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.


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    Title :

    Practical Finite-Time Attitude Reorientation Control for Rigid Spacecraft With Forbidden Pointing Constraints and Physical Limitations


    Contributors:
    Su, Yuhan (author) / Shen, Shaoping (author) / Hu, Zikun (author) / Li, Zhibin (author)


    Publication date :

    2025-04-01


    Size :

    3302903 byte




    Type of media :

    Article (Journal)


    Type of material :

    Electronic Resource


    Language :

    English



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