The invention provides an ultra-fast rendezvous pair approach distance guidance method and device. The method comprises the following steps: acquiring a preset terminal anchor point of a tracking spacecraft in a long-distance guidance section; taking a preset terminal anchor point as an initial condition, enabling the tracking spacecraft to enter an approaching section by adopting a CW guidance and sight guidance strategy, and then entering a translation approaching section comprising a top speed section and a safe approaching section so as to complete short-distance guidance; wherein sight guidance is executed after CW guidance is executed for three times. According to the ultra-fast rendezvous pair approaching distance guidance method provided by the scheme, a homing section is omitted, the approaching distance guidance time is shortened, and 2h ultra-fast rendezvous docking can be realized.

    本发明提供了一种超快速交会对接近距离制导方法及装置,该方法包括:获取追踪航天器在远距离导引段的预设终端锚点;以预设终端锚点为初始条件,追踪航天器采用CW制导和视线制导的策略进入接近段,然后进入包括极速段和安全接近段的平移靠拢段,以完成近距离制导;其中,在执行3次CW制导后执行视线制导。本方案提供的超快速交会对接近距离制导方法省去了寻的段,减少了近距离制导时间,能实现2h超快速交会对接。


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    Title :

    Ultra-fast rendezvous approach distance guidance method and device


    Additional title:

    一种超快速交会对接近距离制导方法及装置


    Contributors:
    CHEN CHANGQING (author) / ZHANG QIANG (author) / LIU ZONGYU (author) / XIE YONGCHUN (author) / HU HAIXIA (author) / SU YAN (author)

    Publication date :

    2023-08-04


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    Chinese


    Classification :

    IPC:    B64G Raumfahrt , COSMONAUTICS



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