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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    Titel :

    Thermostructural analysis of three structural concepts for reusable space vehicles


    Beteiligte:
    Taylor, A. H. (Autor:in) / Jackson, L. R. (Autor:in)

    Kongress:

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


    Erscheinungsdatum :

    01.01.1979


    Medientyp :

    Sonstige


    Format :

    Keine Angabe


    Sprache :

    Englisch





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