This paper presents an approach to large-angle rotational maneuvers of a spacecraft-beam-tip body configuration based on nonlinear invertibility and linear feedback stabilization. A control law u sub d is derived for the decoupled control of attitude angles, lateral elastic deflections, slopes due to bending and angular deflection due to torsion at the tip of the beam using torquers and force actuators. For the stabilization of the elastic modes, a linear feedback control law u sub s is obtained based on a linearized model augmented with a servocompensator. Simulation results are presented to show that large slewing and elastic mode stabilization can be accomplished.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    Robust nonlinear attitude control of flexible spacecraft


    Contributors:


    Publication date :

    1987-05-01



    Type of media :

    Miscellaneous


    Type of material :

    No indication


    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