The navigation and control of the space shuttle during atmospheric entry are discussed. A functional flow diagram presenting the basic approach to the deobit targeting problem is presented. The major inputs to be considered are: (1) vehicle state vector, (2) landing site location, (3) entry interface parameters, (4) earliest desired time of landing, and (5) maximum cross range. Mathematical models of the navigational procedures based on controlled thrust times are developed. (Author)


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    Title :

    Deorbit Targeting


    Contributors:

    Publication date :

    1973


    Size :

    26 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English




    Deorbit targeting

    Tempelman, W. H. | NTRS | 1973


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