A new formulation for soft-constraint trajectory optimization is presented as a real-time optimal feedback guidance method for multiburn orbital maneuvers. Control is always chosen to minimize burn time plus a quadratic penalty for end condition errors, weighted so that early in the mission (when controllability is greatest) terminal errors are held negligible. Eventually, as controllability diminishes, the method partially relaxes but effectively still compensates perturbations in whatever subspace remains controllable. Although the soft-constraint concept is well-known in optimal control, the present formulation is novel in addressing the loss of controllability inherent in multiple burn orbital maneuvers. Moreover the necessary conditions usually obtained from a Bolza formulation are modified in this case so that the fully hard constraint formulation is a numerically well behaved subcase. As a result convergence properties have been greatly improved.


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    Titel :

    Real-time optimal guidance for orbital maneuvering.


    Beteiligte:
    Cohen, A. O. (Autor:in) / Brown, K. R. (Autor:in)

    Kongress:

    Aerospace Sciences Meeting ; 1973 ; Washington, DC


    Erscheinungsdatum :

    01.01.1973


    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Keine Angabe


    Sprache :

    Englisch


    Schlagwörter :


    Real-Time Optimal Guidance for Orbital Maneuvering

    AUDREY 0. COHEN AND KENNETH R. BROWN | AIAA | 1973


    Real-time optimal guidance for orbital maneuvering

    COHEN, A. / BROWN, K. | AIAA | 1973


    Orbital maneuvering vehicle guidance, navigation and control

    Huber, W. G. / Finnell, W., III | NTRS | 1985


    Optimal Guidance with Maneuvering Targets

    ROBERT B. ASHER AND JOHN P. MATUSZEWSKi | AIAA | 1974


    Automated low-thrust guidance for the orbital maneuvering vehicle

    Rose, Richard E. / Schmeichel, Harry / Shortwell, Charles P. et al. | NTRS | 1988