Abstract: The attitude control of satellite with flexible appendage and rotatable payload is investigated. Attitude dynamics equations and rotatable payload torque model are presented on the basis of NewtonEuler method with generalized coordinates. The theory and characteristics on imbalance torque of rotatable payload are analyzed. Secondly, the influence of payload disturbance characteristics on attitude of satellite is studied, and the estimation method of attitude jitter is illustrated based on Laplace transform of transfer equation. Finally, the condition of a disturbance reduction controller is developed, which is applied to the satellite attitude control system, and the controller engineering application method is presented. The verification results show the effectiveness of the proposed approach, and the accuracy of satellite attitude is improved.

Key words: static imbalance, dynamic imbalance, rotatable payload, disturbance compensation