Abstract: In this paper, the large angle attitude maneuver of a rigid flexible liquid coupled spacecraft is studied. The liquid sloshing is equivalent to the second order spring mass model, and the flexible panels are assumed to be Euler Bernoulli beams. Considering the situation that in actual space engineering, the spacecraft is subjected to unknown interfering torques, invisible state variables and oscillation suppression problems, an adaptive output feedback hybrid control method based on Lyapunov second method is designed combining with fuzzy control technology and input shaping technology. The fuzzy controller is used to dynamically optimize the parameters of the hybrid controller and enhance the robustness of the hybrid controller; the multi mode input shaping feedforward controller is designed to suppress the liquid sloshing and vibrations of flexible attachments caused by the large angle attitude maneuvering. The time history diagram of each state variable during spacecraft attitude maneuver is given by numerical simulation. The results verify the effectiveness of the hybrid control method.

Key words: rigid flexible liquid coupled spacecraft, kinetic modeling, adaptive control, fuzzy control, input shaping