The invention relates to a method for designing a tethered satellite transfer orbit between coplanar elliptical orbits, and provides an orbit transfer strategy for enabling an assembly to spin arounda centroid and enabling a tether to be kept tensioned by centrifugal force aiming at the potential collision risk of binding bodies at two ends of the assembly caused by thrust closing between tethered satellite pulse maneuvers. When the assembly moves near a distant place, a strategy of obtaining an expected speed increment by cutting off the tether is provided, and compared with Hough transfer,the method can save half of fuel consumption at most.

    本发明涉及一种共面椭圆轨道间的绳系卫星转移轨道设计方法,针对绳系卫星脉冲机动间由于推力关闭带来的组合体两端绑体的潜在碰撞风险,提出使组合体绕质心自旋,用离心力使系绳保持张紧的变轨策略;在组合体运动到远地点附近时,提出通过剪断系绳获得期望的速度增量的策略,与霍曼转移相比,该方法最多可以节约二分之一的燃料消耗。


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    Title :

    Method for designing tethered satellite transfer orbit between coplanar elliptical orbits


    Additional title:

    一种共面椭圆轨道间的绳系卫星转移轨道设计方法


    Contributors:
    MENG ZHONGJIE (author) / JIA CHENG (author) / HUANG PANFENG (author)

    Publication date :

    2020-06-02


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    Chinese


    Classification :

    IPC:    B64G Raumfahrt , COSMONAUTICS



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