New concept results in family of compact shapes with lift-to-drag ratios of 0.5 to 1.0; main heat shield consists of circular cone raked off at angle to provide lifting surface; afterbody is elliptical cone fitted to forecone; trim at zero angle of attack results in symmetrical flow field over forebody which makes shape amenable to reliable analysis; re-entry criteria are evaluated in terms of aerodynamic and guidance requirements for speeds up to 65, 000 fps; operational trajectories are described; for re-entry at 65, 000 fps, heat-shield weight for six man vehicle is about one-third of total vehicle weight.


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    Title :

    Configuration for re-entry from mars missions using aerobraking


    Additional title:

    J Spacecraft Rockets


    Contributors:
    Shapland, D.J. (author) / Price, D.A. (author) / Hearne, L.F. (author)

    Published in:

    Publication date :

    1965


    Size :

    7 pages


    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English


    Keywords :



    A configuration for re-entry from mars missions using aerobraking.

    Hearne, L. F. / Price, D. A. / Shapland, D. J. | NTRS | 1965


    A configuration for re-entry from mars missions using aerobraking

    HEARNE, L. F. / PRICE, D. A. / SHAPLAND, D. J. | AIAA | 1965


    Aerothermodynamic environments for Mars entry, Mars return, and lunar return aerobraking missions

    Rochelle, W. C. / Bouslog, S. A. / Ting, P. C. et al. | NTRS | 1990