Spacecraft large angle eigenaxis maneuver control under sensor and actuator saturation

The problem of spacecraft large angle maneuver control under the saturation limit of sensor and actuator is investigated. The nonlinear feedback control logic with MRP as the representation of the attitude is introduced, avoiding the saturation of the sensor and the actuator during the maneuver. The maneuver is divided into two phases by a threshold determined by the error of the attitude. The setting way and scope of the control parameters are given and the stability of the system is proved by Lyapunov theory. A near-minimum-time eigenaxis rotation is used to improve the speed of the maneuver. Finally, the simulation of the control law is provided, the result of which proves the control law to be effective and reliable.