The satellite integrated attitude-orbit control method based on variable structure control

Herein, we design an attitude control method that used in the orbit maneuver mode. In the designed method, four incline-fixed thrusters with chemical propulsion are required to simultaneously perform orbit and attitude control. Although this is convenient, it causes attitude disturbance. This study aims to develop a simple and robust attitude control method to address this situation. Therefore, we design a two-class pulse width’s phase plane attitude controller. We construct a dynamic model for the variable structure controller, and analyze the stability under various time-frequency field parameter values. We use the sliding mode and modern control theory to determine the lower bound of the parameter. The controller can decrease the chattering of the switching line, as well as guarantee the stability of the system. Then, we simulate the most severe fix error under flexible conditions. We also verify the correctness, effectiveness, and robustness of the proposed method based on the excellent performance of satellites on orbit.