Method, device and launch vehicle for determining the timing of shutdown of a launch vehicle

Abstract

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.

Description

Technical field [0001] The invention relates to the technical field of launch vehicle guidance and control, and in particular to a method, a device and a launch vehicle for determining the timing of a launch vehicle shutdown. Background technique [0002] Carrier rocket refers to a spacecraft that sends various spacecraft such as artificial earth satellites, manned spacecraft, space stations, or interplanetary probes into space. The rocket takes off from the ground until it enters the final orbit to go through the following flight stages: intra-atmospheric flight period, constant angular velocity program flight period, or for high orbit or interplanetary missions, it can also include transition orbits. When the launch vehicle enters a predetermined orbit, it needs to execute a shutdown command. [0003] Existing launch vehicles generally use the shutdown judgment method of the orbit section to determine whether the real-time calculated orbit semi-major axis is greater than or equa...

AI Technical Summary

Problems solved by technology

[0004] In view of this, the embodiment of the present invention provides a method, device and launch vehicle for determining the shutdown timing of the launch vehicle, so as to solve the problem of determining the shutdown timing of the launch vehicle

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