Prescribed-time attitude control during solid thrusting orbital maneuver

With the development of aerospace technology, solid propulsion system is gradually applied in the orbital maneuver missions. However, there are some unavoidable problems of solid thruster, such as the strong time constraint caused by the fuel limitation and the strong unknown attitude disturbance caused by the thrust misalignment. In this paper, a prescribed-time attitude stabilization control strategy based on thrust vector control (TVC) technique is proposed. Firstly, the attitude dynamics model of the solid propulsion satellite is established. Considering the strictly limited control time during orbital maneuver, the time-varying constraint boundary function is constructed based on the prescribed time and attitude accuracy requirements. Then, the prescribed-time attitude controller is designed on the basis of the adaptive backstepping method, and the prescribed-time stability of the satellite system is proved via Lyapunov stability theory. Finally, simulations verify the effectiveness of the proposed prescribed-time controller for attitude control of the satellite during solid thrusting orbital maneuver.