Problems that occur during manned earth entry in return from planetary missions are reviewed to evaluate current technology and systems concepts; analytical results show that lift-to-drag ratio (L/D) of 0.5 provides sufficiently large entry corridor depth at velocities up to 55,000 fps to allow safe entry within capability of existing guidance and navigation systems; increase in vehicle slenderness to reduce radiant heating results in higher surface Reynolds numbers, thus increasing possibility of boundary-layer transition and attendant increase in convective heating; experimental data for ablative heat shield of Apollo command module imply that existing heat shields can provide efficient thermal protection for planetary return missions. (02636)


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    Titel :

    Manned earth entry at hyperbolic velocities


    Weitere Titelangaben:

    J Spacecraft Rockets


    Beteiligte:

    Erschienen in:

    Erscheinungsdatum :

    1968


    Format / Umfang :

    7 pages


    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Print


    Sprache :

    Englisch


    Schlagwörter :



    Look at manned entry at circular to hyperbolic velocities

    Love, E.S. / Pritchard, E.B. | Engineering Index Backfile | 1963



    A LOOK AT MANNED ENTRY AT CIRCULAR TO HYPERBOLIC VELOCITIES

    Love, E. S. / Pritchard, E. B. | NTRS | 1963


    A LOOK AT MANNED ENTRY AT CIRCULAR TO HYPERBOLIC VELOCITIES

    Love, E. S. / Pritchard, E. B. | NTRS | 1963