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


    Erscheinungsdatum :

    01.01.1997


    Medientyp :

    Sonstige


    Format :

    Keine Angabe


    Sprache :

    Englisch




    Near-Optimal Entry Trajectories for Reusable Launch Vehicles

    H.-C. Chou / M. D. Ardema / J. V. Bowles | AIAA | 1998


    Near-optimal re-entry trajectories for reusable launch vehicles

    Chou, H.-C. / Ardema, M. / Bowles, J. | AIAA | 1997


    Near-Optimal Re-Entry Trajectories for Reusable Launch Vehicles

    Chou, H. / Ardema, M. / Bowles, J. et al. | British Library Conference Proceedings | 1997


    Near-Optimal Re-Entry Trajectories for Reusable Launch Vehicles

    H. C. Chou / M. D. Ardema / J. V. Bowles | NTIS | 1997