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Mixed injector and small liquid rocket engine

An injector and shell technology, which is applied in the fields of hybrid injectors and small liquid rocket engines, can solve the problems of complex injector structure, poor generality of small liquid rocket engines, etc., and achieves compact structure, wide working pressure range, Applicable effect

Inactive Publication Date: 2018-10-23
BEIHANG UNIV
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] The object of the present invention is to provide a mixing injector and a small liquid rocket engine to solve the technical problem that the structure of the injector in the prior art is relatively complicated and the versatility of the small liquid rocket engine is poor

Method used

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  • Mixed injector and small liquid rocket engine
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  • Mixed injector and small liquid rocket engine

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Embodiment Construction

[0030] 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.

[0031] The components of the embodiments of the invention generally described and shown in the figures herein may be arranged and designed in a variety of different configurations. Accordingly, the following detailed description of the embodiments of the invention provided in the accompanying drawings is not intended to limit the scope of the claimed invention, but merely represents selected embodiments of the invention.

[0032] 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.

[0033] In the description of the present invention, it should be noted that the...

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Abstract

The invention relates to the technical field of liquid rocket engines, and particularly relates to a mixed injector and a small liquid rocket engine. The mixed injector comprises a shell, a cover plate and a core, wherein an oxidant cavity and a fuel cavity are formed in the shell; the oxidant cavity is annular, and the oxidant cavity surrounds the fuel cavity; the cover plate covers the upper endsurface of the shell and is welded with the shell and is used for sealing the oxidant cavity; the core is arranged in the fuel cavity, and fuel in the fuel cavity can be rotational and centrifugal bythe core; and a panel is arranged on the lower end surface of the shell, a fuel nozzle and an oxidant nozzle are formed in positions, which correspond to the fuel cavity and the oxidant cavity, of the panel, the fuel which is rotational and centrifugal in the fuel cavity by the core is sprayed by the fuel nozzle, and oxidant in the oxidant cavity can be sprayed by the oxidant nozzle. According tothe mixed injector, the core structure of the fuel nozzle is additionally arranged, so that the centrifugal spraying of the fuel is realized, the mixed injector and a straight-flow oxygen nozzle forma mixed spraying mode, the atomization effect is good, and the combustion efficiency is high.

Description

technical field [0001] The invention relates to the technical field of liquid rocket engines, in particular to a mixing injector and a small liquid rocket engine. Background technique [0002] Small liquid rocket engines play an extremely important role in the control of many spacecraft. They can provide power for orbit changes, rendezvous and docking, and attitude control of satellites and spacecraft. They can also be used for the start-up guarantee system of the main engine and the soft Landing systems, etc., the development of small liquid rocket engines is an important direction in the field of aerospace power control research. [0003] The injector is an extremely important part of the liquid rocket engine, which is directly related to the injection, atomization and mixing of the propellant, thus affecting the combustion stability and combustion efficiency of the engine. Due to the small propellant flow rate of small liquid rocket engines, small head size, and limited ...

Claims

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Application Information

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IPC IPC(8): F02K9/52
CPCF02K9/52
Inventor 杨庆春屈原朱韶华徐旭
Owner BEIHANG UNIV
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