This article investigates the spacecraft attitude reorientation problem with forbidden pointing constraints and physical limitations. Relying on the kinematics of the spacecraft, a nominal virtual angular velocity is first designed to guarantee that the spacecraft can maneuver to the desired attitude within a finite settling time while avoiding the unwinding problem. Then, based on control barrier function theory, a safety filter is constructed to synthesize a safe virtual angular velocity, which ensures the satisfaction of attitude constraints and angular velocity limitations. At the dynamic system level, a prescribed performance controller is developed to provide feasible transient and steady-state performance requirements for the angular velocity tracking error. Moreover, an antisaturation compensator is introduced to mitigate control input saturation. Lyapunov methods are employed to demonstrate the practical finite-time stability of the closed-loop system under attitude pointing constraints, physical limitations, and external disturbances. Two numerical simulations are presented to verify the effectiveness and advantages of the proposed approach.
Practical Finite-Time Attitude Reorientation Control for Rigid Spacecraft With Forbidden Pointing Constraints and Physical Limitations
IEEE Transactions on Aerospace and Electronic Systems ; 61 , 2 ; 3387-3397
01.04.2025
3302903 byte
Aufsatz (Zeitschrift)
Elektronische Ressource
Englisch
An Optimal Feedback Control Law for Spacecraft Reorientation with Attitude Pointing Constraints
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