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  • SPACECRAFT DESIGN, TESTING AND PERFORMANCE
  • 1980-1984
  • 1975-1979  (15)
  • 1970-1974
  • 1977  (15)
  • 1
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    New directions in space electronics (1977)
    In:  Other Sources
    Details
    Publication Date: 2011-08-17
    Description: Five new directions in space electronics are defined to yield improvements over present means: automated operations aimed at a tenfold reduction in mission support costs, precision pointing and control, efficient data acquisition to permit the tenfold increase in information collection needed for global coverage, real-time data management, and low-cost data distribution to allow a thousand-fold increase in information availability and space-systems effectiveness. Technological developments and resources for each of the new directions are derived from space-technology and space-theme workshops. One to two order of magnitude improvements in instrument pointing stability will be necessary for Shuttle and planetary payloads of the 1980s. Low-cost user terminals will involve technological addressing both near-term and long-term applications. NASA has reoriented its research and technology-base programs to support the goals represented by the new directions in space electronics. Numerous charts and schematic diagrams supplement the text.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Astronautics and Aeronautics; 15; Feb. 197
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Space Shuttle's orbital environment (1977)
    In:  Other Sources
    Details
    Publication Date: 2011-08-17
    Description: Variations with the solar cycle of chemical composition, density and temperature of the orbital environment of the Space Shuttle are reviewed; micrometeoroid fluxes, ionizing radiation, photon fluxes and cosmic ray bombardment to which the Shuttle will be subjected are also mentioned. In addition, gases arising from offgassing and outgassing of contaminants (at about 300 K) from the Shuttle are considered, and particulates ejected during rocket firings or from the leakage of pressurized vessels (i.e., the cabin) are taken into account.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Proceedings of the Spacecraft Charging Technology Conference: Executive Summary (1977)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Aerospace environments are reviewed in reference to spacecraft charging. Modelling, a theoretical scheme which can be used to describe the structure of the sheath around the spacecraft and to calculate the charging currents within, is discussed. Materials characterization is considered for experimental determination of the behavior of typical spacecraft materials when exposed to simulated geomagnetic substorm conditions. Materials development is also examined for controlling and minimizing spacecraft charging or at least for distributing the charge in an equipotential manner, using electrical conductive surfaces for materials exposed to space environment.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA. Lewis Res. Center Proc. of the Spacecraft Charging Technol. Conf.; p 9-20
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Post Viking planetary protection requirements study (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Past planetary quarantine requirements were reviewed in the light of present Viking data to determine the steps necessary to prevent contamination of the Martian surface on future missions. The currently used term planetary protection reflects a broader scope of understanding of the problems involved. Various methods of preventing contamination are discussed in relation to proposed projects, specifically the 1984 Rover Mission.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-155585
    Format: application/pdf
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  • 5
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    The dynamics and optimal control of spinning spacecraft and movable telescoping appendages, part A (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The problem of optimal control with a minimum time criterion as applied to a single boom system for achieving two axis control is discussed. The special case where the initial conditions are such that the system can be driven to the equilibrium state with only a single switching maneuver in the bang-bang optimal sequence is analyzed. The system responses are presented. Application of the linear regulator problem for the optimal control of the telescoping system is extended to consider the effects of measurement and plant noises. The noise uncertainties are included with an application of the estimator - Kalman filter problem. Different schemes for measuring the components of the angular velocity are considered. Analytical results are obtained for special cases, and numerical results are presented for the general case.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-152692
    Format: application/pdf
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  • 6
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    Experimental studies of the Space Shuttle payload acoustic environment (1977)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Two series of experiments were conducted to reduce the uncertainties concerning the Space Shuttle payload bay acoustic environment. Tests using a one-fifth scale model showed large changes in level below 125 Hz with the introduction of typical payloads. The changes were associated with particular acoustic modal behavior and were sensitive to the type of acoustic excitation. Another series of experiments evaluated the noise reduction of the first orbiter vehicle (OV-101). The results showed consistently greater noise reduction for grazing excitation than for diffuse excitation. The results were extrapolated to OV-102 using mass law relations and acceleration measurements.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: SAE PAPER 770973 , Aerospace Meeting; Nov 14, 1977 - Nov 17, 1977; Los Angeles, CA
    Format: text
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  • 7
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    Shuttle elevon cove aerodynamic heating by internal flow (1977)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The thermal response of the cove seal area of the Shuttle elevon wing junction is investigated in an arc heated supersonic duct. The temperature response of the seal area is measured for various seal gap widths, ambient pressures, and enthalpies to determine the dependence of internal heating on these parameters. A correlation of the results shows that the internal heating to the seal is proportional to the product of the external pressure, the gap width and the square root of the total enthalphy. Temperatures at the end of a simulated Shuttle entry compare well with predictions based on this correlation for the narrower gap widths where there is only a small pressure drop at the cove inlet. Similar predictions are made for Shuttle flight as a function of seal gap widths to determine the maximum gap width allowable, yet not exceed design temperatures on the structure.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 77-757 , Thermophysics Conference; Jun 27, 1977 - Jun 29, 1977; Albuquerque, NM
    Format: text
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  • 8
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    The dynamics and optimal control of spinning spacecraft and movable telescoping appendages, part B: Effect of gravity-gradient torques on the dynamics of a spinning spacecraft with telescoping appendages (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The effects of gravity gradient torques during boom deployment maneuvers of a spinning spacecraft are examined. Configurations where the booms extended only along the hub principal axes and where one or two booms are offset from the principal axes were considered. For the special case of symmetric deployment (principal axes booms) the stability boundaries are determined, and a stability chart is used to study the system behavior. Possible cases of instability during this type of maneuver are identified. In the second configuration an expression for gravity torque about the hub center of mass was developed. The nonlinear equations of motion are solved numerically, and the substantial influence of the gravity torque during asymmetric deployment maneuvers is indicated.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-152691
    Format: application/pdf
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  • 9
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    Evaluation of techniques for removal of spacecraft contaminants from activated carbon (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Alternative techniques for the regeneration of carbon contaminated with various spacecraft contaminants were evaluated. Four different modes of regeneration were evaluated: (1) thermal desorption via vacuum, (2) thermal desorption via nitrogen purge, (3) in-situ catalytic oxidation of adsorbed contaminants, and (4) in-situ non-catalytic oxidation of adsorbed contaminants.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-151968
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  • 10
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    Stochastic optimal attitude control of spacecraft with movable appendages (1977)
    In:  Other Sources
    Details
    Publication Date: 2019-07-27
    Description: This paper deals with the application of linear optimal control and filtering theory to control a spinning spacecraft with movable telescoping appendages. The equations of motion are linearized about the desired final state. A feedback control system is designed to maintain this final state, with plant noise and measurement noise present in the system. Analytic results are obtained for special cases and numerical results are presented for the general case.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Astrodynamics Specialist Conference; Sept. 7-9, 1977; Jackson Hole, WY; US
    Format: text
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