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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    Title :

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


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


    Publication date :

    2023-07-14


    Size :

    822300 byte




    Type of media :

    Conference paper


    Type of material :

    Electronic Resource


    Language :

    English