The invention provides a modeling method of a spacecraft electromagnetic docking and separation attitude and orbit integrated dynamic model, belongs to the technical field of spacecraft attitude and orbit integrated dynamic modeling, and adopts an approximate linearization method to establish a spacecraft electromagnetic docking and separation dynamic attitude and orbit integrated linearization dynamic model. According to the method, the coupling action mechanism between electromagnetic force, electromagnetic torque and spacecraft relative motion in spacecraft electromagnetic docking and separation attitude and orbit integrated dynamic modeling is clarified, the complexity of a conventional nonlinear coupling model is reduced, unknown quality characteristic parameters are separated to comprehensive interference, the purpose of no parameter identification is achieved, and the method has the advantages of being high in reliability and high in reliability. And a foundation is laid for the design of an efficient control method.

    本发明提供了一种航天器电磁对接与分离姿轨一体化动力学模型建模方法,属于航天器姿轨一体化动力学建模技术领域,本发明采用近似线性化的方法建立了一种航天器电磁对接与分离动力学姿轨一体线性化动力学模型,厘清了航天器电磁对接与分离姿轨一体化动力学建模中电磁力、电磁力矩与航天器相对运动之间的耦合作用机理,降低了常规非线性耦合模型的复杂性,并通过将未知质量特性参数分离至综合干扰,实现了无需参数辨识的目的,为高效控制方法的设计奠定了基础。


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    Title :

    Modeling method of spacecraft electromagnetic docking and separation attitude-orbit integrated kinetic model


    Additional title:

    航天器电磁对接与分离姿轨一体化动力学模型建模方法


    Contributors:
    SHI KEKE (author) / LIU XINGCHEN (author) / ZHI YINING (author) / LIU RUIXIA (author)

    Publication date :

    2024-11-08


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    Chinese


    Classification :

    IPC:    B64G Raumfahrt , COSMONAUTICS



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