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    CSVS Method for Spacecraft with Two Flexible Appendages during Attitude Maneuver

    CSVS Method for Spacecraft with Two Flexible Appendages during Attitude Maneuver


    An angle maneuver control strategy of spacecraft with two flexible appendages based on component synthesis vibration suppression (CSVS) method is put forward. Unwanted flexible vibration modes can be eliminated while desired rigid motion can be achieved by this method. Jet device and Momentum wheel system are used as the actuator of the spacecraft’s angle maneuver. Several time-fuel control strategies are designed for spacecraft with flexible appendages. Simulation results validate the feasibility of the CSVS method. The DC motor control method is researched in order to combine momentum wheel system with CSVS method.

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    Title :

    CSVS Method for Spacecraft with Two Flexible Appendages during Attitude Maneuver

    Contributors:
    Wang, Guan Yu / Ge, Wei Ping / Yang, Guang Wei / Wang, Sheng Chao
    Published in:

    Advanced Materials Research ; 1049-1050 ; 939-944

    Publication date :

    2014-10-10

    Size :

    6 pages

    ISSN :

    1662-8985 , 1022-6680

    DOI :

    https://doi.org/10.4028/www.scientific.net/AMR.1049-1050.939

    Type of media :

    Article (Journal)

    Type of material :

    Electronic Resource

    Language :

    English

    Keywords :

    Component Synthesis Vibration Suppression (CSVS) Method , Multi-Deformable-Body Dynamics , Large Angle Maneuver

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