Robust attitude tracking control scheme for flexible spacecraft with vibration suspension

In this paper, a novel robust control algorithm is proposed to carry out large-angle attitude tracking control of a flexible spacecraft subject to external disturbances. An adaptive scheme based on neural network system is designed to ensure the actual attitude to track the command input in the presence of external disturbances. To reduce adverse effects caused by the elastic vibration on the closed-loop performance of the flexible spacecraft, an active vibration controller with independent modal space method is added to the overall control algorithm. Moreover, for achieving perfect control performance and constructing systematic tuning procedure for controller parameters, genetic algorithm is applied to search the optimal values of active vibration controller. Stability of the whole closed-loop system is proved via Laypunov theory and simulation results confirm the effectiveness of the proposed method.