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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    Titel :

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


    Beteiligte:
    Su, Yuhan (Autor:in) / Shen, Shaoping (Autor:in) / Hu, Zikun (Autor:in) / Li, Zhibin (Autor:in)


    Erscheinungsdatum :

    01.04.2025


    Format / Umfang :

    3302903 byte




    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Elektronische Ressource


    Sprache :

    Englisch



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