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  • SPACECRAFT DESIGN, TESTING AND PERFORMANCE  (42)
  • 1980-1984  (42)
  • 1955-1959
  • 1940-1944
  • 1981  (42)
  • 1
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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
  • 2
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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
  • 3
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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
  • 4
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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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    NASA TECHNICAL REPORTS
  • 5
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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
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  • 6
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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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    NASA TECHNICAL REPORTS
  • 7
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    Optimal air-breathing launch vehicle design (1981)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: A generalized two-point boundary problem methodology, similar to techniques used in deterministic optimal control studies, is applied to the design and flight analysis of a two-stage air-breathing launch vehicle. Simultaneous consideration is given to configuration and trajectory by treating geometry, dynamic discontinuities, and time-dependent flight variables all as controls to be optimized with respect to a single mathematical performance measure. While minimizing fuel consumption, inequality constraints are applied to dynamic pressure and specific force. The optimal system fuel consumption and staging Mach number are found to vary little with changes in the inequality constraints due to substantial geometry and trajectory adjustments. Staging, from an air-breathing first stage to a rocket-powered second stage, consistently occurs near Mach 3.5. The dynamic pressure bound has its most pronounced effects on vehicle geometry, particularly the air-breathing propulsion inlet area, and on the first-stage altitude profile. The specific force has its greatest influence on the second-stage thrust history.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Journal of Guidance and Control; 4; Sept
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  • 8
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    Meteoroid bumper experiment on Explorer 46 (1981)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The effectiveness of a meteoroid bumper in reducing meteoroid penetrations is discussed. The bumper reduced the penetration flux by a factor of 30 and demonstrated a weight savings of a factor of 6.9 in the material needed to resist meteoroid penetration. The method of calculating the penetration flux recommended in the NASA space vehicle design criteria for meteoroid damage assessment was found to be very conservative, and changes are suggested. The optimum distribution of material between a bumper and the main wall is discussed.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AD-A277032 , NASA-TP-1879 , L-14329
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 9
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    Distributed control of large space structures (1981)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Theoretical developments and the results of laboratory experiments are treated as they apply to active attitude and vibration control, as well as static shape control. Modern control theory was employed throughout as the method for obtaining estimation and control laws.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-164365 , JPL-PUB-81-15
    Format: application/pdf
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  • 10
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    Aerodynamic enhancement of space transportation systems (1981)
    In:  Other Sources
    Details
    Publication Date: 2019-07-27
    Description: The results of a number of recent investigations are reviewed and used to demonstrate gains in launch, orbital transfer, and planetary vehicle performance and economy that can result from the proper exploitation of aerodynamic phenomena. For launch vehicles, application of control-configured design is shown to allow substantial reduction in wing and vertical fin area (and hence, weight) while maintaining acceptable vehicle performance and control. For orbital transfer and planetary vehicles, the use of aerodynamic lift and drag to reduce retropropulsion requirements is shown to produce payload increases of up to 100 percent and to enable some planetary missions that are not feasible with all-propulsive vehicles. Finally, the application of various advanced technologies to a complete set of launch and orbit transfer vehicles in an early space industrialization mission scenario is considered.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: IAF PAPER 81-3 , International Astronautical Congress; Sept. 6-12, 1981; Rome; Italy
    Format: text
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