The general logic of a material testing program designed to test the Hermes Thermal Protection System (TPS) is described. Mission specifications during launch, orbital mission and reentry are taken into consideration in the program. Two types of materials, carbon-carbon and carbon-silicon carbide composites are selected as candidates for the TPS system. The specifications of each of these materials are presented with respect to the nominal design. Definition of antioxidation processes is discussed. Optimal material development is outlined.


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    Title :

    Materials for Hermes Hot Structural Parts: Requirements and Testing


    Contributors:
    G. Bernhart (author)

    Publication date :

    1990


    Size :

    7 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English




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