The invention discloses a method and device for determining rocket launching parameters and detector injection orbit parameters, belongs to the technical field of spacecraft orbit design, and is used for jointly and rapidly determining the rocket launching parameters and the detector injection orbit parameters. In the method, a rocket inclination angle value range and a corresponding rocket gliding time value range are determined according to a detector injection orbit inclination angle, predicted rocket gliding time is determined based on a detector injection orbit perigee argument, and predicted rocket injection orbit ascending node longitude is determined based on the predicted rocket gliding time. And determining the predicted injection time of the detector according to the ascending node longitude difference of the rocket and the detector. According to the detector injection orbit inclination angle, the rocket inclination angle value range, the predicted rocket sliding time, the rocket sliding time value range and the predicted detector injection time, the rocket launching time and the launching azimuth angle are determined, and rocket injection orbit parameters and rocket launching parameters consistent with the detector injection orbit parameters are obtained.

    本申请公开一种火箭发射参数与探测器入轨轨道参数的确定方法及装置,属于航天器轨道设计技术领域,用以联合快速确定火箭发射参数和探测器入轨轨道参数。该方法中,根据探测器入轨轨道倾角确定火箭倾角取值范围以及相应的火箭滑行时间取值范围,并基于探测器入轨轨道近地点幅角确定预计的火箭滑行时间,并基于预计的火箭滑行时间确定预计的火箭入轨轨道升交点经度。根据火箭与探测器的升交点经度差确定预计的探测器入轨时刻。根据探测器入轨轨道倾角、火箭倾角取值范围、预计的火箭滑行时间、火箭滑行时间取值范围以及预计的探测器入轨时刻确定火箭发射时刻和发射方位角,获得火箭入轨轨道参数与探测器入轨轨道参数衔接一致的火箭发射参数。


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    Title :

    Method for determining rocket launching parameters and detector injection orbit parameters


    Additional title:

    一种火箭发射参数与探测器入轨轨道参数的确定方法


    Contributors:
    LI GEFEI (author) / LIU YONG (author) / SHENG QINGXUAN (author) / MA CHUANLING (author) / LI HAOHAO (author) / FAN DAWEI (author) / LUO YUYU (author) / YE KAI (author) / CAO PENGFEI (author) / WANG JIAYU (author)

    Publication date :

    2025-03-14


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    Chinese


    Classification :

    IPC:    B64G Raumfahrt , COSMONAUTICS