Anti-Unwinding Sliding Mode Attitude Maneuver Control for Rigid Spacecraft

In this article, anti-unwinding attitude maneuver control for rigid spacecraft is considered. First, in order to avoid the unwinding phenomenon when system states are restricted switching surface, a novel function designed by hyperbolic sine such that surface contains two equilibriums. Then, sliding mode controller developed based on proposed ensure robustness of closed-loop disturbance and inertia uncertainty. Another important feature presented law dynamic parameter constructed guarantee unwinding-free performance before reach surface. Furthermore, boundary layer introduced chattering phenomenon. Moreover, convergence property within proven. The simulation results demonstrate problem settled during adopting newly scheme.