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Cryogenic Tankage for Chemical Space Power Systems

  • R. J. Corbett
  • J. E. Bell
  • J. M. Lester
Conference paper
Part of the Advances in Cryogenic Engineering book series (ACRE, volume 7)

Abstract

Various studies have indicated that hydrogen-oxygen propellant systems offer significant advantages over other propellants for short-time space missions. The advantages include weight savings as reflected by an excellent specific fuel consumption and an inherent ability of the cryogenic fluids to absorb large heat inputs.

Keywords

Heat Input Mass Flow Rate Tank System Heat Leak Tank Pressure 
These keywords were added by machine and not by the authors. This process is experimental and the keywords may be updated as the learning algorithm improves.

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Copyright information

© Springer Science+Business Media New York 1962

Authors and Affiliations

  • R. J. Corbett
    • 1
  • J. E. Bell
    • 1
  • J. M. Lester
    • 1
  1. 1.Beech Aircraft CorporationBoulderUSA

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