The invention provides an ultra-fast rendezvous and docking method based on a long-distance guide terminal anchor point, and relates to the technical field of rendezvous and docking, and the method comprises the steps: obtaining parameter information when a tracking spacecraft enters an orbit; according to the parameter information, a remote guidance strategy and preset rendezvous and docking time, determining a target value of a terminal anchor point of the tracking spacecraft in a remote guidance section; and taking the target value as an initial condition of a close-range autonomous control section, entering an approaching section, and translating the approaching section to complete docking with the target spacecraft. According to the ultra-fast rendezvous and docking method based on the long-distance guide terminal anchor point provided by the scheme, the rendezvous and docking time can be remarkably shortened.

    本发明提供了一种基于远距离导引终端锚点的超快速交会对接方法,涉及交会对接技术领域,该方法包括:获取追踪航天器入轨时的参数信息;根据参数信息、远距离导引策略和预设交会对接时间,确定追踪航天器在远距离导引段的终端锚点的目标值;将目标值作为近距离自主控制段的初始条件,并进入接近段、平移靠拢段以完成与目标航天器的对接。本方案提供的基于远距离导引终端锚点的超快速交会对接方法能够显著缩短交会对接时间。


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    Titel :

    Ultra-fast rendezvous and docking method based on long-distance guide terminal anchor point


    Weitere Titelangaben:

    一种基于远距离导引终端锚点的超快速交会对接方法


    Beteiligte:
    XIE YONGCHUN (Autor:in) / CHEN CHANGQING (Autor:in) / ZHANG QIANG (Autor:in) / HU HAIXIA (Autor:in) / WANG MIN (Autor:in) / SU YAN (Autor:in)

    Erscheinungsdatum :

    01.08.2023


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Chinesisch


    Klassifikation :

    IPC:    B64G Raumfahrt , COSMONAUTICS



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