Results show effects on performance boundaries of variations in initial entry conditions and vehicle characteristics and of constraints on such trajectory variables as altitude and acceleration; effect of earth's rotation on optimal performance is also included; typical trajectories are presented to illustrate and contrast basic nature of various optimal entry missions; results also show that there are numerous trade-offs possible between maximum maneuver capability and optimal entry heating; factors for trade-off are initial entry conditions, trajectory constraints, and physical characteristics of vehicle; results also show that, although radiative effects can account for significant portion of total entry heating, trajectories for optimal heat entries are largely determined by convective inputs.


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    Title :

    Trajectory optimization for apollo-type vehicle under entry conditions encountered during lunar return


    Additional title:

    NASA -- Tech Report


    Contributors:


    Publication date :

    1967


    Size :

    39 pages


    Type of media :

    Report


    Type of material :

    Print


    Language :

    English


    Keywords :