Scientific and Technical Aerospace Reports Volume 38 July 28, 2000

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The instrumentation funding for the Laboratory of Lightwave Technology permitted a significant extension of our experimental capabilities. The largest single item was the Purchase of a Coherent FReD Laser. DTIC Lasers; Optical Measuring Instruments 20000064685 NASA Marshall Space Flight Center, Huntsville, AL USA Performance Modeling of an Experimental Laser Propelled Lightcraft Wang, Ten-See, NASA Marshall Space Flight Center, USA; Chen, Yen-Sen, Engineering Sciences, Inc., USA; Liu, Jiwen, Engineering Sciences, Inc., USA; Myrabo, Leik N., Rensselaer Polytechnic Inst., USA; Mead, Franklin B., Jr., Air Force Research Lab., USA; [2000]; 33p; In English; 31st; Plasmadynamics and Lasers, 19-22 Jun. 2000, Denver, CO, USA; Sponsored by American Inst. of Aeronautics and Astronautics, USA; Original contains color illustrations; No Copyright; Avail: CASI; A03, Hardcopy; A01, Microfiche A computational plasma aerodynamics model is developed to study the performance of an experimental laser propelled lightcraft. The computational methodology is based on a time-accurate, three-dimensional, finite-difference, chemically reacting, unstructured grid, pressure- based formulation. The underlying physics are added and tested systematically using a building-block approach. The physics modeled include non-equilibn’um thermodynamics, non-equilibrium air-plasma finite-rate kinetics, specular ray tracing, laser beam energy absorption and equi refraction by plasma, non-equilibrium plasma radiation, and plasma resonance. A series of transient computations are performed at several laser pulse energy levels and the simulated physics are discussed and compared with those of tests and literature. The predicted coupling coefficients for the lightcraft compared reasonably well with those of tests conducted on a pendulum apparatus. Author Computational Fluid Dynamics; Coupling Coefficients; Kinetics; Models; Lasers; Propeller Drive; Plasmas (Physics) 20000064721 City Univ. of New York, Research Foundation, NY USA Optical Amplification and Nonlinear Optical Processes in Random Scattering Media Alfano, R. R.; Liu, F.; Guo, Y.; Liu, C. H.; Ying, J.; Apr. 20, 2000; 7p; In English Contract(s)/Grant(s): F49620-96-1-0004 Report No.(s): AD-A377025; CUNY-47361-00-01; No Copyright; Avail: CASI; A02, Hardcopy; A01, Microfiche The objective of the research program was to investigate nonlinear optical phenomena and optical amplification and lasing in highly scattering active and non-active random media. The aim of research was to develop a deeper fundamental understanding of light propagation in active random media for future generation of optical display, imaging techniques and laser devices. Two photon excited fluorescence and second harmonic generation tomographic imaging of biomedical tissues were demonstrated. Lasing and optical amplification from dyed active turbid media and biological tissues were explored. A feedback mechanism from scattering walls was proposed to describe lasing characteristics in random media. We have published 12 papers and submitted two patent applications. DTIC Nonlinear Optics; Lasers; Lasing; Optical Properties; Amplification; Light Scattering 20000064725 California Univ., Dept. of Electrical and Computer Engineering, Santa Barbara, CA USA Low-Power VCSEL-Based Smart Pixels With Simplified Optics Final Report, 1 Aug. 1996-31 Mar. 2000 Coldren, Larry A.; Mar. 31, 2000; 283p; In English Contract(s)/Grant(s): F49620-96-1-0342; AF Proj. 2305 Report No.(s): AD-A377066; CU-ECE-00-06; AFRL-SR-BL-TR-00-0173; No Copyright; Avail: CASI; A13, Hardcopy; A03, Microfiche Over the last four years, vast improvements have been made in the area of VCSEL technology, moving them toward integration as smart pixels. VCSEL design such as tapered oxide apertures, mirror doping schemes, and improved active regions have benefited greatly during this time period. Finally, an easy to use graphical user interface and modeling program has been developed to estimate the optical scattering losses in oxide-defined VCSELs. DTIC Semiconductor Lasers; Surface Emitting Lasers 90
37 MECHANICAL ENGINEERING �� 20000064017 NASA Marshall Space Flight Center, Huntsville, AL USA NASA Fastrac Engine Gas Generator Component Test Program and Results Dennis, Henry J., Jr., NASA Marshall Space Flight Center, USA; Sanders, T., NASA Marshall Space Flight Center, USA; [2000]; 11p; In English; 36th; 36th Joint Propulsion Conference, 17-19 Jul. 2000, Huntsville, AL, USA; Sponsored by American Inst. of Aeronautics and Astronautics, USA Report No.(s): AIAA Paper 2000-3401; Copyright Waived; Avail: CASI; A03, Hardcopy; A01, Microfiche Low cost access to space has been a long-time goal of the National Aeronautics and Space Administration (NASA). The Fastrac engine program was begun at NASA’s Marshall Space Flight Center to develop a 60,000-pound (60K) thrust, liquid oxygen/ hydrocarbon (LOX/RP), gas generator-cycle booster engine for a fraction of the cost of similar engines in existence. to achieve this goal, off-the-shelf components and readily available materials and processes would have to be used. This paper will present the Fastrac gas generator (GG) design and the component level hot-fire test program and results. The Fastrac GG is a simple, 4-piece design that uses well-defined materials and processes for fabrication. Thirty-seven component level hot-fire tests were conducted at MSFC’s component test stand #116 (TS116) during 1997 and 1998. The GG was operated at all expected operating ranges of the Fastrac engine. Some minor design changes were required to successfully complete the test program as development issues arose during the testing. The test program data results and conclusions determined that the Fastrac GG design was well on the way to meeting the requirements of NASA’s X-34 Pathfinder Program that chose the Fastrac engine as its main propulsion system. Author Gas Generators; NASA Programs; Engine Parts; Engine Tests; Engine Design; Oxygen-Hydrocarbon Rocket Engines 20000064612 NASA Glenn Research Center, Cleveland, OH USA Object Based Numerical Zooming Between the NPSS Version 1 and a 1-Dimensional Meanline High Pressure Compressor Design Analysis Code Follen, G., NASA Glenn Research Center, USA; Naiman, C., NASA Glenn Research Center, USA; auBuchon, M., Pratt and Whitney Aircraft, USA; February 2000; In English; See also 20000064579; No Copyright; Abstract Only; Available from CASI only as part of the entire parent document Within NASA’s High Performance Computing and Communication (HPCC) program, NASA Glenn Research Center is developing an environment for the analysis/design of propulsion systems for aircraft and space vehicles called the Numerical Propulsion System Simulation (NPSS). The NPSS focuses on the integration of multiple disciplines such as aerodynamics, structures, and heat transfer, along with the concept of numerical zooming between 0- Dimensional to 1-, 2-, and 3-dimensional component engine codes. The vision for NPSS is to create a ”numerical test cell” enabling full engine simulations overnight on cost-effective computing platforms. Current ”state-of-the-art” engine simulations are 0-dimensional in that there is there is no axial, radial or circumferential resolution within a given component (e.g. a compressor or turbine has no internal station designations). In these 0-dimensional cycle simulations the individual component performance characteristics typically come from a table look-up (map) with adjustments for off-design effects such as variable geometry, Reynolds effects, and clearances. Zooming one or more of the engine components to a higher order, physics-based analysis means a higher order code is executed and the results from this analysis are used to adjust the 0-dimensional component performance characteristics within the system simulation. by drawing on the results from more predictive, physics based higher order analysis codes, ”cycle” simulations are refined to closely model and predict the complex physical processes inherent to engines. As part of the overall development of the NPSS, NASA and industry began the process of defining and implementing an object class structure that enables Numerical Zooming between the NPSS Version I (0-dimension) and higher order 1-, 2- and 3-dimensional analysis codes. The NPSS Version I preserves the historical cycle engineering practices but also extends these classical practices into the area of numerical zooming for use within a companies’ design system. What follows here is a description of successfully zooming I-dimensional (row-by-row) high pressure compressor results back to a NPSS engine 0-dimension simulation and a discussion of the results illustrated using an advanced data visualization tool. This type of high fidelity system-level analysis, made possible by the zooming capability of the NPSS, will 91
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Scientific and Technical Aerospace
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Introduction Scientific and Technic
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Subject Divisions Table of Contents
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ground equipment and systems. For a
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Subject Categories of the Division
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48 Oceanography 139 Includes the ph
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72 Atomic and Molecular Physics 191
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Document Availability Information T
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Avail: NASA Public Document Rooms.
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NASA CASI Price Tables — Effectiv
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ALABAMA AUBURN UNIV. AT MONTGOMERY
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��
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20000061433 Pisa Univ., Dipartiment
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English; 34th; 34th Thermophysics C
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ciency of the generated derivative
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20000063509 NASA Glenn Research Cen
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05 AIRCRAFT DESIGN, TESTING AND PER
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A long tradition of aerodynamic des
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sonic and transonic cases will be p
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20000061449 British Aerospace Publi
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20000064593 NASA Langley Research C
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performance required for a proposed
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ment cost and create better product
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tion (NPSS), is focused on the inte
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surface measurement techniques used
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with emphasis on the search for lin
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20000063520 NASA Kennedy Space Cent
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primary issues for it’s adaptatio
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Footage shows the night vertical ta
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Page 133 and 134: in Yellowstone National Park. We ar
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Page 155 and 156: We investigate the compositional di
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51 LIFE SCIENCES (GENERAL) Includes
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20000062717 Joint Inst. for Nuclear
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20000064015 Institute for Human Fac
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during 50% (SD 4%) of the breathing
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20000064711 Massachusetts Inst. of
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The analysis of this smaller data s
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vided a functional helmet mount. Th
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61 COMPUTER PROGRAMMING AND SOFTWAR
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The goal of multi-image classificat
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20000063526 Defence Science and Tec
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85 dB amplifier design evolved by o
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20000064594 New Mexico Univ., Elect
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20000064615 NASA Ames Research Cent
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declarations with a pattern recogni
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containing point where interpolatio
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has his own responsibility, while t
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the people, documents and projects
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and experimental technology, many o
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tems. In particular this applicatio
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Over the past decade, high performa
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expensive than a single analysis. I
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20000064726 Carnegie-Mellon Univ.,
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20000064099 Teledyne Brown Engineer
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20000066597 Geophysical Observatory
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20000065633 Institute TNO of Applie
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important conclusion is that for su
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est frame of the string. The modifi
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isotopes. The method and program we
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A detailed study is undertaken, usi
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20000063497 Kaiser Electro-Optics,
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delivers 60% of the x-ray flux from
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76 SOLID-STATE PHYSICS ��
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20000064660 Abdus Salam Internation
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20000067648 NASA Marshall Space Fli
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20000064703 Institute of Atomic Ene
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The BRST approach is applied to the
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20000067671 Hampton Univ., VA USA A
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82 DOCUMENTATION AND INFORMATION SC
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ecoming almost too cumbersome to be
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physical world. These are the two p
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with WFPC2 data. Tests of HSTphot
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A brief description is given of the
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20000064070 NASA Ames Research Cent
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gas, show variations that have rema
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egy, called Power In that would all
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20000064089 Smithsonian Astrophysic
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A ABERRATION, 143, 198 ABRASION, 22
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COMPRESSIBLE FLOW, 83 COMPRESSION L
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FATIGUE (MATERIALS), 50, 93, 96 FAT
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LASING, 90 LATE STARS, 224 LATITUDE
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PATCH ANTENNAS, 74 PATHOLOGY, 98 PA
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SPACE PLATFORMS, 38 SPACE PROBES, 2
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WIND PROFILES, 137 WIND TUNNEL TEST
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Brown, Andy, 38 Brown, April S., 20
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Grosvenor, C. A., 70 Grosvenor, J.
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Lu, Gui-Ying, 50 Lugg, Desmond J.,
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Robertson, Tony, 39 Robinson, Jeffr
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Warner, J. D., 63 Warren, James, 16
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Scientific and Technical Aerospace Reports Volume 38 July 28, 2000

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