Fixed‐time attitude tracking control for rigid spacecraft

Abstract

This study addresses the fixed‐time attitude tracking for rigid spacecraft with inertia uncertainties and external disturbances. Firstly, a new fixed‐time sliding surface based on the bi‐limit homogeneous theory is proposed. Secondly, a non‐singular sliding mode control is designed to solve the robust fixed‐time attitude tracking problem. It is proved that the proposed control can ensure that the sliding surface and attitude tracking errors converge to zero within fixed time. The appealing features of the proposed control are exact fixed‐time tracking stability with fast convergence, high precision, strong robustness and easy implementation. Simulations verify the effectiveness and improved performance of the proposed approach.