A near-optimal guidance law for the descent trajectory for earth orbit re-entry of a fully reusable single-stage-to-orbit pure rocket launch vehicle is derived. A methodology is developed to investigate using both bank angle and altitude as control variables and selecting parameters that maximize various performance functions. The method is based on the energy-state model of the aircraft equations of motion. The major task of this paper is to obtain optimal re-entry trajectories under a variety of performance goals: minimum time, minimum surface temperature, minimum heating, and maximum heading change; four classes of trajectories were investigated: no banking, optimal left turn banking, optimal right turn banking, and optimal bank chattering. The cost function is in general a weighted sum of all performance goals. In particular, the trade-off between minimizing heat load into the vehicle and maximizing cross range distance is investigated. The results show that the optimization methodology can be used to derive a wide variety of near-optimal trajectories.


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    Titel :

    Near-Optimal Re-Entry Trajectories for Reusable Launch Vehicles


    Beteiligte:
    H. C. Chou (Autor:in) / M. D. Ardema (Autor:in) / J. V. Bowles (Autor:in)

    Erscheinungsdatum :

    1997


    Format / Umfang :

    12 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch




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