The invention discloses a flexible spacecraft attitude maneuver control method based on a disturbance observer, relates to the field of aerospace control systems, and solves the problem that the control performance is reduced due to vibration of flexible accessories and external disturbance when an existing spacecraft is subjected to in-orbit attitude maneuver. According to kinematics, dynamics and vibration equations of the flexible spacecraft, a spacecraft second-order quasi-linear system model of a flexible spacecraft attitude control system is established by utilizing Lagrange mechanics, a nonlinear interference observer is provided to estimate external interference, and existence conditions of the interference observer and an observer parameter selection method are given. A parameterization method is utilized to design a controller composed of a state feedback part and a feed-forward compensation part. The control requirement of the flexible spacecraft is met, and the spacecraft control precision is effectively improved.

    基于干扰观测器的挠性航天器姿态机动控制方法,涉及航空航天控制系统领域,解决现有航天器在轨姿态机动时,挠性附件振动和外部干扰带来的控制性能下降的问题。本发明依据挠性航天器运动学、动力学和振动方程,利用Lagrange力学建立了挠性航天器姿态控制系统的航天器二阶拟线性系统模型,提出了一种非线性干扰观测器来估计外部干扰,给出了干扰观测器的存在条件和观测器参数选取方法。利用参数化方法设计了具有状态反馈与前馈补偿两部分组成的控制器。本发明满足挠性航天器的控制需求,有效提升了航天器控制精度。


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    Titel :

    Flexible spacecraft attitude maneuver control method based on disturbance observer


    Weitere Titelangaben:

    基于干扰观测器的挠性航天器姿态机动控制方法


    Beteiligte:
    ZHANG LIU (Autor:in) / LIU QUANZHI (Autor:in) / FAN GUOWEI (Autor:in) / LYU XUEYING (Autor:in) / GAO YU (Autor:in) / XIAO YANG (Autor:in)

    Erscheinungsdatum :

    2022-11-29


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Chinesisch


    Klassifikation :

    IPC:    B64G Raumfahrt , COSMONAUTICS



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