Most aerospace tasks require satellites to perform large-angle attitude tracking maneuvers [1, 2]. Many investigations on large-angle attitude controller design have been reported to accomplish these maneuvers. The work in [3] was an earlier attempt to achieve this objective. An adaptive attitude controller was presented. However, modeling error was not handled; moreover, a linearized model was used, even though this model may not fully and well characterize the satellite dynamics. A simple controller demanding minimum onboard computations was presented in [4] for large pitch-angle maneuver without considering any modeling error. To address the problem of fast and large-angle attitude control, a robust control law was developed for flexible satellites [5]. In [6], the robust large-angle attitude control problem with modeling error due to external disturbance and delayed control inputs was investigated. In [7], a model predictive controller was designed for satellites to perform the large-angle attitude maneuvers with input-to-state stability ensured. To the authors’ best knowledge, few studies are seen on angular velocity observer-free attitude control design for satellites with modeling error due to external disturbances [8]. Although this was achieved in [9] with the attitude stabilized with good accuracy, the structure of the controller was complicated.


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    Titel :

    Observer-Free Output Feedback Attitude Control


    Beteiligte:
    Xiao, Bing (Autor:in) / Chen, Zhaoyue (Autor:in) / Xu, Jingwen (Autor:in) / Cao, Lu (Autor:in)

    Erschienen in:

    Erscheinungsdatum :

    03.07.2024


    Format / Umfang :

    21 pages




    Medientyp :

    Aufsatz/Kapitel (Buch)


    Format :

    Elektronische Ressource


    Sprache :

    Englisch