Three structural concepts are studied: (1) a state-of-the-art insulated aluminum skin-stringer structure; (2) a near-art insulated evacuated aluminum-alloy honeycomb structure; and (3) an advanced evacuated Rene 41 honeycomb hot structure. Each is evaluated for its thermostructural performance for each of the flight profiles (ascent, entry, and a recall or abort). Results indicate that (1) the state-of-the-art structure encounters negligible thermal stress; (2) the near-art structure has acceptable thermal stresses; and (3) the advanced structure will have thermal stress levels above the material allowables.


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    Title :

    Thermostructural analysis of three structural concepts for reusable space vehicles


    Contributors:

    Conference:

    Conference on Advanced Technology for Future Space Systems ; 1979 ; Hampton, VA


    Publication date :

    1979-01-01


    Type of media :

    Miscellaneous


    Type of material :

    No indication


    Language :

    English





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