In this paper, equation of motion of three axis attitude dynamic of flexible spacecraft is derived using combination of finite element method and Euler equation. Flexible appendafes are modeled by beam elements. Goal of control is target attitude of spacecraft from initial state to desired attitude and suppression of vibration that induced in flexible appendages. So a combination of backstepping and sliding mode control method used for three-axis attitude maneuver of flexible spacecraft and for suppressing vibration of flexible appendage used from active vibration control method by PZT actuator. Control law for vibration control is based on LQG method


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    Title :

    Flexible Spacecraft Three Axis Attitude Maneuver by Active Vibration Control


    Contributors:
    M. Sayanjali (author) / J. Roshanian (author) / A. Ghafari (author)


    Publication date :

    2009



    Type of media :

    Article (Journal)


    Type of material :

    Electronic Resource


    Language :

    Unknown