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Rocket attitude control system

An attitude control and attitude control technology, applied in the aerospace field, can solve problems such as the inability to achieve attitude stability, and achieve the effects of reducing the difficulty and cost of development, simplifying the control system, and reducing the number of

Pending Publication Date: 2020-06-26
BEIJING XINGJI RONGYAO SPACE TECH CO LTD +1
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  • Abstract
  • Description
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  • Application Information

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Problems solved by technology

[0004] In view of this, the embodiment of the present invention provides a rocket attitude control system to solve the problem that the existing attitude control nozzle configuration scheme cannot achieve attitude stability

Method used

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Embodiment Construction

[0025] 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.

[0026] 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 discloses a rocket attitude control system. The rocket attitude control system includes first attitude control nozzles, second attitude control nozzles, and third attitude control nozzles; the first attitude control nozzles are distributed in a first mounting surface perpendicular to the longitudinal axis of the rocket body, and the first mounting surface is close to the head of a rocket sub-stage; the second attitude control nozzles are distributed in a second mounting surface perpendicular to the longitudinal axis of the rocket body, and the second mounting surface is close tothe tail of the rocket sub-stage; and the third attitude control nozzles are distributed in a third mounting surface perpendicular to the longitudinal axis of the rocket body, and the third mounting surface is located between the first mounting surface and the second mounting surface and is close to the second mounting surface; wherein the thrust of the first attitude control nozzle is greater than the thrust of the third attitude control nozzle, and the thrust of the third attitude control nozzle is greater than the thrust of the second attitude control nozzle. By means of the rocket attitudecontrol system, the control torque requirements under low dynamic pressure at different flight stages can be satisfied, and the stable control of the rocket is realized; and therefore, a swing engineand a servo mechanism thereof are replaced, the number of actuators is reduced, the control system is simplified, and the development difficulty and cost of commercial carrier rockets are reduced.

Description

technical field [0001] The invention relates to the field of aerospace technology, in particular to a rocket attitude control system. Background technique [0002] For traditional launch vehicles, attitude control nozzles are usually only configured for flight phases such as trajectory finishing, load release, and unpowered taxiing, and attitude control nozzles for positive and negative thrust directions are respectively configured for pitch, yaw, and roll channels. Tube. The main feature of these stages is that the interference acting on the rocket body is very small, and at the same time, in order to ensure that the load enters the orbit accurately, the thrust of the attitude control nozzle is relatively small and the number is large. [0003] In recent years, with the rapid development of the commercial aerospace field, more demands have been placed on low-cost launch vehicles. In order to reduce the complexity of the control system and reduce the development and produc...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F42B10/66
CPCF42B10/66
Inventor 彭小波张勇黄佩
Owner BEIJING XINGJI RONGYAO SPACE TECH CO LTD
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