The invention provides an orbit injection method and system for a large-ellipse frozen orbit. The orbit injection method comprises the steps that the perigee height is increased through multiple times of low-thrust orbit transfer of an apogee; the perigee argument is naturally increased by using a perturbation forward factor; the working time of each thruster is equally and reasonably distributed; ignition orbital transfer of each time is completed in an inertia pointing mode. The perigee height of the target orbit is positively biased; performing low-thrust orbital transfer near the apogee to reduce the perigee height to a target value, and finally completing satellite orbit injection; and the ignition height is selected to be 28000 kilometers or above. The satellite can still enter a task orbit under the fault condition, and the service life of the satellite is guaranteed.

    本发明提供了一种大椭圆冻结轨道入轨方法和系统,包括远地点多次小推力变轨抬高近地点高度;利用摄动正向因素自然增大近地点幅角;均等合理分配各推力器工作时间;采用惯性指向方式完成每次点火变轨;正向偏置目标轨道近地点高度;在远地点附近进行小推力变轨降低近地点高度至目标值,最终完成卫星入轨;点火高度选择在28000公里以上。本发明中卫星在故障条件下仍可进入任务轨道并保证卫星使用寿命。


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    Titel :

    Large elliptical frozen orbit injection method and system


    Weitere Titelangaben:

    大椭圆冻结轨道入轨方法和系统


    Beteiligte:
    CHEN XIANG (Autor:in) / LI JIAN (Autor:in) / BIE SHUYOU (Autor:in) / LI YUNFEI (Autor:in) / XIA YONG (Autor:in) / LU JING (Autor:in) / YU JIE (Autor:in) / YANG LIFENG (Autor:in) / ZHAO JIN (Autor:in)

    Erscheinungsdatum :

    28.11.2023


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Chinesisch


    Klassifikation :

    IPC:    B64G Raumfahrt , COSMONAUTICS



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