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Multi-starting thrust chamber head structure and thrust chamber

A technology of thrust chamber and head, which is applied in the field of thrust chamber head structure and thrust chamber for multiple starts, can solve the problems of unfavorable injector product quality, injector deformation, influence, etc., to improve processing accuracy and process flexibility Sexuality, compact structure, and the effect of reducing production costs

Active Publication Date: 2022-03-29
BEIJING AEROSPACE PROPULSION INST
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

This further introduces the welding process and causes further deformation of the injector, which adversely affects the quality of the injector product

Method used

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  • Multi-starting thrust chamber head structure and thrust chamber
  • Multi-starting thrust chamber head structure and thrust chamber

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Embodiment Construction

[0028] The following describes the present invention in detail, and the features and advantages of the present invention will become more clear and definite along with these descriptions.

[0029] The word "exemplary" is used exclusively herein to mean "serving as an example, embodiment, or illustration." Any embodiment described herein as "exemplary" is not necessarily to be construed as superior or better than other embodiments. While various aspects of the embodiments are shown in drawings, the drawings are not necessarily drawn to scale unless specifically indicated.

[0030] The purpose of the present invention is to provide a multiple-start thrust chamber head structure, which can be used for the head of a hydrogen-oxygen rocket engine, and solve the problems of many welding procedures and great deformation influence after the welding inspection of the injector of the traditional structure. The head structure of the thrust chamber for multiple starts in the present inve...

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Abstract

The invention discloses a multi-start thrust chamber head structure and a thrust chamber, in the multi-start thrust chamber head structure, on the premise that a bearing cone is kept in a conical upward contraction configuration, non-contact electron beam welding or laser welding is adopted to replace traditional argon arc welding or flange connection of a two-hole seat through compact design of the two-hole seat, so that the two-hole seat is more compact in structure and more compact in structure. The liquid oxygen top cover, the force bearing cone and the reinforcing ribs can be integrally designed, the integrated reinforcing structure unit is arranged in the integrated top cover, all the parts of the integrated top cover are effectively reinforced through the multiple reinforcing ribs, and meanwhile the requirement for weight reduction is met. Compared with a traditional split type welding structure, the welding seam number and welding heat input are effectively reduced, the welding procedure after welding detection is reduced, meanwhile, the influence on injector deformation is reduced, and the welding structure is suitable for the hydrogen-oxygen rocket engine, particularly suitable for the hydrogen-oxygen rocket engine and particularly suitable for the hydrogen-oxygen rocket engine. The invention relates to an oxyhydrogen rocket engine and other liquid rocket engines with more than two starting requirements.

Description

technical field [0001] The invention belongs to the technical field of liquid rocket engines, and in particular relates to a multiple-start thrust chamber head structure and a thrust chamber. Background technique [0002] The hydrogen-oxygen rocket engine uses liquid hydrogen and liquid oxygen as propellants, and has the advantages of high specific impulse and no pollution. It is one of the mainstream propulsion technologies used by upper-level engines and deep space probes in the world today. When working, the fuel hydrogen and the oxidant liquid oxygen are respectively distributed to the nozzle through the hydrogen head cavity and the oxygen head cavity. After the hydrogen and oxygen are mixed in the nozzle outlet area, the chemical energy is converted into heat energy and pressure potential energy, and then the combustion products pass through the throat and The nozzle squeezes out to generate thrust. [0003] The head of a hydrogen-oxygen rocket engine is equipped with ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F02K9/62
CPCF02K9/62
Inventor 张亚刘倩刘红珍谢恒潘亮田原韩长霖孔维鹏潘刚郭洪坤
Owner BEIJING AEROSPACE PROPULSION INST
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