Difficulties arise in guiding a solar electric propulsion spacecraft due to nongravitational accelerations caused by random fluctuations in the magnitude and direction of the thrust vector. These difficulties may be handled by using a low thrust guidance law based on the linear-quadratic-Gaussian problem of stochastic control theory with a minimum terminal miss performance criterion. Explicit constraints are imposed on the variances of the control parameters, and an algorithm based on the Hilbert space extension of a parameter optimization method is presented for calculation of gains in the guidance law. The terminal navigation of a 1980 flyby mission to the comet Encke is used as an example.


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    Title :

    Limited variance control in statistical low thrust guidance analysis


    Contributors:

    Conference:

    Astrodynamics Specialist Conference ; 1975 ; Nassau, Bahamas


    Publication date :

    1975-07-01


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English