Fully reusable launch vehicle concepts being studied for post-Shuttle era transports present major challenges for the structural design of large propellant tankage. The dominant structural elements are internal tankage for both cryogenic and non-cryogenic propellants which must operate in a broad range of thermal environments while meeting requirements for low weight and reusability. Several approaches to integral tank design are discussed and an analysis of a hot structure honeycomb sandwich tank for a circular body vehicle is presented.


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    Title :

    Structural design of integral tankage for advanced space transportation systems


    Contributors:

    Conference:

    In: Structures, Structural Dynamics and Materials Conference ; 1982 ; New Orleans, LA


    Publication date :

    1982-01-01


    Type of media :

    Miscellaneous


    Type of material :

    No indication


    Language :

    English




    Structural design of integral tankage for advanced space transportation systems

    MACCONOCHIE, I. / DAVIS, R. / LEMESSURIER, R. | AIAA | 1982





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