Large Flexible Spacecraft Simulation System: Control, Identification and Effectiveness Evaluation

This paper proposes a simulation system design together with an effectiveness evaluation method for large flexible spacecraft. To handle the vibration problem of the flexible accessory of the spacecraft simulation system, a sliding mode controller is used to suppress the flexible vibration. To realize the on-orbit identification of the moment of inertia of the flexible spacecraft and improve the identification accuracy, a parallel recursive method is proposed by combining generalized Kalman filtering with recursive least squares. The simulation results verify that the proposed sliding mode control algorithm has strong stability and can effectively suppress the vibration of flexible accessories, and its adjustment time is about 1/10 of PID control. Meanwhile, the proposed identification method has improved accuracy compared with traditional methods, and the identification error can be reduced to 4%. Furthermore, the analytic hierarchy process (AHP) is used to evaluate the effectiveness of the spacecraft simulation device proposed in this paper. The reliability of the simulation system is calculated to be 96.7%, which can be used as a verification plat form for related algorithm research.