A multidisciplinary conceptual study was conducted to define a reusable Lunar transfer vehicle (LTV) aerobrake which could be launched on a Space Shuttle or Titan IV and assembled on orbit at Space Station Freedom. A major objective of this study 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. This paper describes the aerobrake segmentation concepts, the structural concepts, a joint concept for assembly, and a structural design with analysis of the aerobrake. 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 :

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


    Contributors:

    Conference:

    AIAA, Structures, Structural Dynamics and Materials Conference ; 1993 ; La Jolla, CA, United States


    Publication date :

    1993-04-01


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English