Abstract:

Considering the switching-type characteristic of attitude control actuators used in spacecraft three loop coupling attitude control systems, a large angle attitude maneuver control scheme of spacecraft is proposed. To avoid the singularity due to the use of Euler angle in large angle attitude maneuvers，the attitude kinematics of the spacecraft is described by quaternion. A variable structure controller with bounded inputs is designed by the method of Lyapunov and the stability of the system is proved. In order to avoid chattering, a boundary layer is used to replace the sign function in the variable structure control law. The rest-to-rest attitude tracking control problem is simulated. Numerical simulation results show the effectiveness of the proposed attitude control method.