The invention discloses a spacecraft orbit-attitude-modal information observation and disturbance estimation method, and belongs to the technical field of large spacecraft stability control. A large spacecraft orbit-attitude-vibration integrated dynamic model is established, and an information observation and comprehensive disturbance estimator is introduced; and real-time observation and feedback compensation of orbit, attitude, modal and disturbance information are carried out to realize the design of the controller, so that the problem that the performance of a control system is reduced due to span change of on-orbit assembly dynamic characteristics of a large spacecraft is overcome, the spacecraft orbit-attitude-vibration integrated control robustness is higher, the assembly process is more reliable, the precision is higher, and the reliability of the system is improved. And therefore, the on-orbit assembly efficiency is remarkably improved.

    本发明公开了一种航天器轨道‑姿态‑模态信息观测与扰动估计方法,属于大型航天器稳定控制技术领域,本发明建立大型航天器轨道‑姿态‑振动一体化动力学模型,引入信息观测与综合扰动估计器,进行轨道、姿态、模态、扰动信息的实时观测与反馈补偿,实现控制器的设计,从而克服大型航天器在轨装配动力学特性的跨度性变化导致的控制系统性能下降,使得航天器轨道‑姿态‑振动一体化控制鲁棒性更强、组装过程更可靠、精度更高,进而显著提升在轨装配效率。


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    Title :

    Spacecraft orbit-attitude-modal information observation and disturbance estimation method


    Additional title:

    一种航天器轨道-姿态-模态信息观测与扰动估计方法


    Contributors:
    LIU CHUANG (author) / LYU BAILIANG (author) / YUE XIAOKUI (author) / DAI HONGHUA (author) / ZHANG JIANQIAO (author)

    Publication date :

    2022-08-30


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    Chinese


    Classification :

    IPC:    B64G Raumfahrt , COSMONAUTICS



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