AbstractOn the attitude maneuvering problem of a class of spacecraft with flexible appendages, this paper proposes a control concept satisfying the both characteristics of the open-loop control of the rigid body modes in the sense of the maximum principle and the robust feedback control of the elastic vibration mode in the sense of the LQ regulator. Two candidates of control algorithms are proposed and discussed to satisfy this concept requirement. Their validity is verified through a ground-based hardware demonstration.


    Access

    Check access

    Check availability in my library

    Order at Subito €


    Export, share and cite



    Title :

    An optimal slewing maneuver approach for a class of spacecraft with flexible appendages


    Contributors:

    Published in:

    Acta Astronautica ; 13 , 6-7 ; 311-318


    Publication date :

    1986-01-28


    Size :

    8 pages




    Type of media :

    Article (Journal)


    Type of material :

    Electronic Resource


    Language :

    English




    On the Dynamics of Spacecraft with Flexible, Deployable and Slewing Appendages

    Shen, Q. / Modi, V. J. / American Astronautical Society et al. | British Library Conference Proceedings | 1993



    Slewing maneuver control of flexible spacecraft by output feedback

    Bang, Hyochoong / Cho, Yuncheol / Lee, Hyunjae | Elsevier | 2004


    CSVS Method for Spacecraft with Two Flexible Appendages during Attitude Maneuver

    Wang, Guan Yu ;Ge, Wei Ping ;Yang, Guang Wei | Trans Tech Publications | 2014