Effect of vehicle shape on heat-protection weight at nominal entry velocity of 27,600 fps and effect of initial entry velocity on heat shielding of selected configuration for entry velocities between 27, 600 and 39,000 fps are studied; gas radiation is major source of gasdynamic heating during atmospheric braking, even for entry at 27, 600 fps; blunt shapes such as Apollo configuration have higher heat-protection weight requirements than finer shapes; Mars aerodynamic deceleration appears technically feasible and attractive when compared to use of retrothrust for orbiting Mars.


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    Title :

    Spacecraft heat-protection requirements for Mars aerodynamic braking


    Additional title:

    J Spacecraft Rockets


    Contributors:
    Hanley, G.M. (author) / Lyon, F.J. (author)

    Published in:

    Publication date :

    1965


    Size :

    8 pages


    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English


    Keywords :