The invention relates to a space anti-approaching observation attitude and orbit coupling control method based on a guard moonlet. The method comprises the following steps: establishing a guard moonlet orbit and attitude dynamics model; designing an expected trajectory of the guard moonlet in a mother satellite orbit system; designing an expected attitude of the guard moonlet; according to the guard moonlet orbit and attitude dynamic model and the expected attitude, constructing a relative position and attitude coupling dynamic model of the guard moonlet relative to the mother satellite; constructing a dynamic model for representing the control input of the relative position and attitude coupling dynamic model by adopting thruster control force; and according to the kinetic model and the expected trajectory of the control input represented by the control force of the thruster, constructing an optimal sliding mode attitude and orbit coupling controller of the guard moonlet. According to the method, the advantage of flexibility and portability of a guard moonlet is utilized, and an anti-approaching observation strategy that the guard moonlet actively approaches the incoming attack satellite from the sight direction of the incoming attack satellite and interferes the incoming attack satellite is adopted, so that the condition that the incoming attack satellite carries out approaching observation on our mother satellite can be effectively defended.

    本申请涉及一种基于护卫小卫星的空间反抵近观测姿轨耦合控制方法,该方法包括:建立护卫小卫星轨道与姿态动力学模型;设计护卫小卫星在母星轨道系中的期望轨迹;设计护卫小卫星期望姿态;根据护卫小卫星轨道与姿态动力学模型和期望姿态,构建护卫小卫星相对母星的相对位置和姿态耦合动力学模型;构建采用推力器控制力表征相对位置和姿态耦合动力学模型的控制输入的动力学模型;根据采用推力器控制力表征控制输入的动力学模型、期望轨迹,构建护卫小卫星最优滑模姿轨耦合控制器。本方法利用护卫小卫星灵活轻便的优点,主动从来袭卫星视线方向接近来袭卫星并对其进行干扰的反抵近观测策略,可对来袭卫星对我方母星进行抵近观测的情况进行有效防御。


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    Titel :

    Spatial anti-approaching observation attitude and orbit coupling control method based on guard moonlet


    Weitere Titelangaben:

    基于护卫小卫星的空间反抵近观测姿轨耦合控制方法


    Beteiligte:
    ZHANG JIN (Autor:in) / HUANG XUAN (Autor:in) / JANG TAEK YONG (Autor:in) / WANG LIYAO (Autor:in) / CHEN YUAN (Autor:in) / WANG KEMAO (Autor:in)

    Erscheinungsdatum :

    2024-02-06


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Chinesisch


    Klassifikation :

    IPC:    B64G Raumfahrt , COSMONAUTICS



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