Abstract:

Considering the attitude constraint problem during spacecraft attitude tracking, a control algorithm based on potential function for safe attitude maneuver is presented. Different from the case of fixed-point maneuver, error quaternion and error angular velocity are introduced to construct the spacecraft attitude tracking error model. Quaternions are used to describe the region of forbidden attitude, and a new Gauss avoidant potential function is proposed using the minimum angle allowed by the forbidden attitude. A safe attitude maneuver controller is obtained by employing the avoidant potential function and an attractive potential function, meanwhile the Lyapunov stability of the closedloop control system is analyzed with and without disturbance torque respectively. Finally, computer numerical simulations are carried out in attitude tracking with attitude constraint. Simulation results show that the proposed control approach can not only achieve the purpose of attitude tracking, but also guarantee the spacecraft far away the region of the forbidden attitude.