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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    Title :

    Iterative explicit guidance for low thrust spacecraft.


    Contributors:

    Conference:

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


    Publication date :

    1972-09-01


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English


    Keywords :


    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