Research on the Rapid Large-angle Attitude Maneuver of the LEO Communication Satellite

A specific type of the large-angle attitude maneuver problem is concerned for the low earth orbit communication satellites, characterized by the closely connected maneuver stages, and with both high -precision and finite-time stabilize emphasized. To address such issues, the control scheme is proposed by combining a trajectory optimization and a closed-loop attitude controller. As a practice, the seven-segment cosine angular acceleration planning and the real-coded genetic algorithm are applied to provide the maneuver trajectory optimization, generally considering the practical performance of the sensors and actuators. Meanwhile, the controller is designed by an improved global fast terminal sliding mode method which brings a better convergence. Numerical simulation shows that the high accuracy is guaranteed during the fast attitude tracking even considering the actuator limitations.