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  • 1
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    Space Tethers: Design Criteria (1997)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This document is prepared to provide a systematic process for the selection of tethers for space applications. Criteria arc provided for determining the strength requirement for tether missions and for mission success from tether severing due to micrometeoroids and orbital debris particle impacts. Background information of materials for use in space tethers is provided, including electricity-conducting tethers. Dynamic considerations for tether selection is also provided. Safety, quality, and reliability considerations are provided for a tether project.
    Keywords: Spacecraft Design, Testing and Performance
    Type: NASA-TM-108537 , NAS 1.15:108537
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Dynamic passivation of a spinning and tumbling satellite using free-flying teleoperators. (1973)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: A satellite will generally have some initial angular motion. Before the satellite can be retrieved, it will be necessary to null its angular rates. A method is presented for nulling the simultaneous angular rates for cylindrical and near-cylindrical satellites. It is assumed that there are no external torques acting on the satellite initially. A model is being fabricated to verify the analysis. The analysis shows that it is feasible to null the spin and tumble rates for cylindrical and near-cylindrical satellites with an arm attached to a remote manipulator unit.
    Keywords: SPACE VEHICLES
    Type: National Conference on Remotely manned systems: Exploration and operation in space; Sep 13, 1972 - Sep 15, 1972; Pasadena, CA
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Finite element analysis of the Space Shuttle Main Engine (SSME) high pressure fuel turbopump turbine blade (HPFTP) (1989)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Cracking of the turbine blades of the SSME HPFTP is studied using two- and three-dimensional finite element analysis. The development and composition of the two- and three-dimensional models are described. Analyses are conducted under the speed, pressure, and thermal load conditions that occur during the full power level of the engine. The effects of friction on the two-dimensional model are examined. The strain and life cycle data reveal that the LCF cracking in the first stage is not probable unless the effects of fit-up tolerance between the blade and rotor are present, and for the second stage it is predicted that hydrogen assisted LCF cracking will occur under the present thermal environment. Design modifications to alleviate this cracking are discussed.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: ASME/JSME Pressure Vessels and Piping Conference; Jul 23, 1989 - Jul 27, 1989; Honolulu, HI; United States
    Format: text
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    NASA TECHNICAL REPORTS
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