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    This study presents a new attitude maneuver control for rigid spacecraft, enabling arbitrary convergence times. The novel control law ensures stability and avoids the unwinding phenomenon.

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    Area of Science:

    • Aerospace Engineering
    • Control Systems Theory

    Background:

    • Spacecraft attitude control is crucial for mission success.
    • Achieving precise and rapid attitude maneuvers with guaranteed stability is a persistent challenge.

    Purpose of the Study:

    • To develop a novel attitude maneuver control law for rigid spacecraft.
    • To enable arbitrary convergence times for attitude stabilization.
    • To prevent the undesirable unwinding phenomenon in spacecraft attitude control.

    Main Methods:

    • Design of a time-varying sliding mode function using a piecewise exponential function.
    • Development of an attitude control law based on the designed sliding mode function.
    • Analysis of system stability and convergence properties.

    Main Results:

    • The proposed control law ensures that the closed-loop attitude system states remain on the sliding mode surface from the initial time.
    • Attitude convergence to the origin is achieved at an arbitrarily preset time.
    • The unwinding phenomenon is effectively avoided by the proposed control strategy.

    Conclusions:

    • The developed attitude control law offers precise and flexible control over spacecraft maneuvers.
    • The method provides a robust solution for achieving desired convergence times while ensuring stability.
    • This approach enhances the reliability and performance of spacecraft attitude control systems.