The feasibility of an aerocapture vehicle mission has been emphasized recently for inner and outer planetary missions. Aerocapture involves a system concept which utilizes aerodynamic drag to acquire the velocity reduction necessary to obtain a closed planetary orbit from a hyperbolic flyby trajectory. It has been proposed to use the atmosphere of Titan for braking into a Saturn orbit. This approach for a Saturn orbital mission is expected to cut the interplanetary cruise travel time to Saturn from 8 to 3.5 years. In connection with the preparation of such a mission, it will be necessary to provide a complete analysis of the aerodynamic environment of the Titan aerocapture vehicle. The main objective of the present investigation is, therefore, to determine the extent of convective and radiative heating for the aerocapture vehicle under different entry conditions. This can be essentially accomplished by assessing the heating rates in the stagnation and windward regions of an equivalent body.


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    Title :

    Analysis of aerothermodynamic environment of a Titan aerocapture vehicle


    Contributors:
    Tiwari, S. N. (author) / Chow, H. (author) / Moss, J. N. (author)

    Conference:

    Thermophysics of atmospheric entry; Aerospace Sciences Meeting ; 1981 ; St. Louis, MO


    Publication date :

    1982-01-01


    Type of media :

    Miscellaneous


    Type of material :

    No indication


    Language :

    English


    Keywords :