Abstract:The applications of space science observation, situational awareness, earth remote sensing and spatial manipulation have put forward the requirement of high precision, high stability, steady and compliant attitude maneuver for satellites. In this paper, Euler angle is used to analyze and model the time-varying and nonlinear satellite attitude dynamics system. Each sampling control period is regarded as an attitude maneuver process. Based on the motion principle of dynamics system under control, attitude deviation is predicted during each attitude tracking maneuver. Control instructions are obtained by the inversion of satellite attitude evolution. Based on trigonometric functions, a motion trajectory planning method for large angle maneuver of satellite attitude is designed. The proposed trajectory planning and control method is characterized by high tracking accuracy, good stability, smooth tracking and maneuvering process. The feasibility and effectiveness of the method are verified by a mathematical simulation.