The invention provides a spacecraft thrust layout and attitude and orbit integrated control method. The method comprises the following steps of: firstly, considering the requirement on combined work of multiple spacecrafts in an aerospace mission in recent years, researching the flight performance of the spacecrafts in an accompanying mission requirement, and establishing a coupling relative motion model between the spacecrafts and a main spacecraft; and then, aiming at the characteristics that the relative distance between the spacecrafts is relatively small and the main spacecraft does elliptical orbit motion, designing a gain guidance method based on a Hill equation, and uniformly obtaining attitude orbit control instructions of the spacecrafts in combination with attitude control of a sliding mode variable structure. Further, propeller switch logic is uniformly distributed according to force and torque instructions, and guidance control is achieved. Finally, the feasibility and effectiveness of the novel spacecraft thruster layout scheme are verified through a simulation experiment.

    本发明提出航天器推力布局及姿轨一体化控制方法。所述方法首先,考虑近年来航天任务中对多航天器联合工作的需求,研究航天器在伴飞任务要求中的飞行性能,建立了与主航天器之间的耦合相对运动模型。随后,针对航天器之间相对距离较小且主航天器做椭圆轨道运动的特点,设计基于Hill方程的增益制导方法,并结合滑模变结构姿态控制,统一获得航天器的姿态轨道控制指令。进而,根据力与力矩指令统一分配推进器开关逻辑,实现制导控制。最终,通过仿真实验,验证了新型航天器推力器布局方案的可行性与有效性。


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    Titel :

    Spacecraft thrust layout and attitude and orbit integrated control method


    Weitere Titelangaben:

    航天器推力布局及姿轨一体化控制方法


    Beteiligte:
    ZHOU DI (Autor:in) / LI JINGHAN (Autor:in) / DU RUNLE (Autor:in) / LI SIYUAN (Autor:in)

    Erscheinungsdatum :

    2024-05-07


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Chinesisch


    Klassifikation :

    IPC:    B64G Raumfahrt , COSMONAUTICS



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