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  • 1
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    An optical fixed control structure design with minimal sensitivity for a large elastic booster (1968)
    In:  CASI
    Details
    Publication Date: 2006-02-13
    Description: Optimal fixed control structure design with minimal sensitivity for large elastic booster
    Keywords: ELECTRONICS
    Type: EXTENSION OF MOD. CONTROL SYSTEM THEORY MAR. 1968 (SEE N68-23561 13-10)
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    A summary of the Skylab crew/vehicle disturbances experiment T-013 (1976)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A manned space flight experiment (designated experiment T-013) to assess the characteristics of astronaut crew-motion disturbances was conducted on the second manned Skylab mission. A brief description of the experiment hardware utilized is given, and a comprehensive discussion of the experiment data reduction and analysis is presented. Data obtained from a force-measuring system, an astronaut limb-motion measuring system, motion-picture film, and the Skylab attitude and pointing control system is described. Results show that astronaut crew members can produce significant disturbance inputs to a spacecraft's attitude control system. Total forces of up to 400 N were exerted during vigorous soaring activities, whereas ""restrained'' motions by the experiment subject generated total forces of up to 300 N. A discussion of potential applications of the experiment results is given and appendixes provide additional detail with respect to experiment operations and results.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-TN-D-8128 , L-10415
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Trajectory sensitivity of an optimal control system. (1966)
    In:  Other Sources
    Details
    Publication Date: 2019-06-27
    Description: Optimal control for linear system with respect to performance functional which includes trajectory sensitivity
    Keywords: ELECTRONICS
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    NASA TECHNICAL REPORTS
  • 4
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    Missions to Titan /1983-2000/ - An analysis of orbiters and entry vehicles (1976)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Mission Analysis data is presented which forms a basis for planning future missions to Titan, the seventh moon of Saturn. Four Titan mission options are studied: orbiters, probes, penetrators and landers. The generated data supports these mission modes. A comprehensive launch and trajectory analysis of earth to Saturn opportunities from 1983 to 2000 is given. Direct ballistic and Delta VEGA trajectory modes are evaluated. Orbital insertion, orbital trim, entry vehicle deployment options are all studied in parametric detail.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: AIAA PAPER 76-799 , Astrodynamics Conference; Aug 18, 1976 - Aug 20, 1976; San Diego, CA
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    NASA TECHNICAL REPORTS
  • 5
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    Trajectory sensitivity of an optimal control system (1968)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Trajectory sensitivity of optimal control system
    Keywords: ELECTRONICS
    Type: EXTENSION OF MOD. CONTROL SYSTEM THEORY MAR. 1968 (SEE N68-23561 13-10)
    Format: text
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    NASA TECHNICAL REPORTS
  • 6
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    Stochastic crew motion modeling. (1969)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Representative data of actual forces and moments applicable to large spacecraft attitude control system for typical crew activities obtained through simulation programs
    Keywords: FACILITIES, RESEARCH, AND SUPPORT
    Type: AIAA PAPER 69-1006 , AMERICAN INST. OF AERONAUTICS AND ASTRONAUTICS, AEROSPACE COMPUTER SYSTEMS CONFERENCE; Sep 08, 1969 - Sep 10, 1969; LOS ANGELES, CALIF.
    Format: text
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  • 7
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    Navigation and dispersion analysis for probe missions to Jupiter, Saturn, and Uranus (1973)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Probe missions to the outer planets must consider the effects of dispersions in entry and communication parameters which results from navigation and executions errors. Presented are navigation analyses and trends in entry and communication dispersions for probe missions to Jupiter, Saturn and Uranus. It is shown that the dispersions at Jupiter are dominated by execution errors while the dispersions at Uranus are totally influenced by navigation uncertainties. It is further shown that a successful probe mission to Uranus requires an optical navigation capability aboard the spacecraft to yield a reasonable entry footprint.
    Keywords: NAVIGATION
    Type: AAS PAPER 73-245 , Astrodynamics Conference; Jul 16, 1973 - Jul 18, 1973; Vail, CO; US
    Format: text
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