A Shuttle-compatible systems design based on the core concept of attachable modules for the major vehicle components is proposed. The principal features include a disposable cargo/extra-propellant tank module; a porous, radiative, back-scattering drag-brake surface material of thin silica cloth; and a lightweight carbon-composite support structure. The mission payload capability for delivery, retrieval, and combined operations is determined for a broad range of missions including NASA/DOD requirements and extending through cislunar space. The effects of finite-rate surface catalysis, negative lift, and multiple atmospheric passes in reducing the aerothermodynamic heating rates are also investigated. In addition, the structural and thermal protection problems of the drag-brake support apparatus are analyzed, and recommendations are proposed for future design refinements.


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    Title :

    Design and Performance Analysis of a Conical Aerobrake Orbital Transfer Vehicle Concept


    Contributors:

    Conference:

    Aerospace Sciences ; 1984 ; Reno, NV, United States



    Publication date :

    1985-01-01


    Type of media :

    Miscellaneous


    Type of material :

    No indication


    Language :

    English