Abstract
Near time-optimal controller based on analytical trajectory planning algorithm for satellite attitude maneuver is proposed in this paper. The attitude maneuver issue is constructed as three successive attitude maneuvers and the desired trajectory is derived by calculating the minimum rotate angle, meanwhile each maneuver process is optimized by Bang–Bang control logic so that the system could have near time optimal character. The constraint on control torque is discussed and the relationship between system upper bound and control parameters is given. A special case of attitude maneuver is discussed and system acceleration and deceleration process is optimized inspired by Hohmann transfer of orbit control. The analytical solution of desired trajectory is given hence the computation is largely reduced. The attitude tracking controller is designed so that system could maneuver along the designed trajectory. System stability is proved by Lyapunov method and system performance is demonstrated by numerical simulation.
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