Rocket orbit injection control method and device and rocket

A control method and a technology of a control device, applied to projectiles, self-propelled missiles, offensive equipment, etc., can solve the problems of iterative guidance algorithm deviation, failure to provide acceleration information, etc., and achieve the effect of improving the safety factor

Active Publication Date: 2020-05-12
BEIJING XINGJI RONGYAO SPACE TECH CO LTD +1
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  • Abstract
  • Description
  • Claims
  • Application Information

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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

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  • Rocket orbit injection control method and device and rocket
  • Rocket orbit injection control method and device and rocket
  • Rocket orbit injection control method and device and rocket

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Embodiment Construction

[0063] The technical solutions of the present invention will be clearly and completely described below in conjunction with the accompanying drawings. Apparently, the described embodiments are some of the embodiments of the present invention, but not all of them. Based on the embodiments of the present invention, all other embodiments obtained by persons of ordinary skill in the art without making creative efforts belong to the protection scope of the present invention.

[0064] In the description of the present invention, it should be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer" etc. The indicated orientation or positional relationship is based on the orientation or positional relationship shown in the drawings, and is only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the referred device or element must have a specific orientation, ...

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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...

Claims

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Application Information

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IPC IPC(8): F42B15/00F42B15/01
CPCF42B15/00F42B15/01
Inventor 季海波徐国光尤刘球
Owner BEIJING XINGJI RONGYAO SPACE TECH CO LTD
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