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A rocket attitude control system

An attitude control and attitude control technology, applied in the aerospace field, can solve problems such as high procurement or self-development costs, large demand for swing engines and their supporting servo mechanisms, and restrictions on the commercial competitiveness of launch vehicles.

Active Publication Date: 2022-02-25
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

At this time, if the traditional control scheme continues to be used, the demand for the swing engine and its supporting servo mechanisms will be large, the cost of procurement or self-development will be high, and the control system will be complicated, which will restrict the commercial competitiveness of the launch vehicle.

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  • A rocket attitude control system
  • A rocket attitude control system
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Embodiment Construction

[0026] 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.

[0027] 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, which comprises: a grid rudder distributed on the outer wall of the first-stage tail section of the rocket body; a first thrust attitude control nozzle distributed in the first installation surface perpendicular to the longitudinal axis of the rocket body , the first installation surface is close to the head of the rocket sub-stage; the second thrust attitude control nozzle is distributed in the second installation surface perpendicular to the longitudinal axis of the rocket body, and the second installation surface is close to the tail of the rocket sub-stage; wherein, the first The thrust of the first thrust attitude control nozzle is greater than the thrust of the second thrust attitude control nozzle. The present invention arranges grid rudders on the outer wall of the tail section of the first stage of the rocket body, and arranges two kinds of attitude control nozzles with different thrusts on the uppermost stage of the rocket body, which can meet the control torque requirements of the rocket in different flight stages and realize the full flight of the rocket The stable control makes it possible to use fixed engines at all stages, cancel the swing nozzle and its servo mechanism, simplify the control system, and reduce the cost of the launch vehicle.

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, the swing engine is usually configured as the main actuator at each stage, and the nozzle is configured as the auxiliary actuator at the final stage to achieve the stability control of the rocket throughout the flight. Taking the four-stage rocket as an example, multiple sets of swing engines (and their matching servo mechanisms) and final nozzles are required in the control scheme. [0003] In recent years, with the rapid development of the commercial aerospace field, the importance of cost and economic benefits in the decision-making of launch vehicle development and production has increased rapidly. At this time, if the traditional control scheme continues to be used, the demand for the swing engine and its supporting servo mechanisms will be large, the cost of procurement or s...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64G1/24B64G1/26
CPCB64G1/244B64G1/26
Inventor 彭小波董彦民黄佩
Owner BEIJING XINGJI RONGYAO SPACE TECH CO LTD
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