Attitude control method for flexible spacecraft based on LPV model

The dynamic parameters of spacecraft with rotating flexible panels are uncertain. In view of this problem, a robust attitude controller design method based on linear parameter varying (LPV) theory was proposed. Firstly, the LPV model of attitude dynamics of flexible spacecraft was established by taking the angles of rotations of solar panels as the variable parameter. The limited input and rates of change of input signals were considered, and the quadratic control indicator limit was optimized. Based on the linear matrix inequality (LMI) method, An LPV state feedback controller with variable parameter scheduling was obtained. The obtained controller can maintain robust stability under the condition of a wide range of system parameters and has anti-interference ability. Finally, the simulation was verified by numerical method and compared with the steady robust controller. The adaptability and robustness of the proposed LPV robust controller were verified. © 2024 Beijing University of Aeronautics and Astronautics (BUAA). All rights reserved.