Abstract This paper investigates the time efficient maneuver of rigid satellites with inertia uncertainty and bounded external disturbance. A redundant cluster of four reaction wheels is used to control the spacecraft. To make full use of the controllability and avoid frequent unload for reaction wheels, a maximum output torque and maximum angular momentum constrained torque distribution method is developed. Based on this distribution approach, the maximum allowable acceleration and velocity of the satellite are optimized during the maneuvering. A novel braking curve is designed on the basis of the optimization strategy of the control torque distribution. A quaternion-based sliding mode control law is proposed to render the state to track the braking curve strictly. The designed controller provides smooth control torque, time efficiency and high control precision. Finally, practical numerical examples are illustrated to show the effectiveness of the developed torque distribution strategy and control methodology.

    Highlights A control allocation method is developed to avoid frequent unload for wheels. The maximum allowable acceleration and velocity of the satellite are optimized. A novel quaternion-based braking curve is proposed. Rapid maneuver with inertia uncertainty and disturbance is achieved.


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    Title :

    Time efficient spacecraft maneuver using constrained torque distribution


    Contributors:
    Cao, Xibin (author) / Yue, Chengfei (author) / Liu, Ming (author) / Wu, Baolin (author)

    Published in:

    Acta Astronautica ; 123 ; 320-329


    Publication date :

    2016-03-27


    Size :

    10 pages




    Type of media :

    Article (Journal)


    Type of material :

    Electronic Resource


    Language :

    English





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