The design of the 1975 Viking lander is based, in part, upon performance optimization analyses and a requirement to maximize operational flexibility. The analysis technique is characterized by a graphical tradeoff approach found to be the most effective for evaluating lifting-entry trajectory performance. The analysis eliminates the constraint of a level flight trajectory and allows the lander to reach positive flight-path angles before parachute deployment. Updated Mars environmental knowledge and recent test results and design decisions are analysis factors. The entry-phase analysis indicates that a hypersonic lift-to-drag ratio of 0.18 and an entry flight-path-angle corridor of -15 to -19 deg satisfy the requirements of optimum performance (maximum payload and sufficient terrain height capability).


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    Titel :

    A new approach to performance optimization of the 1975 Mars Viking lander.


    Beteiligte:
    Zeiner, H. N. (Autor:in) / French, C. E. (Autor:in) / Howard, D. A. (Autor:in)

    Kongress:

    Guidance and Control Conference ; 1973 ; Key Biscayne, FL


    Erscheinungsdatum :

    01.08.1973


    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Keine Angabe


    Sprache :

    Englisch


    Schlagwörter :


    Performance Optimization Technique for the 1975 Mars Viking Lander

    HUGH N. ZEINER / CHARLES E. FRENCH / AND DUANE A. HOWARD | AIAA | 1972


    A new approach to performance optimization of the 1975 Mars Viking lander

    ZEINER, H. / FRENCH, C. / HOWARD, D. | AIAA | 1973



    Biological experiments - The Viking Mars Lander.

    Klein, H. P. / Lederberg, J. / Rich, A. | NTRS | 1972


    The Viking Mars Lander decelerator system

    HUSSONG, J. / LAU, R. | AIAA | 1970