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  • SPACECRAFT DESIGN, TESTING AND PERFORMANCE
  • 1980-1984  (42)
  • 1970-1974  (23)
  • 1940-1944
  • 1981  (42)
  • 1974  (23)
  • 1
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    Study of providing omnidirectional vibration isolation to entire space shuttle payload packages (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Techniques to provide omnidirectional vibration isolation for a space shuttle payload package were investigated via a reduced-scale model. Development, design, fabrication, assembly and test evaluation of a 0.125-scale isolation model are described. Final drawings for fabricated mechanical components are identified, and prints of all drawings are included.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-132550
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Space payload dynamic testing (1974)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: More cost effective methods for insuring payload reliability are required to efficiently utilize the projected payload capacity of future space systems such as the Space Shuttle. Studies are needed to better define the vibration environment of space vehicles to develop improved and more routine methods of testing and to develop better dynamic protection systems. Such improvements in environment definition, testing, and isolation will lead to less stringent design specification, improved payload reliability, fewer and more realistic qualification and flight acceptance tests. This paper presents current payload test philosophies, effectiveness of testing, and research needed to achieve more cost effective payload reliability for future applications.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Reliability design for vibroacoustic environments; Winter Annual Meeting; Nov 17, 1974 - Nov 21, 1974; New York, NY
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    A feasibility study of developing toroidal tanks for a spinning spacecraft (1974)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The use of toroidal tanks in an advanced Pioneer, spin-stabilized Jupiter orbiter was investigated. Fluid behavior in spinning toroids was evaluated and the need for a propellant acquisition system was established. A common surface tension acquisition system design was selected from four candidates for gas-free liquid feed to a single outlet in both MMH and N2O4 tanks. Fabrication of toroidal tanks using either titanium or aluminum alloys is feasible. Integration of two toroidal tanks with surface tension systems in place of four spherical tanks provides spacecraft weight, packaging, structural mounting, thermal control and stability advantages.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 74-1154 , American Institute of Aeronautics and Astronautics and Society of Automotive Engineers, Propulsion Conference; Oct 21, 1974 - Oct 23, 1974; San Diego, CA
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    Modeling and analysis of power processing systems: Feasibility investigation and formulation of a methodology (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A review is given of future power processing systems planned for the next 20 years, and the state-of-the-art of power processing design modeling and analysis techniques used to optimize power processing systems. A methodology of modeling and analysis of power processing equipment and systems has been formulated to fulfill future tradeoff studies and optimization requirements. Computer techniques were applied to simulate power processor performance and to optimize the design of power processing equipment. A program plan to systematically develop and apply the tools for power processing systems modeling and analysis is presented so that meaningful results can be obtained each year to aid the power processing system engineer and power processing equipment circuit designers in their conceptual and detail design and analysis tasks.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-134686 , TRW-24888-6001-RU-00
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Experimental demonstration of static shape control (1981)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Results of a microprocessor-controlled implementation of static shape control using a specially constructed flexible beam facility are presented. The discussion covers the development of shape control algorithms, adaptation of the algorithms for use with finite element models, construction of a flexible beam, characterization and calibration of the facility, development of a finite element model for the beam, and the development of computer hardware and software. It is shown that feedback control yields better results than open-loop control, and that the use of more than two sensors in the control loop has little effect on the system performance.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 81-1785 , Guidance and Control Conference; Aug 19, 1981 - Aug 21, 1981; Albuquerque, NM
    Format: text
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    NASA TECHNICAL REPORTS
  • 6
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    Effects of antenna blockage on radio frequency performance of the microwave radiometer spacecraft (1981)
    In:  CASI
    Details
    Publication Date: 2006-02-14
    Description: Radio frequency scaled models of the microwave radiometer spacecraft suspended feed concept were tested to determine the effects of aperture blockage on the antenna radiation pattern. Contributors to the uncertainty of the test measurements were evaluated, and an estimate of the blockage effects was made for comparison with the test measurements. The gain loss budget associated with reflector performance characteristics (aperture blockage, surface reflectivity, reflector roughness, and defocus) was determined.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA. Langley Research Center The Microwave Radiometer Spacecraft; p 141-165
    Format: text
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    NASA TECHNICAL REPORTS
  • 7
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    Contributions of orbital mechanics to conducting experiments in space (1981)
    In:  CASI
    Details
    Publication Date: 2006-02-14
    Description: Orbital mechanics as a discipline is principally concerned with solving the set of equations for analyzing the motion of a satellite under various conditions. This activity on the surface may not seem crucial to conducting experiments in space, but it provides insights into the way in which forces may influence these experiments. More directly, for experiments concerned with external targets, it provides predictions of the satellites's position and velcoity verus time, enabling extensive preflight planning and resulting in optimum use of on-orbit time.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Spacecraft Dyn. as Related to Lab. Expt. in Space; p 129-136
    Format: text
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    NASA TECHNICAL REPORTS
  • 8
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    Charging and discharging characteristics of a rigid solar array (1981)
    In:  Other Sources
    Details
    Publication Date: 2016-06-07
    Description: Two rigid solar array panels were subjected to a simulated geosynchronous orbit substorm environment. During the charging sequence, distributions of accumulated surface charge were measured under eclipse and sunlight conditions. Discharge events were characterized with respect to voltage pulse signatures and amplitudes on the solar array bus leads. Post-exposure analysis of the solar array panels indicated that the electrical characteristics were not degraded in spite of the substantial discharge actvity. However, significant cratering and discoloration of the Tedlar dielectric were observed.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA. Lewis Research Center Spacecraft Charging Technol., 1980; p 228-236
    Format: text
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  • 9
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    Electrostatic discharging behaviour of Kapton irradiated with electrons (1981)
    In:  Other Sources
    Details
    Publication Date: 2016-06-07
    Description: The electrostatic charging and discharging of Kapton when irradiated with monoenergetic electrons of 5 to 30 keV energy were studied. The leakage currents and rates of discharging always increased with the incident electron energy and flux, whereas the surface voltage showed a more complex behavior depending on the thickness of the material: for the thinner films it exhibited a maximum and then fell at higher energies. The surface voltage, the rate of discharging, and the peak current and total charge flow during a discharge were enhanced as the temperature was decreased from 70 C to -180 C, and were accompanied by a decreasing leakage current. Visible light or the presence of an aluminum coating on the irradiated surface caused reductions in the surface voltage and changes in the discharging characteristics. The results are discussed in terms of the leakage currents and the secondary emission of electrons. Photomicrographs taken after irradiation, and photographs of samples during irradiation, show good correlations between the positions of light flashes and of pinholes produced by the discharge arcs.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA. Lewis Research Center Spacecraft Charging Technol., 1980; p 96-114
    Format: text
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    NASA TECHNICAL REPORTS
  • 10
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    Autonomous spacecraft maintenance study group (1981)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A plan to incorporate autonomous spacecraft maintenance (ASM) capabilities into Air Force spacecraft by 1989 is outlined. It includes the successful operation of the spacecraft without ground operator intervention for extended periods of time. Mechanisms, along with a fault tolerant data processing system (including a nonvolatile backup memory) and an autonomous navigation capability, are needed to replace the routine servicing that is presently performed by the ground system. The state of the art fault handling capabilities of various spacecraft and computers are described, and a set conceptual design requirements needed to achieve ASM is established. Implementations for near term technology development needed for an ASM proof of concept demonstration by 1985, and a research agenda addressing long range academic research for an advanced ASM system for 1990s are established.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-164076 , JPL-PUB-80-88
    Format: application/pdf
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