Design of Output Feedback Controller for Attitude Control System of Flexible Satellite Based on LMI

This paper considers the attitude stability of a flexible satellite. We use the idea of H _¿ control to design a controller to eliminate the effect which results from the external disturbance for the satellite. The pitch angle, the roll angle, the yaw angle and the angular velocities are relatively small amounts in allusion to the flexible satellite attitude control system. According to the above idea, the kinematical equation and dynamical equation of the attitude system can be designed to a relatively simple linear system. Then the optimal output feedback H _¿ controller of the attitude control system could be designed based on LMI. The mathematical simulation results show that the method can effectively eliminate the impact, which results from the external space disturbance.