Established procedures of linear, quadratic Gaussian optimal estimation and control are developed and interpreted for their application to spacecraft with dynamically significant elastic appendages. Comparisons are made between alternative coordinate systems, and a realistic range of design parameters is considered. For single axis control system evaluation is accomplished by simulation of a fifteenth-order spacecraft plant with alternative second-order, fourth-order, and sixth-order constant gain estimators. Results point out the importance of modeling errors.


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    Title :

    Optimal estimation and attitude control of a solar electric propulsion spacecraft


    Additional title:

    Optimalwertbestimmung und Stellungsregelung eines Sonnenenergie-getriebenen Raumfahrzeuges


    Contributors:
    Larson, V. (author) / Likins, P. (author) / Marsh, E. (author)


    Publication date :

    1977


    Size :

    13 Seiten, 15 Quellen



    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English