Parametric study was conducted to determine performance of soft lander using two distinct thrust levels during terminal phase of out-of-orbit entry; analysis is applicable to vehicle descending along trajectory governed by gravity turn maneuver; with residual landed fraction as performance criterion, superiority of dual thrust-level concept as compared to single thrust-level model was demonstrated and tabulated; entry conditions, atmospheric profile, ballistic coefficient, thrust levels, and entry mass were variables used in determining optimum ignition altitudes for single and dual thrust-level systems.


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    Title :

    Performance of mars soft lander with staged propulsion


    Additional title:

    J Spacecraft Rockets


    Contributors:

    Published in:

    Publication date :

    1968


    Size :

    7 pages


    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English


    Keywords :



    Performance of a Mars soft lander with staged propulsion.

    Ginsberg, L. J. / Kelley, J. H. | NTRS | 1968


    Performance of a Mars soft lander with staged propulsion.

    Ginsberg, L. J. / Kelley, J. H. | NTRS | 1967


    Performance of a Mars soft lander with staged propulsion

    GINSBERG, L. / KELLEY, J. | AIAA | 1967


    Mars Lander Propulsion

    Wrobel, J. Richard | SAE Technical Papers | 1968