The results of a parametric study of corridor width and stagnation point heating are presented for a range of a probable mission designs and vehicle configurations. Entry velocities were varied from 6 to 10 km/s, L/Ds from 0.1 to 1.0, and ballistic coefficients from 100 to 500 kg/sq m. It is found that vehicles with an L/D of 0.4 to 0.5 provide an entry corridor width of at least 1 deg for velocities up to 10 km/s. For entry velocities below approximately 7 km/s, radiative cooling may be possible for the thermal protection system. It is recommended that, at higher entry speeds, ablative heat shields be used. Maximum integrated stagnation point heat loads were equivalent to or less than those experienced by the Space Shuttle on a typical reentry.


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    Title :

    A parametric study of manned aerocapture at Mars


    Contributors:
    Tauber, M. E. (author) / Lyne, J. E. (author) / Anagnost, A. (author)

    Conference:

    AIAA Atmospheric Flight Mechanics Conference ; 1991 ; New Orleans, LA, United States


    Publication date :

    1991-01-01


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English


    Keywords :


    Parametric study of manned aerocapture. II - Mars entry

    Lyne, J. E. / Anagnost, A. / Tauber, M. E. | NTRS | 1992


    Parametric study of manned aerocapture. II - Mars entry

    LYNE, J. E. / ANAGNOST, A. / TAUBER, M. E. | AIAA | 1992


    Parametric study of manned aerocapture. I - Earth return from Mars

    Lyne, J. E. / Tauber, M. E. / Braun, Robert D. | NTRS | 1992


    Parametric study of manned aerocapture. I - Earth return from Mars

    LYNE, J. E. / NASA, Ames Research Center / Moffett Field et al. | AIAA | 1992


    Earth return aerocapture for manned Mars missions

    Tauber, M. E. / Braun, Robert D. / Lyne, J. E. | NTRS | 1991