cour-Palais single-wall BLE contains shield material properties as parameters, but it was formulated only from tests of different aluminum alloys. Single-wall Ti shield tests were run (thicknesses of 2.0 mm, 1.5 mm, 1.0 mm, and 0.5 mm) on Ti 15-3-3-3 material custom cut from rod stock. Hypervelocity impact (HVI) tests were used to establish the failure threshold empirically, using the additional constraint that the damage scales with impact energy, as was indicated by hydrocode simulations. The criterion for shield failure was defined as no detached spall from the shield back surface during HVI. Based on the test results, which confirmed an approximately energy-dependent shield effectiveness, the Cour-Palais equation was modified.
Author
TITANIUM; IMPACT TESTS; HYPERVELOCITY IMPACT; SHIELDING; FAILURE; DAMAGE
20090007781 NASA Johnson Space Center, Houston, TX, United States
Lunar Landing Trajectory Design for Onboard Hazard Detection and Avoidance
Paschall, Steve; Brady, Tye; Sostaric, Ron; January 31, 2009; In English; 32nd Annual AAS Guidance and Control Conference, 31 Jan. - 4 Feb. 2009, Breckenridge, CO, United States; Original contains color and black and white illustrations
Report No.(s): AAS 09-075; JSC-17675; Copyright; Avail.: CASI: A03, Hardcopy
The Autonomous Landing and Hazard Avoidance Technology (ALHAT) Project is developing the software and hardware technology needed to support a safe and precise landing for the next generation of lunar missions. ALHAT provides this capability through terrain-relative navigation measurements to enhance global-scale precision, an onboard hazard detection system to select safe landing locations, and an Autonomous Guidance, Navigation, and Control (AGNC) capability to process these measurements and safely direct the vehicle to a landing location. This paper focuses on the key trajectory design issues relevant to providing an onboard Hazard Detection and Avoidance (HDA) capability for the lander. Hazard detection can be accomplished by the crew visually scanning the terrain through a window, a sensor system imaging the terrain, or some combination of both. For ALHAT, this hazard detection activity is provided by a sensor system, which either augments the crew s perception or entirely replaces the crew in the case of a robotic landing. Detecting hazards influences the trajectory design by requiring the proper perspective, range to the landing site, and sufficient time to view the terrain. Following this, the trajectory design must provide additional time to process this information and make a decision about where to safely land. During the final part of the HDA process, the trajectory design must provide sufficient margin to enable a hazard avoidance maneuver. In order to demonstrate the effects of these constraints on the landing trajectory, a tradespace of trajectory designs was created for the initial ALHAT Design Analysis Cycle (ALDAC-1) and each case evaluated with these HDA constraints active. The ALHAT analysis process, described in this paper, narrows down this tradespace and subsequently better defines the trajectory design needed to support onboard HDA. Future ALDACs will enhance this trajectory design by balancing these issues and others in an overall system design process.
Author
LUNAR LANDING; TRAJECTORIES; HAZARDS; DETECTION; AUTONOMOUS NAVIGATION; ROBOTICS; GUIDANCE (MOTION)
20090007783 NASA Johnson Space Center, Houston, TX, United States
Low Impact Docking System (LIDS)
LaBauve, Tobie E.; February 2009; In English; Original contains color illustrations
Report No.(s): JSC-17710; No Copyright; Avail.: CASI: A01, Hardcopy
Avail Online: http://hdl.handle.net/2060/20090007783
Since 1996, NASA has been developing a docking system that will simplify operations and reduce risks associated with mating spacecraft. This effort has focused on developing and testing an original, reconfigurable, active, closed-loop, force-feedback controlled docking system using modern technologies. The primary objective of this effort has been to design a docking interface that is tunable to the unique performance requirements for all types of mating operations (i.e. docking and berthing, autonomous and piloted rendezvous, and in-space assembly of vehicles, modules and structures). The docking system must also support the transfer of crew, cargo, power, fluid, and data. As a result of the past 10 years of docking system advancement, the Low Impact Docking System or LIDS was developed. The current LIDS design incorporates the lessons learned and development experiences from both previous and existing docking systems. LIDS feasibility was established through multiple iterations of prototype hardware development and testing. Benefits of LIDS include safe, low impact mating operations, more effective and flexible mission implementation with an anytime/anywhere mating capability, system level redundancy, and a more affordable and sustainable mission architecture with reduced mission and life cycle costs. In 1996 the LIDS project, then known as the Advanced Docking Berthing System (ADBS) project, launched a four year developmental period. At the end of the four years, the team had built a prototype of the soft-capture hardware and verified the control system that will be used to control the soft-capture system. In 2001, the LIDS team was tasked to work with the X- 38 Crew Return Vehicle (CRV) project and build its first Engineering Development Unit (EDU).
Author
SPACECRAFT DOCKING; FEEDBACK CONTROL; LIFE CYCLE COSTS; PRODUCT DEVELOPMENT; FEASIBILITY; MODULES
Additions to the NASA Aeronautics and Space Database as of 03/06/2009
20090007797 NASA Dryden Flight Research Center, Edwards, CA, United States
Design and Development of the Blackbird: Challenges and Lessons Learned
Merlin, Peter W.; January 05, 2009; In English; 47th AIAA Aerospace Sciences Meeting, 5 - 8 Jan. 2009, Florida, United States; Original contains color and black and white illustrations
Report No.(s): AIAA-Paper-2009-1522; DFRC-935; Copyright; Avail.: CASI: A03, Hardcopy
The Lockheed Blackbirds hold a unique place in the development of aeronautics. In their day, the A-12, YF-12, M-21, D-21, and SR-71 variants outperformed all other jet airplanes in terms of altitude and speed. Now retired, they remain the only production aircraft capable of sustained Mach 3 cruise and operational altitudes above 80,000 feet. In this paper the author describes the design evolution of the Blackbird from Lockheed's early Archangel studies for the Central Intelligence Agency through Senior Crown, production of the Air Force's SR-71. He describes the construction and materials challenges faced by Lockheed, the Blackbird's performance characteristics and capabilities, and the National Aeronautics and Space Administration's role in using the aircraft as a flying laboratory to collect data on materials, structures, loads, heating, aerodynamics, and performance for high-speed aircraft.
Author
SR-71 AIRCRAFT; AIRCRAFT DESIGN; AIRCRAFT PRODUCTION; AIRCRAFT STRUCTURES; AIRCRAFT CONSTRUCTION MATERIALS; AIRCRAFT PERFORMANCE; LESSONS LEARNED
Additions to the NASA Aeronautics and Space Database as of 03/09/2009
20090007804 NASA Marshall Space Flight Center, Huntsville, AL, United States
Use of Probabilistic Engineering Methods in the Detailed Design and Development Phases of the NASA Ares Launch Vehicle
Fayssal, Safie; Weldon, Danny; October 21, 2008; In English; 3rd IAASS Conference: Building a Safer Space Together, 21 - 23 Oct. 2008, Rome, Italy; Original contains color and black and white illustrations
Report No.(s): M09-2039; MSFC-2039; No Copyright; Avail.: CASI: A02, Hardcopy
Avail Online: http://hdl.handle.net/2060/20090007804
The United States National Aeronautics and Space Administration (NASA) is in the midst of a space exploration program called Constellation to send crew and cargo to the international Space Station, to the moon, and beyond. As part of the Constellation program, a new launch vehicle, Ares I, is being developed by NASA Marshall Space Flight Center. Designing a launch vehicle with high reliability and increased safety requires a significant effort in understanding design variability and design uncertainty at the various levels of the design (system, element, subsystem, component, etc.) and throughout the various design phases (conceptual, preliminary design, etc.). In a previous paper [1] we discussed a probabilistic functional failure analysis approach intended mainly to support system requirements definition, system design, and element design during the early design phases. This paper provides an overview of the application of probabilistic engineering methods to support the detailed subsystem/component design and development as part of the "Design for Reliability and Safety" approach for the new Ares I Launch Vehicle. Specifically, the paper discusses probabilistic engineering design analysis cases that had major impact on the design and manufacturing of the Space Shuttle hardware. The cases represent important lessons learned from the Space Shuttle Program and clearly demonstrate the significance of probabilistic engineering analysis in better understanding design deficiencies and identifying potential design improvement for Ares I. The paper also discusses the probabilistic functional failure analysis approach applied during the early design phases of Ares I and the forward plans for probabilistic design analysis in the detailed design and development phases.
Author
ARES 1 LAUNCH VEHICLE; DESIGN ANALYSIS; FUNCTIONAL ANALYSIS; SYSTEMS ENGINEERING; FAILURE ANALYSIS; LAUNCH VEHICLES; RELIABILITY
20090007807 NASA Glenn Research Center, Cleveland, OH, United States
NASA Partnerships and Collaborative Research on Ultra High Bypass Cycle Propulsion Concepts
Hughes, Chris; September 23, 2009; In English; Fall Acoustics Technical Working Group Meeting, 23 - 24 Sep. 2008, Virginia, United States; Original contains color illustrations
Report No.(s): E-16904; No Copyright; Avail.: CASI: A03, Hardcopy
Avail Online: http://hdl.handle.net/2060/20090007807
Current collaborative research with General Electric Aviation on Open Rotor propulsion as part of the Subsonic Fixed Wing Project Ultra High Bypass Engine Partnership Element is discussed. The Subsonic Fixed Wing Project goals are reviewed, as well as their relative technology level compared to previous NASA noise program goals. The current Open Rotor propulsion research activity at NASA and GE are discussed including the contributions each entity bring toward the research project, and technical plans and objectives.
Author
BYPASSES; PROPULSION; ROTORS; TURBOFAN ENGINES
20090007808 NASA Glenn Research Center, Cleveland, OH, United States
NASA / GE Aviation Collaborative Partnership Research in Ultra High Bypass Cycle Propulsion Concepts
Hughes, Christopher E.; Zeug, Theresa; October 07, 2008; In English; FA Annual Meeting, 7 - 9 Oct. 2008, Georgia, United States; Original contains color and black and white illustrations
Report No.(s): E-169003; Copyright; Avail.: CASI: A03, Hardcopy
Current collaborative research with General Electric Aviation on Open Rotor propulsion as part of the Subsonic Fixed Wing Project Ultra High Bypass Engine Partnership Element is discussed. The Subsonic Fixed Wing Project goals are reviewed, as well as their relative technology level compared to previous NASA noise program goals. The current Open Rotor propulsion research activity at NASA and GE are discussed including the contributions each entity bring toward the research project, and technical plans and objectives. GE Open Rotor propulsion technology and business plans currently and toward the future are also discussed, including the role the NASA SFW UHB partnership plays toward achieving those goals.
Author
TURBOFAN ENGINES; PROPULSION; BYPASSES; ROTORS
20090007812 Wisconsin-Stout Univ., Menomonie, WI, United States
Joining of Zirconium Diboride-Based Ceramic Composites to Metallic Systems for High-Temperature Applications
Asthana, R.; Singh, M.; October 05, 2008; In English; 2008 Materials Science and Technology: Joining of Advanced and Speciality Materials, 5 - 9 Oct. 2008, Pennsylvania, United States; Original contains black and white illustrations
Contract(s)/Grant(s): NNC07TB09T
Report No.(s): E-16898; Copyright; Avail.: CASI: A03, Hardcopy
Three types of hot-pressed zirconium diboride (ZrB2)-based ultra-high-temperature ceramic composites (UHTCC), ZrB2-SiC (ZS), ZrB2-SiC-C (ZSC), and ZrB2-SCS9-SiC (ZSS), were joined to Cu-clad-Mo using two Ag-Cu brazes (Cusil-ABA and Ticusil, T(sub L) approx.1073-1173 K) and two Pd-base brazes (Palco and Palni, T(sub L) approx.1493-1513 K). Scanning Electron Microscopy (SEM) coupled with energy-dispersive spectroscopy (EDS) revealed greater chemical interaction in joints made using Pd-base brazes than in joints made using Ag-Cu based active brazes. The degree of densification achieved in hot pressed composites influenced the Knoop hardness of the UHTCC and the hardness distribution across the braze interlayer. The braze region in Pd-base system displayed higher hardness in joints made using fully-dense ZS composites than in joints made using partially-dense ZSS composites and the carbon-containing ZSC composites. Calculations indicate a small negative elastic strain energy and an increase in the UHTCC's fracture stress up to a critical clad layer thickness . Above this critical thickness, strain energy in the UHTCC is positive, and it increases with increasing clad layer thickness. Empirical projections show a reduction in the effective thermal resistance of the joints and highlight the potential benefits of joining the UHTCC to Cu-clad-Mo.
Author
CERAMIC MATRIX COMPOSITES; ZIRCONIUM; HIGH TEMPERATURE; THERMAL RESISTANCE; HOT PRESSING; DENSIFICATION; INTERLAYERS; CARBON
20090007813 ASRC Aerospace Corp., Cleveland, OH, United States
Advanced Solar Cell and Array Technology for NASA Deep Space Missions
Piszczor, Michael; Benson, Scott; Scheiman, David; Finacannon, Homer; Oleson, Steve; Landis, Geoffrey; May 16, 2008; In English; 33rd IEEE Photovoltaic Specialists Conference, 11 - 16 May 2008, California, United States; Original contains color illustrations
Report No.(s): E-16814-1; Copyright; Avail.: CASI: A03, Hardcopy
A recent study by the NASA Glenn Research Center assessed the feasibility of using photovoltaics (PV) to power spacecraft for outer planetary, deep space missions. While the majority of spacecraft have relied on photovoltaics for primary power, the drastic reduction in solar intensity as the spacecraft moves farther from the sun has either limited the power available (severely curtailing scientific operations) or necessitated the use of nuclear systems. A desire by NASA and the scientific community to explore various bodies in the outer solar system and conduct "long-term" operations using using smaller, "lower-cost" spacecraft has renewed interest in exploring the feasibility of using photovoltaics for to Jupiter, Saturn and beyond. With recent advances in solar cell performance and continuing development in lightweight, high power solar array technology, the study determined that photovoltaics is indeed a viable option for many of these missions.
Author
PHOTOVOLTAIC CONVERSION; SOLAR ARRAYS; SOLAR CELLS; SPACE MISSIONS; GAS GIANT PLANETS; NASA SPACE PROGRAMS
20090007814 NASA Glenn Research Center, Cleveland, OH, United States
Numerical Investigation of LO2 and LCH4 Storage Tanks on the Lunar Surface
Moder, Jeff; Barsi, Stephen; Kassemi, Mohammad; December 2008; In English; 44th AIAA Joint Propulsion Conference`, 21 - 23 Jul. 2008, Connecticut, United States; Original contains color and black and white illustrations
Report No.(s): NASA/TM-2008-215443; AIAA-Paper-2008-4749; E-16641; Copyright; Avail.: CASI: A03, Hardcopy
Currently NASA is developing technologies to enable human exploration of the lunar surface for duration of up to 210 days. While trade studies are still underway, a cryogenic ascent stage using liquid oxygen (LO2) and liquid methane (LCH4) is being considered for the Altair lunar lander. For a representative Altair cryogenic ascent stage, we present a detailed storage analysis of the LO2 and LCH4 propellant tanks on the lunar surface for durations of up to 210 days. Both the LO2 and LCH4 propellant tanks are assumed to be pressurized with gaseous helium at launch. A two-phase lumped-vapor computational fluid dynamics model has been developed to account for the presence of a noncondensable gas in the ullage. The CFD model is used to simulate the initial pressure response of the propellant tanks while they are subjected to representative heat leak rates on the lunar surface. Once a near stationary state is achieved within the liquid phase, multizone model is used to extrapolate the solution farther in time. For fixed propellant mass and tank size, the long-term pressure response for different helium mass fractions in both the LO2 and LCH4 tanks is examined.
Author
CRYOGENICS; STORAGE TANKS; COMPUTATIONAL FLUID DYNAMICS; LUNAR SURFACE; PROPELLANT TANKS; LIQUEFIED GASES; LIQUID OXYGEN; METHANE
20090007818 NASA Johnson Space Center, Houston, TX, United States
The International Space Station Urine Monitoring System (UMS)
Feeback, Daniel L.; Cibuzar, Branelle R.; Milstead, Jeffery R.; Pietrzyk,, Robert A.; Clark, Mark S.F.; February 02, 2009; In English; Human Research Program Investigators Workshop, 2 - 4 Feb. 2009, Texas, United States; Original contains color illustrations
Report No.(s): JSC-17705; Copyright; Avail.: CASI: A01, Hardcopy
A device capable of making in-flight volume measurements of single void urine samples, the Urine Monitoring System (UMS), was developed and flown on seven U.S. Space Shuttle missions. This device provided volume data for each urine void from multiple crewmembers and allowed samples of each to be taken and returned to Earth for post-flight analysis. There were a number of design flaws in the original instrument including the presence of liquid carry-over producing invalid "actual" micturition volumes and cross-contamination between successive users from residual urine in "dead" spots". Additionally, high or low volume voids could not be accurately measured, the on-orbit calibration and nominal use sequence was time intensive, and the unit had to be returned and disassembled to retrieve the volume data. These problems have been resolved in a new version, the International Space Station (ISS) UMS, that has been designed to provide real-time in-flight volume data with accuracy and precision equivalent to measurements made on Earth and the ability to provide urine samples that are unadulterated by the device. Originally conceived to be interfaced with a U.S.-built Waste Collection System (WCS), the unit now has been modified to interface with the Russian-supplied Sanitary Hygiene Device (ASY). The ISS UMS provides significant advantages over the current method of collecting urine samples into Urine Collection Devices (UCDs), from which samples are removed and returned to Earth for analyses. A significant future advantage of the UMS is that it can provide an interface to analytical instrumentation that will allow real-time measurement of urine bioanalytes allowing monitoring of crewmember health status during flight and the ability to provide medical interventions based on the results of these measurements. Currently, the ISS UMS is scheduled to launch along with Node-3 on STS-130 (20A) in December 2009. UMS will be installed and scientific/functional verification completed prior to placing the instrument into operation. Samples collected during the verification sequence will be returned for analyses on STS-131 (19A) currently scheduled for launch in March 2010. The presence of a UMS on ISS will provide the capability to conduct additional collaborative human life science investigations among the ISS International Partners.
Author
INTERNATIONAL SPACE STATION; LIFE SCIENCES; URINE; REAL TIME OPERATION; POSTFLIGHT ANALYSIS; HEALTH; HYGIENE; COLLECTION; URINATION
20090007819 United Space Alliance, Houston, TX, United States
Rendezvous Integration Complexities of NASA Human Flight Vehicles
Brazzel, Jack P.; Goodman, John L.; January 30, 2009; In English; 2009 AAS GN&C Conference, 30 Jan - 04 Feb 2009, Virginia, United States; Original contains color and black and white illustrations
Contract(s)/Grant(s): NNJ06VA01C
Report No.(s): JSC-17709; AAS 09-065; Copyright; Avail.: CASI: A03, Hardcopy
Propellant-optimal trajectories, relative sensors and navigation, and docking/capture mechanisms are rendezvous disciplines that receive much attention in the technical literature. However, other areas must be considered. These include absolute navigation, maneuver targeting, attitude control, power generation, software development and verification, redundancy management, thermal control, avionics integration, robotics, communications, lighting, human factors, crew timeline, procedure development, orbital debris risk mitigation, structures, plume impingement, logistics, and in some cases extravehicular activity. While current and future spaceflight programs will introduce new technologies and operations concepts, the complexity of integrating multiple systems on multiple spacecraft will remain. The systems integration task may become more difficult as increasingly complex software is used to meet current and future automation, autonomy, and robotic operation requirements.
Author
SPACE RENDEZVOUS; RENDEZVOUS TRAJECTORIES; SPACECRAFT DOCKING; ATTITUDE CONTROL; SOFTWARE ENGINEERING; AUTONOMY; HUMAN FACTORS ENGINEERING
20090007820 NASA Johnson Space Center, Houston, TX, United States
Usability: Human Research Program - Space Human Factors and Habitability
Sandor, Aniko; Holden, Kritina L.; February 02, 2009; In English; Human Reseach Program Investigators Workshop, 2 - 4 Feb. 2009, Texas, United States; Original contains color and black and white illustrations
Report No.(s): JSC-17723; Copyright; Avail.: CASI: A01, Hardcopy
The Usability project addresses the need for research in the area of metrics and methodologies used in hardware and software usability testing in order to define quantifiable and verifiable usability requirements. A usability test is a human-in-the-loop evaluation where a participant works through a realistic set of representative tasks using the hardware/software under investigation. The purpose of this research is to define metrics and methodologies for measuring and verifying usability in the aerospace domain in accordance with FY09 focus on errors, consistency, and mobility/maneuverability. Usability metrics must be predictive of success with the interfaces, must be easy to obtain and/or calculate, and must meet the intent of current Human Systems Integration Requirements (HSIR). Methodologies must work within the constraints of the aerospace domain, be cost and time efficient, and be able to be applied without extensive specialized training.
Author
COMPUTER PROGRAMS; HUMAN FACTORS ENGINEERING; PROGRAM VERIFICATION (COMPUTERS); SYSTEMS INTEGRATION; ERRORS; MANEUVERABILITY; MOBILITY; CONSISTENCY; EDUCATION
20090007821 NASA Johnson Space Center, Houston, TX, United States
Lunar Analog
Cromwell, Ronita L.; February 02, 2009; In English; Human Research Program Investigators Workshop, 2 - 4 Feb. 2009, Texas, United States; Original contains color illustrations
Report No.(s): JSC-17735; Copyright; Avail.: CASI: A03, Hardcopy
In this viewgraph presentation, a ground-based lunar analog is developed for the return of manned space flight to the Moon. The contents include: 1) Digital Astronaut; 2) Bed Design; 3) Lunar Analog Feasibility Study; 4) Preliminary Data; 5) Pre-pilot Study; 6) Selection of Stockings; 7) Lunar Analog Pilot Study; 8) Bed Design for Lunar Analog Pilot.
CASI
MANNED SPACE FLIGHT; MOON; LUNAR EXPLORATION; ANALOGS
20090007822 NASA Johnson Space Center, Houston, TX, United States
Information Presentation
Holden, K.L.; Boyer, J.L.; Sandor, A.; Thompson, S.G.; McCann, R.S.; Begault, D.R.; Adelstein, B.D.; Beutter, B.R.; Stone, L.S.; February 02, 2009; In English; Human Research Program Investigators Workshop, 2 - 4 Feb. 2009, Texas, United States; Original contains color illustrations
Copyright; Avail.: CASI: A01, Hardcopy
The goal of the Information Presentation Directed Research Project (DRP) is to address design questions related to the presentation of information to the crew. The major areas of work, or subtasks, within this DRP are: 1) Displays, 2) Controls, 3) Electronic Procedures and Fault Management, and 4) Human Performance Modeling. This DRP is a collaborative effort between researchers at Johnson Space Center and Ames Research Center.
Author
DISPLAY DEVICES; HUMAN PERFORMANCE; PERFORMANCE PREDICTION
20090007823 Lockheed Martin Mission Services Co., Greenbelt, MD, United States
SDBI 1904: Human Factors Assessment of Vibration Effects on Visual Performance during Launch
Thompson, Shelby G.; Holden, Kritina; Root, Phillip; Ebert, Douglas; Jones, Jeffery; Adelstein, Bernard; February 02, 2009; In English; Human Research Program Investigators Workshop, 2 - 4 Feb. 2009, Texas, United States; Original contains color and black and white illustrations
Report No.(s): JSC-17737; Copyright; Avail.: CASI: A01, Hardcopy
The primary objective of the of Human Factors Short Duration Bioastronautics Investigation (SDBI) 1904 is to determine visual performance limits during operational vibration and g-loads, specifically through the determination of minimal usable font sized using Orion-type display formats. Currently there is little to no data available to quantify human visual performance under these extreme conditions. Existing data on shuttle vibration magnitude and frequency is incomplete, does not address sear and crew vibration in the current configuration, and does not address human visual performance. There have been anecdotal reports of performance decrements from shuttle crews, but no structured data has been collected. The SDBI is a companion effort to the Detailed Test Objective (DTO) 695, which will measure shuttle seat accelerations (vibration) during ascent. Data fro the SDBI will serve an important role in interpreting the DTO vibration data. This data will be collected during the ascent phase of three shuttle missions (STS-119, 127, and 128). Both SDBI1904 and DTO 695 are low impact with respect to flight resources, and combined they represent an efficient and focused problem solving approach. The SDBI and DTO data will be correlated to determine the nature of perceived visual performance under varying vibrations and g-loads. This project will provide: 1) Immediate data for developing preliminary human performance vibration requirements; 2) Flight validated inputs for ongoing and future ground-based research; and 3) Information of functional needs that will drive Orion display format design decisions.
Author (revised)
HUMAN FACTORS ENGINEERING; VIBRATION EFFECTS; BIOASTRONAUTICS; SPACE SHUTTLE MISSIONS; SPACE TRANSPORTATION SYSTEM; SPACECRAFT LAUNCHING; VISUAL STIMULI
20090007824 NASA Johnson Space Center, Houston, TX, United States
Neuromuscular Adaptations to Reduced Use
Ploutz-Snyder, Lori; January 29, 2009; In English; Lecture to faculty in Kinesiology at Texas A and M, 29 Jan 2009, Texas, United States; Original contains color and black and white illustrations
Report No.(s): JSC-17748; No Copyright; Avail.: CASI: A03, Hardcopy
Avail Online: http://hdl.handle.net/2060/20090007824
This viewgraph presentation reviews the studies done to reduce neuromuscular strength loss during unilateral lower limb suspension (ULLS). Since there are animals that undergo fairly long periods of muscular disuse without any or minimal muscular atrophy, there is an answer to that might be applicable to human in situations that require no muscular use to diminish the effects of muscular atrophy. Three sets of ULLS studies were reviewed indicated that muscle strength decreased more than the muscle mass. The study reviewed exercise countermeasures to combat the atrophy, including: ischemia maintained during Compound muscle action potential (CMAP), ischemia and low load exercise, Japanese kaatsu, and the potential for rehabilitation or situations where heavy loading is undesirable. Two forms of countermeasures to unloading have been successful, (1) high-load resistance training has maintained muscle mass and strength, and low load resistance training with blood flow restriction (LL(sub BFR)). The LL(sub BFR) has been shown to increase muscle mass and strength. There has been significant interest in Tourniquet training. An increase in Growth Hormone(GH) has been noted for LL(sub BFR) exercise. An experimental study with 16 subjects 8 of whom performed ULLS, and 8 of whom performed ULLS and LL(sub BFR) exercise three times per week during the ULLS. Charts show the results of the two groups, showing that performing LL(sub BFR) exercise during 30 days of ULLS can maintain muscle size and strength and even improve muscular endurance.
CASI
ATROPHY; BLOOD FLOW; COUNTERMEASURES; PHYSICAL EXERCISE; TOURNIQUETS; EXERCISE PHYSIOLOGY; MUSCULAR FUNCTION; HYPOKINESIA
20090007825 Texas Univ., Houston, TX, United States
The GuideView System for Interactive, Structured, Multi-modal Delivery of Clinical Guidelines
Iyengar, Sriram; Florez-Arango, Jose; Garcia, Carlos Andres; February 02, 2009; In English; HRP Investigators' Workshop, 2-4 Feb. 2009, Houston, TX, United States; Original contains color illustrations
Report No.(s): JSC-17752; Copyright; Avail.: CASI: A01, Hardcopy
GuideView is a computerized clinical guideline system which delivers clinical guidelines in an easy-to-understand and easy-to-use package. It may potentially enhance the quality of medical care or allow non-medical personnel to provide acceptable levels of care in situations where physicians or nurses may not be available. Such a system can be very valuable during space flight missions when a physician is not readily available, or perhaps the designated medical personnel is unable to provide care. Complex clinical guidelines are broken into simple steps. At each step clinical information is presented in multiple modes, including voice,audio, text, pictures, and video. Users can respond via mouse clicks or via voice navigation. GuideView can also interact with medical sensors using wireless or wired connections. The system's interface is illustrated and the results of a usability study are presented.
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CLINICAL MEDICINE; COMPUTER SYSTEMS PROGRAMS
20090007827 NASA Johnson Space Center, Houston, TX, United States
Assessment and Optimization of Medical Risks using the Integrated Medical Model
Baumann, D.K.; Fogarty, J.; Kerstman, E.; Butler, D.J.; Walton, M.E.; Minard, C.G.; Saile, L.G.; Myers, J.; February 02, 2009; In English; Human Research Program Investigator's Workshop, 2 - 4 Feb. 2009, Texas, United States; Original contains color illustrations
Report No.(s): JSC-17762; Copyright; Avail.: CASI: A01, Hardcopy
ObjectiveDevelop an evidence-based, probabilistic risk forecasting model that can help guide mission planning, requirements development, and align science with engineering technology development.
Author
PRODUCT DEVELOPMENT; FORECASTING; RISK ASSESSMENT; CLINICAL MEDICINE; MISSION PLANNING
20090007828 Wyle Integrated Science and Engineering Group, Houston, TX, United States
Metabolic and Subjective Results Review of the Integrated Suit Test Series
Norcross, J.R.; Stroud, L.C.; Klein, J.; Desantis, L.; Gernhardt, M.L.; February 02, 2009; In English; Human Research Program Investigators Workshop, 2 - 4 Feb. 2009, Texas, United States; Original contains color illustrations
Report No.(s): JSC-17770; Copyright; Avail.: CASI: A02, Hardcopy
Crewmembers will perform a variety of exploration and construction activities on the lunar surface. These activities will be performed while inside an extravehicular activity (EVA) spacesuit. In most cases, human performance is compromised while inside an EVA suit as compared to a crewmember s unsuited performance baseline. Subjects completed different EVA type tasks, ranging from ambulation to geology and construction activities, in different lunar analog environments including overhead suspension, underwater and 1-g lunar-like terrain, in both suited and unsuited conditions. In the suited condition, the Mark III (MKIII) EVA technology demonstrator suit was used and suit pressure and suit weight were parameters tested. In the unsuited conditions, weight, mass, center of gravity (CG), terrain type and navigation were the parameters. To the extent possible, one parameter was varied while all others were held constant. Tests were not fully crossed, but rather one parameter was varied while all others were left in the most nominal setting. Oxygen consumption (VO2), modified Cooper-Harper (CH) ratings of operator compensation and ratings of perceived exertion (RPE) were measured for each trial. For each variable, a lower value correlates to more efficient task performance. Due to a low sample size, statistical significance was not attainable. Initial findings indicate that suit weight, CG and the operational environment can have a large impact on human performance during EVA. Systematic, prospective testing series such as those performed to date will enable a better understanding of the crucial interactions of the human and the EVA suit system and their environment. However, work remains to be done to confirm these findings. These data have been collected using only unsuited subjects and one EVA suit prototype that is known to fit poorly on a large demographic of the astronaut population. Key findings need to be retested using an EVA suit prototype better suited to a larger anthropometric portion of the astronaut population, and elements tested only in the unsuited condition need to be evaluated with an EVA suit and appropriate analog environment.
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EXTRAVEHICULAR ACTIVITY; HUMAN PERFORMANCE; LUNAR ENVIRONMENT; METABOLISM; PHYSICAL WORK; SPACE SUITS
20090007829 NASA Johnson Space Center, Houston, TX, United States
Human Research Program Requirements Document (Revision C)
Vargas, Paul R.; January 2009; In English
Report No.(s): JSC-17772; HRP-47052, Rev. C; Copyright; Avail.: CASI: A03, Hardcopy
The purpose of this document is to define, document, and allocate the Human Research Program (HRP) requirements to the HRP Program Elements. It establishes the flow-down of requirements from Exploration Systems Mission Directorate (ESMD) and Office of the Chief Health and Medical Officer (OCHMO) to the various Program Elements of the HRP to ensure that human research and technology countermeasure investments are made to insure the delivery of countermeasures and technologies that satisfy ESMD's and OCHMO's exploration mission requirements. Requirements driving the HRP work and deliverables are derived from the exploration architecture, as well as Agency standards regarding the maintenance of human health and performance. Agency human health and performance standards will define acceptable risk for each type and duration of exploration mission. It is critical to have the best available scientific and clinical evidence in setting and validating these standards. In addition, it is imperative that the best available evidence on preventing and mitigating human health and performance risks is incorporated into exploration mission and vehicle designs. These elements form the basis of the HRP research and technology development requirements and highlight the importance of HRP investments in enabling NASA's exploration missions. This PRD defines the requirements of the HRP which is comprised of the following major Program Elements: Behavioral Health and Performance (BHP), Exploration Medical Capability (ExMC), Human Health Countermeasures (HHC), ISS Medical Project (ISSMP), Space Human Factors and Habitability (SHFH), and Space Radiation (SR).
Derived from text
NASA PROGRAMS; RESEARCH AND DEVELOPMENT; HEALTH; AEROSPACE ENVIRONMENTS; BIOASTRONAUTICS; AEROSPACE MEDICINE; MEDICAL SCIENCE; MEDICAL SERVICES
20090007830 NASA Dryden Flight Research Center, Edwards, CA, United States
Design and Calibration of a Flowfield Survey Rake for Inlet Flight Research
Flynn, Darin C.; Ratnayake, Nalin A.; Frederick, Michael; January 08, 2009; In English; 47th AIAA Aerospace Sciences Meeting, 5 - 8 Jan. 2009, Florida, United States; Original contains color and black and white illustrations
Report No.(s): DFRC-941; No Copyright; Avail.: CASI: A03, Hardcopy
Avail Online: http://hdl.handle.net/2060/20090007830
Flowfield rake was designed to quantify the flowfield for inlet research underneath NASA DFRC s F-15B airplane. Detailed loads and stress analysis performed using CFD and empirical methods to assure structural integrity. Calibration data were generated through wind tunnel testing of the rake. Calibration algorithm was developed to determine the local Mach and flow angularity at each probe. RAGE was flown November, 2008. Data is currently being analyzed.
Author
FLOW DISTRIBUTION; STRESS ANALYSIS; LOADS (FORCES); WIND TUNNEL TESTS; STRUCTURAL FAILURE; CALIBRATING; COMPUTATIONAL FLUID DYNAMICS
20090007833 NASA Johnson Space Center, Houston, TX, United States
Surface Habitat Systems
Kennedy, Kriss J.; February 2009; In English; Original contains color and black and white illustrations
Report No.(s): JSC-17681; No Copyright; Avail.: CASI: A03, Hardcopy
Avail Online: http://hdl.handle.net/2060/20090007833
The Surface Habitat Systems (SHS) Focused Investment Group (FIG) is part of the National Aeronautics and Space Administration (NASA) Johnson Space Center (JSC) effort to provide a focused direction and funding to the various projects that are working on human surface habitat designs and technologies for the planetary exploration missions. The overall SHS-FIG effort focuses on directing and guiding those projects that: 1) develop and demonstrate new surface habitat system concepts, innovations, and technologies to support human exploration missions, 2) improve environmental systems that interact with human habitats, 3) handle and emplace human surface habitats, and 4) focus on supporting humans living and working in habitats on planetary surfaces. The activity areas of the SHS FIG described herein are focused on the surface habitat project near-term objectives as described in this document. The SHS-FIG effort focuses on mitigating surface habitat risks (as identified by the Lunar Surface Systems Project Office (LSSPO) Surface Habitat Element Team; and concentrates on developing surface habitat technologies as identified in the FY08 gap analysis. The surface habitat gap assessment will be updated annually as the surface architecture and surface habitat definition continues to mature. These technologies are mapped to the SHS-FIG Strategic Development Roadmap. The Roadmap will bring to light the areas where additional innovative efforts are needed to support the development of habitat concepts and designs and the development of new technologies to support of the LSSPO Habitation Element development plan. Three specific areas of development that address Lunar Architecture Team (LAT)-2 and Constellation Architecture Team (CxAT) Lunar habitat design issues or risks will be focused on by the SHS-FIG. The SHS-FIG will establish four areas of development that will help the projects prepare in their planning for surface habitat systems development. Those development areas are the 1) surface habitat concept definition, 2) inflatable surface habitat development, and 3) autonomous habitat operations, and 4) cross-cutting / systems engineering. In subsequent years, the SHS-FIG will solicit a call for innovations and technologies that will support the development of these four development areas. The other development areas will be assessed yearly and identified on the SHS-FIG s Strategic Development Roadmap. Initial investment projects that are funded by the Constellation Program Office (CxPO), LSSPO, or the Exploration Technology Development Projects (ETDP) will also be included on the Roadmap. For example, in one or two years from now, the autonomous habitat operations and testbed would collaborations with the Integrated Systems Health Management (ISHM) and Automation for Operations ETDP projects, which will give the surface habitat projects an integrated habitat autonomy testbed to test software and systems. The SHS-FIG scope is to provide focused direction for multiple innovations, technologies and subsystems that are needed to support humans at a remote planetary surface habitat during the concept development, design definition, and integration phases of that project. Subsystems include: habitability, lightweight structures, power management, communications, autonomy, deployment, outfitting, life support, wireless connectivity, lighting, thermal and more.
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CONSTELLATION PROGRAM; LUNAR SURFACE; NASA PROGRAMS; LUNAR SHELTERS
20090007834 NASA Johnson Space Center, Houston, TX, United States
2008 Accomplishments for CEV Parachute Assembly System (CPAS)
Martin, Ricardo; February 2009; In English; Original contains color illustrations
Report No.(s): JSC-17689; No Copyright; Avail.: CASI: A01, Hardcopy
Avail Online: http://hdl.handle.net/2060/20090007834
The Crew Exploration Vehicle (CEV) Parachute Assembly System (CPAS) project is responsible for the design, development, fabrication, qualification and delivery of the CEV parachute system to support the Orion pad/ascent flight tests and the first three orbital flight tests (including the first human mission). This article will discuss the technical and research achievements accomplished in calendar year 2008, broken into three key categories: prototype testing and analysis (also referred to as the Generation 1 design), system requirements definition and design of the flight engineering development unit, and support for the Orion vehicle flight testing (primarily Pad-Abort 1).
Author
AERONAUTICAL ENGINEERING; FLIGHT TESTS; PARACHUTES; FABRICATION; ASCENT
Additions to the NASA Aeronautics and Space Database as of 03/10/2009
20090007922 NASA Johnson Space Center, Houston, TX, United States
Extravehicular Activity Testing in Analog Environments: Evaluating the Effects of Center of Gravity and Environment on Human Performance
Chappell, Steve P.; Gernhardt, Michael L.; February 02, 2009; In English; Human Research Program (HRP) Investigators' Workshop, 2-4 Feb. 2009, League City, TX, United States; Original contains color and black and white illustrations
Report No.(s): JSC-17775; Copyright; Avail.: CASI: A02, Hardcopy
Center of gravity (CG) is likely to be an important variable in astronaut performance during partial gravity extravehicular activity (EVA). The Apollo Lunar EVA experience revealed challenges with suit stability and control. The EVA Physiology, Systems and Performance Project (EPSP) in conjunction with the Constellation EVA Systems Project Office have developed plans to systematically understand the role of suit weight, CG and suit pressure on astronaut performance in partial gravity environments. This presentation based upon CG studies seeks to understand the impact of varied CG on human performance in lunar gravity.
Derived from text
CENTER OF GRAVITY; ASTRONAUT PERFORMANCE; EXTRAVEHICULAR ACTIVITY; LUNAR ENVIRONMENT; MICROGRAVITY; GRAVITATIONAL EFFECTS
20090007925 NASA Marshall Space Flight Center, Huntsville, AL, United States
Powering Exploration: The Ares I Crew Launch Vehicle and Ares V Cargo Launch Vehicle
Cook, Stephen A.; July 20, 2008; In English; AIAA Joint Propulsion Conference, 20 - 23 Jul. 2008, Connecticut, United States; Original contains color illustrations
No Copyright; Avail.: CASI: A03, Hardcopy
Avail Online: http://hdl.handle.net/2060/20090007925
The National Aeronautics and Space Administration (NASA)'s Constellation Program is depending on the Ares Projects to deliver the crew and cargo launch capabilities needed to send human explorers to the Moon and beyond. The Ares Projects continue to make progress toward design, component testing, and early flight testing of the Ares I crew launch vehicle, as well as early design work for Ares V cargo launch vehicle. Ares I and Ares V will form the core space launch capabilities the United States needs to continue its pioneering tradition as a spacefaring nation. This paper will discuss programmatic, design, fabrication, and testing progress toward building these new launch vehicles.
Author
ARES 1 LAUNCH VEHICLE; ARES 5 CARGO LAUNCH VEHICLE; SPACECRAFT DESIGN; FABRICATION; PERFORMANCE TESTS; ASTRIONICS; DESIGN ANALYSIS; CONSTELLATION PROGRAM; WIND TUNNEL TESTS; FLIGHT TESTS
Additions to the NASA Aeronautics and Space Database as of 03/11/2009
20090007950 NASA Glenn Research Center, Cleveland, OH, United States
CFD Simulation on the J-2X Engine Exhaust in the Center-Body Diffuser and Spray Chamber at the B-2 Facility
Wang, Xiao-Yen; Wey, Thomas; Buehrle, Robert; January 2009; In English; Original contains color and black and white illustrations
Report No.(s): NASA/TM-2009-215464; TFAWS08-1013; E-16610; No Copyright; Avail.: CASI: A03, Hardcopy
Avail Online: http://hdl.handle.net/2060/20090007950
A computational fluid dynamic (CFD) code is used to simulate the J-2X engine exhaust in the center-body diffuser and spray chamber at the Spacecraft Propulsion Facility (B-2). The CFD code is named as the space-time conservation element and solution element (CESE) Euler solver and is very robust at shock capturing. The CESE results are compared with independent analysis results obtained by using the National Combustion Code (NCC) and show excellent agreement.
Author
COMPUTATIONAL FLUID DYNAMICS; SIMULATION; SPACECRAFT PROPULSION
20090007951 NASA Glenn Research Center, Cleveland, OH, United States
Channel Temperature Determination for AlGaN/GaN HEMTs on SiC and Sapphire
Freeman, Jon C.; Mueller, Wolfgang; December 2008; In English; Original contains color and black and white illustrations
Report No.(s): NASA/TM-2008-215444; E-15699-1; Copyright; Avail.: CASI: A06, Hardcopy
Numerical simulation results (with emphasis on channel temperature) for a single gate AlGaN/GaN High Electron Mobility Transistor (HEMT) with either a sapphire or SiC substrate are presented. The static I-V characteristics, with concomitant channel temperatures (T(sub ch)) are calculated using the software package ATLAS, from Silvaco, Inc. An in-depth study of analytical (and previous numerical) methods for the determination of T(sub ch) in both single and multiple gate devices is also included. We develop a method for calculating T(sub ch) for the single gate device with the temperature dependence of the thermal conductivity of all material layers included. We also present a new method for determining the temperature on each gate in a multi-gate array. These models are compared with experimental results, and show good agreement. We demonstrate that one may obtain the channel temperature within an accuracy of +/-10 C in some cases. Comparisons between different approaches are given to show the limits, sensitivities, and needed approximations, for reasonable agreement with measurements.
Author
HIGH ELECTRON MOBILITY TRANSISTORS; STATIC CHARACTERISTICS; TEMPERATURE DEPENDENCE; THERMAL CONDUCTIVITY; NUMERICAL ANALYSIS
20090007953 NASA Glenn Research Center, Cleveland, OH, United States
Novel Carbon Dioxide Microsensor Based on Tin Oxide Nanomaterial Doped With Copper Oxide
Xu, Jennifer C.; Hunter, Gary W.; Lukco, Dorothy; Liu, Chung-Chiun; Ward, Benjamin J.; December 2008; In English; Original contains color illustrations
Report No.(s): NASA/TM-2008-215436; E-16606; Copyright; Avail.: CASI: A02, Hardcopy
Carbon dioxide (CO2) is one of the major indicators of fire and therefore its measurement is very important for low-false-alarm fire detection and emissions monitoring. However, only a limited number of CO2 sensing materials exist due to the high chemical stability of CO2. In this work, a novel CO2 microsensor based on nanocrystalline tin oxide (SnO2) doped with copper oxide (CuO) has been successfully demonstrated. The CuO-SnO2 based CO2 microsensors are fabricated by means of microelectromechanical systems (MEMS) technology and sol-gel nanomaterial-synthesis processes. At a doping level of CuO: SnO2 = 1:8 (molar ratio), the resistance of the sensor has a linear response to CO2 concentrations for the range of 1 to 4 percent CO2 in air at 450 C. This approach has demonstrated the use of SnO2, typically used for the detection of reducing gases, in the detection of an oxidizing gas.
Author
CARBON DIOXIDE; MICROELECTROMECHANICAL SYSTEMS; TIN OXIDES; FALSE ALARMS; CARBON DIOXIDE CONCENTRATION; COPPER OXIDES; MICROINSTRUMENTATION; DETECTION
20090007954 NASA Glenn Research Center, Cleveland, OH, United States
Astable Oscillator Circuits using Silicon-on-Insulator Timer Chip for Wide Range Temperature Sensing
Patterson, Richard L.; Culley, Dennis; Hammoud, Ahmad; Elbuluk, Malik; November 2008; In English; Original contains color and black and white illustrations
Contract(s)/Grant(s): NNC06BA07B
Report No.(s): NASA/TM-2008-215417; E-16581; Copyright; Avail.: CASI: A03, Hardcopy
Two astable oscillator circuits were constructed using a new silicon-on-insulator (SOI) 555 timer chip for potential use as a temperature sensor in harsh environments encompassing jet engine and space mission applications. The two circuits, which differed slightly in configuration, were evaluated between -190 and 200 C. The output of each circuit was made to produce a stream of rectangular pulses whose frequency was proportional to the sensed temperature. The preliminary results indicated that both circuits performed relatively well over the entire test temperature range. In addition, after the circuits were subjected to limited thermal cycling over the temperature range of -190 to 200 C, the performance of either circuit did not experience any significant change.
Author
SOI (SEMICONDUCTORS); TEMPERATURE MEASUREMENT; THERMAL CYCLING TESTS; CIRCUITS; OSCILLATORS
20090007955 NASA Glenn Research Center, Cleveland, OH, United States
Application of Synthetic Jets to Reduce Stator Flow Separation in a Low Speed Axial Compressor
Braunscheidel, Edward P.; Culley, Dennis E.; Zaman, Khairul B.M.Q.; December 2008; In English; Original contains color and black and white illustrations
Report No.(s): NASA/TM-2008-215145; AIAA Paper-2008-0602; E-16308; No Copyright; Avail.: CASI: A03, Hardcopy
Avail Online: http://hdl.handle.net/2060/20090007955
Flow control using synthetic jet injection has been applied in a low speed axial compressor. The synthetic jets were applied from the suction surface of a stator vane via a span-wise row of slots pitched in the streamwise direction. Actuation was provided externally from acoustic drivers coupled to the vane tip via flexible tubing. The acoustic resonance characteristics of the system, and the resultant jet velocities were obtained. The effects on the separated flow field for various jet velocities and frequencies were explored. Total pressure loss reductions across the vane passage were measured. The effect of synthetic jet injection was shown to be comparable to that of pulsatory injection with mass addition for stator vanes which had separated flow. While only a weak dependence of the beneficial effect was noted based on the excitation frequency, a strong dependence on the amplitude was observed at all frequencies.
Author
FLOW DISTRIBUTION; INJECTION; STATORS; TURBOCOMPRESSORS; SEPARATED FLOW; BOUNDARY LAYER SEPARATION; ACOUSTIC RESONANCE
20090007956 NASA Glenn Research Center, Cleveland, OH, United States
Advanced Stirling Convertor (ASC)--From Technology Development to Future Flight Product
Wong, Wayne A.; Wood, J. Gary; Wilson, Kyle; December 2008; In English; Original contains color and black and white illustrations
Report No.(s): NASA/TM-2008-215282; E-16548; Copyright; Avail.: CASI: A03, Hardcopy
The Advanced Stirling Convertor (ASC) is being developed by Sunpower Inc. under contract to NASA s Glenn Research Center (GRC) with critical technology support tasks led by GRC. The ASC development, funded by NASA s Science Mission Directorate, started in 2003 as one of 10 competitively awarded contracts that were intended to address the power conversion needs of future Radioisotope Power Systems (RPS). The ASC technology has since evolved through progressive convertor builds and successful testing to demonstrate high conversion efficiency (38 percent), low mass (1.3 kg), hermetic sealing, launch vibration simulation, EMI characterization, and is undergoing extended operation. The GRC and Sunpower team recently delivered two ASC-E convertors to the Department of Energy (DOE) and Lockheed Martin Space Systems Company for integration onto the Advanced Stirling Radioisotope Generator Engineering Unit (ASRG EU) plus one spare. The design of the next build, called the ASC-E2, has recently been initiated and is based on the heritage ASC-E with design refinements to increase reliability margin and offer higher temperature operation and improve performance. The ASC enables RPS system specific power of about 7 to 8 W/kg. This paper provides a chronology of ASC development to date and summarizes technical achievements including advancements toward flight implementation of the technology on ASRG by as early as 2013.
Author
STIRLING CYCLE; ENERGY CONVERSION EFFICIENCY; SYSTEMS INTEGRATION; VIBRATION; HERMETIC SEALS; AEROSPACE SYSTEMS
20090007957 NASA Glenn Research Center, Cleveland, OH, United States
NEXT Long-Duration Test After 11,570 h and 237 kg of Xenon Processed
Soulas, George C.; Patterson, Michael J.; Herman, Daniel A.; January 2009; In English; Original contains color and black and white illustrations
Contract(s)/Grant(s): GESS-2
Report No.(s): NASA/TM-2009-215265; IEPC-2007-033; E-16534; Copyright; Avail.: CASI: A03, Hardcopy
The NASA s Evolutionary Xenon Thruster (NEXT) program is developing the next-generation ion propulsion system with significant enhancements beyond the state-of-the-art in ion propulsion to provide future NASA science missions with enhanced mission capabilities at a low total development cost. As part of a comprehensive thruster service life assessment utilizing both testing and analyses, a Long-Duration Test (LDT) was initiated to validate and qualify the NEXT propellant throughput capability to a qualification-level of 450 kg, 1.5 times the mission-derived throughput requirement of 300 kg. This wear test is being conducted with a modified, flight-representative NEXT engineering model ion thruster, designated EM3. As of September 1, 2007, the thruster has accumulated 11,570 h of operation primarily at the thruster full-input-power of 6.9 kW with 3.52 A beam current and 1800 V beam power supply voltage. The thruster has processed 237 kg of xenon surpassing the NSTAR propellant throughput demonstrated during the extended life testing of the Deep Space 1 (DS1) flight spare. The NEXT LDT has demonstrated a total impulse of 9.78 10(exp 6) N(dot)s; the highest total impulse ever demonstrated by an ion thruster. Thruster performance tests are conducted periodically over the entire NEXT throttle table with input power ranging 0.5 to 6.9 kW. Thruster performance parameters including thrust, input power, specific impulse, and thruster efficiency have been nominal with little variation to date. Lifetime-limiting component erosion rates have been consistent with the NEXT service life assessment, which predicts the earliest failure sometime after 750 kg of xenon propellant throughput; well beyond the mission-derived lifetime requirement. The NEXT wear test data confirm that the erosion of the discharge keeper orifice, enlarging of nominal-current-density accelerator grid aperture cusps at full-power, and the decrease in cold grid-gap observed during NSTAR wear testing have been mitigated in the NEXT design. NEXT grid-gap data indicate a hot grid-gap at full-power that is 60 percent of the nominal cold grid-gap. This paper presents the status of the NEXT LDT to date with emphasis on comparison to the NSTAR extended life test results.
Author
ION ENGINES; ION PROPULSION; ELECTRIC POTENTIAL; XENON; ROCKET ENGINES; AERONAUTICAL ENGINEERING
20090007959 NASA Glenn Research Center, Cleveland, OH, United States
Vibroacoustic Response of the NASA ACTS Spacecraft Antenna to Launch Acoustic Excitation
Larko, Jeffrey M.; Cotoni, Vincent; December 2008; In English; Original contains color and black and white illustrations
Report No.(s): NASA/TM-2008-215168; E-16407; Copyright; Avail.: CASI: A03, Hardcopy
The Advanced Communications Technology Satellite was an experimental NASA satellite launched from the Space Shuttle Discovery. As part of the ground test program, the satellite s large, parabolic reflector antennas were exposed to a reverberant acoustic loading to simulate the launch acoustics in the Shuttle payload bay. This paper describes the modelling and analysis of the dynamic response of these large, composite spacecraft antenna structure subjected to a diffuse acoustic field excitation. Due to the broad frequency range of the excitation, different models were created to make predictions in the various frequency regimes of interest: a statistical energy analysis (SEA) model to capture the high frequency response and a hybrid finite element-statistical energy (hybrid FE-SEA) model for the low to mid-frequency responses. The strengths and limitations of each of the analytical techniques are discussed. The predictions are then compared to the measured acoustic test data and to a boundary element (BEM) model to evaluate the performance of the hybrid techniques.
Author
ACOUSTIC PROPERTIES; VIBRATIONAL STRESS; SPACE SHUTTLE PAYLOADS; PARABOLIC REFLECTORS; GROUND TESTS; SPACECRAFT ANTENNAS; LOADS (FORCES); DYNAMIC RESPONSE
20090007960 NASA Johnson Space Center, Houston, TX, United States
NASA Space Flight Human System Standard, Volume 2, and HIDH (Human Integration Design Handbook)
Connolly, Janis; Fitts, David; Stroud, Kenneth; Boyer, Jennifer; Holubec, Keith; Tillman, Barry; February 04, 2009; In English; Human Research Program Investigators' Workshop, 2-4 Feb. 2009, League City, TX, United States; Original contains color illustrations
Report No.(s): JSC-17767; Copyright; Avail.: CASI: A01, Hardcopy
This viewgraph presentation reports on the review and re-issuance of the NASA Space Flight Human System Standard, Volume 2, and the Human Integration Design Handbook. These standards were last updated in 1995. The target date for the release is September 2009.
CASI
HANDBOOKS; STANDARDS; HUMAN FACTORS ENGINEERING; AEROSPACE MEDICINE
20090007962 NASA Glenn Research Center, Cleveland, OH, United States
Continued Development of the Advanced Stirling Convertor (ASC)
Wong, Wayne A.; Wood, J. Gary; Wilson, Kyle; Buffalino, Andrew; Frye, Patrick; Matejczyk, Dan; Penswick, L.B.; December 2008; In English; Original contains color and black and white illustrations
Contract(s)/Grant(s): NAS3-03128
Report No.(s): NASA/TM-2008-215021; E-16192; Copyright; Avail.: CASI: A03, Hardcopy
The Advanced Stirling Convertor (ASC) is being developed under contract with the NASA Glenn Research Center (GRC) and is supported by NASA s Science Mission Directorate for potential use in future radioisotope power systems having significantly increased efficiency and higher specific power compared to the current thermoelectric systems. An ASC with a lower temperature (approx.650 C) Inconel heater head is currently being substituted into the DOE/Lockheed Martin Advanced Stirling Radioisotope Generator (ASRG) program with a predicted convertor efficiency of 34 percent (AC electrical out to heat input ) at a temperature ratio of 2.7 and is expected to deliver approximately 75 W(sub ac). Continued development of the higher temperature (approx.850 C) version using existing materials and fabrication techniques in the hot portions is reported on here. The higher temperature ASC is expected to have 38 percent efficiency (AC electrical out to heat input) at a temperature ratio of 3.1 and is expected to deliver approximately 88 W(sub ac). The high temperature ASC also has approximately 30 C higher rejection temperature, which allows for further reduced system mass because of the reduced radiator size. Six higher temperature and hermetically sealed convertors are being built under this effort for extended life testing at GRC.
Author
STIRLING CYCLE; TEMPERATURE RATIO; ALTERNATING CURRENT; INCONEL (TRADEMARK); THERMOELECTRICITY
20090007963 Institute for Scientific Research, Fairmont, WV, United States
Pulsed Plasma Accelerator Modeling
Goodman, M.; Kazeminezhad, F.; Owens, T.; January 2009; In English; Original contains color and black and white illustrations
Contract(s)/Grant(s): NNM04AA67G
Report No.(s): NASA/CR-2009-215635; M-1249; Copyright; Avail.: CASI: A04, Hardcopy
This report presents the main results of the modeling task of the PPA project. The objective of this task is to make major progress towards developing a new computational tool with new capabilities for simulating cylindrically symmetric 2.5 dimensional (2.5 D) PPA's. This tool may be used for designing, optimizing, and understanding the operation of PPA s and other pulsed power devices. The foundation for this task is the 2-D, cylindrically symmetric, magnetohydrodynamic (MHD) code PCAPPS (Princeton Code for Advanced Plasma Propulsion Simulation). PCAPPS was originally developed by Sankaran (2001, 2005) to model Lithium Lorentz Force Accelerators (LLFA's), which are electrode based devices, and are typically operated in continuous magnetic field to the model, and implementing a first principles, self-consistent algorithm to couple the plasma and power circuit that drives the plasma dynamics.
Author
ELECTRIC PROPULSION; PLASMA ACCELERATORS; MAGNETOHYDRODYNAMICS; LORENTZ FORCE; PLASMA PROPULSION; LITHIUM; PLASMA DYNAMICS
20090007964 Jet Propulsion Lab., California Inst. of Tech., Pasadena, CA, United States
FPGA NEPP FY08 Summary Report
Sheldon, Douglas; January 23, 2009; In English; Original contains color and black and white illustrations
Contract(s)/Grant(s): NAS7-03001102197.03.02.01; JPL Proj. 102197
Report No.(s): JPL Publication 09-1; Copyright; Avail.: CASI: A03, Hardcopy
This report documents the activities and results of the Fiscal Year 2008 (FY08) funding for the NASA Electronic Parts and Packaging (NEPP) program for Re-programmable Field Programmable Gate Arrays (FPGA). The FY08 task was divided into two sections. The first was focused on establishing a plan to develop long-term life-test reliability circuit designs with Xilinx, the manufacturer of the FPGAs of interest. Long-term life tests are the basic tool of technology analysis. Results from life tests are used to identify failure mechanisms and provide quantitative estimates of device performance over the various required mission lifetimes. The second section was to develop parametric test capability for state of the art FPGAs. This test capability was developed with Integra Corporation. Parametric testing is the first line of electrical testing of FPGAs. Results from parametric testing are used to determine whether or not the device meets the manufacturers data sheet specifications. Parametric testing is also used to determine quality and variability of devices obtained by a customer
Author
ELECTRONIC PACKAGING; FIELD-PROGRAMMABLE GATE ARRAYS; CIRCUITS; ESTIMATES; FAILURE
20090008382 NASA Glenn Research Center, Cleveland, OH, United States
NASA / Pratt and Whitney Collaborative Partnership Research in Ultra High Bypass Cycle Propulsion Concepts
Hughes, Chris; Lord, Wed; October 07, 2008; In English; Fundamental Aeronautics Program - 2nd Annual Meeting, 7 - 9 Oct. 2008, Georgia, United States; Original contains color illustrations
Report No.(s): E-16905; Copyright; Avail.: CASI: A03, Hardcopy
Current collaborative research with Pratt & Whitney on Ultra High Bypass Engine Cycle noise, performance and emissions improvements as part of the Subsonic Fixed Wing Project Ultra High Bypass Engine Partnership Element is discussed. The Subsonic Fixed Wing Project goals are reviewed, as well as their relative technology level compared to previous NASA noise program goals. Progress toward achieving the Subsonic Fixed Wing Project goals over the 2008 fiscal year by the UHB Partnership in this area of research are reviewed. The current research activity in Ultra High Bypass Engine Cycle technology, specifically the Pratt & Whitney Geared Turbofan, at NASA and Pratt & Whitney are discussed including the contributions each entity bring toward the research project, and technical plans and objectives. Pratt & Whitney Geared Turbofan current and future technology and business plans are also discussed, including the role the NASA SFW UHB partnership plays toward achieving those goals.
Author
BYPASSES; PROPULSION; TURBOFAN ENGINES; ENGINE NOISE
20090008398 NASA Glenn Research Center, Cleveland, OH, United States; Ohio Aerospace Inst., Cleveland, OH, United States
SiC/SiC Composites: The Effect of Fiber Type and Fiber Architecture on Mechanical Properties
Morscher, Gregory N.; November 12, 2008; In English; The 9th International Symposium on Ceramic Materials and Components for Energy and Environmental Applications, 10 - 14 Nov. 2008, Shanghai, China; Original contains color and black and white illustrations
Contract(s)/Grant(s): NNC07TA78T
Report No.(s): E-16908; Copyright; Avail.: CASI: A03, Hardcopy
Woven SiC/SiC composites represent a broad family of composites with a broad range of properties which are of interest for many energy-based and aero-based applications. Two important features of SiC/SiC composites which one must consider are the reinforcing fibers themselves and the fiber-architecture they are formed into. The range of choices for these two features can result in a wide range of elastic, mechanical, thermal, and electrical properties. In this presentation, it will be demonstrated how the effect of fiber-type and fiber architecture effects the important property of "matrix cracking stress" for slurry-cast melt-infiltrated SiC matrix composites, which is often considered to be a critical design parameter for this system of composites.
Author
WOVEN COMPOSITES; REINFORCING FIBERS; DESIGN ANALYSIS; MECHANICAL PROPERTIES
20090008400 Akron Univ., Akron, OH, United States
Electrical Resistance Technique to Monitor SiC Composite Detection
Smith, Craig; Morscher, Gregory; Xia, Zhenhai; October 07, 2008; In English; Fundamental Aeronautics Program Annual Meeting, 7 - 9 Oct. 2008, Georgia, United States; Original contains color and black and white illustrations
Contract(s)/Grant(s): NNC07TA78TNNX07AN56H
Report No.(s): E-16909; Copyright; Avail.: CASI: A03, Hardcopy
Ceramic matrix composites are suitable for high temperature structural applications such as turbine airfoils and hypersonic thermal protection systems. The employment of these materials in such applications is limited by the ability to process components reliable and to accurately monitor and predict damage evolution that leads to failure under stressed-oxidation conditions. Current nondestructive methods such as ultrasound, x-ray, and thermal imaging are limited in their ability to quantify small scale, transverse, in-plane, matrix cracks developed over long-time creep and fatigue conditions. Electrical resistance of SiC/SiC composites is one technique that shows special promise towards this end. Since both the matrix and the fibers are conductive, changes in matrix or fiber properties should relate to changes in electrical conductivity along the length of a specimen or part. The effect of matrix cracking on electrical resistivity for several composite systems will be presented and some initial measurements performed at elevated temperatures under stress-rupture conditions. The implications towards electrical resistance as a technique applied to composite processing, damage detection (health monitoring), and life-modeling will be discussed.
Author
ELECTRICAL RESISTANCE; CERAMIC MATRIX COMPOSITES; MATRIX MATERIALS; HIGH TEMPERATURE; CREEP PROPERTIES
20090008406 NASA, Washington, DC, United States
NASA Tech Briefs, January 2009
January 2009; In English; Original contains color and black and white illustrations
Copyright; Avail.: CASI: A03, Hardcopy
Tech Briefs are short announcements of innovations originating from research and development activities of the National Aeronautics and Space Administration. They emphasize information considered likely to be transferable across industrial, regional, or disciplinary lines and are issued to encourage commercial application. Topics covered include: The Radio Frequency Health Node Wireless Sensor System; Effects of Temperature on Polymer/Carbon Chemical Sensors; Small CO2 Sensors Operate at Lower Temperature; Tele-Supervised Adaptive Ocean Sensor Fleet; Synthesis of Submillimeter Radiation for Spectroscopy; 100-GHz Phase Switch/Mixer Containing a Slot-Line Transition; Generating Ka-Band Signals Using an X-Band Vector Modulator; SiC Optically Modulated Field-Effect Transistor; Submillimeter-Wave Amplifier Module with Integrated Waveguide Transitions; Metrology System for a Large, Somewhat Flexible Telescope; Economical Implementation of a Filter Engine in an FPGA; Improved Joining of Metal Components to Composite Structures; Machined Titanium Heat-Pipe Wick Structure; Gadolinia-Doped Ceria Cathodes for Electrolysis of CO2; Utilizing Ocean Thermal Energy in a Submarine Robot; Fuel-Cell Power Systems Incorporating Mg-Based H2 Generators; Alternative OTEC Scheme for a Submarine Robot; Sensitive, Rapid Detection of Bacterial Spores; Adenosine Monophosphate-Based Detection of Bacterial Spores; Silicon Microleaks for Inlets of Mass Spectrometers; CGH Figure Testing of Aspherical Mirrors in Cold Vacuums; Series-Coupled Pairs of Silica Microresonators; Precise Stabilization of the Optical Frequency of WGMRs; Formation Flying of Components of a Large Space Telescope; Laser Metrology Heterodyne Phase-Locked Loop; Spatial Modulation Improves Performance in CTIS; High-Performance Algorithm for Solving the Diagnosis Problem; Truncation Depth Rule-of-Thumb for Convolutional Codes; Efficient Method for Optimizing Placement of Sensors.
Author
COMPOSITE STRUCTURES; ELECTROLYSIS; FIELD-PROGRAMMABLE GATE ARRAYS; HUBBLE SPACE TELESCOPE; MASS SPECTROMETERS; WAVEGUIDES; TEMPERATURE EFFECTS; PHASE LOCKED SYSTEMS; RADIO FREQUENCIES
20090008407 California Inst. of Tech., Pasadena, CA, United States
Spatial Modulation Improves Performance in CTIS
Bearman, Gregory H.; Wilson, Daniel W.; Johnson, William R.; NASA Tech Briefs, January 2009; January 2009; pp. 29-3; In English
Report No.(s): NPO-41557; Copyright; Avail.: CASI: A01, Hardcopy
Avail Online: http://www.techbriefs.com/component/content/article/3511
Suitably formulated spatial modulation of a scene imaged by a computed-tomography imaging spectrometer (CTIS) has been found to be useful as a means of improving the imaging performance of the CTIS. As used here, "spatial modulation" signifies the imposition of additional, artificial structure on a scene from within the CTIS optics. The basic principles of a CTIS were described in "Improvements in Computed- Tomography Imaging Spectrometry" (NPO-20561) NASA Tech Briefs, Vol. 24, No. 12 (December 2000), page 38 and "All-Reflective Computed-Tomography Imaging Spectrometers" (NPO-20836), NASA Tech Briefs, Vol. 26, No. 11 (November 2002), page 7a. To recapitulate: A CTIS offers capabilities for imaging a scene with spatial, spectral, and temporal resolution. The spectral disperser in a CTIS is a two-dimensional diffraction grating. It is positioned between two relay lenses (or on one of two relay mirrors) in a video imaging system. If the disperser were removed, the system would produce ordinary images of the scene in its field of view. In the presence of the grating, the image on the focal plane of the system contains both spectral and spatial information because the multiple diffraction orders of the grating give rise to multiple, spectrally dispersed images of the scene. By use of algorithms adapted from computed tomography, the image on the focal plane can be processed into an image cube a three-dimensional collection of data on the image intensity as a function of the two spatial dimensions (x and y) in the scene and of wavelength (lambda). Thus, both spectrally and spatially resolved information on the scene at a given instant of time can be obtained, without scanning, from a single snapshot; this is what makes the CTIS such a potentially powerful tool for spatially, spectrally, and temporally resolved imaging. A CTIS performs poorly in imaging some types of scenes in particular, scenes that contain little spatial or spectral variation. The computed spectra of such scenes tend to approximate correct values to within acceptably small errors near the edges of the field of view but to be poor approximations away from the edges. The additional structure imposed on a scene according to the present method enables the CTIS algorithms to reconstruct acceptable approximations of the spectral data throughout the scene.
Author
SPATIAL RESOLUTION; MODULATION; SPATIAL DISTRIBUTION; TOMOGRAPHY; IMAGING TECHNIQUES; EMISSION SPECTRA; IMAGING SPECTROMETERS
20090008408 Jet Propulsion Lab., California Inst. of Tech., Pasadena, CA, United States
Generating Ka-Band Signals Using an X-Band Vector Modulator
Smith, Scott; Mysoor, Narayan; Lux, James; Cook, Brian; Shah, Biren; NASA Tech Briefs, January 2009; January 2009; pp. 1; In English; Original contains color illustrations
Report No.(s): NPO-42995; Copyright; Avail.: CASI: A01, Hardcopy
Avail Online: http://www.techbriefs.com/component/content/article/3489
A breadboard version of a transmitter for radio communication at a carrier frequency of 32 GHz (which is in the Ka band) utilizes a vector modulator operating at a carrier frequency of 8 GHz (the low end of the X band) to generate any of a number of advanced modulations that could include amplitude and/or phase modulation components. The 8-GHz modulated signal is mixed with a 24-GHz signal generated by an upconverter to obtain the desired 32-GHz modulated output. The transmitter is being developed as a prototype of downlink transmitters for transmission of data from spacecraft to Earth at high rates (>100 Mb/s). The transmitter design could also be adapted to terrestrial and Earth/satellite communication links. The advanced modulations (which can include M-ary phase-shift keying (M-PSK), offset phase-shift keying (OPSK), and M-ary quadrature amplitude modulation (M-QAM). These modulations are needed because for a given amount of signal bandwidth, they enable transmission of data at rates greater than those of older, simpler modulation schemes. The transmitter architecture (see figure) was chosen not only to enable generation of the required modulations at 32 GHz but also to reduce the number of components needed to implement the transmitter. Instead of incorporating an 8-GHz signal source, the transmitter utilizes an 8-GHz signal generated by a voltage-controlled oscillator that is part of an X-band transponder with which the fully developed version of this transmitter would be used in the original intended spacecraft application. The oscillator power is divided onto two paths, one of which goes through the vector modulator, the other through amplifiers and a 3 frequency multiplier. Band-pass filters are included downstream of the frequency multiplier to suppress unwanted harmonics.
Author
BANDWIDTH; VOLTAGE CONTROLLED OSCILLATORS; RADIO COMMUNICATION; QUADRATURE AMPLITUDE MODULATION; PHASE MODULATION; EXTREMELY HIGH FREQUENCIES; FREQUENCY MULTIPLIERS; COMMUNICATION NETWORKS
20090008409 California Inst. of Tech., Pasadena, CA, United States
Tele-Supervised Adaptive Ocean Sensor Fleet
Lefes, Alberto; Podnar, Gregg W.; Dolan, John M.; Hosler, Jeffrey C.; Ames, Troy J.; NASA Tech Briefs, January 2009; January 2009; pp. 7-; In English; Original contains color illustrations
Report No.(s): NPO-45478; Copyright; Avail.: CASI: A01, Hardcopy
Avail Online: www.techbriefs.com/component/content/article/3480
The Tele-supervised Adaptive Ocean Sensor Fleet (TAOSF) is a multi-robot science exploration architecture and system that uses a group of robotic boats (the Ocean-Atmosphere Sensor Integration System, or OASIS) to enable in-situ study of ocean surface and subsurface characteristics and the dynamics of such ocean phenomena as coastal pollutants, oil spills, hurricanes, or harmful algal blooms (HABs). The OASIS boats are extended- deployment, autonomous ocean surface vehicles. The TAOSF architecture provides an integrated approach to multi-vehicle coordination and sliding human-vehicle autonomy. One feature of TAOSF is the adaptive re-planning of the activities of the OASIS vessels based on sensor input ( smart sensing) and sensorial coordination among multiple assets. The architecture also incorporates Web-based communications that permit control of the assets over long distances and the sharing of data with remote experts. Autonomous hazard and assistance detection allows the automatic identification of hazards that require human intervention to ensure the safety and integrity of the robotic vehicles, or of science data that require human interpretation and response. Also, the architecture is designed for science analysis of acquired data in order to perform an initial onboard assessment of the presence of specific science signatures of immediate interest. TAOSF integrates and extends five subsystems developed by the participating institutions: Emergent Space Tech - nol ogies, Wallops Flight Facility, NASA s Goddard Space Flight Center (GSFC), Carnegie Mellon University, and Jet Propulsion Laboratory (JPL). The OASIS Autonomous Surface Vehicle (ASV) system, which includes the vessels as well as the land-based control and communications infrastructure developed for them, controls the hardware of each platform (sensors, actuators, etc.), and also provides a low-level waypoint navigation capability. The Multi-Platform Simulation Environment from GSFC is a surrogate for the OASIS ASV system and allows for independent development and testing of higher-level software components. The Platform Communicator acts as a proxy for both actual and simulated platforms. It translates platform-independent messages from the higher control systems to the device-dependent communication protocols. This enables the higher-level control systems to interact identically with heterogeneous actual or simulated platforms.
Author
OCEAN SURFACE; COASTS; OIL SLICKS; HURRICANES; AIR WATER INTERACTIONS; ROBOTICS; BOATS; COMMUNICATION NETWORKS; SURFACE VEHICLES; CONTAMINANTS
20090008410 NASA Marshall Space Flight Center, Huntsville, AL, United States
Improved Joining of Metal Components to Composite Structures
Semmes, Edmund; NASA Tech Briefs, January 2009; January 2009; pp. 15-1; In English; Original contains color illustrations
Report No.(s): MFS-31813-1; Copyright; Avail.: CASI: A01, Hardcopy
Avail Online: http://www.techbriefs.com/component/content/article/3493
Systems requirements for complex spacecraft drive design requirements that lead to structures, components, and/or enclosures of a multi-material and multifunctional design. The varying physical properties of aluminum, tungsten, Invar, or other high-grade aerospace metals when utilized in conjunction with lightweight composites multiply system level solutions. These multi-material designs are largely dependent upon effective joining techAn improved method of joining metal components to matrix/fiber composite material structures has been invented. The method is particularly applicable to equipping such thin-wall polymer-matrix composite (PMC) structures as tanks with flanges, ceramic matrix composite (CMC) liners for high heat engine nozzles, and other metallic-to-composite attachments. The method is oriented toward new architectures and distributing mechanical loads as widely as possible in the vicinities of attachment locations to prevent excessive concentrations of stresses that could give rise to delaminations, debonds, leaks, and other failures. The method in its most basic form can be summarized as follows: A metal component is to be joined to a designated attachment area on a composite-material structure. In preparation for joining, the metal component is fabricated to include multiple studs projecting from the aforementioned face. Also in preparation for joining, holes just wide enough to accept the studs are molded into, drilled, or otherwise formed in the corresponding locations in the designated attachment area of the uncured ("wet') composite structure. The metal component is brought together with the uncured composite structure so that the studs become firmly seated in the holes, thereby causing the composite material to become intertwined with the metal component in the joining area. Alternately, it is proposed to utilize other mechanical attachment schemes whereby the uncured composite and metallic parts are joined with "z-direction" fasteners. The resulting "wet" assembly is then subjected to the composite-curing heat treatment, becoming a unitary structure. It should be noted that this new art will require different techniques for CMC s versus PMC's, but the final architecture and companion curing philosophy is the same. For instance, a chemical vapor infiltration (CVI) fabrication technique may require special integration of the pre-form and
Author
FIBER COMPOSITES; COMPOSITE STRUCTURES; DEBONDING (MATERIALS); COMPOSITE MATERIALS; CERAMIC MATRIX COMPOSITES; POLYMER MATRIX COMPOSITES; METAL MATRIX COMPOSITES
20090008411 NASA Glenn Research Center, Cleveland, OH, United States
Machined Titanium Heat-Pipe Wick Structure
Rosenfeld, John H.; Minnerly, Kenneth G.; Gernert, Nelson J.; NASA Tech Briefs, January 2009; January 2009; pp. 1; In English; Original contains black and white illustrations
Report No.(s): LEW-18206-1; Copyright; Avail.: CASI: A01, Hardcopy
Avail Online: http://www.techbriefs.com/component/content/article/3494
Wick structures fabricated by machining of titanium porous material are essential components of lightweight titanium/ water heat pipes of a type now being developed for operation at temperatures up to 530 K in high-radiation environments. In the fabrication of some prior heat pipes, wicks have been made by extruding axial grooves into aluminum unfortunately, titanium cannot be extruded. In the fabrication of some other prior heat pipes, wicks have been made by in-situ sintering of metal powders shaped by the use of forming mandrels that are subsequently removed, but in the specific application that gave rise to the present fabrication method, the required dimensions and shapes of the heat-pipe structures would make it very difficult if not impossible to remove the mandrels due to the length and the small diameter. In the present method, a wick is made from one or more sections that are fabricated separately and assembled outside the tube that constitutes the outer heat pipe wall. The starting wick material is a slab of porous titanium material. This material is machined in its original flat configuration to form axial grooves. In addition, interlocking features are machined at the mating ends of short wick sections that are to be assembled to make a full-length continuous wick structure. Once the sections have been thus assembled, the resulting full-length flat wick structure is rolled into a cylindrical shape and inserted in the heatpipe tube (see figure). This wick-structure fabrication method is not limited to titanium/water heat pipes: It could be extended to other heat pipe materials and working fluids in which the wicks could be made from materials that could be pre-formed into porous slabs.
Author
HEAT PIPES; TITANIUM; ALUMINUM; WICKS; POROUS MATERIALS; FABRICATION; EXTRUDING
20090008412 California Inst. of Tech., Pasadena, CA, United States
Laser Metrology Heterodyne Phase-Locked Loop
Loya, Frank; Halverson, Peter; NASA Tech Briefs, January 2009; January 2009; pp. 2; In English
Report No.(s): NPO-40080; Copyright; Avail.: CASI: A01, Hardcopy
Avail Online: http://www.techbriefs.com/component/docman/doc_details/3394-laser-metrology-heterodyne-phase-locked-loop
A method reduces sensitivity to noise in a signal from a laser heterodyne interferometer. The phase-locked loop (PLL) removes glitches that occur in a zero-crossing detector s output [that can happen if the signal-to-noise ratio (SNR) of the heterodyne signal is low] by the use of an internal oscillator that produces a square-wave signal at a frequency that is inherently close to the heterodyne frequency. It also contains phase-locking circuits that lock the phase of the oscillator to the output of the zero-crossing detector. Because the PLL output is an oscillator signal, it is glitch-free. This enables the ability to make accurate phase measurements in spite of low SNR, creates an immunity to phase error caused by shifts in the heterodyne frequency (i.e. if the target moves causing Doppler shift), and maintains a valid phase even when the signal drops out for brief periods of time, such as when the laser is blocked by a stray object.
Author
PHASE LOCKED SYSTEMS; HETERODYNING; INTERFEROMETERS; SIGNAL TO NOISE RATIOS
20090008413 California Inst. of Tech., Pasadena, CA, United States
Effects of Temperature on Polymer/Carbon Chemical Sensors
Manfireda, Allison; Lara, Liana; Homer, Margie; Yen, Shiao-Pin; Kisor, Adam; Ryan, Margaret; Zhou, Hanying; Shevade, Abhijit; James, Lim; Manatt, Kenneth; NASA Tech Briefs, January 2009; January 2009; pp. ; In English
Copyright; Avail.: CASI: A01, Hardcopy
Avail Online: http://www.techbriefs.com/component/content/article/3478
Experiments were conducted on the effects of temperature, polymer molecular weight, and carbon loading on the electrical resistances of polymer/carbon-black composite films. The experiment were performed in a continuing effort to develop such films as part of the JPL Electronic Nose (ENose), that would be used to detect, identify, and quantify parts-per-million (ppm) concentration levels of airborne chemicals in the space shuttle/space station environments. The polymers used in this study were three formulations of poly(ethylene oxide) [PEO] that had molecular weights of 20 kilodaltons, 600 kilodaltons, and 1 megadalton, respectively. The results of one set of experiments showed a correlation between the polymer molecular weight and the percolation threshold. In a second set of experiments, differences among the temperature dependences of resistance were observed for different carbon loadings; these differences could be explained by a change in the conduction mechanism. In a third set of experiments, the responses of six different polymer/carbon composite sensors to three analytes (water vapor, methanol, methane) were measured as a function of temperature (28 to 36 C). For a given concentration of each analyte, the response of each sensor decreased with increasing temperature, in a manner different from those of the other sensors.
Author
TEMPERATURE EFFECTS; CARBON; POLYMERS; METHYL ALCOHOL; CHEMICAL TESTS; MOLECULAR WEIGHT
20090008414 Washington Univ., Seattle, WA, United States; NASA Glenn Research Center, Cleveland, OH, United States
Gadolinia-Doped Ceria Cathodes for Electrolysis of CO2
Adler, Stuart B.; NASA Tech Briefs, January 2009; January 2009; pp. 17-1; In English; Original contains color illustrations
Report No.(s): LEW-18211-1; Copyright; Avail.: CASI: A01, Hardcopy
Avail Online: http://www.techbriefs.com/component/content/article/3495
Gadolinia-doped ceria, or GDC, (Gd(0.4)Ce(0.6)O(2-delta), where the value of delta in this material varies, depending on the temperature and oxygen concentration in the atmosphere in which it is being used) has shown promise as a cathode material for high-temperature electrolysis of carbon dioxide in solid oxide electrolysis cells. The polarization resistance of a GDC electrode is significantly less than that of an otherwise equivalent electrode made of any of several other materials that are now in use or under consideration for use as cathodes for reduction of carbon dioxide. In addition, GDC shows no sign of deterioration under typical temperature and gas-mixture operating conditions of a high-temperature electrolyzer. Electrolysis of CO2 is of interest to NASA as a way of generating O2 from the CO2 in the Martian atmosphere. On Earth, a combination of electrolysis of CO2 and electrolysis of H2O might prove useful as a means of generating synthesis gas (syngas) from the exhaust gas of a coal- or natural-gas-fired power plant, thereby reducing the emission of CO2 into the atmosphere. The syngas a mixture of CO and H2 could be used as a raw material in the manufacture, via the Fisher-Tropsch process, of synthetic fuels, lubrication oils, and other hydrocarbon prod
Author
CARBON DIOXIDE; GAS MIXTURES; CATHODES; ELECTROLYSIS; SYNTHESIS GAS; NATURAL GAS; HYDROCARBONS; EXHAUST GASES
20090008415 Jet Propulsion Lab., California Inst. of Tech., Pasadena, CA, United States
Efficient Method for Optimizing Placement of Sensors
Fijany, Amir; Vatan, Farrokh; NASA Tech Briefs, January 2009; January 2009; pp. 32-3; In English; Original contains color illustrations
Report No.(s): NPO-42481; Copyright; Avail.: CASI: A01, Hardcopy
Avail Online: http://www.techbriefs.com/component/content/article/3505
A computationally efficient method has been developed to enable optimization of the placement of sensors for the purpose of diagnosis of a complex engineering system (e.g., an aircraft or spacecraft). The method can be used both in (1) designing a sensor system in which the number and positions of sensors are initially not known and must be determined and (2) adding sensors to a pre-existing system to increase the diagnostic capability. The optimal-sensor-placement problem can be summarized as involving the following concepts, issues, and subproblems: a) Degree of Diagnosability - This is a concept for characterizing the set of faults that can be discriminated by use of a given set of sensors. b) Minimal Sensor Set - The idea is one of finding a minimal set of sensors that guarantees a specific degree of diagnosability. c) Minimal-Cost Sensors - In a case in which different sensors are assigned with different costs, it is desired to choose the least costly set of sensors that affords a specific degree of diagnosability.
Author
COMPLEX SYSTEMS; DIAGNOSIS; STRUCTURAL ANALYSIS; NONLINEAR PROGRAMMING; MATHEMATICAL MODELS
20090008416 NASA Kennedy Space Center, Cocoa Beach, FL, United States
The Radio Frequency Health Node Wireless Sensor System
Valencia, J. Emilio; Stanley, Priscilla C.; Mackey, Paul J.; NASA Tech Briefs, January 2009; January 2009; pp. ; In English; Original contains color illustrations
Report No.(s): KSC-12798; Copyright; Avail.: CASI: A01, Hardcopy
Avail Online: http://www.techbriefs.com/component/docman/doc_details/3405-the-radio-frequ
The Radio Frequency Health Node (RFHN) wireless sensor system differs from other wireless sensor systems in ways originally intended to enhance utility as an instrumentation system for a spacecraft. The RFHN can also be adapted to use in terrestrial applications in which there are requirements for operational flexibility and integrability into higher-level instrumentation and data acquisition systems. As shown in the figure, the heart of the system is the RFHN, which is a unit that passes commands and data between (1) one or more commercially available wireless sensor units (optionally, also including wired sensor units) and (2) command and data interfaces with a local control computer that may be part of the spacecraft or other engineering system in which the wireless sensor system is installed. In turn, the local control computer can be in radio or wire communication with a remote control computer that may be part of a higher-level system. The remote control computer, acting via the local control computer and the RFHN, cannot only monitor readout data from the sensor units but can also remotely configure (program or reprogram) the RFHN and the sensor units during operation. In a spacecraft application, the RFHN and the sensor units can also be configured more nearly directly, prior to launch, via a serial interface that includes an umbilical cable between the spacecraft and ground support equipment. In either case, the RFHN wireless sensor system has the flexibility to be configured, as required, with different numbers and types of sensors for different applications. The RFHN can be used to effect realtime transfer of data from, and commands to, the wireless sensor units. It can also store data for later retrieval by an external computer. The RFHN communicates with the wireless sensor units via a radio transceiver module. The modular design of the RFHN makes it possible to add radio transceiver modules as needed to accommodate additional sets of wireless sensor units. The RFHN includes a core module that performs generic computer functions, including management of power and input, output, processing, and storage of data. In a typical application, the processing capabilities in the RFHN are utilized to perform preprocessing, trending, and fusion of sensor data. The core module also serves as the unit through which the remote control computer configures the sensor units and the rest of the RFHN.
Author
RADIO FREQUENCIES; WIRELESS COMMUNICATION; TRANSMITTER RECEIVERS; RADIO COMMUNICATION; REAL TIME OPERATION; DATA STRUCTURES; DATA RETRIEVAL; MODULES
20090008417 California Inst. of Tech., Pasadena, CA, United States
Synthesis of Submillimeter Radiation for Spectroscopy
Maiwald, Frank; Drouin, Brian; NASA Tech Briefs, January 2009; January 2009; pp. ; In English; Original contains color illustrations
Report No.(s): NPO-43091; Copyright; Avail.: CASI: A01, Hardcopy
Avail Online: http://www.techbriefs.com/component/content/article/3488
The frequency-multiplier submillimeter spectrometer (FMSS) is a laboratory apparatus for far-infrared molecular spectroscopy, embodying several advances over prior such apparatuses. The most innovative part of the FMSS is a source of monochromatic submillimeter- wavelength radiation that can be tuned over a wide frequency range, as needed for trace gas analyses and molecular- structure studies for which such apparatuses are typically used. The radiation source features a modular design and is built mostly from commercially available components. It includes a computer-controlled radio-frequency synthesizer, amplifiers, and frequency multipliers of a type heretofore used in local oscillators for heterodyne far-infrared receivers. In conjunction with the rest of the apparatus, this source makes it possible to perform measurements over large portions of the submillimeter-wavelength spectrum with resolution, accuracy, and sensitivity greater than those achievable in Fourier-transform infrared spectroscopy. In comparison with prior laboratory submillimeter- wavelength radiation sources, this source is much lighter in weight, less cumbersome, less power-hungry, and capable of sustained operation with less intervention by laboratory personnel. Also, unlike some prior submillimeter-wavelength sources, this source does not require a high-voltage power source. As shown in more detail in the figure, the radiation source includes a sweep frequency synthesizer connected to an external waveform generator, the output of which is used as a reference signal. The synthesizer is computer-controlled through a standard general-purpose interface bus (GPIB) and is operated in phase-locked continuous- wave mode for all measurements. The synthesizer output ranges in frequency from 11 to 18 GHz. For suppression of frequency spurs and harmonics, the output of the frequency synthesizer is fed through a tunable yttrium iron garnet (YIG) filter, which is swept in frequency simultaneously with the frequency synthesizer.
Author
SUBMILLIMETER WAVES; MOLECULAR STRUCTURE; FREQUENCY SYNTHESIZERS; MOLECULAR SPECTROSCOPY; RADIATION SOURCES; FREQUENCY RANGES; WAVEFORMS; YTTRIUM-ALUMINUM GARNET; SWEEP FREQUENCY; CONTINUOUS RADIATION; INFRARED SPECTROSCOPY
20090008418 California Inst. of Tech., Pasadena, CA, United States
100-GHz Phase Switch/Mixer Containing a Slot-Line Transition
Gaier, Todd; Wells, Mary; Dawson, Douglas; NASA Tech Briefs, January 2009; January 2009; pp. 10-1; In English; Original contains color illustrations
Report No.(s): NPO-30916; Copyright; Avail.: CASI: A01, Hardcopy
Avail Online: http://www.techbriefs.com/component/content/article/3491
A circuit that can function as a phase switch, frequency mixer, or frequency multiplier operates over a broad frequency range in the vicinity of 100 GHz. Among the most notable features of this circuit is a grounded uniplanar transition (in effect, a balun) between a slot line and one of two coplanar waveguides (CPWs). The design of this circuit is well suited to integration of the circuit into a microwave monolithic integrated circuit (MMIC) package. One CPW is located at the input end and one at the output end of the top side of a substrate on which the circuit is fabricated (see Figure 1). The input CPW feeds the input signal to antiparallel flip-chip Schottky diodes connected to the edges of the slot line. Phase switching is effected by the combination of (1) the abrupt transition from the input CPW to the slot line and (2) CPW ground tuning effected by switching of the bias on the diodes. Grounding of the slot metal to the bottom metal gives rise to a frequency cutoff in the slot. This cutoff is valuable for separating different frequency components when the circuit is used as a mixer or multiplier. Proceeding along the slot line toward the output end, one encounters the aforementioned transition, which couples the slot line to the output CPW. Impedance tuning of the transition is accomplished by use of a high-impedance section immediately before the transition.
Author
FREQUENCY MULTIPLIERS; CIRCUITS; FREQUENCY RANGES; INTEGRATED CIRCUITS; WAVEGUIDES; SWITCHING; COUPLERS
20090008419 Jet Propulsion Lab., California Inst. of Tech., Pasadena, CA, United States
Formation Flying of Components of a Large Space Telescope
Mettler, Edward; Quadrelli, Marco; Breckenridge, William; NASA Tech Briefs, January 2009; January 2009; pp. 2; In English
Report No.(s): NPO-45199; Copyright; Avail.: CASI: A01, Hardcopy
Avail Online: http://www.techbriefs.com/component/content/article/3508
A conceptual space telescope having an aperture tens of meters wide and a focal length of hundreds of meters would be implemented as a group of six separate optical modules flying in formation: a primary-membrane-mirror module, a relay-mirror module, a focal-plane-assembly module containing a fast steering mirror and secondary and tertiary optics, a primary-mirror-figure-sensing module, a scanning-electron-beam module for controlling the shape of the primary mirror, and a sunshade module. Formation flying would make it unnecessary to maintain the required precise alignments among the modules by means of an impractically massive rigid structure. Instead, a control system operating in conjunction with a metrology system comprising optical and radio subsystems would control the firing of small thrusters on the separate modules to maintain the formation, thereby acting as a virtual rigid structure. The control system would utilize a combination of centralized- and decentralized-control methods according to a leader-follower approach. The feasibility of the concept was demonstrated in computational simulations that showed that relative positions could be maintained to within a fraction of a millimeter and orientations to within several microradians.
Author
FORMATION FLYING; SPACEBORNE TELESCOPES; RIGID STRUCTURES; HUBBLE SPACE TELESCOPE; MIRRORS
20090008420 California Inst. of Tech., Pasadena, CA, United States
Fuel-Cell Power Systems Incorporating Mg-Based H2 Generators
Kindler, Andrew; Narayan, Sri R.; NASA Tech Briefs, January 2009; January 2009; pp. 20-2; In English; Original contains color illustrations
Report No.(s): NPO-43554; Copyright; Avail.: CASI: A01, Hardcopy
Avail Online: www.techbriefs.com/component/content/article/3498
Two hydrogen generators based on reactions involving magnesium and steam have been proposed as means for generating the fuel (hydrogen gas) for such fuel-cell power systems as those to be used in the drive systems of advanced motor vehicles. The hydrogen generators would make it unnecessary to rely on any of the hydrogen storage systems developed thus far that are, variously, too expensive, too heavy, too bulky, and/or too unsafe to be practical. The two proposed hydrogen generators are denoted basic and advanced, respectively. In the basic hydrogen generator (see figure), steam at a temperature greater than or equals 330 C would be fed into a reactor charged with magnesium, wherein hydrogen would be released in the exothermic reaction Mg + H2O yields MgO + H2. The steam would be made in a flash boiler. To initiate the reaction, the boiler could be heated electrically by energy borrowed from a storage battery that would be recharged during normal operation of the associated fuel-cell subsystem. Once the reaction was underway, heat from the reaction would be fed to the boiler. If the boiler were made an integral part of the hydrogen-generator reactor vessel, then the problem of transfer of heat from the reactor to the boiler would be greatly simplified. A pump would be used to feed water from a storage tank to the boiler.
Author
MAGNESIUM OXIDES; STEAM; HYDROGEN; EXOTHERMIC REACTIONS; ENERGY STORAGE; STORAGE TANKS; HEAT TRANSFER; FUEL CELLS
20090008421 California Inst. of Tech., Pasadena, CA, United States
Metrology System for a Large, Somewhat Flexible Telescope
Liebe, Carl Christian; Bartman, Randall; Cook, Walter; Craig, William; NASA Tech Briefs, January 2009; January 2009; pp. 1; In English; Original contains color illustrations
Report No.(s): NPO-44119; Copyright; Avail.: CASI: A01, Hardcopy
Avail Online: http://www.techbriefs.com/component/docman/doc_details/3400-metrology-syste
A proposed metrology system would be incorporated into a proposed telescope that would include focusing optics on a rigid bench connected via a deployable mast to another rigid bench holding a focal-plane array of photon counting photodetectors. Deformations of the deployable mast would give rise to optical misalignments that would alter the directions (and, hence, locations) of incidence of photons on the focal plane. The metrology system would measure the relative displacement of the focusing- optics bench and the focal-plane array bench. The measurement data would be used in post-processing of the digitized photodetector outputs to compensate for the mast-deformation-induced changes in the locations of incidence of photons on the focal plane, thereby making it possible to determine the original directions of incidence of photons with greater accuracy. The proposed metrology system is designed specifically for the Nuclear Spectroscopic Telescope Array (NuSTAR) a proposed spaceborne x-ray telescope. The basic principles of design and operation are also applicable to other large, somewhat flexible telescopes, both terrestrial and spaceborne. In the NuSTAR, the structural member connecting the optical bench and the photodetector array would be a 10-m-long deployable mast, and there is a requirement to keep errors in measured directions of incidence of photons below 10 arc seconds (3 sigma). The proposed system would include three diode lasers that would be mounted on the focusing-optics bench. For clarity, only one laser is shown in the figure, which is a greatly simplified schematic diagram of the system. Each laser would be aimed at a position-sensitive photodiode that would be mounted on the detector bench alongside the aforementioned telescope photodetector array. The diode lasers would operate at a wavelength of 830 nm, each at a power of 200 mW. Each laser beam would be focused to a spot of .1-mm diameter on the corresponding position-sensitive photodiode. To reduce the effect of sunlight on the measurements, a one-stage light baffle and an 830-nm transmission filter of 10-nm bandwidth would be placed in front of the position- sensitive photodiode. For each metrology reading, the output of the position-sensitive detector would be sampled and digitized twice: once with the lasers turned on, then once with the lasers turned off. The data from these two sets of samples would be subtracted from each other to further reduce the effects of sun glints or other background light sources.
Author
SPACEBORNE TELESCOPES; METROLOGY; FOCUSING; STRUCTURAL MEMBERS; DEFORMATION; LIGHT SOURCES; PHOTODIODES; X RAY TELESCOPES; SPECTROSCOPIC TELESCOPES; SEMICONDUCTOR LASERS
20090008422 California Inst. of Tech., Pasadena, CA, United States
Sensitive, Rapid Detection of Bacterial Spores
Kern, Roger G.; Venkateswaran, Kasthuri; Chen, Fei; Pickett, Molly; Matsuyama, Asahi; NASA Tech Briefs, January 2009; January 2009; pp. 2; In English; Original contains color illustrations
Report No.(s): NPO-40976; Copyright; Avail.: CASI: A01, Hardcopy
Avail Online: www.techbriefs.com/component/content/article/3499
A method of sensitive detection of bacterial spores within delays of no more than a few hours has been developed to provide an alternative to a prior three-day NASA standard culture-based assay. A capability for relatively rapid detection of bacterial spores would be beneficial for many endeavors, a few examples being agriculture, medicine, public health, defense against biowarfare, water supply, sanitation, hygiene, and the food-packaging and medical-equipment industries. The method involves the use of a commercial rapid microbial detection system (RMDS) that utilizes a combination of membrane filtration, adenosine triphosphate (ATP) bioluminescence chemistry, and analysis of luminescence images detected by a charge-coupled-device camera. This RMDS has been demonstrated to be highly sensitive in enumerating microbes (it can detect as little as one colony-forming unit per sample) and has been found to yield data in excellent correlation with those of culture-based methods. What makes the present method necessary is that the specific RMDS and the original protocols for its use are not designed for discriminating between bacterial spores and other microbes. In this method, a heat-shock procedure is added prior to an incubation procedure that is specified in the original RMDS protocols. In this heat-shock procedure (which was also described in a prior NASA Tech Briefs article on enumerating sporeforming bacteria), a sample is exposed to a temperature of 80 C for 15 minutes. Spores can survive the heat shock, but nonspore- forming bacteria and spore-forming bacteria that are not in spore form cannot survive. Therefore, any colonies that grow during incubation after the heat shock are deemed to have originated as spores.
Author
BACTERIA; SPORES; DETECTION; SENSITIVITY; MEDICAL EQUIPMENT; PUBLIC HEALTH; MICROORGANISMS; SANITATION; BIOLUMINESCENCE
20090008423 California Inst. of Tech., Pasadena, CA, United States
Adenosine Monophosphate-Based Detection of Bacterial Spores
Kern, Roger G.; Chen, Fei; Venkateswaran, Kasthuri; Hattori, Nori; Suzuki, Shigeya; NASA Tech Briefs, January 2009; January 2009; pp. 23-2; In English; Original contains color illustrations
Report No.(s): NPO-40938; Copyright; Avail.: CASI: A01, Hardcopy
Avail Online: www.techbriefs.com/component/content/article/3500
A method of rapid detection of bacterial spores is based on the discovery that a heat shock consisting of exposure to a temperature of 100 C for 10 minutes causes the complete release of adenosine monophosphate (AMP) from the spores. This method could be an alternative to the method described in the immediately preceding article. Unlike that method and related prior methods, the present method does not involve germination and cultivation; this feature is an important advantage because in cases in which the spores are those of pathogens, delays involved in germination and cultivation could increase risks of infection. Also, in comparison with other prior methods that do not involve germination, the present method affords greater sensitivity. At present, the method is embodied in a laboratory procedure, though it would be desirable to implement the method by means of a miniaturized apparatus in order to make it convenient and economical enough to encourage widespread use.
Author
ADENOSINE MONOPHOSPHATE; BACTERIA; GERMINATION; INFECTIOUS DISEASES; BIOLUMINESCENCE; DETECTION; THERMAL SHOCK
20090008424 Case Western Reserve Univ., Cleveland, OH, United States
SiC Optically Modulated Field-Effect Transistor
Tabib-Azar, Massood; NASA Tech Briefs, January 2009; January 2009; pp. 1; In English
Report No.(s): LEW-18349-1; Copyright; Avail.: CASI: A01, Hardcopy
Avail Online: http://www.techbriefs.com/component/content/article/3492
An optically modulated field-effect transistor (OFET) based on a silicon carbide junction field-effect transistor (JFET) is under study as, potentially, a prototype of devices that could be useful for detecting ultraviolet light. The SiC OFET is an experimental device that is one of several devices, including commercial and experimental photodiodes, that were initially evaluated as detectors of ultraviolet light from combustion and that could be incorporated into SiC integrated circuits to be designed to function as combustion sensors. The ultraviolet-detection sensitivity of the photodiodes was found to be less than desired, such that it would be necessary to process their outputs using high-gain amplification circuitry. On the other hand, in principle, the function of the OFET could be characterized as a combination of detection and amplification. In effect, its sensitivity could be considerably greater than that of a photodiode, such that the need for amplification external to the photodetector could be reduced or eliminated. The experimental SiC OFET was made by processes similar to JFET-fabrication processes developed at Glenn Research Center. The gate of the OFET is very long, wide, and thin, relative to the gates of typical prior SiC JFETs. Unlike in prior SiC FETs, the gate is almost completely transparent to near-ultraviolet and visible light. More specifically: The OFET includes a p+ gate layer less than 1/4 m thick, through which photons can be transported efficiently to the p+/p body interface. The gate is relatively long and wide (about 0.5 by 0.5 mm), such that holes generated at the body interface form a depletion layer that modulates the conductivity of the channel between the drain and the source. The exact physical mechanism of modulation of conductivity is a subject of continuing research. It is known that injection of minority charge carriers (in this case, holes) at the interface exerts a strong effect on the channel, resulting in amplification of the photon-detection signal. A family of operating curves characterizing the OFET can be generated in a series of measurements performed at different intensities of incident ultraviolet light.
Author
SILICON CARBIDES; FIELD EFFECT TRANSISTORS; CHARGE CARRIERS; ULTRAVIOLET RADIATION; PHOTOMETERS; MODULATION; INTEGRATED CIRCUITS; HIGH GAIN; AMPLIFICATION
20090008425 NASA Glenn Research Center, Cleveland, OH, United States
Small CO2 Sensors Operate at Lower Temperature
Hunter, Gary W.; Xu, Jennifer C.; NASA Tech Briefs, January 2009; January 2009; pp. 6-; In English; Original contains color illustrations
Report No.(s): LEW-18324-1; Copyright; Avail.: CASI: A01, Hardcopy
Avail Online: http://www.techbriefs.com/component/content/article/3475
Solid-electrolyte-based amperometric sensors for measuring concentrations of CO2 in air are being developed for use in detection of fires, environmental monitoring, and other applications where liquid-based electrochemical cells are problematic. These sensors are small (sizes of the order of a millimeter), are robust, are amenable to batch fabrication at relatively low cost, and exhibit short response times (seconds) and wide detection ranges. A sensor of this type at a previous stage of development included a solid electrolyte of Na3Zr2Si2PO12 deposited mainly between interdigitated Pt electrodes on an alumina substrate, all overcoated with an auxiliary solid electrolyte of (Na2CO3:BaCO3 in a molar ratio of 1:1.7). It was necessary to heat this device to a temperature as high as 600 C to obtain the desired sensitivity and rapid response. Heating sensors increases the power consumption of the sensor system and complicates the use of the sensor in some applications. Thus, decreasing a sensor s power consumption while maintaining its performance is a technical goal of ongoing development.
Author
CARBON DIOXIDE; ELECTROCHEMICAL CELLS; ENVIRONMENTAL MONITORING; SOLID ELECTROLYTES; LOW COST; LOW TEMPERATURE; ALUMINUM OXIDES; ENERGY CONSUMPTION
20090008426 Jet Propulsion Lab., California Inst. of Tech., Pasadena, CA, United States
Economical Implementation of a Filter Engine in an FPGA
Kowalski, James E.; NASA Tech Briefs, January 2009; January 2009; pp. 1; In English; Original contains color illustrations
Report No.(s): NPO-44662; Copyright; Avail.: CASI: A01, Hardcopy
Avail Online: http://www.techbriefs.com/component/content/article/3487
A logic design has been conceived for a field-programmable gate array (FPGA) that would implement a complex system of multiple digital state-space filters. The main innovative aspect of this design lies in providing for reuse of parts of the FPGA hardware to perform different parts of the filter computations at different times, in such a manner as to enable the timely performance of all required computations in the face of limitations on available FPGA hardware resources. The implementation of the digital state-space filter involves matrix vector multiplications, which, in the absence of the present innovation, would ordinarily necessitate some multiplexing of vector elements and/or routing of data flows along multiple paths. The design concept calls for implementing vector registers as shift registers to simplify operand access to multipliers and accumulators, obviating both multiplexing and routing of data along multiple paths. Each vector register would be reused for different parts of a calculation. Outputs would always be drawn from the same register, and inputs would always be loaded into the same register. A simple state machine would control each filter. The output of a given filter would be passed to the next filter, accompanied by a "valid" signal, which would start the state machine of the next filter. Multiple filter modules would share a multiplication/accumulation arithmetic unit. The filter computations would be timed by use of a clock having a frequency high enough, relative to the input and output data rate, to provide enough cycles for matrix and vector arithmetic operations. This design concept could prove beneficial in numerous applications in which digital filters are used and/or vectors are multiplied by coefficient matrices. Examples of such applications include general signal processing, filtering of signals in control systems, processing of geophysical measurements, and medical imaging. For these and other applications, it could be advantageous to combine compact FPGA digital filter implementations with other application-specific logic implementations on single integrated-circuit chips. An FPGA could readily be tailored to implement a variety of filters because the filter coefficients would be loaded into memory at startup.
Author
FIELD-PROGRAMMABLE GATE ARRAYS; INTEGRATED CIRCUITS; ACCUMULATORS; COMPLEX SYSTEMS; DIGITAL FILTERS; ARITHMETIC AND LOGIC UNITS; SIGNAL PROCESSING; MULTIPLEXING; MATRICES (MATHEMATICS); LOGIC DESIGN
20090008427 Jet Propulsion Lab., California Inst. of Tech., Pasadena, CA, United States
Truncation Depth Rule-of-Thumb for Convolutional Codes
Moision, Bruce; NASA Tech Briefs, January 2009; January 2009; pp. 3; In English
Report No.(s): NPO-45009; Copyright; Avail.: CASI: A01, Hardcopy
Avail Online: http://www.techbriefs.com/component/content/article/3506
In this innovation, it is shown that a commonly used rule of thumb (that the truncation depth of a convolutional code should be five times the memory length, m, of the code) is accurate only for rate 1/2 codes. In fact, the truncation depth should be 2.5 m/(1 - r), where r is the code rate. The accuracy of this new rule is demonstrated by tabulating the distance properties of a large set of known codes. This new rule was derived by bounding the losses due to truncation as a function of the code rate. With regard to particular codes, a good indicator of the required truncation depth is the path length at which all paths that diverge from a particular path have accumulated the minimum distance of the code. It is shown that the new rule of thumb provides an accurate prediction of this depth for codes of varying rates.
Author
TABULATION PROCESSES; BOUNDARIES; SIGNAL TO NOISE RATIOS
20090008428 NASA Goddard Space Flight Center, Greenbelt, MD, United States
CGH Figure Testing of Aspherical Mirrors in Cold Vacuums
Chambers, Victor John; Ohl, Raymond G.; Mink, Ronald G.; Arnold, Steven; NASA Tech Briefs, January 2009; January 2009; pp. 26-2; In English; Original contains color illustrations
Report No.(s): GSC-14789-1; Copyright; Avail.: CASI: A01, Hardcopy
Avail Online: http://www.techbriefs.com/component/content/article/3501
An established method of room-temperature interferometric null testing of mirrors having simple shapes (e.g., flat, spherical, or spheroidal) has been augmented to enable measurement of errors in the surface figures of off-axis, non-axisymmetric, aspherical mirrors when the mirrors are located inside cryogenic vacuum chambers. The established method involves the use of a computer-generated hologram (CGH), functionally equivalent to a traditional null lens, to modify the laser beam of an imaging interferometer to obtain a reference wavefront that matches the ideal surface figure of a mirror under test. The CGH is inserted at the appropriate position and orientation in the optical path of the imaging interferometer, which, in turn, is appropriately positioned and oriented with respect to the mirror under test. Deviations of the surface figure of the mirror from the ideal surface figure manifest themselves as interference fringes. Interferograms are recorded and analyzed to deduce figure errors.
Author
ASPHERICITY; MIRRORS; HOLOGRAPHY; VACUUM CHAMBERS; OPTICAL PATHS; CRYOGENICS; IMAGING TECHNIQUES
20090008429 Jet Propulsion Lab., California Inst. of Tech., Pasadena, CA, United States
High-Performance Algorithm for Solving the Diagnosis Problem
Fijany, Amir; Vatan, Farrokh; NASA Tech Briefs, January 2009; January 2009; pp. 3; In English; Original contains color illustrations
Report No.(s): NPO-41456; Copyright; Avail.: CASI: A01, Hardcopy
Avail Online: http://www.techbriefs.com/component/content/article/3504
An improved method of model-based diagnosis of a complex engineering system is embodied in an algorithm that involves considerably less computation than do prior such algorithms. This method and algorithm are based largely on developments reported in several NASA Tech Briefs articles: The Complexity of the Diagnosis Problem (NPO-30315), Vol. 26, No. 4 (April 2002), page 20; Fast Algorithms for Model-Based Diagnosis (NPO-30582), Vol. 29, No. 3 (March 2005), page 69; Two Methods of Efficient Solution of the Hitting-Set Problem (NPO-30584), Vol. 29, No. 3 (March 2005), page 73; and Efficient Model-Based Diagnosis Engine (NPO-40544), on the following page. Some background information from the cited articles is prerequisite to a meaningful summary of the innovative aspects of the present method and algorithm. In model-based diagnosis, the function of each component and the relationships among all the components of the engineering system to be diagnosed are represented as a logical system denoted the system description (SD). Hence, the expected normal behavior of the engineering system is the set of logical consequences of the SD. Faulty components lead to inconsistencies between the observed behaviors of the system and the SD. Diagnosis the task of finding faulty components is reduced to finding those components, the abnormalities of which could explain all the inconsistencies. The solution of the diagnosis problem should be a minimal diagnosis, which is a minimal set of faulty components. The calculation of a minimal diagnosis is inherently a hard problem, the solution of which requires amounts of computation time and memory that increase exponentially with the number of components of the engineering system. Among the developments to reduce the computational burden, as reported in the cited articles, is the mapping of the diagnosis problem onto the integer-programming (IP) problem. This mapping makes it possible to utilize a variety of algorithms developed previously for IP to solve the diagnosis problem. In the IP approach, the diagnosis problem can be formulated as a linear integer optimization problem, which can be solved by use of well-developed integer-programming algorithms. This concludes the background information.
Author
ALGORITHMS; COMPLEX SYSTEMS; DIAGNOSIS; ABNORMALITIES; COMPUTATION
20090008430 California Inst. of Tech., Pasadena, CA, United States
Precise Stabilization of the Optical Frequency of WGMRs
Savchenkov, Anatoliy; Matsko, Andrey; Matsko, Andrey; Yu, Nan; Maleki, Lute; Iltchenko, Vladimir; NASA Tech Briefs, January 2009; January 2009; pp. 2; In English; Original contains color illustrations
Report No.(s): NPO-45180; Copyright; Avail.: CASI: A01, Hardcopy
Avail Online: http://www.techbriefs.com/component/content/article/3510
Crystalline whispering gallery mode resonators (CWGMRs) made of crystals with axial symmetry have ordinary and extraordinary families of optical modes. These modes have substantially different thermo-refractive constants. This results in a very sharp dependence of differential detuning of optical frequency on effective temperature. This frequency difference compared with clock gives an error signal for precise compensation of the random fluctuations of optical frequency. Certain crystals, like MgF2, have turnover points where the thermo-refractive effect is completely nullified. An advantage for applications using WGMRs for frequency stabilization is in the possibility of manufacturing resonators out of practically any optically transparent crystal. It is known that there are crystals with negative and zero thermal expansion at some specific temperatures. Doping changes properties of the crystals and it is possible to create an optically transparent crystal with zero thermal expansion at room temperature. With this innovation s stabilization technique, the resultant WGMR will have absolute frequency stability The expansion of the resonator s body can be completely compensated for by nonlinear elements. This results in compensation of linear thermal expansion (see figure). In three-mode, the MgF2 resonator, if tuned at the turnover thermal point, can compensate for all types of random thermal-related frequency drift. Simplified dual-mode method is also available. This creates miniature optical resonators with good short- and long-term stability for passive secondary frequency ethalon and an active resonator for active secondary frequency standard (a narrowband laser with long-term stability).
Author
WHISPERING GALLERY MODES; OPTICAL RESONATORS; FREQUENCY STABILITY; SYMMETRY; CRYSTALLINITY; FREQUENCY STANDARDS
20090008431 California Inst. of Tech., Pasadena, CA, United States
Submillimeter-Wave Amplifier Module with Integrated Waveguide Transitions
Samoska, Lorene; Chattopadhyay, Goutam; Pukala, David; Gaier, Todd; Soria, Mary; ManFung, King; Deal, William; Mei, Gerry; Radisic, Vesna; Lai, Richard; NASA Tech Briefs, January 2009; January 2009; pp. 12-1; In English; Original contains color illustrations
Contract(s)/Grant(s): DARPA MIPR 06-U037; W911Q-06-C-0050
Report No.(s): NPO-45088; Copyright; Avail.: CASI: A01, Hardcopy
Avail Online: http://www.techbriefs.com/component/content/article/3485
To increase the usefulness of monolithic millimeter-wave integrated circuit (MMIC) components at submillimeter-wave frequencies, a chip has been designed that incorporates two integrated, radial E-plane probes with an MMIC amplifier in between, thus creating a fully integrated waveguide module. The integrated amplifier chip has been fabricated in 35-nm gate length InP high-electron-mobility-transistor (HEMT) technology. The radial probes were mated to grounded coplanar waveguide input and output lines in the internal amplifier. The total length of the internal HEMT amplifier is 550 m, while the total integrated chip length is 1,085 m. The chip thickness is 50 m with the chip width being 320 m. The internal MMIC amplifier is biased through wire-bond connections to the gates and drains of the chip. The chip has 3 stages, employing 35-nm gate length transistors in each stage. Wire bonds from the DC drain and gate pads are connected to off-chip shunt 51-pF capacitors, and additional off-chip capacitors and resistors are added to the gate and drain bias lines for low-frequency stability of the amplifier. Additionally, bond wires to the grounded coplanar waveguide pads at the RF input and output of the internal amplifier are added to ensure good ground connections to the waveguide package. The S-parameters of the module, not corrected for input or output waveguide loss, are measured at the waveguide flange edges. The amplifier module has over 10 dB of gain from 290 to 330 GHz, with a peak gain of over 14 dB at 307 GHz. The WR2.2 waveguide cutoff is again observed at 268 GHz. The module is biased at a drain current of 27 mA, a drain voltage of 1.24 V, and a gate voltage of +0.21 V. Return loss of the module is very good between 5 to 25 dB. This result illustrates the usefulness of the integrated radial probe transition, and the wide (over 10-percent) bandwidth that one can expect for amplifier modules with integrated radial probes in the submillimeter-regime (>300 GHz).
Author
SUBMILLIMETER WAVES; AMPLIFIERS; WAVEGUIDES; CIRCUITS; ELECTRIC POTENTIAL; HIGH ELECTRON MOBILITY TRANSISTORS; MICROWAVE CIRCUITS; RADIO FREQUENCIES
20090008432 California Inst. of Tech., Pasadena, CA, United States
Alternative OTEC Scheme for a Submarine Robot
Jones, Jack; Chao, Yi; NASA Tech Briefs, January 2009; January 2009; pp. 21-2; In English; Original contains color illustrations
Report No.(s): NPO-43500; Copyright; Avail.: CASI: A01, Hardcopy
Avail Online: www.techbriefs.com/component/content/article/3496
A proposed system for exploiting the ocean thermal gradient to generate power would be based on the thawing-expansion/ freezing-contraction behavior of a wax or perhaps another suitable phase-change material. The power generated by this system would be used to recharge the batteries in a battery-powered unmanned underwater vehicle [UUV (essentially, a small exploratory submarine robot)] of a type that has been deployed in large numbers in research pertaining to global warming. A UUV of this type travels between the ocean surface and various depths, measuring temperature and salinity. This proposed system would be an alternative to another proposed ocean thermal energy conversion (OTEC) system that would serve the same purpose but would utilize a thermodynamic cycle in which CO2 would be the working fluid. That system is described in Utilizing Ocean Thermal Energy in a Submarine Robot (NPO-43304), immediately following this brief. The main advantage of this proposed system over the one using CO2 is that it could derive a useful amount of energy from a significantly smaller temperature difference. At one phase of its operational cycle, the system now proposed would utilize the surface ocean temperature (which lies between 15 and 20 C over most of the Earth) to melt a wax (e.g., pentadecane) that has a melting/freezing temperature of about 10 C. At the opposite phase of its operational cycle, the system would utilize the lower ocean temperature at depth (e.g., between 4 and 7 C at a depth of 300 m) to freeze the wax. The melting or freezing causes the wax to expand or contract, respectively, by about 8 volume percent.
Author
CONTRACTION; WAXES; UNDERWATER VEHICLES; ROBOTS; FREEZING; MELTING; THERMAL ENERGY; TEMPERATURE GRADIENTS; OCEAN THERMAL ENERGY CONVERSION; OCEAN SURFACE
20090008433 California Inst. of Tech., Pasadena, CA, United States
Series-Coupled Pairs of Silica Microresonators
Savchenkov, Anatoliy; Iltchenko, Vladimir; Maleki, Lute; Handley, Tim; NASA Tech Briefs, January 2009; January 2009; pp. 27-2; In English; Original contains color illustrations
Report No.(s): NPO-30828; Copyright; Avail.: CASI: A01, Hardcopy
Avail Online: http://www.techbriefs.com/component/content/article/3503
Series-coupled pairs of whispering-gallery-mode optical microresonators have been demonstrated as prototypes of stable, narrow-band-pass photonic filters. Characteristics that are generally considered desirable in a photonic or other narrow-band-pass filter include response as nearly flat as possible across the pass band, sharp roll-off, and high rejection of signals outside the pass band. A single microresonator exhibits a Lorentzian filter function: its peak response cannot be made flatter and its roll-off cannot be made sharper. However, as a matter of basic principle applicable to resonators in general, it is possible to (1) use multiple resonators, operating in series or parallel, to obtain a roll-off sharper, and out-of-band rejection greater, relative to those of a Lorentzian filter function and (2) to make the peak response (the response within the pass band) flatter by tuning the resonators to slightly different resonance frequencies that span the pass band. The first of the two microresonators in each series-coupled pair was a microtorus made of germania-doped silica (containing about 19 mole percent germania), which is a material used for the cores of some optical fibers. The reasons for choosing this material is that exposing it to ultraviolet light causes it to undergo a chemical change that changes its index of refraction and thereby changes the resonance frequency. Hence, this material affords the means to effect the desired slight relative detuning of the two resonators. The second microresonator in each pair was a microsphere of pure silica. The advantage of making one of the resonators a torus instead of a sphere is that its spectrum of whispering-gallery-mode resonances is sparser, as needed to obtain a frequency separation of at least 100 GHz between resonances of the filter as a whole.
Author
WHISPERING GALLERY MODES; RESONANT FREQUENCIES; MICROPARTICLES; DOPED CRYSTALS; BANDPASS FILTERS; ULTRAVIOLET RADIATION; SILICON DIOXIDE; RESONATORS
20090008434 NASA Goddard Space Flight Center, Greenbelt, MD, United States
Silicon Microleaks for Inlets of Mass Spectrometers
Harpold, Dan; Hasso, Niemann; Jamieson, Brian G.; Lynch, Bernard A.; NASA Tech Briefs, January 2009; January 2009; pp. 25-2; In English; Original contains color illustrations
Report No.(s): GSC-15341-1; Copyright; Avail.: CASI: A01, Hardcopy
Avail Online: http://www.techbriefs.com/component/content/article/3502
Microleaks for inlets of mass spectrometers used to analyze atmospheric gases can be fabricated in silicon wafers by means of photolithography, etching, and other techniques that are commonly used in the manufacture of integrated circuits and microelectromechanical systems. The microleaks serve to limit the flows of the gases into the mass-spectrometer vacuums to specified very small flow rates consistent with the capacities of the spectrometer vacuum pumps. There is a need to be able to precisely tailor the dimensions of each microleak so as to tailor its conductance to a precise low value. (As used here, "conductance" signifies the ratio between the rate of flow in the leak and the pressure drop from the upstream to the downstream end of the leak.) To date, microleaks have been made, variously, of crimped metal tubes, pulled glass tubes, or frits. Crimped-metal and pulled-glass-tube microleaks cannot readily be fabricated repeatably to precise dimensions and are susceptible to clogging with droplets or particles. Frits tend to be differentially chemically reactive with various gas constituents and, hence, to distort the gas mixtures to be analyzed. The present approach involving microfabrication in silicon largely overcomes the disadvantages of the prior approaches.
Author
SILICON; MASS SPECTROMETERS; PHOTOLITHOGRAPHY; LEAKAGE; GAS MIXTURES; MICROELECTROMECHANICAL SYSTEMS; SPECTROMETERS
20090008435 California Inst. of Tech., Pasadena, CA, United States
Utilizing Ocean Thermal Energy in a Submarine Robot
Jones, Jack; Chao, Yi; NASA Tech Briefs, January 2009; January 2009; pp. 19-2; In English; Original contains color illustrations
Report No.(s): NPO-43304; Copyright; Avail.: CASI: A01, Hardcopy
Avail Online: http://www.techbriefs.com/component/content/article/3497
A proposed system would exploit the ocean thermal gradient for recharging the batteries in a battery-powered unmanned underwater vehicle [UUV (essentially, a small exploratory submarine robot)] of a type that has been deployed in large numbers in research pertaining to global warming. A UUV of this type travels between the ocean surface and depths, measuring temperature and salinity. The proposed system is related to, but not the same as, previously reported ocean thermal energy conversion (OTEC) systems that exploit the ocean thermal gradient but consist of stationary apparatuses that span large depth ranges. The system would include a turbine driven by working fluid subjected to a thermodynamic cycle. CO2 has been provisionally chosen as the working fluid because it has the requisite physical properties for use in the range of temperatures expected to be encountered in operation, is not flammable, and is much less toxic than are many other commercially available refrigerant fluids. The system would be housed in a pressurized central compartment in a UUV equipped with a double hull (see figure). The thermodynamic cycle would begin when the UUV was at maximum depth, where some of the CO2 would condense and be stored, at relatively low temperature and pressure, in the annular volume between the inner and outer hulls. The cycle would resume once the UUV had ascended to near the surface, where the ocean temperature is typically greater than or equals 20 C. At this temperature, the CO2 previously stored at depth in the annular volume between the inner and outer hulls would be pressurized to approx. equals 57 bar (5.7 MPa). The pressurized gaseous CO2 would flow through a check valve into a bladder inside the pressurized compartment, thereby storing energy of the relatively warm, pressurized CO2 for subsequent use after the next descent to maximum depth.
Author
THERMAL ENERGY; OCEAN THERMAL ENERGY CONVERSION; UNDERWATER VEHICLES; ROBOTS; OCEAN SURFACE; CARBON DIOXIDE; DEPTH; THERMODYNAMIC CYCLES; OCEAN TEMPERATURE
Additions to the NASA Aeronautics and Space Database as of 03/12/2009
20090008496 NASA Glenn Research Center, Cleveland, OH, United States
High Temperature Aerogels in the Al2O3-SiO2 System
Hurwitz, Frances I.; Aranda, Denisse V.; Gallagher, Meghan E.; August 20, 2008; In English; American Chemical Society 236th National Meeting, 17 - 21 Aug. 2008, Pennsylvania, United States; Original contains color and black and white illustrations
Report No.(s): E-16906; Copyright; Avail.: CASI: A03, Hardcopy
Al2O3-SiO2 aerogels are of interest as constituents of thermal insulation systems for use at high temperatures. Al2O3 and mullite aerogels are expected to crystallize at higher temperatures than their SiO2 counterparts, hence avoiding the shrinkages that accompany the formation of lower temperature SiO2 phases and preserving pore structures into higher temperature regimes. The objective of this work is to determine the influence of processing parameters on shrinkage, gel structure (including surface area, pore size and distribution) and pyrolysis behavior.
Author
AEROGELS; ALUMINUM OXIDES; SILICON DIOXIDE; THERMAL INSULATION; HIGH TEMPERATURE; TEMPERATURE DISTRIBUTION
20090008498 NASA Glenn Research Center, Cleveland, OH, United States
Space Program Testing in the NASA Glenn Research Center 10x10 SWT
Ogorzaly, Matthew; Becks, Edward; October 26, 2008; In English; 110th STAI Meeting, 26 - 28 Oct. 2008, Tel Aviv, Israel; Original contains color illustrations
Contract(s)/Grant(s): NNC05CA95C
Report No.(s): E-16911; Copyright; Avail.: CASI: A03, Hardcopy
Historically, testing in the 10x10 Supersonic Wind Tunnel involved aeronautics type testing including testing of Supersonic Propulsion Components such as inlets and nozzles, Propulsion System Integration, Full-scale Jet and Rocket Engines, Aerodynamic Force and Moment testing, Sonic Boom Mitigation and the investigation of Advanced Aircraft Models. The New Space Directive(s) called for new areas of testing. Two interesting and challenging tests were proposed for the 10x10 SWT, the Inflatable Aerodynamic Decelerator (IAD) and the Mars Science Lab (MSL) Flexible Parachute. This presentation highlights those tests and plans for future testing in the 10x10 SWT.
Author
SUPERSONIC WIND TUNNELS; AERODYNAMIC FORCES; INLET NOZZLES; PERFORMANCE TESTS; PROPULSION SYSTEM CONFIGURATIONS; JET ENGINES
20090008499 NASA Glenn Research Center, Cleveland, OH, United States; Ohio Aerospace Inst., Cleveland, OH, United States
Active Metal Brazing and Characterization of Brazed Joints in C-C and C-SiC Composites to Copper-Clad-Molybdenum System
Singh, M.; Asthana, R.; October 05, 2008; In English; Materials Science and Technology 2008, 5 - 9 Oct. 2008, Pennsylvania, United States; Original contains black and white illustrations
Contract(s)/Grant(s): NNC07TB09T
Report No.(s): E-16912; Copyright; Avail.: CASI: A03, Hardcopy
Carbon/carbon composites with CVI and resin-derived matrices, and C/SiC composites reinforced with T-300 carbon fibers in a CVI SiC matrix were joined to Cu-clad Mo using two Ag-Cu braze alloys, Cusil-ABA (1.75% Ti) and Ticusil (4.5% Ti). The brazed joints revealed good interfacial bonding, preferential precipitation of Ti at the composite/braze interface, and a tendency toward delamination in resin-derived C/C composite. Extensive braze penetration of the inter-fiber channels in the CVI C/C composites was observed. The Knoop microhardness (HK) distribution across the C/C joints indicated sharp gradients at the interface, and a higher hardness in Ticusil than in Cusil-ABA. For the C/SiC composite to Cu-clad-Mo joints, the effect of composite surface preparation revealed that ground samples did not crack whereas unground samples cracked. Calculated strain energy in brazed joints in both systems is comparable to the strain energy in a number of other ceramic/metal systems. Theoretical predictions of the effective thermal resistance suggest that such joined systems may be promising for thermal management applications.
Author
CARBON-CARBON COMPOSITES; BRAZING; THERMAL RESISTANCE; MATRIX MATERIALS; CARBON FIBERS; COPPER; HARDNESS; RESIN MATRIX COMPOSITES
20090008500 NASA Glenn Research Center, Cleveland, OH, United States
Joining and Integration of Advanced Carbon-Carbon Composites to Metallic Systems for Thermal Management Applications
Singh, M.; Asthana, R.; November 10, 2008; In English; The 9th International Symposium on Ceramic Materials and Components for Energy and Environmental Applications, 10 - 14 Nov. 2008, Shanghai, China; Original contains black and white illustrations
Contract(s)/Grant(s): NNC07TB09T
Report No.(s): E-16913; Copyright; Avail.: CASI: A03, Hardcopy
Recent research and development activities in joining and integration of carbon-carbon (C/C) composites to metals such as Ti and Cu-clad-Mo for thermal management applications are presented with focus on advanced brazing techniques. A wide variety of carbon-carbon composites with CVI and resin-derived matrices were joined to Ti and Cu-clad Mo using a number of active braze alloys. The brazed joints revealed good interfacial bonding, preferential precipitation of active elements (e.g., Ti) at the composite/braze interface. Extensive braze penetration of the inter-fiber channels in the CVI C/C composites was observed. The chemical and thermomechanical compatibility between C/C and metals at elevated temperatures is assessed. The role of residual stresses and thermal conduction in brazed C/C joints is discussed. Theoretical predictions of the effective thermal resistance suggest that composite-to-metal brazed joints may be promising for lightweight thermal management applications.
Author
CARBON-CARBON COMPOSITES; BONDING; RESIN MATRIX COMPOSITES; TITANIUM; THERMAL RESISTANCE; RESIDUAL STRESS; METAL JOINTS; CHEMICAL COMPATIBILITY; CLADDING
20090008501 NASA Glenn Research Center, Cleveland, OH, United States
Di-Isocyanate Crosslinked Aerogels with 1, 6-Bis (Trimethoxysilyl) Hexane Incorporated in Silica Backbone
Vivod, Stephanie L.; Meador, Mary Ann B.; Nguyen, Baochau N.; Quade, Derek; Randall, Jason; Perry, Renee; August 17, 2008; In English; 236th ACS National Meeting, 17 - 21 Aug. 2008, Pennsylvania, United States; Original contains color and black and white illustrations
Report No.(s): E-16914; No Copyright; Avail.: CASI: A01, Hardcopy
Avail Online: http://hdl.handle.net/2060/20090008501
Silica aerogels are desirable materials for many applications that take advantage of their light weight and low thermal conductivity. Addition of a conformal polymer coating which bonds with the amine decorated surface of the silica network improves the strength of the aerogels by as much as 200 times. Even with vast improvement in strength they still tend to undergo brittle failure due to the rigid silica backbone. We hope to increase the flexibility and elastic recovery of the silica based aerogel by altering the silica back-bone by incorporation of more flexible hexane links. To this end, we investigated the use of 1,6-bis(trimethoxysilyl)hexane (BTMSH), a polysilsesquioxane precursor3, as an additional co-reactant to prepare silica gels which were subsequently cross-linked with di-isocyanate. Previously, this approach of adding flexibility by BTMSH incorporation was demonstrated with styrene cross-linked aerogels. In our study, we varied silane concentration, mol % of silicon from BTMSH and di-isocyanate concentration by weight percent to attempt to optimize both the flexibility and the strength of the aerogels.
Author
AEROGELS; THERMAL CONDUCTIVITY; SILICON DIOXIDE; CROSSLINKING; BONDING; AMINES
20090008503 NASA Glenn Research Center, Cleveland, OH, United States
Processing and Preparation of Advanced Stirling Convertors for Extended Operation
Oriti, Salvatore M.; Cornell, Paggy A.; July 29, 2008; In English; 6th International Energy Conversion Engineering Conference (IECEC 2008), 28-30 Jul. 2008, Cleveland, OH, United States; Original contains color illustrations
Contract(s)/Grant(s): WBS 138494.04.01.01
Report No.(s): E-16916; No Copyright; Avail.: CASI: A03, Hardcopy
Avail Online: http://hdl.handle.net/2060/20090008503
The U.S. Department of Energy (DOE), Lockheed Martin Space Company (LMSC), Sunpower Inc., and NASA Glenn Research Center (GRC) have been developing an Advanced Stirling Radioisotope Generator (ASRG) for use as a power system on space science missions. This generator will make use of the free-piston Stirling convertors to achieve higher conversion efficiency than currently available alternatives. NASA GRC is supporting the development of the ASRG by providing extended operation of several Sunpower Inc. Advanced Stirling Convertors (ASCs). In the past year and a half, eight ASCs have operated in continuous, unattended mode in both air and thermal vacuum environments. Hardware, software, and procedures were developed to prepare each convertor for extended operation with intended durations on the order of tens of thousands of hours. Steps taken to prepare a convertor for long-term operation included geometry measurements, thermocouple instrumentation, evaluation of working fluid purity, evacuation with bakeout, and high purity charge. Actions were also taken to ensure the reliability of support systems, such as data acquisition and automated shutdown checkouts. Once a convertor completed these steps, it underwent short-term testing to gather baseline performance data before initiating extended operation. These tests included insulation thermal loss characterization, low-temperature checkout, and full-temperature and power demonstration. This paper discusses the facilities developed to support continuous, unattended operation, and the processing results of the eight ASCs currently on test.
Author
STIRLING CYCLE; ENERGY CONVERSION EFFICIENCY; SPACE MISSIONS; PISTON ENGINES; SUPPORT SYSTEMS; THERMOCOUPLES; THERMAL ENVIRONMENTS
20090008504 NASA Glenn Research Center, Cleveland, OH, United States
Characterization of a New Phase and Its Effect on the Work Characteristics of a Near-Stoichiometric Ni30Pt20Ti50 High-Temperature Shape Memory Alloy (HTSMA)
Garg, A.; Gaydosh, D.; Noebe, R.D.; Padula II, Santo; Bigelow, G.S.; Kaufman, M.; Kovarik, L.; Mills, M.J.; Diercks, D.; McMurray, S.; September 21, 2008; In English; International Conference for Shape Memory and Superelastic Technologies (SMST) 2008, 21 - 25 Sep. 2008, Stresa, Italy; Original contains color and black and white illustrations
Report No.(s): E-16917; Copyright; Avail.: CASI: A03, Hardcopy
A new phase observed in a nominal Ni30Pt20Ti50 (at.%) high temperature shape memory alloy has been characterized using transmission electron microscopy and 3-D atom probe tomography. This phase forms homogeneously in the B2 austenite matrix by a nucleation and growth mechanism and results in a concomitant increase in the martensitic transformation temperature of the base alloy. Although the structure of this phase typically contains a high density of faults making characterization difficult, it appears to be trigonal (-3m point group) with a(sub o) approx. 1.28 nm and c(sub o) approx. 1.4 nm. Precipitation of this phase increases the microhardness of the alloy substantially over that of the solution treated and quenched single-phase material. The effect of precipitation strengthening on the work characteristics of the alloy has been explored through load-biased strain-temperature testing in the solution-treated condition and after aging at 500 C for times ranging from 1 to 256 hours. Work output was found to increase in the aged alloy as a result of an increase in transformation strain, but was not very sensitive to aging time. The amount of permanent deformation that occurred during thermal cycling under load was small but increased with increasing aging time and stress. Nevertheless, the dimensional stability of the alloy at short aging times (1-4 hours) was still very good making it a potentially useful material for high-temperature actuator applications.
Author
SHAPE MEMORY ALLOYS; HIGH TEMPERATURE; TRANSMISSION ELECTRON MICROSCOPY; THERMAL CYCLING TESTS; DIMENSIONAL STABILITY; HEAT RESISTANT ALLOYS; AGING (METALLURGY); MARTENSITIC TRANSFORMATION
20090008505 NASA Glenn Research Center, Cleveland, OH, United States
Multidisciplinary Analysis and Optimization Generation 1 and Next Steps
Naiman, Cynthia Gutierrez; October 07, 2008; In English; Fundamental Aeronautics Program 2nd Annual Meeting, 7 - 9 Oct. 2008, Georgia, United States; Original contains color illustrations
Report No.(s): E-16918; No Copyright; Avail.: CASI: A03, Hardcopy
Avail Online: http://hdl.handle.net/2060/20090008505
The Multidisciplinary Analysis & Optimization Working Group (MDAO WG) of the Systems Analysis Design & Optimization (SAD&O) discipline in the Fundamental Aeronautics Program s Subsonic Fixed Wing (SFW) project completed three major milestones during Fiscal Year (FY)08: "Requirements Definition" Milestone (1/31/08); "GEN 1 Integrated Multi-disciplinary Toolset" (Annual Performance Goal) (6/30/08); and "Define Architecture & Interfaces for Next Generation Open Source MDAO Framework" Milestone (9/30/08). Details of all three milestones are explained including documentation available, potential partner collaborations, and next steps in FY09.
Author
SYSTEMS ANALYSIS; DESIGN OPTIMIZATION; FIXED WINGS
20090008506 NASA Glenn Research Center, Cleveland, OH, United States
Supporting Technology at GRC to Mitigate Risk as Stirling Power Conversion Transitions to Flight
Schreiber, Jeffrey G.; Thieme, Lanny G.; Wong, Wayne A.; July 28, 2008; In English; The 6th International Energy Conversion Engineering Conference (IECEC), 28 - 30 Jul. 2008, Ohio, United States; Original contains color illustrations
Report No.(s): E-16919; No Copyright; Avail.: CASI: A03, Hardcopy
Avail Online: http://hdl.handle.net/2060/20090008506
Stirling power conversion technology has been reaching more advanced levels of maturity during its development for space power applications. The current effort is in support of the Advanced Stirling Radioisotope Generator (ASRG), which is being developed by the U.S. Department of Energy (DOE), Lockheed Martin Space Systems Company (LMSSC), Sunpower Inc., and the NASA Glenn Research Center (GRC). This generator would use two high-efficiency Advanced Stirling Convertors (ASCs) to convert thermal energy from a radioisotope heat source into electricity. Of paramount importance is the reliability of the power system and as a part of this, the Stirling power convertors. GRC has established a supporting technology effort with tasks in the areas of reliability, convertor testing, high-temperature materials, structures, advanced analysis, organics, and permanent magnets. The project utilizes the matrix system at GRC to make use of resident experts in each of the aforementioned fields. Each task is intended to reduce risk and enhance reliability of the convertor as this technology transitions toward flight status. This paper will provide an overview of each task, outline the recent efforts and accomplishments, and show how they mitigate risk and impact the reliability of the ASC s and ultimately, the ASRG.
Author
STIRLING CYCLE; AEROSPACE SYSTEMS; RADIOISOTOPE HEAT SOURCES; REFRACTORY MATERIALS; THERMAL ENERGY; PERMANENT MAGNETS
20090008508 NASA Glenn Research Center, Cleveland, OH, United States
Partnership for the Revitalization of National Wind Tunnel Force Measurement Capability
Rhew, Ray D.; Skelley, Marcus L.; Woike, Mark R.; Bader, Jon B.; Marshall, Timothy J.; January 05, 2009; In English; 47th AIAA Aerosciences Conference, 5-8 Jan. 2009, Orlando, FL, United States; Original contains color illustrations
Contract(s)/Grant(s): wbs 122711.03.09.03.01
Report No.(s): E-16921; No Copyright; Avail.: CASI: A02, Hardcopy
Avail Online: http://hdl.handle.net/2060/20090008508
Lack of funding and lack of focus on research over the past several years, coupled with force measurement capabilities being decentralized and distributed across the National Aeronautics and Space Administration (NASA) research centers, has resulted in a significant erosion of (1) capability and infrastructure to produce and calibrate force measurement systems; (2) NASA s working knowledge of those systems; and (3) the quantity of high-quality, full-capability force measurement systems available for use in aeronautics testing. Simultaneously, and at proportional rates, the capability of industry to design, manufacture, and calibrate these test instruments has been eroding primarily because of a lack of investment by the aeronautics community. Technical expertise in this technology area is a core competency in aeronautics testing; it is highly specialized and experience-based, and it represents a niche market for only a few small precision instrument shops in the United States. With this backdrop, NASA s Aeronautics Test Program (ATP) chartered a team to examine the issues and risks associated with the problem, focusing specifically on strain- gage balances. The team partnered with the U.S. Air Force s Arnold Engineering Development Center (AEDC) to exploit their combined capabilities and take a national level government view of the problem. This paper describes the team s approach, its findings, and its recommendations, and the current status for revitalizing the government s balance capability with respect to designing, fabricating, calibrating, and using the instruments.
Author
WIND TUNNEL TESTS; CALIBRATING; NASA PROGRAMS; STRAIN GAGE BALANCES
20090008509 NASA Glenn Research Center, Cleveland, OH, United States
Extreme Temperature Operation of a 10 MHz Silicon Oscillator Type STCL1100
Patterson, Richard L.; Hammoud, Ahmad; [2008]; In English; Original contains color and black and white illustrations
Contract(s)/Grant(s): NNC06BA07BWBS 724297.40.43.03.01
Report No.(s): E-16922; Copyright; Avail.: CASI: A02, Hardcopy
The performance of STMicroelectronics 10 MHz silicon oscillator was evaluated under exposure to extreme temperatures. The oscillator was characterized in terms of its output frequency stability, output signal rise and fall times, duty cycle, and supply current. The effects of thermal cycling and re-start capability at extreme low and high temperatures were also investigated. The silicon oscillator chip operated well with good stability in its output frequency over the temperature region of -50 C to +130 C, a range that by far exceeded its recommended specified boundaries of -20 C to +85 C. In addition, this chip, which is a low-cost oscillator designed for use in applications where great accuracy is not required, continued to function at cryogenic temperatures as low as - 195 C but at the expense of drop in its output frequency. The STCL1100 silicon oscillator was also able to re-start at both -195 C and +130 C, and it exhibited no change in performance due to the thermal cycling. In addition, no physical damage was observed in the packaging material due to extreme temperature exposure and thermal cycling. Therefore, it can be concluded that this device could potentially be used in space exploration missions under extreme temperature conditions in microprocessor and other applications where tight clock accuracy is not critical. In addition to the aforementioned screening evaluation, additional testing, however, is required to fully establish the reliability of these devices and to determine their suitability for long-term use.
Author
MICROPROCESSORS; TEMPERATURE EFFECTS; THERMAL CYCLING TESTS; HIGH TEMPERATURE; EXPOSURE; CRYOGENIC TEMPERATURE
20090008515 NASA Marshall Space Flight Center, Huntsville, AL, United States
[Sections of Chapter 2 of PhD Dissertation 'Simulation, Kriging, and Visualization of Circular-Spatial Data']
Morphet, William J.; [2008]; In English; Original contains color and black and white illustrations
Contract(s)/Grant(s): NAS8-97238
Report No.(s): MSFC-2025; Copyright; Avail.: CASI: A02, Hardcopy
Portions of a discertation describing the circular-spatial data of the Space Shuttle Rocket Motor Nozzle is presented.
CASI
SPACE SHUTTLE BOOSTERS; SPACE SHUTTLES; SIMULATION; NOZZLE FLOW
20090008516 NASA Marshall Space Flight Center, Huntsville, AL, United States
Radiation-Hardened Electronics for Space Environments (RHESE)
Keys, Andrew S.; Adams, James H.; Patrick, Marshall C.; Johnson, Michael; Cressler, John D.; September 09, 2008; In English; AIAA Space 2008, 9 - 11 Sep. 2008, California, United States; Original contains color illustrations
Report No.(s): MSFC-2029; Copyright; Avail.: CASI: A01, Hardcopy
This conference poster explores NASA's Radiation-Hardened Electronics for Space Environments project. This project aims to advance the state of the art in high performance, radiation-hardened electronics that enable the long-term, reliable operation of a spacecraft in extreme radiation and temperature of space and the lunar surface.
CASI
RADIATION EFFECTS; RADIATION HARDENING; ELECTRONIC EQUIPMENT; NASA PROGRAMS
20090008529 NASA Marshall Space Flight Center, Huntsville, AL, United States
Magnetic Reconfiguration in CMEs/Ejective Flares
Moore, Ronald L.; Sterling, A. C.; Suess, S. T.; October 27, 2008; In English; 2008 Workshop: The Physical Processes for Energy and Plasma Transport across Magnetic Boundaries, 27-31 Oct. 2008, Huntsville, AL, United States; Original contains black and white illustrations
Report No.(s): MSFC-2045; No Copyright; Avail.: CASI: A03, Hardcopy
Avail Online: http://hdl.handle.net/2060/20090008529
We present (1) the standard concept for the large transient change in field configuration in the solar magnetic explosions that produce an ejective flare and become a coronal mass ejection (CME) and (2) an observational test of this picture of CME production. In linear span, the largest change in field configuration in these events is wrought by the CME in the outer corona and solar wind. In the outer corona, the CME is essentially a magnetic bubble that transiently pushes aside the previously radial surrounding field. The source magnetic field that explodes to become the CME is initially a closed arcade enveloping sheared and twisted sigmoid field that snakes along the polarity dividing line and forms the core of the arcade. The sigmoid field has a large store of pent-up free magnetic energy. This eventually causes the sigmoid to become unstable and to begin to erupt as a flux rope. The erupting flux rope becomes the core of the CME plasmoid. The flux rope and enveloping CME plasmoid are created and built up (given more magnetic flux) and unleashed to escape by reconnection of the legs of the erupting sigmoid and arcade. Simultaneously, this tether-cutting reconnection produces beneath the escaping plasmoid a growing coronal X-ray flare arcade rooted in two separating ribbons of chromospheric flare emission. As the unleashed CME plasmoid propels itself into the outer corona, it takes with it the top of the arcade envelope field that arches over it. The continuing reconnection finally recloses the 'opened' stretched legs of the envelope, thus restoring the pre-eruption closed-arcade field configuration. This reconnection scenario for producing the CME plasmoid implies that the magnetic flux spanned by the full-grown flare arcade nearly equals the magnetic flux in the CME plasmoid in the outer corona. We have found that a wide range of exploding source regions produce CMEs that pass this test for production by tether-cutting reconnection (Moore, Sterling, &Suess 2007, ApJ, 668,1221).
Author
CORONAL MASS EJECTION; SOLAR FLARES; SOLAR MAGNETIC FIELD; MAGNETIC FIELD RECONNECTION; PLASMAS (PHYSICS)
20090008534 NASA Marshall Space Flight Center, Huntsville, AL, United States
Ares V: Progress Towards a Heavy Lift Capability for the Moon and Beyond
Creech, Steve; September 09, 2008; In English; AIAA Space 2008, 9-11 Sep. 2008, San Diego, CA, United States; Original contains color illustrations
Report No.(s): MSFC-2050; No Copyright; Avail.: CASI: A01, Hardcopy
Avail Online: http://hdl.handle.net/2060/20090008534
NASA's new exploration initiative will again take humans beyond low Earth orbit, to the moon, and into deep space. The space agency is developing a new fleet of launch vehicles that will fulfill the national goals of replacing the Space Shuttle fleet, completing the International Space Station, establishing a permanent outpost on the moon, and eventually traveling to Mars. Separate crew and cargo vehicles emerged from mission architecture studies - the Ares I to carry the Orion crew exploration vehicle and its crew of4 to 6 astronauts, and the Ares V to carry the Altair lunar lander or other supplies to support future exploration missions. (Figure 1) These vehicles will be designed to be safe, affordable, sustainable, reliable, operable with the safety, reliability, flexibility, and operability to serve this nation's manned and unmanned exploration programs for the coming decades. This paper discusses recent and current progress on the Ares V and planned future activities.
Author
ARES 5 CARGO LAUNCH VEHICLE; CREW EXPLORATION VEHICLE; LOW EARTH ORBITS; LAUNCH VEHICLES; CARGO
20090008536 NASA Marshall Space Flight Center, Huntsville, AL, United States
Taking the Next Steps: The Ares I Crew Launch Vehicle and Ares V Cargo Launch Vehicle
Cook, Stephen A.; Vanhooser, Teresa; September 09, 2008; In English; AIAA Space 2008 Conference and Exposition, 9-11 Sep. 2008, San Diego, CA, United States; Original contains black and white illustrations
Report No.(s): MSFC-2052; No Copyright; Avail.: CASI: A01, Hardcopy
Avail Online: http://hdl.handle.net/2060/20090008536
The National Aeronautics and Space Administration (NASA)'s Constellation Program is depending on the Ares Projects Office (APO) to deliver the crew and cargo launch capabilities needed to send human explorers to the Moon, Mars, and beyond. The APO continues to make progress toward design, component testing, and early flight testing of the Ares I crew launch vehicle, as well as early design work for the Ares V cargo launch vehicle. Ares I and Ares V will form the core space launch capabilities that the United States needs to continue its pioneering tradition as a spacefaring nation (Figure 1). This paper will discuss design, fabrication, and testing progress toward building these new launch vehicles.
Author
ARES 1 LAUNCH VEHICLE; FLIGHT TESTS; LAUNCH VEHICLES; SPACECRAFT LAUNCHING; ARES 5 CARGO LAUNCH VEHICLE
20090008537 NASA Marshall Space Flight Center, Huntsville, AL, United States
Ares I-X Flight Test - The Future Begins Here
Davis, Stephan R.; September 09, 2008; In English; AIAA Space 2008, 9-11 Sep. 2008, San Diego, CA, United States; Original contains color illustrations
Report No.(s): MSFC-2051; No Copyright; Avail.: CASI: A01, Hardcopy
Avail Online: http://hdl.handle.net/2060/20090008537
In less than two years, the National Aeronautics and Space Administration (NASA) will launch the Ares I-X mission. This will be the first flight of the Ares I crew launch vehicle, which, together with the Ares V cargo launch vehicle, will eventually send humans to the Moon, Mars, and beyond. As the countdown to this first Ares mission continues, personnel from across the Ares I-X Mission Management Office (MMO) are finalizing designs and fabricating vehicle hardware for an April 2009 launch. This paper will discuss the hardware and programmatic progress of the Ares I-X mission. Like the Apollo program, the Ares launch vehicles will rely upon extensive ground, flight, and orbital testing before sending the Orion crew exploration vehicle into space with humans on board. The first flight of Ares I, designated Ares I-X, will be a suborbital development flight test. Ares I-X gives NASA its first opportunity to gather critical data about the flight dynamics of the integrated launch vehicle stack; understand how to control its roll during flight; better characterize the severe stage separation environments that the upper stage engine will experience during future operational flights; and demonstrate the first stage recovery system. NASA also will begin modifying the launch infrastructure and fine-tuning ground and mission operations, as the agency makes the transition from the Space Shuttle to the Ares/Orion system.
Author
ARES 1 LAUNCH VEHICLE; CREW EXPLORATION VEHICLE; LAUNCH VEHICLES; GROUND OPERATIONAL SUPPORT SYSTEM; ARES 5 CARGO LAUNCH VEHICLE
20090008538 NASA Marshall Space Flight Center, Huntsville, AL, United States
NASA Ares I Crew Launch Vehicle Upper Stage Overview
McArthur, J. Craig; September 09, 2008; In English; AIAA Space 2008 Conference, 9-11 Sep. 2008, San Diego, CA, United States; Original contains color illustrations
Report No.(s): MSFC-2053; No Copyright; Avail.: CASI: A02, Hardcopy
Avail Online: http://hdl.handle.net/2060/20090008538
By incorporating rigorous engineering practices, innovative manufacturing processes and test techniques, a unique multi-center government/contractor partnership, and a clean-sheet design developed around the primary requirements for the International Space Station (ISS) and Lunar missions, the Upper Stage Element of NASA's Crew Launch Vehicle (CLV), the "Ares I," is a vital part of the Constellation Program's transportation system. Constellation's exploration missions will include Ares I and Ares V launch vehicles required to place crew and cargo in low-Earth orbit (LEO), crew and cargo transportation systems required for human space travel, and transportation systems and scientific equipment required for human exploration of the Moon and Mars. Early Ares I configurations will support ISS re-supply missions. A self-supporting cylindrical structure, the Ares I Upper Stage will be approximately 84' long and 18' in diameter. The Upper Stage Element is being designed for increased supportability and increased reliability to meet human-rating requirements imposed by NASA standards. The design also incorporates state-of-the-art materials, hardware, design, and integrated logistics planning, thus facilitating a supportable, reliable, and operable system. With NASA retiring the Space Shuttle fleet in 2010, the success of the Ares I Project is essential to America's continued leadership in space. The first Ares I test flight, called Ares I-X, is scheduled for 2009. Subsequent test flights will continue thereafter, with the first crewed flight of the Crew Exploration Vehicle (CEV), "Orion," planned for no later than 2015. Crew transportation to the ISS will follow within the same decade, and the first Lunar excursion is scheduled for the 2020 timeframe.
Author
ARES 1 LAUNCH VEHICLE; ARES 5 CARGO LAUNCH VEHICLE; LAUNCH VEHICLES; LOW EARTH ORBITS; FLIGHT CREWS; FLIGHT TESTS
20090008541 NASA Marshall Space Flight Center, Huntsville, AL, United States
Engineering America's Current and Future Space Transportation Systems: 50 Years of Systems Engineering Innovation for Sustainable Exploration
Dmbacher, Daniel L.; Lyles, Garry M.; McConnaughey, Paul; September 29, 2008; In English; International Astronautical Congress, 29 Sep. - 3 Oct. 2008, Glasgow, United Kingdom; Original contains color illustrations
Report No.(s): MSFC-2057; No Copyright; Avail.: CASI: A01, Hardcopy
Avail Online: http://hdl.handle.net/2060/20090008541
Over the past 50 years, the National Aeronautics and Space Administration (NASA) has delivered space transportation solutions for America's complex missions, ranging from scientific payloads that expand knowledge, such as the Hubble Space Telescope, to astronauts and lunar rovers destined for voyages to the Moon. Currently, the venerable Space Shuttle, which has been in service since 1981, provides the United States' (U.S.) capability for both crew and heavy cargo to low-Earth orbit to' construct the International Space Station, before the Shuttle is retired in 2010. In the next decade, NASA will replace this system with a duo of launch vehicles: the Ares I Crew Launch Vehicle and the Ares V Cargo Launch Vehicle (Figure 1). The goals for this new system include increased safety and reliability coupled with lower operations costs that promote sustainable space exploration for decades to come. The Ares I will loft the Orion Crew Exploration Vehicle, while the heavy-lift Ares V will carry the Altair Lunar Lander and the equipment and supplies needed to construct a lunar outpost for a new generation of human and robotic space pioneers. This paper will provide details of the in-house systems engineering and vehicle integration work now being performed for the Ares I and planned for the Ares V. It will give an overview of the Ares I system-level test activities, such as the ground vibration testing that will be conducted in the Marshall Center's Dynamic Test Stand to verify the integrated vehicle stack's structural integrity and to validate computer modeling and simulation (Figure 2), as well as the main propulsion test article analysis to be conducted in the Static Test Stand. These activities also will help prove and refine mission concepts of operation, while supporting the spectrum of design and development work being performed by Marshall's Engineering Directorate, ranging from launch vehicles and lunar rovers to scientific spacecraft and associated experiments. Ultimately, fielding a robust space transportation solution that will carry international explorers and essential payloads will pave the way for a new century of scientific discovery beyond planet Earth.
Author
ARES 1 LAUNCH VEHICLE; ARES 5 CARGO LAUNCH VEHICLE; CARGO; CREW EXPLORATION VEHICLE; SPACE TRANSPORTATION; SYSTEMS ENGINEERING; PAYLOADS; NASA PROGRAMS; SPACE EXPLORATION; MISSION PLANNING
20090008542 NASA Marshall Space Flight Center, Huntsville, AL, United States
Engineering America's Future in Space: Systems Engineering Innovations for Sustainable Exploration
Dumbacher, Daniel L.; Jones, Carl P.; September 09, 2008; In English; AIAA Space 2008, 9-11 Sep. 2008, San Diego, CA, United States; Original contains color illustrations
Report No.(s): MSFC-2058; No Copyright; Avail.: CASI: A01, Hardcopy
Avail Online: http://hdl.handle.net/2060/20090008542
The National Aeronautics and Space Administration (NASA) delivers space transportation solutions for America's complex missions, ranging from scientific payloads that expand knowledge, such as the Hubble Space Telescope, to astronauts and lunar rovers destined for voyages to the Moon. Currently, the venerable Space Shuttle, which has been in service since 1981, provides U.S. capability for both crew and cargo to low-Earth orbit to construct the International Space Station, before the Shuttle is retired in 2010, as outlined in the 2006 NASA Strategic Plan. I In the next decade, NASA will replace this system with a duo of launch vehicles: the Ares I Crew Launch Vehicle/Orion Crew Exploration Vehicle and the Ares V Cargo Launch Vehicle/Altair Lunar Lander. The goals for this new system include increased safety and reliability, coupled with lower operations costs that promote sustainable space exploration over a multi-decade schedule. This paper will provide details of the in-house systems engineering and vehicle integration work now being performed for the Ares I and planned for the Ares V. It will give an overview of the Ares I system-level test activities, such as the ground vibration testing that will be conducted in the Marshall Center's Dynamic Test Stand to verify the integrated vehicle stack's structural integrity against predictions made by modern modeling and simulation analysis. It also will give information about the work in progress for the Ares I-X developmental test flight planned in 2009 to provide key data before the Ares I Critical Design Review. Activities such as these will help prove and refine mission concepts of operation, while supporting the spectrum of design and development tasks being performed by Marshall's Engineering Directorate, ranging from launch vehicles and lunar rovers to scientific spacecraft and associated experiments. Ultimately, the work performed will lead to the fielding of a robust space transportation solution that will carry international explorers and essential payloads for sustainable scientific discovery beyond planet Earth.
Derived from text
ARES 5 CARGO LAUNCH VEHICLE; NASA PROGRAMS; SPACE TRANSPORTATION; SYSTEMS ENGINEERING; ARES 1 LAUNCH VEHICLE; MISSION PLANNING
20090008543 NASA Marshall Space Flight Center, Huntsville, AL, United States
Ares I-X Flight Test - On the Fast Track to the Future
Davis, Stephan R.; Robinson, Kimberly F.; September 29, 2008; In English; International Astronautical Conference, 29 Sep. 3 Oct. 2008, Glasgow, United Kingdom; Original contains black and white illustrations
Report No.(s): MSFC-2060; No Copyright; Avail.: CASI: A01, Hardcopy
Avail Online: http://hdl.handle.net/2060/20090008543
In less than two years, the National Aeronautics and Space Administration (NASA) will launch the Ares I-X mission. This will be the first flight of the Ares I crew launch vehicle, which, together with the Ares V cargo launch vehicle, will send humans to the Moon and beyond. Personnel from the Ares I-X Mission Management Office (MMO) are finalizing designs and fabricating vehicle hardware for an April 2009 launch. Ares I-X will be a suborbital development flight test that will gather critical data about the flight dynamics of the integrated launch vehicle stack; understand how to control its roll during flight; better characterize the severe stage separation environments that the upper stage engine will experience during future flights; and demonstrate the first stage recovery system. NASA also will modify the launch infrastructure and ground and mission operations. The Ares I-X Flight Test Vehicle (FTV) will incorporate flight and mockup hardware similar in mass and weight to the operational vehicle. It will be powered by a four-segment Solid Rocket Booster (SRB), which is currently in Shuttle inventory, and will include a fifth spacer segment and new forward structures to make the booster approximately the same size and weight as the five-segment SRB. The Ares I-X flight profile will closely approximate the flight conditions that the Ares I will experience through Mach 4.5, up to approximately130,OOO feet and through maximum dynamic pressure ("Max Q") of approximately 800 pounds per square foot. Data from the Ares I-X flight will support the Ares I Critical Design Review (CDR), scheduled for 2010. Work continues on Ares I-X design and hardware fabrication. All of the individual elements are undergoing CDRs, followed by an integrated vehicle CDR in March 2008. The various hardware elements are on schedule to begin deliveries to Kennedy Space Center (KSC) in early September 2008.
Author
ARES 1 LAUNCH VEHICLE; FLIGHT TESTS; DESIGN ANALYSIS; DYNAMIC PRESSURE; NASA PROGRAMS; LAUNCH VEHICLES; FLIGHT TEST VEHICLES; GROUND OPERATIONAL SUPPORT SYSTEM; AERODYNAMICS
20090008544 NASA Marshall Space Flight Center, Huntsville, AL, United States
Building on 50 Years of Mission Operations Experience for a New Era of Space Exploration
Onken, Jay F.; Singer, Christopher E.; September 09, 2008; In English; AIAA Space 2008, 9-11 Sep. 2008, San Diego, CA, United States; Original contains color illustrations
Report No.(s): MSFC-2059; No Copyright; Avail.: CASI: A01, Hardcopy
Avail Online: http://hdl.handle.net/2060/20090008544
The U.S. National Space Policy, I the 14-nation Global Exploration Strategy,2 and the National Aeronautics and Space Administration's (NASA) 2006 Strategic Plan3 provide foundational direction for far-ranging missions, from safely flying the Space Shuttle and completing construction of the International Space Station by 2010, to fielding a next generation space transportation system consisting of the Ares I Crew Launch Vehicle!Orion Crew Exploration Vehicle and the Ares V Cargo Launch Vehicle!Altair Lunar Lander (fig. 1). Transportation beyond low-Earth orbit will open the frontier for a lunar outpost, where astronauts will harness in-situ resources while exploring this 4 billion-year-old archaeological site, which may hold answers to how the Earth and its satellite were formed. Ultimately, this experience will pave the way for the first human footprint on Mars. In October 2007, NASA" announced assignments for this lunar exploration work.4 The Marshall Space Flight Center is responsible for designing, developing, testing, and evaluating the Ares I and Ares V, which are Space Shuttle derived launch vehicles, along with a number of lunar tasks. The Marshall Center's Engineering Directorate provides the skilled workforce and unique manufacturing, testing, and operational infrastructure needed to deliver space transportation solutions that meet the requirements stated in the Constellation Architecture Requirements Document (CARD). While defining design reference missions to the Station and the Moon, the CARD includes goals that include reducing recurring and nonrecurring costs, while increasing safety and reliability. For this reason, future systems are being designed with operability considerations and lifecycle expenses as independent variables in engineering trade studies.
Author
ARES 1 LAUNCH VEHICLE; ARES 5 CARGO LAUNCH VEHICLE; SPACE TRANSPORTATION SYSTEM; SPACE EXPLORATION; LUNAR EXPLORATION; LOW EARTH ORBITS; INTERNATIONAL SPACE STATION; COST REDUCTION; CARGO; NASA PROGRAMS
20090008549 Colorado Univ., Boulder, CO, United States; Helsinki Univ. of Technology, Espoo, Finland; NASA Goddard Space Flight Center, Greenbelt, MD United States; Massachusetts Inst. of Tech., Cambridge, MA, United States
Recommended Terminology for Microwave Radiometry
Randa, J.; Lahtinen, J.; Camps, A.; Gasiewski, A. J.; Hallikainen, M.; LeVine, David M.; Shiue, James; Piepmeier, Jeff; Martin-Neira, Manuel; Rosenkranz, Philip W.; Ruf, Christopher S.; Skou, Niels; Aug. 2008; In English
Report No.(s): PB2009-101694; NIST TN 1551; No Copyright; Avail.: CASI: A03, Hardcopy
Avail Online: http://hdl.handle.net/2060/20090008549
We present recommended definitions for common terms in microwave remote sensing radiometry. Terms are grouped into three chapters: General Terminology, Real- Aperture Radiometers, and Polarimetric Radiometry. An alphabetical index lists the terms that are defined and the chapters in which the definitions are located.
Author
MICROWAVE RADIOMETERS; REMOTE SENSING; TERMINOLOGY
20090008575 NASA Langley Research Center, Hampton, VA, United States
Validation of Improved Broadband Shortwave and Longwave Fluxes Derived From GOES
Khaiyer, Mandana M.; Nordeen, Michele L.; Palikonda, Rabindra; Yi, Yuhong; Minnis, Patrick; Doelling, David R.; January 11, 2009; In English; AMS 16th Conference on Satellite Meteorology and Oceanography, 11-15 Jan. 2009, Phoenix, AZ, United States; Original contains color and black and white illustrations
Contract(s)/Grant(s): 18971WBS 534173.02.07.8919.03
Report No.(s): LF99-7486; Copyright; Avail.: CASI: A02, Hardcopy
Broadband (BB) shortwave (SW) and longwave (LW) fluxes at TOA (Top of Atmosphere) are crucial parameters in the study of climate and can be monitored over large portions of the Earth's surface using satellites. The VISST (Visible Infrared Solar Split-Window Technique) satellite retrieval algorithm facilitates derivation of these parameters from the Geostationery Operational Environmental Satellites (GOES). However, only narrowband (NB) fluxes are available from GOES, so this derivation requires use of narrowband-to-broadband (NB-BB) conversion coefficients. The accuracy of these coefficients affects the validity of the derived broadband (BB) fluxes. Most recently, NB-BB fits were re-derived using the NB fluxes from VISST/GOES data with BB fluxes observed by the CERES (Clouds and the Earth's Radiant Energy Budget) instrument aboard Terra, a sun-synchronous polar-orbiting satellite that crosses the equator at 10:30 LT. Subsequent comparison with ARM's (Atmospheric Radiation Measurement) BBHRP (Broadband Heating Rate Profile) BB fluxes revealed that while the derived broadband fluxes agreed well with CERES near the Terra overpass times, the accuracy of both LW and SW fluxes decreased farther away from the overpass times. Terra's orbit hampers the ability of the NB-BB fits to capture diurnal variability. To account for this in the LW, seasonal NB-BB fits are derived separately for day and night. Information from hourly SW BB fluxes from the Meteosat-8 Geostationary Earth Radiation Budget (GERB) is employed to include samples over the complete solar zenith angle (SZA) range sampled by Terra. The BB fluxes derived from these improved NB-BB fits are compared to BB fluxes computed with a radiative transfer model.
Author
BROADBAND; NARROWBAND; RADIANT FLUX DENSITY; EARTH ATMOSPHERE; GEOPHYSICS; GOES 8; REMOTE SENSING; DATA RETRIEVAL; ALGORITHMS
20090008629 NASA, Washington, DC, United States
NASA Tech Briefs, February 2009
February 2009; In English; Original contains color and black and white illustrations
Copyright; Avail.: CASI: A03, Hardcopy
Tech Briefs are short announcements of innovations originating from research and development activities of the National Aeronautics and Space Administration. They emphasize information considered likely to be transferable across industrial, regional, or disciplinary lines and are issued to encourage commercial application. Topics covered include: Measuring Low Concentrations of Liquid Water in Soil; The Mars Science Laboratory Touchdown Test Facility; Non-Contact Measurement of Density and Thickness Variation in Dielectric Materials; Compact Microwave Fourier Spectrum Analyzer; InP Heterojunction Bipolar Transistor Amplifiers to 255 GHz; Combinatorial Generation of Test Suites; In-Phase Power-Combined Frequency Tripler at 300 GHz; Electronic System for Preventing Airport Runway Incursions; Smaller but Fully Functional Backshell for Cable Connector; Glove-Box or Desktop Virtual-Reality System; Composite Layer Manufacturing with Fewer Interruptions; Improved Photoresist Coating for Making CNT Field Emitters; A Simplified Diagnostic Method for Elastomer Bond Durability; Complex Multifunctional Polymer/Carbon-Nanotube Composites; Very High Output Thermoelectric Devices Based on ITO Nanocomposites; Reducing Unsteady Loads on a Piggyback Miniature Submarine; Ultrasonic/Sonic Anchor; Grooved Fuel Rings for Nuclear Thermal Rocket Engines; Pulsed Operation of an Ion Accelerator; Autonomous Instrument Placement for Mars Exploration Rovers; Mission and Assets Database; TCP/IP Interface for the Satellite Orbit Analysis Program (SOAP); Trajectory Calculator for Finite-Radius Cutter on a Lathe; Integrated System Health Management Development Toolkit.
Author
BIPOLAR TRANSISTORS; CARBON NANOTUBES; COMBINATORIAL ANALYSIS; DIELECTRICS; HETEROJUNCTIONS; ION ACCELERATORS; SOFTWARE DEVELOPMENT TOOLS; THERMOELECTRICITY; SYSTEMS INTEGRATION; SYSTEMS ENGINEERING; VIRTUAL REALITY; TRANSISTOR AMPLIFIERS
20090008630 California Inst. of Tech., Pasadena, CA, United States
Mission and Assets Database
Baldwin, John; Zendejas, Silvino; Gutheinz, Sandy; Borden, Chester; Wang, Yeou-Fang; NASA Tech Briefs, February 2009; February 2009; pp. 2; In English
Report No.(s): NPO-44714; Copyright; Avail.: CASI: A01, Hardcopy
Avail Online: www.techbriefs.com/component/content/article/3536
Mission and Assets Database (MADB) Version 1.0 is an SQL database system with a Web user interface to centralize information. The database stores flight project support resource requirements, view periods, antenna information, schedule, and forecast results for use in mid-range and long-term planning of Deep Space Network (DSN) assets.
Author
DATA BASES; SUPPORT SYSTEMS; SOFTWARE ENGINEERING; DATA BASE MANAGEMENT SYSTEMS; PROJECT PLANNING
20090008631 California Inst. of Tech., Pasadena, CA, United States
A Simplified Diagnostic Method for Elastomer Bond Durability
White, Paul; NASA Tech Briefs, February 2009; February 2009; pp. 17-1; In English; Original contains color illustrations
Report No.(s): NPO-43912; Copyright; Avail.: CASI: A01, Hardcopy
Avail Online: http://www.techbriefs.com/component/content/article/3538
A simplified method has been developed for determining bond durability under exposure to water or high humidity conditions. It uses a small number of test specimens with relatively short times of water exposure at elevated temperature. The method is also gravimetric; the only equipment being required is an oven, specimen jars, and a conventional laboratory balance.
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ELASTOMERS; BONDING; ADHESION TESTS
20090008632 NASA Stennis Space Center, Stennis Space Center, MS, United States
Integrated System Health Management Development Toolkit
Figueroa, Jorge; Smith, Harvey; Morris, Jon; NASA Tech Briefs, February 2009; February 2009; pp. 2; In English
Report No.(s): SSC-00255-1; Copyright; Avail.: CASI: A01, Hardcopy
Avail Online: www.techbriefs.com/component/content/article/3533
This software toolkit is designed to model complex systems for the implementation of embedded Integrated System Health Management (ISHM) capability, which focuses on determining the condition (health) of every element in a complex system (detect anomalies, diagnose causes, and predict future anomalies), and to provide data, information, and knowledge (DIaK) to control systems for safe and effective operation.
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SYSTEMS INTEGRATION; SYSTEMS HEALTH MONITORING; SOFTWARE RELIABILITY
20090008633 Northrop Grumman Corp., United States
InP Heterojunction Bipolar Transistor Amplifiers to 255 GHz
Radisic, Vesna; Sawdai, Donald; Scott, Dennis; Deal, William; Dang, Linh; Li, Danny; Cavus, Abdullah; To, Richard; Lai, Richard; NASA Tech Briefs, February 2009; February 2009; pp. 8-; In English; Original contains color illustrations
Contract(s)/Grant(s): W911QX-06-C-0050
Report No.(s): NPO-45465; Copyright; Avail.: CASI: A01, Hardcopy
Avail Online: www.techbriefs.com/component/content/article/3526
Two single-stage InP heterojunction bipolar transistor (HBT) amplifiers operate at 184 and 255 GHz, using Northrop Grumman Corporation s InP HBT MMIC (monolithic microwave integrated circuit) technology. At the time of this reporting, these are reported to be the highest HBT amplifiers ever created. The purpose of the amplifier design is to evaluate the technology capability for high-frequency designs and verify the model for future development work.
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AMPLIFIER DESIGN; BIPOLAR TRANSISTORS; HETEROJUNCTION DEVICES; INTEGRATED CIRCUITS; MICROWAVE CIRCUITS; TRANSISTOR AMPLIFIERS; POWER AMPLIFIERS
20090008634 California Inst. of Tech., Pasadena, CA, United States
Measuring Low Concentrations of Liquid Water in Soil
Buehler, Martin; NASA Tech Briefs, February 2009; February 2009; pp. 5-; In English; Original contains color illustrations
Report No.(s): NPO-41822; Copyright; Avail.: CASI: A01, Hardcopy
Avail Online: www.techbriefs.com/component/content/article/3521
An apparatus has been developed for measuring the low concentrations of liquid water and ice in relatively dry soil samples. Designed as a prototype of instruments for measuring the liquidwater and ice contents of Lunar and Martian soils, the apparatus could also be applied similarly to terrestrial desert soils and sands. The apparatus is a special-purpose impedance spectrometer: Its design is based on the fact that the electrical behavior of a typical soil sample is well approximated by a network of resistors and capacitors in which resistances decrease and capacitances increase (and, hence, the magnitude of impedance decreases) with increasing water content.
Author
MOISTURE CONTENT; SOIL SAMPLING; SOILS; WATER; SPECTROMETERS
20090008635 Zyvex Corp., Richardson, TX, United States
Complex Multifunctional Polymer/Carbon-Nanotube Composites
Patel, Pritesh; Balasubramaniyam, Gobinath; Chen, Jian; NASA Tech Briefs, February 2009; February 2009; pp. 1; In English; Original contains color illustrations
Report No.(s): MFS-32355-1; Copyright; Avail.: CASI: A01, Hardcopy
Avail Online: http://www.techbriefs.com/component/content/article/3540
A methodology for developing complex multifunctional materials that consist of or contain polymer/carbon-nanotube composites has been conceived. As used here, "multifunctional" signifies having additional and/or enhanced physical properties that polymers or polymer-matrix composites would not ordinarily be expected to have. Such properties include useful amounts of electrical conductivity, increased thermal conductivity, and/or increased strength. In the present methodology, these properties are imparted to a given composite through the choice and processing of its polymeric and CNT constituents.
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CARBON NANOTUBES; POLYMER MATRIX COMPOSITES
20090008636 NASA Glenn Research Center, Cleveland, OH, United States
Non-Contact Measurement of Density and Thickness Variation in Dielectric Materials
Roth, Ron; NASA Tech Briefs, February 2009; February 2009; pp. 6-; In English
Report No.(s): LEW-18262-1/3-1; Copyright; Avail.: CASI: A01, Hardcopy
Avail Online: http://www.techbriefs.com/component/docman/doc_details/3414-non-contact-mea
This non-contact, single-sided terahertz electromagnetic measurement and imaging method characterizes micro structural (e.g., spatially-lateral density) and thickness variation in dielectric (insulating) materials. This method was demonstrated for space shuttle external tank sprayed-on foam insulation and has been designed for use as an inspection method for current and future NASA thermal protection systems and other dielectric material inspection applications where no contact can be made with the sample due to fragility and it is impractical to use ultrasonic methods
Author
DIELECTRICS; ELECTROMAGNETIC MEASUREMENT; IMAGING TECHNIQUES; THICKNESS
20090008637 California Inst. of Tech., Pasadena, CA, United States
TCP/IP Interface for the Satellite Orbit Analysis Program (SOAP)
Carnright, Robert; Stodden, David; Coggi, John; NASA Tech Briefs, February 2009; February 2009; pp. 25-2; In English
Report No.(s): NPO-45056; Copyright; Avail.: CASI: A01, Hardcopy
Avail Online: http://www.techbriefs.com/component/content/article/3534
The Transmission Control Protocol/ Internet protocol (TCP/IP) interface for the Satellite Orbit Analysis Program (SOAP) provides the means for the software to establish real-time interfaces with other software. Such interfaces can operate between two programs, either on the same computer or on different computers joined by a network. The SOAP TCP/IP module employs a client/server interface where SOAP is the server and other applications can be clients. Real-time interfaces between software offer a number of advantages over embedding all of the common functionality within a single program. One advantage is that they allow each program to divide the computation labor between processors or computers running the separate applications. Secondly, each program can be allowed to provide its own expertise domain with other programs able to use this expertise.
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PROTOCOL (COMPUTERS); REAL TIME OPERATION; EXPERT SYSTEMS; SATELLITE ORBITS
20090008638 California Inst. of Tech., Pasadena, CA, United States
Compact Microwave Fourier Spectrum Analyzer
Savchenkov, Anatoliy; Matsko, Andrey; Strekalov, Dmitry; NASA Tech Briefs, February 2009; February 2009; pp. 7-; In English; Original contains color illustrations
Report No.(s): NPO-43992; Copyright; Avail.: CASI: A01, Hardcopy
Avail Online: www.techbriefs.com/component/content/article/3522
A compact photonic microwave Fourier spectrum analyzer [a Fourier-transform microwave spectrometer, (FTMWS)] with no moving parts has been proposed for use in remote sensing of weak, natural microwave emissions from the surfaces and atmospheres of planets to enable remote analysis and determination of chemical composition and abundances of critical molecular constituents in space. The instrument is based on a Bessel beam (light modes with non-zero angular momenta) fiber-optic elements. It features low power consumption, low mass, and high resolution, without a need for any cryogenics, beyond what is achievable by the current state-of-the-art in space instruments. The instrument can also be used in a wide-band scatterometer mode in active radar systems.
Author
HIGH RESOLUTION; MICROWAVE EMISSION; MICROWAVE SPECTROMETERS; REMOTE SENSING
20090008639 California Inst. of Tech., Pasadena, CA, United States
Trajectory Calculator for Finite-Radius Cutter on a Lathe
Savchenkov, Anatoliy; Strekalov, Dmitry; Yu, Nan; NASA Tech Briefs, February 2009; February 2009; pp. 2; In English
Report No.(s): NPO-45086; Copyright; Avail.: CASI: A01, Hardcopy
Avail Online: http://www.techbriefs.com/component/content/article/3537
A computer program calculates the two-dimensional trajectory (radial vs. axial position) of a finite-radius-of-curvature cutting tool on a lathe so as to cut a workpiece to a piecewise-continuous, analytically defined surface of revolution. (In the original intended application, the tool is a diamond cutter, and the workpiece is made of a crystalline material and is to be formed into an optical resonator disk.) The program also calculates an optimum cutting speed as F/L, where F is a material-dependent empirical factor and L is the effective instantaneous length of the cutting edge.
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COMPUTER PROGRAMS; LATHES; TRAJECTORIES; CUTTERS
20090008640 NASA Marshall Space Flight Center, Huntsville, AL, United States
Grooved Fuel Rings for Nuclear Thermal Rocket Engines
Emrich, William; NASA Tech Briefs, February 2009; February 2009; pp. 2; In English; Original contains color illustrations
Report No.(s): MFS-32342-1; Copyright; Avail.: CASI: A01, Hardcopy
Avail Online: http://www.techbriefs.com/component/content/article/3545
An alternative design concept for nuclear thermal rocket engines for interplanetary spacecraft calls for the use of grooved-ring fuel elements. Beyond spacecraft rocket engines, this concept also has potential for the design of terrestrial and spacecraft nuclear electric-power plants. The grooved ring fuel design attempts to retain the best features of the particle bed fuel element while eliminating most of its design deficiencies. In the grooved ring design, the hydrogen propellant enters the fuel element in a manner similar to that of the Particle Bed Reactor (PBR) fuel element.
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NUCLEAR ROCKET ENGINES; GROOVES; NUCLEAR FUEL ELEMENTS
20090008641 Paris VI Univ., France
In-Phase Power-Combined Frequency Tripler at 300 GHz
Maestrini, Alain; Ward, John; Lin, Robert; Gill, John; Lee, Choonsup; Mehdi, Imran; Javadi, Hamid; Chattopadhyay, Goutam; NASA Tech Briefs, February 2009; February 2009; pp. 1; In English
Report No.(s): NPO-45479; Copyright; Avail.: CASI: A01, Hardcopy
Avail Online: http://www.techbriefs.com/component/content/article/3527
This design starts with commercial 85- to 115-GHz sources that are amplified to as much as 250 mW using power amplifiers developed for the Herschel Space Observatory. The frequency is then tripled using a novel waveguide GaAs Schottky diode frequency tripler. This planar diode produces 26 mW at 318 GHz. Peak conversion efficiency is over 15 percent, and the measured bandwidth of about 265 - 30 GHz is limited more by the driving source than by the tripler itself. This innovation is based on an integrated circuit designed originally for a single-chip 260- to 340-GHz balanced tripler. The power-combined version has two mirror-image tripler chips that are power-combined in-phase in a single waveguide block using a compact Y-junction divider at the input waveguide, and a Y-junction combiner at the output waveguide. The tripler uses a split-block waveguide design with two independent DC bias lines.
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FREQUENCIES; POWER AMPLIFIERS; WAVEGUIDES; FREQUENCY MULTIPLIERS
20090008642 California Inst. of Tech., Pasadena, CA, United States
Pulsed Operation of an Ion Accelerator
Wirz, Richard; Gamero-Castano, Manuel; Goebel, Dan; NASA Tech Briefs, February 2009; February 2009; pp. 2; In English; Original contains color illustrations
Report No.(s): NPO-44961; Copyright; Avail.: CASI: A01, Hardcopy
Avail Online: http://www.techbriefs.com/component/content/article/3546
Electronic circuitry has been devised to enable operation of an ion accelerator in either a continuous mode or a highpeak power, low-average-power pulsed mode. In the original intended application, the ion accelerator would be used as a spacecraft thruster and the pulse mode would serve to generate small increments of impulse for precise control of trajectories and attitude. The present electronic drive circuitry generates the extraction voltage in pulses. Pulse-width modulation can affect rapid, fine control of time-averaged impulse or ion flux down to a minimum level much lower than that achievable in continuous operation.
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CIRCUITS; ION ACCELERATORS; PULSE MODULATION; SPACECRAFT PROPULSION
20090008643 California Inst. of Tech., Pasadena, CA, United States
Combinatorial Generation of Test Suites
Dvorak, Daniel L.; Barrett, Anthony C.; NASA Tech Briefs, February 2009; February 2009; pp. ; In English
Report No.(s): NPO-45921; Copyright; Avail.: CASI: A01, Hardcopy
Avail Online: www.techbriefs.com/component/content/article/3525
Testgen is a computer program that generates suites of input and configuration vectors for testing other software or software/hardware systems. As systems become ever more complex, often, there is not enough time to test systems against all possible combinations of inputs and configurations, so test engineers need to be selective in formulating test plans. Testgen helps to satisfy this need: In response to a test-suite-requirement-specification model, it generates a minimal set of test vectors that satisfies all the requirements.
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COMPUTER PROGRAMS; SOFTWARE ENGINEERING; SOFTWARE RELIABILITY; PROGRAM VERIFICATION (COMPUTERS)
20090008644 California Inst. of Tech., Pasadena, CA, United States
Improved Photoresist Coating for Making CNT Field Emitters
Toda, Risaku; Manohara, Harish; NASA Tech Briefs, February 2009; February 2009; pp. 15-1; In English; Original contains color and black and white illustrations
Report No.(s): NPO-45624; Copyright; Avail.: CASI: A01, Hardcopy
Avail Online: http://www.techbriefs.com/component/content/article/3532
An improved photoresist-coating technique has been developed for use in the fabrication of carbon-nanotube- (CNT) based field emitters is described. The improved photoresist coating technique overcomes what, heretofore, has been a major difficulty in the fabrication process.
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CARBON NANOTUBES; COATING; PHOTORESISTS; COATINGS
20090008645 NASA Marshall Space Flight Center, Huntsville, AL, United States
Electronic System for Preventing Airport Runway Incursions
Dabney, Richard; Elrod, Susan; NASA Tech Briefs, February 2009; February 2009; pp. 11-1; In English; Original contains color illustrations
Report No.(s): MFS-32307-1; Copyright; Avail.: CASI: A01, Hardcopy
Avail Online: http://www.techbriefs.com/component/content/article/3529
A proposed system of portable illuminated signs, electronic monitoring equipment, and radio-communication equipment for preventing (or taking corrective action in response to) improper entry of aircraft, pedestrians, or ground vehicles onto active airport runways is described. The main overall functions of the proposed system would be to automatically monitor aircraft ground traffic on or approaching runways and to generate visible and/or audible warnings to affected pilots, ground-vehicle drivers, and control-tower personnel when runway incursions take place.
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AIRPORTS; ELECTRONIC EQUIPMENT; RUNWAY INCURSIONS; AIRFIELD SURFACE MOVEMENTS; COLLISION AVOIDANCE; AIRPORT SURFACE DETECTION EQUIPMENT
20090008646 Hamilton Sundstrand Space Systems International, Inc., Windsor Locks, CT, United States
Smaller but Fully Functional Backshell for Cable Connector
Stephenson, Gregory; NASA Tech Briefs, February 2009; February 2009; pp. 12-1; In English; Original contains color illustrations
Report No.(s): MSC-23670-1; Copyright; Avail.: CASI: A01, Hardcopy
Avail Online: http://www.techbriefs.com/component/content/article/3528
An improved design for the backshell of a connector for a shielded, multiplewire cable reduces the size of the backshell, relative to traditional designs of backshells of otherwise identical cable connectors. Notwithstanding the reduction in size, the design provides all the functionality typically demanded of such a backshell, including (1) termination of the cable shield (that is, grounding of the shield to the backshell), (2) strain relief for the cable, and (3) protection against electromagnetic interference (EMI).
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ELECTRIC CONNECTORS; COAXIAL CABLES
20090008647 NASA Ames Research Center, Moffett Field, CA, United States
Glove-Box or Desktop Virtual-Reality System
Smith, J. D.; Boyle, R. D.; Twombly, I.; NASA Tech Briefs, February 2009; February 2009; pp. 13-1; In English; Original contains color illustrations
Report No.(s): ARC-14756-1; Copyright; Avail.: CASI: A01, Hardcopy
Avail Online: http://www.techbriefs.com/component/content/article/3530
The salient features of the optical layout of a desktop-scale virtual-reality system that is specialized for simulating a glove-box work space are depicted and described.
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SIMULATION; VIRTUAL REALITY
20090008648 NASA Langley Research Center, Hampton, VA, United States
Reducing Unsteady Loads on a Piggyback Miniature Submarine
Lin, John; NASA Tech Briefs, February 2009; February 2009; pp. 21-2; In English; Original contains color and black and white illustrations
Report No.(s): LAR-17364-1; Copyright; Avail.: CASI: A01, Hardcopy
Avail Online: http://www.techbriefs.com/component/content/article/3544
A small, simple fixture has been found to be highly effective in reducing destructive unsteady hydrodynamic loads on a miniature submarine that is attached in piggyback fashion to the top of a larger, nuclear-powered, host submarine. The fixture, denoted compact ramp, can be installed with minimal structural modification, and the use of it does not entail any change in submarine operations.
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LOADS (FORCES); SUBMARINES; STABILITY
20090008649 California Inst. of Tech., Pasadena, CA, United States
Ultrasonic/Sonic Anchor
Bar-Cohen, Yoseph; Sherrit, Stewart; NASA Tech Briefs, February 2009; February 2009; pp. 2; In English; Original contains color illustrations
Report No.(s): NPO-40827; Copyright; Avail.: CASI: A01, Hardcopy
Avail Online: http://www.techbriefs.com/component/content/article/3541
The ultrasonic/sonic anchor (U/S anchor) is an anchoring device that drills a hole for itself in rock, concrete, or other similar material. The U/S anchor is a recent addition to a series of related devices, the first of which were reported in "Ultrasonic/Sonic Drill/Corers With Integrated Sensors"
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ANCHORS (FASTENERS); DRILLS; ULTRASONICS
20090008650 NASA Glenn Research Center, Cleveland, OH, United States; Rhode Island Univ., Kingston, RI, United States
Very High Output Thermoelectric Devices Based on ITO Nanocomposites
Fralick, Gustave; Gregory, Otto J.; NASA Tech Briefs, February 2009; February 2009; pp. 1; In English; Original contains color and black and white illustrations
Report No.(s): LEW-18120-1; Copyright; Avail.: CASI: A01, Hardcopy
Avail Online: http://www.techbriefs.com/component/content/article/3539
A material having useful thermoelectric properties was synthesized by combining indium-tin-oxide (ITO) with a NiCoCrAlY alloy/alumina cermet. This material had a very large Seebeck coefficient with electromotive-force-versustemperature behavior that is considered to be excellent with respect to utility in thermocouples and other thermoelectric devices. When deposited in thin-film form, ceramic thermocouples offer advantages over precious-metal (based, variously, on platinum or rhodium) thermocouples that are typically used in gas turbines. Ceramic thermocouples exhibit high melting temperatures, chemical stability at high temperatures, and little or no electromigration. Oxide ceramics also resist oxidation better than metal thermocouples, cost substantially less than precious-metal thermocouples, and, unlike precious-metal thermocouples, do not exert catalytic effects.
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THERMOELECTRICITY; NICKEL ALUMINIDES; NANOCOMPOSITES; THERMOCOUPLES
20090008651 California Inst. of Tech., Pasadena, CA, United States
The Mars Science Laboratory Touchdown Test Facility
White, Christopher; Frankovich, John; Yates, Phillip; Wells Jr, George H.; Losey, Robert; NASA Tech Briefs, February 2009; February 2009; pp. ; In English
Report No.(s): NPO-45847; Copyright; Avail.: CASI: A01, Hardcopy
Avail Online: http://www.techbriefs.com/component/content/article/3524
In the Touchdown Test Program for the Mars Science Laboratory (MSL) mission, a facility was developed to use a full-scale rover vehicle and an overhead winch system to replicate the Skycrane landing event.
Author
MARS MISSIONS; TEST FACILITIES; TOUCHDOWN; SPACECRAFT LANDING
20090008652 California Inst. of Tech., Pasadena, CA, United States
Autonomous Instrument Placement for Mars Exploration Rovers
Leger, P. Chris; Maimone, Mark; NASA Tech Briefs, February 2009; February 2009; pp. 2; In English
Report No.(s): NPO-44820; Copyright; Avail.: CASI: A01, Hardcopy
Avail Online: http://www.techbriefs.com/component/content/article/3535
Autonomous Instrument Placement (AutoPlace) is onboard software that enables a Mars Exploration Rover to act autonomously in using its manipulator to place scientific instruments on or near designated rock and soil targets. Prior to the development of AutoPlace, it was necessary for human operators on Earth to plan every motion of the manipulator arm in a time-consuming process that included downlinking of images from the rover, analysis of images and creation of commands, and uplinking of commands to the rover. AutoPlace incorporates image analysis and planning algorithms into the onboard rover software, eliminating the need for the downlink/uplink command cycle. Many of these algorithms are derived from the existing groundbased image analysis and planning algorithms, with modifications and augmentations for onboard use.
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AUTONOMY; IMAGE ANALYSIS; COMMAND AND CONTROL; COMPUTER PROGRAMS; MARS ROVING VEHICLES
20090008653 Auburn Univ., AL, United States
Composite Layer Manufacturing with Fewer Interruptions
Jang, Bor Z.; Liu, Junhai; Chen, Shizu; NASA Tech Briefs, February 2009; February 2009; pp. 1; In English
Report No.(s): MSC-23452-1; Copyright; Avail.: CASI: A01, Hardcopy
Avail Online: http://www.techbriefs.com/component/content/article/3531
An improved version of composite layer manufacturing (CLM) has been invented. CLM is a type of solid freeform fabrication (SFF) -- an automated process in which a three-dimensional object is built up, point-by-point, through extrusion of a matrix/fiber composite-material precursor. In CLM, the translation and the extrusion operation are such that the final size and shape of the fabricated object are as specified by a computer-aided design (CAD). Sometimes, in order to achieve the desired final shape,
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COMPOSITE MATERIALS; MANUFACTURING
Additions to the NASA Aeronautics and Space Database as of 03/13/2009
20090008658 NASA Langley Research Center, Hampton, VA, United States
Differential Cross Sections for Proton-Proton Elastic Scattering
Norman, Ryan B.; Dick, Frank; Norbury, John W.; Blattnig, Steve R.; February 2009; In English; Original contains black and white illustrations
Contract(s)/Grant(s): NNL05AA05GWBS 651549.02.07.01
Report No.(s): NASA/TP-2009-215565; L-19507; LF99-5564; Copyright; Avail.: CASI: A05, Hardcopy
Proton-proton elastic scattering is investigated within the framework of the one pion exchange model in an attempt to model nucleon-nucleon interactions spanning the large range of energies important to cosmic ray shielding. A quantum field theoretic calculation is used to compute both differential and total cross sections. A scalar theory is then presented and compared to the one pion exchange model. The theoretical cross sections are compared to proton-proton scattering data to determine the validity of the models.
Author
SCATTERING CROSS SECTIONS; NUCLEON-NUCLEON INTERACTIONS; ELASTIC SCATTERING; EXTRATERRESTRIAL RADIATION
20090008659 NASA Langley Research Center, Hampton, VA, United States
OLTARIS: On-Line Tool for the Assessment of Radiation in Space
Sandridge, Chris A.; Blattnig, Steve R.; Clowdsley, Martha S.; Norbury, John; Qualis, Garry D.; Simonsen, Lisa C.; Singleterry, Robert C.; Slaba, Tony C.; Walker, Steven A.; Badavi, Francis F.; Spangler, Jan L.; Aumann, Aric R.; Lee, Kerry T.; Rutledge, Robert D.; Zapp, E. Neal; February 04, 2009; In English; NASA Human Research Program Investigators' Workshop, 4 Feb. 2009, League City, TX, United States; Original contains color illustrations
Contract(s)/Grant(s): WBS 651549.02.07.01
Report No.(s): LF99-8203; Copyright; Avail.: CASI: A01, Hardcopy
The effects of ionizing radiation on humans in space is a major technical challenge for exploration to the moon and beyond. The radiation shielding team at NASA Langley Research Center has been working for over 30 years to develop techniques that can efficiently assist the engineer throughout the entire design process. OLTARIS: On-Line Tool for the Assessment of Radiation in Space is a new NASA website (http://oltaris.larc.nasa.gov) that allows engineers and physicists to access a variety of tools and models to study the effects of ionizing space radiation on humans and shielding materials. The site is intended to be an analysis and design tool for those working radiation issues for current and future manned missions, as well as a research tool for developing advanced material and shielding concepts. The site, along with the analysis tools and models within, have been developed using strict software practices to ensure reliable and reproducible results in a production environment. They have also been developed as a modular system so that models and algorithms can be easily added or updated.
Author
IONIZING RADIATION; RADIATION EFFECTS; RADIATION SHIELDING; SPACECREWS
20090008660 NASA Langley Research Center, Hampton, VA, United States
Active Management of Flap-Edge Trailing Vortices
Greenblatt, David; Yao, Chung-Sheng; Vey, Stefan; Paschereit, Oliver C.; Meyer, Robert; June 23, 2008; In English; 4th AIAA Flow Control Conference, 23-26 Jun. 2008, Seattle, WA, United States; Original contains color and black and white illustrations
Contract(s)/Grant(s): WBS 877868.02.07.07.05.02
Report No.(s): LF99-7241; Copyright; Avail.: CASI: A03, Hardcopy
The vortex hazard produced by large airliners and increasingly larger airliners entering service, combined with projected rapid increases in the demand for air transportation, is expected to act as a major impediment to increased air traffic capacity. Significant reduction in the vortex hazard is possible, however, by employing active vortex alleviation techniques that reduce the wake severity by dynamically modifying its vortex characteristics, providing that the techniques do not degrade performance or compromise safety and ride quality. With this as background, a series of experiments were performed, initially at NASA Langley Research Center and subsequently at the Berlin University of Technology in collaboration with the German Aerospace Center. The investigations demonstrated the basic mechanism for managing trailing vortices using retrofitted devices that are decoupled from conventional control surfaces. The basic premise for managing vortices advanced here is rooted in the erstwhile forgotten hypothesis of Albert Betz, as extended and verified ingeniously by Coleman duPont Donaldson and his collaborators. Using these devices, vortices may be perturbed at arbitrarily long wavelengths down to wavelengths less than a typical airliner wingspan and the oscillatory loads on the wings, and hence the vehicle, are small. Significant flexibility in the specific device has been demonstrated using local passive and active separation control as well as local circulation control via Gurney flaps. The method is now in a position to be tested in a wind tunnel with a longer test section on a scaled airliner configuration. Alternatively, the method can be tested directly in a towing tank, on a model aircraft, a light aircraft or a full-scale airliner. The authors believed that this method will have significant appeal from an industry perspective due to its retrofit potential with little to no impact on cruise (devices tucked away in the cove or retracted); low operating power requirements; small lift oscillations when deployed in a time-dependent manner; and significant flexibility with respect to the specific devices selected.
Author
TRANSPORT AIRCRAFT; COMMERCIAL AIRCRAFT; AIR TRANSPORTATION; AIR TRAFFIC; ACTIVE CONTROL; VORTICES; FLAPPING; EDGES; CONTROL SURFACES; WAKES
20090008661 NASA Ames Research Center, Moffett Field, CA, United States
Fully Automated Single-Zone Elliptic Grid Generation for Mars Science Laboratory (MSL) Aeroshell and Canopy Geometries
kaul, Upender K.; July 2008; In English; Original contains color illustrations
Report No.(s): NASA/TM-2008-215358; A-080009; No Copyright; Avail.: CASI: A03, Hardcopy
Avail Online: http://hdl.handle.net/2060/20090008661
A procedure for generating smooth uniformly clustered single-zone grids using enhanced elliptic grid generation has been demonstrated here for the Mars Science Laboratory (MSL) geometries such as aeroshell and canopy. The procedure obviates the need for generating multizone grids for such geometries, as reported in the literature. This has been possible because the enhanced elliptic grid generator automatically generates clustered grids without manual prescription of decay parameters needed with the conventional approach. In fact, these decay parameters are calculated as decay functions as part of the solution, and they are not constant over a given boundary. Since these decay functions vary over a given boundary, orthogonal grids near any arbitrary boundary can be clustered automatically without having to break up the boundaries and the corresponding interior domains into various zones for grid generation.
Author
GRID GENERATION (MATHEMATICS); COMPUTATIONAL GRIDS; AEROSHELLS; BOUNDARIES
20090008662 NASA Ames Research Center, Moffett Field, CA, United States
Thermal Capacitance (Slug) Calorimeter Theory Including Heat Losses and Other Decaying Processes
Hightower, T. Mark; Olivares, Ricardo A.; Philippidis, Daniel; September 2008; In English; Thermal and Fluids Analysis Workshop (TFAWS) 2008, 18-22 Aug. 2008, San Jose, CA, United States; Original contains color and black and white illustrations
Report No.(s): NASA/TM-2008-215364; TFAWS 08-1001; A-080019; Copyright; Avail.: CASI: A03, Hardcopy
A mathematical model, termed the Slug Loss Model, has been developed for describing thermal capacitance (slug) calorimeter behavior when heat losses and other decaying processes are not negligible. This model results in the temperature time slope taking the mathematical form of exponential decay. When data is found to fit well to this model, it allows a heat flux value to be calculated that corrects for the losses and may be a better estimate of the cold wall fully catalytic heat flux, as is desired in arc jet testing. The model was applied to the data from a copper slug calorimeter inserted during a particularly severe high heating rate arc jet run to illustrate its use. The Slug Loss Model gave a cold wall heat flux 15% higher than the value of 2,250 W/sq cm obtained from the conventional approach to processing the data (where no correction is made for losses). For comparison, a Finite Element Analysis (FEA) model was created and applied to the same data, where conduction heat losses from the slug were simulated. The heat flux determined by the FEA model was found to be in close agreement with the heat flux determined by the Slug Loss Model.
Author
CALORIMETERS; TEMPERATURE EFFECTS; MATHEMATICAL MODELS; HEAT FLUX; FINITE ELEMENT METHOD
20090008664 NASA Glenn Research Center, Cleveland, OH, United States
Ascent Heating Thermal Analysis on the Spacecraft Adaptor (SA) Fairings and the Interface with the Crew Launch Vehicle (CLV)
Wang, Xiao-Yen; Yuko, James; Motil, Brian; January 2009; In English; 2008 Thermal and Fluids Analysis Workshop, 18-22 Aug. 2008, San Jose, CA, United States; Original contains color and black and white illustrations
Contract(s)/Grant(s): WBS 931164.03.01.02.01
Report No.(s): NASA/TM-2009-215474; TFAWS08-1008; E-16611; No Copyright; Avail.: CASI: A03, Hardcopy
Avail Online: http://hdl.handle.net/2060/20090008664
When the crew exploration vehicle (CEV) is launched, the spacecraft adaptor (SA) fairings that cover the CEV service module (SM) are exposed to aero heating. Thermal analysis is performed to compute the fairing temperatures and to investigate whether the temperatures are within the material limits for nominal ascent aero heating case. Heating rates from Thermal Environment (TE) 3 aero heating analysis computed by engineers at Marshall Space Flight Center (MSFC) are used in the thermal analysis. Both MSC Patran 2007r1b/Pthermal and C&R Thermal Desktop 5.1/Sinda models are built to validate each other. The numerical results are also compared with those reported by Lockheed Martin (LM) and show a reasonably good agreement.
Author
AERODYNAMIC HEATING; THERMAL ANALYSIS; FINITE ELEMENT METHOD; ATMOSPHERIC ENTRY; THERMAL ENVIRONMENTS
20090008665 NASA Glenn Research Center, Cleveland, OH, United States; Army Research Lab., Adelphi, MD, United States
Geometric Modeling of Inclusions as Ellipsoids
Bonacuse, Peter J.; December 2008; In English; Original contains color and black and white illustrations
Contract(s)/Grant(s): WBS 877868.02.07.03.05
Report No.(s): NASA/TM-2008-215477; ARL-TR-4566; E-16650; No Copyright; Avail.: CASI: A03, Hardcopy
Avail Online: http://hdl.handle.net/2060/20090008665
Nonmetallic inclusions in gas turbine disk alloys can have a significant detrimental impact on fatigue life. Because large inclusions that lead to anomalously low lives occur infrequently, probabilistic approaches can be utilized to avoid the excessively conservative assumption of lifing to a large inclusion in a high stress location. A prerequisite to modeling the impact of inclusions on the fatigue life distribution is a characterization of the inclusion occurrence rate and size distribution. To help facilitate this process, a geometric simulation of the inclusions was devised. To make the simulation problem tractable, the irregularly sized and shaped inclusions were modeled as arbitrarily oriented, three independent dimensioned, ellipsoids. Random orientation of the ellipsoid is accomplished through a series of three orthogonal rotations of axes. In this report, a set of mathematical models for the following parameters are described: the intercepted area of a randomly sectioned ellipsoid, the dimensions and orientation of the intercepted ellipse, the area of a randomly oriented sectioned ellipse, the depth and width of a randomly oriented sectioned ellipse, and the projected area of a randomly oriented ellipsoid. These parameters are necessary to determine an inclusion s potential to develop a propagating fatigue crack. Without these mathematical models, computationally expensive search algorithms would be required to compute these parameters.
Author
INCLUSIONS; ELLIPSOIDS; MATHEMATICAL MODELS; POSITION (LOCATION); FATIGUE LIFE
20090008668 NASA Glenn Research Center, Cleveland, OH, United States
Case Study: Using The OMG SWRADIO Profile and SDR Forum Input for NASA's Space Telecommunications Radio System
Briones, Janette C.; Handler, Louis M.; Hall, Steve C.; Reinhart, Richard C.; Kacpura, Thomas J.; January 2009; In English; Software Defi ned Radio Technical Conference and Product Exposition 2008 (SDR 08), 26-30 Oct. 2008, Washington, DC, United States; Original contains color illustrations
Contract(s)/Grant(s): WBS 439432.04.07.01
Report No.(s): NASA/TM-2009-215478; E-16654; Copyright; Avail.: CASI: A03, Hardcopy
The Space Telecommunication Radio System (STRS) standard is a Software Defined Radio (SDR) architecture standard developed by NASA. The goal of STRS is to reduce NASA s dependence on custom, proprietary architectures with unique and varying interfaces and hardware and support reuse of waveforms across platforms. The STRS project worked with members of the Object Management Group (OMG), Software Defined Radio Forum, and industry partners to leverage existing standards and knowledge. This collaboration included investigating the use of the OMG s Platform-Independent Model (PIM) SWRadio as the basis for an STRS PIM. This paper details the influence of the OMG technologies on the STRS update effort, findings in the STRS/SWRadio mapping, and provides a summary of the SDR Forum recommendations.
Author
TELECOMMUNICATION; COMPUTER SYSTEMS PROGRAMS; WAVEFORMS
20090008669 NASA Glenn Research Center, Cleveland, OH, United States
Heat Transfer Measurements for a Film Cooled Turbine Vane Cascade
Poinsatte, Philip E.; Heidmann, James D.; Thurman, Douglas R.; December 2008; In English; Gas Turbine Technical Congress and Exposition (Turbo Expo 2008), 9-13 Jun. 2008, Berlin, Germany; Original contains color and black and white illustrations
Contract(s)/Grant(s): WBS 561581.02.08.03.21.03
Report No.(s): NASA/TM-2008-215485; GT2008-50651; E-16721; No Copyright; Avail.: CASI: A03, Hardcopy
Avail Online: http://hdl.handle.net/2060/20090008669
Experimental heat transfer and pressure measurements were obtained on a large scale film cooled turbine vane cascade. The objective was to investigate heat transfer on a commercial high pressure first stage turbine vane at near engine Mach and Reynolds number conditions. Additionally blowing ratios and coolant density were also matched. Numerical computations were made with the Glenn-HT code of the same geometry and compared with the experimental results. A transient thermochromic liquid crystal technique was used to obtain steady state heat transfer data on the mid-span geometry of an instrumented vane with 12 rows of circular and shaped film cooling holes. A mixture of SF6 and Argon gases was used for film coolant to match the coolant-to-gas density ratio of a real engine. The exit Mach number and Reynolds number were 0.725 and 2.7 million respectively. Trends from the experimental heat transfer data matched well with the computational prediction, particularly for the film cooled case.
Author
HEAT TRANSFER; LIQUID CRYSTALS; GAS DENSITY; PRESSURE MEASUREMENT; FILM COOLING; TURBINES; VANES
20090008673 NASA Marshall Space Flight Center, Huntsville, AL, United States
Marshall Space Flight Center Digital Manufacturing
Arays, Edward; Phillips, Steven; October 07, 2008; In English; DELMIA North America User's Conference, 7-8 Oct. 2008, Michigan, United States; Original contains color illustrations
Report No.(s): M09-2036; MSFC-2036; Copyright; Avail.: CASI: A03, Hardcopy
This presentation highlights the history of DELMIA at MSFC; provides an overview of the Constellation Program; examines the manufacturing of Ares 1 Upper Stage; explains the digital manufacturing implementation for Ares 1 Upper Stage; and, discusses manufacturing and development problems and challenges.
Derived from text
ARES 1 UPPER STAGE; MANUFACTURING; LESSONS LEARNED
20090008674 NASA Marshall Space Flight Center, Huntsville, AL, United States
Launching to the Moon, Mars, and Beyond
Shivers, C. Herbert; September 30, 2008; In English; Presented to the Auburn Chapter of the American Institute of Aeronautics and Astronautics, 30 Sep. 2008, Alabama, United States; Original contains color illustrations
Report No.(s): M09-2037; No Copyright; Avail.: CASI: A03, Hardcopy
Avail Online: http://hdl.handle.net/2060/20090008674
This viewgraph presentation reviews the planned launching to the Moon, and Mars. It is important to build beyond the capacity to ferry astronauts and cargo to low Earth orbit. NASA is starting to design new vehicles using the past lessons to minimize cost, and technical risks. The training and education of engineers that will continue the work of designing, testing and flying the vehicles is important to NASA.
CASI
EDUCATION; ENGINEERS; LAUNCH VEHICLES; MANNED SPACE FLIGHT; SPACE EXPLORATION; NASA PROGRAMS
Additions to the NASA Aeronautics and Space Database as of 03/16/2009
20090008687 NASA Goddard Space Flight Center, Greenbelt, MD, United States
Landsat Data Continuity Mission Calibration and Validation
Markham, Brian L.; Dabney, Philip W.; Storey, James C.; Morfitt, Ron; Knight, Ed; Kvaran, Geir; Lee, Kenton; November 18, 2008; In English; The 17th William T. Pecora Memorial Remote Sensing Symposium, 18 - 20 Nov. 2008, Colorado, United States; Original contains black and white illustrations
Copyright; Avail.: CASI: A02, Hardcopy
The primary payload for the Landsat Data Continuity Mission (LDCM) is the Operational Land Imager (OLI), being built by Ball Aerospace and Technologies, under contract to NASA. The OLI has spectral bands similar to the Landsat-7 ETM+, minus the thermal band and with two new bands, a 443 nm band and 1375 nm cirrus detection band. On-board calibration systems include two solar diffusers (routine and pristine), a shutter and three sets of internal lamps (routine, backup and pristine). Being a pushbroom opposed to a whiskbroom design of ETM+, the system poses new challenges for characterization and calibration, chief among them being the large focal plane with 75000+ detectors. A comprehensive characterization and calibration plan is in place for the instrument and the data throughout the mission including Ball, NASA and the United States Geological Survey, which will take over operations of LDCM after on-orbit commissioning. Driving radiometric calibration requirements for OLI data include radiance calibration to 5% uncertainty (1 q); reflectance calibration to 3% uncertainty (1 q) and relative (detector-to-detector) calibration to 0.5% (J (r). Driving geometric calibration requirements for OLI include bandto- band registration of 4.5 meters (90% confidence), absolute geodetic accuracy of 65 meters (90% CE) and relative geodetic accuracy of 25 meters (90% CE). Key spectral, spatial and radiometric characterization of the OLI will occur in thermal vacuum at Ball Aerospace. During commissioning the OLI will be characterized and calibrated using celestial (sun, moon, stars) sources and terrestrial sources. The USGS EROS ground processing system will incorporate an image assessment system similar to Landsat-7 for characterization and calibration. This system will have the added benefit that characterization data will be extracted as part of the normal image data processing, so that the characterization data available will be significantly larger than for Landsat-7 ETM+.
Author
LANDSAT SATELLITES; IMAGE ANALYSIS; SATELLITE IMAGERY; GEODETIC ACCURACY; CALIBRATING; IMAGE PROCESSING; SPECTRAL BANDS; AEROSPACE ENGINEERING
20090008689 NASA Goddard Space Flight Center, Greenbelt, MD, United States
Temporal Stability of Surface Roughness Effects on Radar Based Soil Moisture Retrieval During the Corn Growth Cycle
Joseph, A.T.; Lang, R.; O'Neill, P.E.; van der Velde, R.; Gish, T.; October 20, 2008; In English; Microwave Land Hydrology Workshop, 20 - 22 Oct. 2008, California, United States
Copyright; Avail.: CASI: A01, Hardcopy
A representative soil surface roughness parameterization needed for the retrieval of soil moisture from active microwave satellite observation is difficult to obtain through either in-situ measurements or remote sensing-based inversion techniques. Typically, for the retrieval of soil moisture, temporal variations in surface roughness are assumed to be negligible. Although previous investigations have suggested that this assumption might be reasonable for natural vegetation covers (Moran et al. 2002, Thoma et al. 2006), insitu measurements over plowed agricultural fields (Callens et al. 2006) have shown that the soil surface roughness can change considerably over time. This paper reports on the temporal stability of surface roughness effects on radar observations and soil moisture retrieved from these radar observations collected once a week during a corn growth cycle (May 10th - October 2002). The data set employed was collected during the Optimizing Production Inputs for Economic and Environmental Enhancement (OPE3) field campaign covering this 2002 corn growth cycle and consists of dual-polarized (HH and VV) L-band (1.6 GHz) acquired at view angles of 15, 35, and 55 degrees. Cross-polarized L baud radar data were also collected as part of this experiment, but are not used in the analysis reported on here. After accounting for vegetation effects on radar observations, time-invariant optimum roughness parameters were determined using the Integral Equation Method (IEM) and radar observations acquired over bare soil and cropped conditions (the complete radar data set includes entire corn growth cycle). The optimum roughness parameters, soil moisture retrieval uncertainty, temporal distribution of retrieval errors and its relationship with the weather conditions (e.g. rainfall and wind speed) have been analyzed. It is shown that over the corn growth cycle, temporal roughness variations due to weathering by rain are responsible for almost 50% of soil moisture retrieval uncertainty depending on the sensing configuration. The effects of surface roughness variations are found to be smallest for observations acquired at a view angle of 55 degrees and HH polarization. A possible explanation for this result is that at 55 degrees and HH polarization the effect of vertical surface height changes on the observed radar response are limited because the microwaves travel parallel to the incident plane and as a result will not interact directly with vertically oriented soil structures.
Author
SOIL MOISTURE; SURFACE ROUGHNESS EFFECTS; PARAMETERIZATION; SATELLITE OBSERVATION; MICROWAVES; IN SITU MEASUREMENT; REMOTE SENSING; INVERSIONS; VEGETATION
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