A multidisciplinary conceptual study was conducted to define a reusable lunar transfer vehicle (LTV) aerobrake which could be launched on a Space Shuttle of Titan 4 and assembled on orbit at Space Station Freedom. A major objective was to design an aerobrake, with integrated structure and thermal protection systems, which has a mass less than 20 percent (9040 lb) of the LTV lunar return mass. The aerobrake segmentation concepts, the structural concepts, a joint concept for assembly, and a structural design with analysis of the aerobrake are described. Results show that a 50-foot diameter LTV aerobrake can be designed for on-orbit assembly which will achieve the 20 percent mass budget.


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    Title :

    Minimum accommodation for aerobrake assembly. Phase 2: Structural concepts for a lunar transfer vehicle aerobrake which can be assembled on orbit


    Contributors:

    Publication date :

    1993-10-01


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English





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    DORSEY, JOHN / WATSON, JUDITH / TUTTEROW, ROBIN | AIAA | 1993


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    Dorsey, J.T. / Watson, J.J. / Tutterow, R. | Tema Archive | 1993