The invention relates to the technical field of carrier rocket guidance control, and specifically relates to a method and device for determining the shutdown opportunity of a semi-major axis of a carrier rocket and the carrier rocket. The method comprises the steps of obtaining a target orbit semi-major axis and a semi-major axis compensation quantity of a target rocket, wherein the semi-major axis compensation quantity is caused by an engine aftereffect of the target rocket; obtaining a semi-major axis of the target rocket in the current orbit; and according to the semi-major axis in the current orbit, the semi-major axis compensation quantity and the target orbit semi-major axis, determining an opportunity of sending a shutdown instruction. Due to the fact that the engine aftereffect ofthe target rocket can bring a certain speed increment to the target rocket, the opportunity of the shutdown instruction is determined in combination with the semi-major axis compensation quantity caused by the engine aftereffect, the accuracy of shutdown opportunity determination can be guaranteed, and thus the precision of carrier rocket orbit injection can be improved.

    本发明涉及运载火箭制导控制技术领域,具体涉及确定运载火箭半长轴关机时机的方法、装置及运载火箭,其中方法包括:获取目标火箭的目标轨道半长轴以及半长轴补偿量;其中,所述半长轴补偿量为所述目标火箭的发动机后效引起的;获取目标火箭在当前轨道的半长轴;根据所述当前轨道的半长轴、所述半长轴补偿量以及所述目标轨道半长轴,确定发出关机指令的时机。由于目标火箭的发动机后效可以给目标火箭带来一部分速度增量,因此,结合由于发动机后效所引起的半长轴补偿量确定关机指令的时机,可以保证关机时机确定的准确性,从而可以提高运载火箭入轨的精度。


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    Title :

    Method and device for determining shutdown opportunity of carrier rocket and carrier rocket


    Additional title:

    确定运载火箭关机时机的方法、装置及运载火箭


    Contributors:
    XU GUOGUANG (author) / YOU LIUQIU (author) / PENG XIAOBO (author)

    Publication date :

    2020-04-10


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    Chinese


    Classification :

    IPC:    B64G Raumfahrt , COSMONAUTICS



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