Abstract In this paper a robust and optimal attitude control design that uses the minimal kinematic parameters and angular velocities feedback is presented for the three-axis attitude stabilization of spacecraft with inertia uncertainties. After proposing a new class of robust attitude control laws for the three-axis attitude stabilization of spacecraft with inertia uncertainties, it is shown that the proposed robust attitude control laws are optimal with respect to performance indices. A numerical example is given to illustrate the theoretical results presented in this paper.


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    Titel :

    Robust and optimal attitude control of spacecraft with inertia uncertainties using minimal kinematic parameters


    Beteiligte:
    Park, Yonmook (Autor:in)

    Erschienen in:

    Erscheinungsdatum :

    2016-04-29


    Format / Umfang :

    10 pages




    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Elektronische Ressource


    Sprache :

    Englisch