Low-Temperature Tensile, Thermal Contraction, and Gaseous Hydrogen Permeability Data on Hydrogen-Vapor Barrier Materials
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.
KeywordsFilm Material Permeation Rate Stress Point Thermal Contraction Hydrogen Permeability
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