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  • ELECTRONICS  (1)
  • SPACECRAFT PROPULSION AND POWER  (1)
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  • 1
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    Evolutionary use of nuclear electric propulsion (1990)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Evolving new propulsion technologies through a rational and conscious effort to minimize development costs and program risks while maximizing the performance benefits is intuitively practical. A phased approach to the evolution of nuclear electric propulsion from use on planetary probes, to lunar cargo vehicles, and finally to manned Mars missions with a concomitant growth in technology is considered. Technology levels and system component makeup are discussed for nuclear power systems and both ion and magnetoplasmadynamic thrusters. Mission scenarios are described, which include analysis of a probe to Pluto, a lunar cargo mission, Martian split, all-up, and quick-trip mission options. Evolutionary progression of the use of NEP in such missions is discussed.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: AIAA PAPER 90-3821
    Format: text
    Location Call Number Expected Availability
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    NASA TECHNICAL REPORTS
  • 2
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    Pilot/vehicle control optimization using averaged operational mode and subsystem relative performance index sensitivities (1972)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: A method is presented for designing optimal feedback controllers for systems having subsystem sensitivity constraints. Such constraints reflect the presence of subsystem performance indices which are in conflict with the performance index of the overall system. The key to the approach is the use of relative performance index sensitivity (a measure of the deviation of a performance index from its optimum value). The weighted sum of subsystem and/or operational mode relative performance index sensitivies is defined as an overall performance index. A method is developed to handle linear systems with quadratic performance indices and either full or partial state feedback. The usefulness of this method is demonstrated by applying it to the design of a stability augmentation system (SAS) for a VTOL aircraft. A desirable VTOL SAS design is one that produces good VTOL transient response both with and without active pilot control. The system designed using this method is shown to effect a satisfactory compromise solution to this problem.
    Keywords: ELECTRONICS
    Type: NASA-TM-X-68041 , E-6879 , Ann. NASA - Univ. Conf. on Manual Control; May 17, 1972 - May 19, 1972; Ann Arbor, MI; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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