Structural layout of a light and small rocket engine

A rocket engine and structure layout technology, which is applied to rocket engine devices, machines/engines, mechanical equipment, etc., can solve the problems of multiple disassembly and assembly of valves, low utilization rate of structural space, and poor compact layout structure. Flow resistance adjustment, beneficial to weight reduction and thermal protection, and beneficial to the effect of structural layout

Active Publication Date: 2021-05-04
SHANGHAI INST OF SPACE PROPULSION
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Problems solved by technology

[0004] Looking at the current state of technology at home and abroad, there are various structural layout forms of light and small rocket engines, and there are many successful cases, but generally have the following shortcomings: 1) The layout structure is not compact, and the structural space utilization rate is low; 2) The engine section When adjusting the orifice plate, it is necessary to repeatedly disassemble and assemble the valve

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  • Structural layout of a light and small rocket engine

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Embodiment Construction

[0010] The present invention will be described in further detail below in conjunction with the accompanying drawings and specific embodiments.

[0011] see figure 1 , The engine structure layout includes head shell module 1, throttle ring 2, propellant control valve 3, injector core 4, nozzle pipe 5, combustion chamber pressure nozzle 6, valve fastener 7, and internal leakage prevention The sealing ring 8 and the anti-leakage sealing ring 9 can realize the compact structure of the engine, which is beneficial to the modular integration of products.

[0012] The power system installation interface of the head shell module 1 is a plane flange interface, and multiple threaded holes are located on the same installation surface, and the middle area of ​​the multiple threaded holes is the installation interface of the throttle ring 2 . The installation interface of the throttle ring 2 is an internal threaded hole. After the throttle ring 2 is installed, the smooth surface of the thr...

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Abstract

The invention relates to the technical field of spacecraft propulsion systems, in particular to a structural layout of a light and small rocket engine, which can realize a compact engine structure and is beneficial to product modularization and integration. According to the engine structure layout of the present invention, it includes a head shell module, a throttle ring, a propellant control valve, an injector core, a nozzle pipe, a combustion chamber pressure nozzle, valve fasteners, an internal leakage prevention sealing ring, and an anti-inner leakage sealing ring. Leaky sealing ring. The invention has the following advantages: 1) The engine product has a compact structure, which is conducive to reducing the envelope size of the engine; 2) The number of engine parts is small, which is conducive to improving the inherent reliability of the engine; 3) The throttle ring is easy to disassemble and assemble, which is convenient for engine flow resistance Adjustment; 4) The structure is properly hollowed out, which is conducive to weight reduction and heat protection of engine products.

Description

technical field [0001] The invention relates to the technical field of spacecraft propulsion systems, in particular to a structural layout of a light and small rocket engine. Background technique [0002] The engine is the heart of spacecraft such as launch vehicles, satellites, and missiles, and provides power for the spacecraft to change its orbit and attitude. With the development of aerospace technology, higher requirements are put forward for the miniaturization of rocket engines. Light and small rocket engines can not only reduce the total weight of the spacecraft, increase the payload of the spacecraft, but also optimize the overall design of the spacecraft, improve the The performance and technical level of spacecraft are of great significance. For example, the application of light and small rocket engines in the field of missile weapons and micro space vehicles can greatly promote the technological progress of civil and military space vehicles. [0003] The structu...

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F02K9/42F02K9/60F02K9/58F02K9/52F02K9/97F02K9/62
Inventor 陈明亮付华林陈师邬二龙陈夏超殷艳媚周斌杰
Owner SHANGHAI INST OF SPACE PROPULSION
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