A retargeting procedure is developed for use as a nonlinear low thrust guidance scheme. The selection of a control program composed of a sequence of inertially fixed thrust-acceleration vectors permits all trajectory computations to be made with closed form expressions, and allows the controls to be represented by constant parameters, thrust-acceleration vectors and thrusting times. By requiring each trajectory to be time optimal, the guidance problem is transformed into a parameter optimization problem which is solved by the conjugate gradient method. The scheme is applied to a low thrust capture mission, and the results of computer simulations are presented.


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    Titel :

    Iterative explicit guidance for low thrust spacecraft.


    Beteiligte:
    Jacobson, R. A. (Autor:in) / Powers, W. F. (Autor:in)

    Kongress:

    American Institute of Aeronautics and Astronautics and American Astronautical Society, Astrodynamics Conference, Palo Alto


    Erscheinungsdatum :

    01.09.1972


    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Keine Angabe


    Sprache :

    Englisch


    Schlagwörter :


    Iterative explicit guidance for low thrust spacecraft

    JACOBSON, R. / POWERS, W. | AIAA | 1972


    Iterative Explicit Guidance for Low Thrust Spaceflight

    ROBERT A. JACOBSON AND WILLIAM F. POWERS | AIAA | 1974


    Explicit guidance law for manned spacecraft

    DELPORTE, M. / SAUVINET, F. | AIAA | 1992