This paper proposes a direct parametric design method for the attitude tracking control of a rigid spacecraft to address the problem of satellite attitude control performance affected by external disturbance. Firstly, the fully-actuated system model for attitude tracking control of a rigid spacecraft is established using quaternions. An extended state observer (ESO) is then developed to handle the influence caused by external disturbances. Then, a controller is designed using the direct parametric method to achieve high-accuracy attitude tracking control of the rigid spacecraft and reach the desired position. Finally, a numerical example involving a rigid spacecraft is presented to demonstrate the effectiveness of the proposed approach in achieving the design objective and exhibiting good control performance.


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    Titel :

    Attitude Tracking Control of Rigid Spacecraft Based on Fully Actuated System Models


    Beteiligte:
    Liu, Quan-Zhi (Autor:in) / Fan, Guo-Wei (Autor:in) / Zhang, Liu (Autor:in) / Lv, Xue-Ying (Autor:in) / Gao, Yu (Autor:in) / Xiao, Yang (Autor:in) / Song, Ying (Autor:in)


    Erscheinungsdatum :

    2023-07-14


    Format / Umfang :

    822300 byte




    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Elektronische Ressource


    Sprache :

    Englisch