The problem of attitude control of a rigid body in the orbital coordinate system is considered. Algorithms for ellipsoidal estimation of the state vector of the control object (CO) are used in the control loop. As distinct from the well-know algorithms, these algorithms are characterized by robustness relative to violations of a priory assumptions as to CO. The control algorithms are synthesized based on the direct Lyapunov method and its generalizations. The efficiency of the adaptive control algorithms is illustrated by results of computer simulation.


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    Title :

    Attitude control of a spacecraft in the orbital coordinate system using ellipsoidal estimates of its state vector


    Contributors:


    Publication date :

    1999


    Size :

    3 Seiten, 25 Quellen



    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English






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