Space shuttle trajectory-shaping optimization considering the vehicle's thermal environment and the resulting requirements of the thermal protection system (TPS) are discussed. Optimization studies have been conducted yielding results which are generally applicable to shuttle orbiters and are independent of evolution and redirection of the space shuttle program. Two investigations of optimal trajectory shaping, with different methods of considering the thermal environment are presented.


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    Titel :

    Orbiter entry trajectory considerations


    Beteiligte:
    Rehder, J. J. (Autor:in) / Holloway, P. F. (Autor:in)


    Erscheinungsdatum :

    01.02.1972


    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Keine Angabe


    Sprache :

    Englisch


    Schlagwörter :




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