Fixed-Time Spacecraft Attitude Control With Unwinding-Free Performance

Abstract

This note studies the problem of rapid attitude control with high accuracy for rigid spacecraft undergoing unwinding-free performance. By designing a novel nonsingular sliding function, fixed-time convergence and unwinding-free performance are rigorously established on the sliding surface. In addition, by introducing a novel potential function to design the controller, unwinding-free performance is also ensured outside of the sliding surface. Furthermore, the chattering problem is tackled by properly modifying the control strategy, with which the attitude tracking error is ensured to converge to an arbitrarily predefined residual set and the unwinding-free performance is also preserved. Numerical simulations also verify the effectiveness of the proposed method.