This paper presents an optimal attitude maneuver by means of Reaction Wheels to achieve desired attitude for a Satellite. At first, Dynamic Equations of motion for a satellite with three Reaction Wheels as its active actuators has been educed, and then State Equations of this system has been obtained. In derivation of equations, coupling of Reaction Wheel electrical equations with dynamic equations of satellite motion, and Reaction wheel saturation avoidance approaches are considered. Then an optimal attitude control with the LQR method has exerted for a distinct satellite by its Reaction Wheels. As a result of simulation has presented an optimal effort by calculated Gain matrix to achieve desired attitude for chosen Satellite. It shows that satellite becomes stable in desired attitude with a low energy and time consumption.


    Zugriff

    Download


    Exportieren, teilen und zitieren



    Titel :

    Spacecraft Optimal Attitude Control by means of Reaction Wheels


    Beteiligte:


    Erscheinungsdatum :

    2010



    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Elektronische Ressource


    Sprache :

    Unbekannt




    Spacecraft Attitude Control Using Two Reaction Wheels

    Yamada, K. / Yoshikawa, S. | British Library Online Contents | 1998


    Inertia-Free Spacecraft Attitude Control Using Reaction Wheels

    Weiss, Avishai / Kolmanovsky, Ilya / Bernstein, Dennis S. et al. | AIAA | 2013



    Time-Optimal Attitude Scheduling of a Spacecraft Equipped with Reaction Wheels

    Alberto Olivares / Ernesto Staffetti | DOAJ | 2018

    Freier Zugriff

    Spacecraft Attitude Sliding Mode Controller Using Reaction Wheels

    Kowalchuk, S. / Hall, C. | British Library Conference Proceedings | 2008