NASA Scientific and Technical Aerospace Reports

instrument were developed during the design process to predict the behavior of the instrument during its mission. In order to
validate those mathematical models, extensive engineering data was recorded during all phases of LITE’s mission. This
inflight engineering data was compared with preflight predictions and, when required, adjustments to the thermal and structural
models were made to more accurately match the instrument s actual behavior. The results of this process for the thermal
analysis and design of LITE are presented in this paper.
Author
Optical Radar; Space Technology Experiments; Mathematical Models; Space Platforms; Space Missions; Spacecraft
Instruments; Thermal Analysis
20040121081 NASA Langley Research Center, Hampton, VA, USA
Use of Piloted Simulation for High-Angle-of-Attack Agility Research and Design Criteria Development
Ogburn, Marilyn E.; Foster, John V.; Hoffler, Keith D.; [1991]; 21 pp.; In English; Original contains black and white
illustrations; Copyright; Avail: CASI; A03, Hardcopy
The use of piloted simulation at Langley Research Center as part of the NASA High-Angle-of-Attack Technology
Program (HATP) to provide methods and concepts for the design of advanced fighter aircraft is discussed. A major focus is
to develop the design process required to fully exploit the benefits from advanced control concepts for high-angle-of attack
agility.
Author
Angle of Attack; Design Analysis; Fighter Aircraft
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SPACECRAFT PROPULSION AND POWER
Includes main propulsion systems and components, e.g., rocket engines; and spacecraft auxiliary power sources. For related
information see also 07 Aircraft Propulsion and Power, 28 Propellants and Fuels, 15 Launch Vehicles and Launch Operations, and 44
Energy Production and Conversion.
20040111082 Utah State Univ., Logan, UT, USA
Instrumentation for Studies of Electron Emission and Charging From Insulators
Thomson, C. D.; Zavyalov, V.; Dennison, J. R.; 8th Spacecraft Charging Technology Conference; March 2004; 16 pp.; In
English; See also 20040111031; No Copyright; Avail: CASI; A03, Hardcopy
Making measurements of electron emission properties of insulators is difficult since insulators can charge either
negatively or positively under charge particle bombardment. In addition, high incident energies or high fluences can result in
modification of a material s conductivity, bulk and surface charge profile, structural makeup through bond breaking and defect
creation, and emission properties. We discuss here some of the charging difficulties associated with making insulator-yield
measurements and review the methods used in previous studies of electron emission from insulators. We present work
undertaken by our group to make consistent and accurate measurements of the electron/ion yield properties for numerous
thin-film and thick insulator materials using innovative instrumentation and techniques. We also summarize some of the
necessary instrumentation developed for this purpose including fast response, low-noise, high-sensitivity ammeters; signal
isolation and interface to standard computer data acquisition apparatus using opto-isolation, sample-and-hold, and boxcar
integration techniques; computer control, automation and timing using Labview software; a multiple sample carousel; a
pulsed, compact, low-energy, charge neutralization electron flood gun; and pulsed visible and UV light neutralization sources.
This work is supported through funding from the NASA Space Environments and Effects Program and the NASA Graduate
Research Fellowship Program.
Author
Electron Emission; Insulators; Charging; Measure and Integration
20040111106 European Space Agency. European Space Research and Technology Center, ESTEC, Noordwijk, Netherlands
Modeling of the Plasma Environment of a FEEP Micro Thruster with PicUp3D Simulation Code: Sample Results
Forest, J.; Hilgers, A.; Thiebault, B.; Popescu, A.; Fehringer, M.; 8th Spacecraft Charging Technology Conference; March
2004; 7 pp.; In English; See also 20040111031
Contract(s)/Grant(s): ESA-13590/99/NL/MV; No Copyright; Avail: CASI; A02, Hardcopy
Electric thrusters are planned to be used on a broad scale on new generation spacecraft as main propulsion engines or for
attitude and orbit control. In parallel many theoretical and experimental works about their performances and functioning are
45