Rocket orbit injection control method and device and rocket

Abstract

The invention provides a rocket orbit injection control method and device. The method comprises the steps that a trajectory inclination angle when a rocket enters an orbit is obtained; the absolute value of the trajectory inclination angle is compared with a first preset value; and if the absolute value of the trajectory inclination angle is larger than the first preset value, the posture of the rocket is adjusted by correcting an engine, and the rocket is made to move according to the orbit. The invention further provides the rocket. According to the rocket orbit injection control method anddevice, the trajectory inclination angle when the rocket enters the circular orbit is compared with the first preset value, the posture of the rocket when the rocket enters the orbit is obtained, theposture of the rocket is adjusted in real time by correcting the engine, the rocket is made to move according to the orbit, the problem that when an accelerometer of the rocket breaks down, an iterative guidance algorithm cannot be used for conducting flight guidance on the rocket is solved, and the safety coefficient of the rocket is increased.

Description

technical field [0001] The invention relates to the technical field of rocket control, in particular to a rocket entry control method, device and rocket. Background technique [0002] The rocket uses iterative guidance technology for flight guidance. During the flight, according to its current position, speed and estimated orbital point, it continuously adjusts the rocket's flight trajectory, calculates the required orbital point, and then according to the current position and orbital point The spatial relative relationship between them, planning a new trajectory, ensuring the accuracy and attitude of orbiting, has the advantages of high precision, strong task adaptability, and simple guidance devices. [0003] However, the iterative guidance technology relies on the acceleration parameters provided by the rocket's accelerometer. When the accelerometer fails, the wrong rocket acceleration parameters are provided or the acceleration parameters cannot be provided, the rocket w...

AI Technical Summary

Problems solved by technology

[0004] Therefore, the technical problem to be solved in the present invention is to overcome the defect that the acceleration information cannot be provided when the accelerometer fails after the rocket is launched, which leads to the deviation of the iterative guidance algorithm, thereby providing a rocket orbit control method, the orbit of the rocket is a circle track, including the following steps:

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