This paper presents an approach to large-angle rotationalmaneuvers of a spacecraft-beam-tip body configuration based onnonlinear invertibility and linear feedback stabilization. A controllaw Ud is derived for the decoupled control of attitude angles, lateralelastic deflections, slopes due to bending and angular deflection dueto torsion at the tip of the beam using torquers and force actuators.For the stabilization of the elastic modes, a linear feedback controllaw us is obtained based on a linearized model augmented with aservocompensator. Simulation results are presented to show thatlarge slewing and elastic mode stabilization can be accomplished.


    Access

    Check access

    Check availability in my library

    Order at Subito €


    Export, share and cite



    Title :

    Robust Nonlinear Attitude Control of Flexible Spacecraft


    Contributors:

    Published in:

    Publication date :

    1987-05-01


    Size :

    1885181 byte




    Type of media :

    Article (Journal)


    Type of material :

    Electronic Resource


    Language :

    English






    Robust Nonlinear Attitude Control of Spacecraft with Flexible Structures

    Lin, Y.-Y. / Lin, G.-L. / American Institute of Aeronautics and Astronautics et al. | British Library Conference Proceedings | 2000


    Robust constrained fault-tolerant attitude control for flexible spacecraft

    Long, Haihui / Zhao, Jiankang | SAGE Publications | 2018