Based on the control theory of the fully actuated system method, this paper proposes a method of attitude-tracking control for rigid spacecraft by using a predefined time terminal sliding mode scheme. First, we establish the fully-actuated system model for the spacecraft by using the attitude dynamics and kinematics equation, then in order to improve the control efficiency, a new predefined time controller is designed by combining the fully actuated system method and the nonsingular terminal sliding mode control method. Finally, the effectiveness of the designed controller is verified by numerical simulation.


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    Title :

    Predefined time sliding mode attitude tracking control for rigid spacecraft based on fully actuated system method


    Contributors:
    Zheng, Yin (author) / Zhang, He (author) / Wang, Yan (author)


    Publication date :

    2024-05-10


    Size :

    1094486 byte




    Type of media :

    Conference paper


    Type of material :

    Electronic Resource


    Language :

    English




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