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  • SPACECRAFT DESIGN, TESTING AND PERFORMANCE
  • 1980-1984  (128)
  • 1975-1979  (130)
  • 11
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    Dynamics of spinning spacecraft during the deployment of flexible boom (1978)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The effect of flexibility on the dynamics of a spinning symmetrical spacecraft during the extension (or retraction) of boom-type appendages is treated by modeling the appendages as compound spherical pendula with varying lengths. Both boom stiffness and structural damping are included. For constant boom length the resulting linearized equations of motion contain periodic coefficients involving the spin frequency. A bounded transformation converts this system into a kinematically equivalent one (with only constant coefficients), whose stability is analyzed using the Kelvin-Tait-Chetaev theorem. The dynamics during extension is predicted by numerical simulation of the nonlinear equations.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 78-489 , Structures, Structural Dynamics and Materials Conference; Apr 03, 1978 - Apr 05, 1978; Bethesda, MD
    Format: text
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    NASA TECHNICAL REPORTS
  • 12
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    Development and test of two flexible cryogenic heat pipes (1976)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Results are presented for a comprehensive test program directed toward determining the physical and thermal performance of two flexible cryogenic heat pipes that can provide a highly efficient thermal link between a detector and a space radiator or other cooling system in spacecraft applications. A 100-200 K high-power heat pipe is tested with methane at 100-140 K while a 15-100 K low-temperature pipe is designed for operation with nitrogen and oxygen and is optimized for oxygen in the range 75-90 K. Parametric performance and design tradeoff studies are carried out to determine the optimum geometry and materials for the container and wicking systems. A spiral multiwrap wick in conjunction with braided bellows appears to be a workable solution to the problem of developing highly flexible heat transport devices for cryogenic applications.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 76-478 , Thermophysics Conference; Jul 14, 1976 - Jul 16, 1976; San Diego, CA
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    NASA TECHNICAL REPORTS
  • 13
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    Interactions between the orbiting Space Shuttle and the ionosphere (1984)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: This paper presents an analysis of interactions between the Space Shuttle Orbiter and the ionosphere based on thermal plasma data obtained from a Spherical Retarding Potential Analyzer (SRPA) and a Langmuir Probe (LP) flown on the third Space Shuttle flight (STS-3) in March 1982. While previous work on spacecraft-plasma interactions has dealt with wake effects, the present work deals with effects that are seen in ram conditions that have not been previously discussed. One observation is a higher degree of plasma turbulence than has been reported from unmanned spacecraft measurements that manifests itself as a frequency component at 2.2 kHz in the SRPA signal. Also seen are unusually high number densities of what appear to be ions with a mass of at least 30 or 32 amu and a temperature in the range 2000-3000 K. Coincident with the enhanced molecular ion species, the temperature of the thermal electrons is seen elevated to above 5000 K. It is hypothesized that these measurements are evidence for a plasma instability resulting from the motion of the outgassing Orbiter through the ionosphere.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Planetary and Space Science (ISSN 0032-0633); 32; 881-896
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    NASA TECHNICAL REPORTS
  • 14
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    Measurements of the thermal plasma environment of the Space Shuttle (1984)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The paper presents some initial results on measurements of the thermal plasma environment obtained by a spherical retarding potential analyzer and a Langmuir probe flown on (STS-3) as part of the NASA Office of Space Science-1 payload in March 1982. One of the major effects observed is a higher degree of turbulence in the ambient plasma compared to what is observed from similar instruments flown on unmanned satellites. In addition we see the temperature of the thermal electrons elevated to values of 4000-5000 K. Associated with elevated electron temperatures are regions of enhanced plasma density resulting from the appearance of high densities of molecular ions. The thermal plasma data also show clear effects of an induced V x B.L potential at the location of the probes which matches that produced by an L vector linking the probes to the engine nozzles; thereby establishing the prime return current location on the Orbiter. The final observations discussed are the pronounced and complex wake effects resulting both from the main structure of the Orbiter and from the complex shapes of appendages attached to the Orbiter.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Planetary and Space Science (ISSN 0032-0633); 32; 457-467
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    NASA TECHNICAL REPORTS
  • 15
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    Supporting flight data analysis for Space Shuttle Orbiter experiments at NASA Ames Research Center (1983)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The space shuttle orbiter experiments program is responsible for collecting flight data to extend the research and technology base for future aerospace vehicle design. The infrared imagery of shuttle (IRIS), catalytic surface effects, and tile gap heating experiments sponsored by Ames Research Center are part of this program. The software required to process the flight data which support these experiments is described. In addition, data analysis techniques, developed in support of the IRIS experiment, are discussed. Using the flight data base, the techniques provide information useful in analyzing and correcting problems with the experiment, and in interpreting the IRIS image obtained during the entry of the third shuttle mission.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-TM-84345 , A-9289 , NAS 1.15:84345
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 16
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    Jovian radiation and charging environment considerations in Galileo (1982)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The Galileo spacecraft which will orbit Jupiter in 1987 will encounter one of the most interesting natural environments. These include high energy radiation electrons and ions and magnetospheric plasmas. The evaluation of Galileo design commenced with a careful consideration of the plasma environment and the now standard spacecraft charging analysis. In addition the intense high energy radiation environment has necessitated the consideration of charges deposited internally to the spacecraft. This paper presents some of the analyses and the design changes which have occurred as a result of the above mentioned environmental interaction considerations.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 82-0118 , Aerospace Sciences Meeting; Jan 11, 1982 - Jan 14, 1982; Orlando, FL
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    NASA TECHNICAL REPORTS
  • 17
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    An evaluation of Space Shuttle Orbiter forward fuselage surface pressures - Comparison with wind tunnel and theoretical predictions (1983)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: In order for ground-based pressure distribution techniques to be verified by the actual performance of the Space Shuttle Orbiter in flight, a comparative study of flight pressure data and both wind tunnel and computational data is presented. The flight pressure data, obtained from measurements on the Orbiter's surface during atmospheric reentry, are part of the overall Orbiter flight data system designated Development Flight Instrumentation. Also given is an analysis of the Orbiter pressure data system, including its transducers, their behavior, and their calibration. The two analyses are the bases of an error assessment calculation for the flight data, as well as an explanation of any discrepancies between flight and ground-based data.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 83-0119 , American Institute of Aeronautics and Astronautics, Aerospace Sciences Meeting; Jan 10, 1983 - Jan 13, 1983; Reno, NV
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    NASA TECHNICAL REPORTS
  • 18
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    Measurement of vehicle potential using a mother-daughter tethered rocket (1982)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The equipment, experimental design, and results of mother-daughter tethered probes for measuring the potential of a spacecraft are described. The object was to inject a probe into the ionosphere by rocket and then lower an impedance voltage monitor-equipped section of the probe by means of a highly insulated wire. The mother probe, also carrying voltage monitors, would inject charges into the plasma that would be measured at both ends of the tether. Instrumentation on the daughter probe included voltage current monitors and a Langmuir probe, while the mother payload also carried a charge probe, floating probe, a Langmuir probe, and an impedance probe. The first launch was from Japan in 1980, and operations confirmed that Langmuir probes with area ratios less than 400:1 can produce changes in the vehicle potential if probe voltages of more than 10 V are applied in the collection mode. A ratio of 200:1 was sufficient for the daughter probe with voltages of 5 V. The experiment is concluded to verify the tethered probe method of measuring vehicle potential.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Artificial particle beams in space plasma studies; Advanced Research Institute; Apr 21, 1981 - Apr 26, 1981; Geilo; Norway
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    NASA TECHNICAL REPORTS
  • 19
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    Additional application of the NASCAP code. Volume 1: NASCAP extension (1981)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The NASCAP computer program comprehensively analyzes problems of spacecraft charging. Using a fully three dimensional approach, it can accurately predict spacecraft potentials under a variety of conditions. Several changes were made to NASCAP, and a new code, NASCAP/LEO, was developed. In addition, detailed studies of several spacecraft-environmental interactions and of the SCATHA spacecraft were performed. The NASCAP/LEO program handles situations of relatively short Debye length encountered by large space structures or by any satellite in low earth orbit (LEO).
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-165349 , SSS-R-81-4847-VOL-1
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    NASA TECHNICAL REPORTS
  • 20
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    Attitude control requirements for an earth-orbital solar electric propulsion stage (1975)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Solar Electric Propulsion Stage (SEPS) application in earth orbit requires considerably more maneuvering for thrust vector steering and solar array pointing than planetary missions. Attitude maneuver requirements for geosynchronous and low earth-orbital missions are presented. Situations which result in optimum steering torque requirements exceeding the capability of current SEPS configurations are defined. Sub-optimal steering techniques are defined which reduce the geosynchronous mission torque requirements to acceptable levels with negligible performance penalties. Some low earth-orbital flight regimes with earth shadowing are found to result in much larger torque requirements and impose significant mechanization penalties if serious performance losses are to be avoided. Alternative attitude control mechanization techniques are defined for these cases.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 75-353 , American Institute of Aeronautics and Astronautics, Electric Propulsion Conference; Mar 19, 1975 - Mar 21, 1975; New Orleans, LA
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    NASA TECHNICAL REPORTS
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