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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    Titel :

    Minimum Accommodation for Aerobrake Assembly. Phase 2: Structural Concepts for a Lunar Transfer Vehicle Aerobrake Which Can Be Assembled on Orbit


    Beteiligte:
    J. T. Dorsey (Autor:in) / J. J. Watson (Autor:in) / R. D. Tutterow (Autor:in)

    Erscheinungsdatum :

    1993


    Format / Umfang :

    38 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch





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


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    Katzberg, Steven J. / Butler, David H. / Doggett, William R. et al. | NTRS | 1991


    Structural concepts for a lunar transfer vehicle aerobrake which can be assembled on orbit

    Dorsey, John T. / Watson, Judith J. / Tutterow, Robin D. | NTRS | 1993


    Structural concepts for a lunar transfer vehicle aerobrake which can be assembled on orbit

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