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Low-Temperature Tensile, Thermal Contraction, and Gaseous Hydrogen Permeability Data on Hydrogen-Vapor Barrier Materials

  • R. P. Caren
  • R. M. Coston
  • A. M. C. Holmes
  • F. Dubus
Part of the Advances in Cryogenic Engineering book series (ACRE, volume 10)

Abstract

Large cryogenic space-vehicle hydrogen propellant tanks may be fabricated in the future, using lightweight, filament-wound tank structures. For ultralightweight tank structures, the filament-wound tanks will be open or porous structures since complete impregnation with a filler, such as epoxy resin, will result in additional system weight. These structures, plus possible filament-wound spacecraft liquid-hydrogen piping, will require liner materials which are impervious to gaseous hydrogen if long-term storage is required. For long-term storage, a multilayer insulation system must be utilized which is thermally very efficient. Leakage of gaseous hydrogen from the stored liquid hydrogen into the surrounding multilayer insulation will seriously compromise the insulation’s effectiveness.

Keywords

Film Material Permeation Rate Stress Point Thermal Contraction Hydrogen Permeability 
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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References

  1. 1.
    A. D. Little, Inc., Report No. 65008–00–04, “Liquid Propellant Losses During Space Flight,” Final Report on NASA Contract NASw-615 (1964).Google Scholar
  2. 2.
    S. Dushman, Scientific Foundations of Vacuum Technique, J. Wiley and Sons, New York (1962).Google Scholar
  3. 3.
    R. M. Barrer, Diffusion In and Through Solids, Macmillan Company, New York (1941).Google Scholar

Copyright information

© Plenum Press, New York 1965

Authors and Affiliations

  • R. P. Caren
    • 1
  • R. M. Coston
    • 1
  • A. M. C. Holmes
    • 1
  • F. Dubus
    • 1
  1. 1.Lockheed Missiles and Space CompanySunnyvaleUSA

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