Backstepping based finite-time control for the spacecraft attitude tracking control with uncertainties

The issue of attitude tracking control with finite-time convergence is investigated based on backstepping method for the spacecraft in presence of external disturbance and uncertain actuator configuration. More specifically, the attitude quaternion can track the demanded command in finite time under the virtual control law by introducing a terminal sliding manifold. Then, the finite-time convergence to the sliding mode of the angular velocity error will be achieved under the proposed novel finite-time control and parameter adjusting law. In addition, the finite-time stabilization/convergence of the sliding surface and the spacecraft attitude tracking error have been proved and analysed using the Lyapunov method theoretically. Finally, numerical simulation results are presented to illustrate the performance of the proposed scheme.