Novel rocket engine

A rocket engine, a new type of technology, applied in the direction of rocket engine devices, machines/engines, mechanical equipment, etc., can solve the problems of low work efficiency, complex structure of liquid propellant rocket engines, etc., achieve good results, novel and unique structure, and low loss Effect

Active Publication Date: 2016-08-03
HENAN HIGH POWER SPECIAL EQUIP ENG CO LTD
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  • Abstract
  • Description
  • Claims
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Problems solved by technology

[0008] In view of the above situation, in order to overcome the defects of the prior art, the object of the present invention is to provide a novel rocket engine, which can effectively s

Method used

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Embodiment Construction

[0016] The specific implementation manners of the present invention will be described in further detail below in conjunction with the accompanying drawings.

[0017] Depend on Figure 1-3 Given, the present invention comprises shell 1, and the afterbody of shell 1 is provided with combustion chamber 11, is provided with nozzle pipe 12 on the burner port of combustion chamber 11, is respectively provided with combustion agent tank 3, oxidant tank in shell 1 5. Combustion agent delivery pump assembly 7 and oxidant delivery pump assembly 8. The outlet of combustion agent storage tank 3 is connected to the inlet of combustion agent delivery pump assembly 7 through the first combustion agent delivery pipeline 4a. The outlet of the pump assembly 7 is equipped with a second combustion agent delivery pipeline 4b, the outlet end of the second combustion agent delivery pipeline 4b extends into the combustion chamber 11, and the first high-pressure water mist nozzle 9 is installed on the...

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Abstract

The invention relates to a novel rocket engine. The problem that a liquid propellant rocket engine is low in work efficiency can be effectively solved. According to the technical scheme, a combustion chamber is arranged at the tail of a shell; a spray pipe is arranged on a fire spitting opening of the combustion chamber; an incendiary agent storage tank, an oxidizing agent storage tank, an incendiary agent conveying pump set assembly and an oxidizing agent conveying pump set assembly are arranged in the shell; an outlet of the incendiary agent storage tank is connected with an inlet of the incendiary agent conveying pump set assembly through a first incendiary agent conveying pipeline; a second incendiary agent conveying pipeline is arranged on an outlet of the incendiary agent conveying pump set assembly; an outlet of the oxidizing agent storage tank is connected with an inlet of the oxidizing agent conveying pump set assembly through a first oxidizing agent conveying pipeline; and a second oxidizing agent conveying pipeline is arranged on an outlet of the oxidizing agent conveying pump set assembly. The novel rocket engine is high in pump set conveying efficiency and low in loss, an incendiary agent and an oxidizing agent are mixed sufficiently, combustion efficiency is high, fuel losses are reduced, use is convenient, and the effect is good.

Description

technical field [0001] The invention relates to an engine, in particular to a novel liquid propellant rocket engine. Background technique [0002] At present, the propellant system of most liquid propellant rocket engines generally uses a traditional turbo pump to deliver propellant to the combustion chamber for combustion, and the exhaust gas generated is ejected from the nozzle to generate propulsion. This turbopump propellant system suffers from the following problems: [0003] 1. The structure of the turbo pump is complex and the working conditions are harsh, so it is difficult to improve the working efficiency of the engine. [0004] 2. The injection power of this structure is insufficient. In order to meet the sufficient thrust of the engine, it is necessary to carry a large amount of propellant for injection and combustion, thereby increasing the volume and weight of the engine and increasing the load, which affects its working efficiency. [0005] 3. With this stru...

Claims

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Application Information

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IPC IPC(8): F02K9/46F02K9/56
CPCF02K9/46F02K9/563
Inventor 许智远胡泽雄许起东
Owner HENAN HIGH POWER SPECIAL EQUIP ENG CO LTD
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