Output Feedback Control for Spacecraft Attitude System with Practical Predefined-Time Stability Based on Anti-Windup Compensator

This paper investigates the problem of output feedback attitude control for rigid spacecraft subject to inertia matrix uncertainty, space disturbance, and input saturation. Firstly, a model transformation is adopted convert an system with immeasurable angular velocity into new system. All states converted are measurable available feedback; however, contains mismatched uncertainty resulting from coordinate transformation. Then, adaptive nonsingular back-stepping practical predefined-time convergence designed. To resolve saturation, anti-windup compensator developed. It analytically proved that stable, such time given tunable constant. The simulation results reveal proposed framework provides rapid maneuver actuator saturation elimination.