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Axial injection end combustion solid-liquid rocket engine structure

A solid-liquid rocket and engine technology, which is applied to rocket engine devices, machines/engines, mechanical equipment, etc., can solve the problems of low filling fraction, long and thin, and limited application range, so as to improve the filling fraction, specific impulse and Performance, the effect of ensuring thermal protection performance

Active Publication Date: 2014-08-06
BEIHANG UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

At the same time, a typical side-burning solid-liquid rocket engine usually has a large channel area and a low filling fraction. In order to provide a sufficient combustion area, the length is long and the slenderness ratio is large, which limits its application range to a certain extent.

Method used

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  • Axial injection end combustion solid-liquid rocket engine structure
  • Axial injection end combustion solid-liquid rocket engine structure

Examples

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Embodiment Construction

[0020] The present invention will be further described in detail below in conjunction with the accompanying drawings and embodiments.

[0021] The structure of the axial injection end-combustion solid-liquid rocket engine of the present invention comprises a motor head cover 1, a charge shell 2, a charge insulation layer 3, an end-fire charge 4, a nozzle casing 5, a nozzle insulation layer 6, Sealing ring A7, bolt assembly A8, sealing ring B9, and bolt assembly B10.

[0022] The drug column housing 2 has a cylindrical structure, with connecting flanges at the front and rear ends; and the front and rear end surfaces of the drug column housing 2 have circumferential sealing grooves, and sealing rings A7 and sealing rings are arranged inside respectively. B9.

[0023] The front end of the engine head cover 1 has an air intake passage for supplying oxidant, and the oxidant can be gas oxidant such as O2 and N2O. The rear end surface of the engine head cover 1 is designed with inn...

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PUM

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Abstract

The invention discloses an axial injection end combustion solid-liquid rocket engine structure which comprises an engine head cover, a solid propellant shell, a solid propellant heat insulating layer, end combustion solid propellants, a spray pipe shell and a spray pipe heat insulating layer. The engine head cover is mounted at the front end of the solid propellant shell, the spray pipe shell is mounted at the rear end of the solid propellant shell, the engine head cover is provided with an air inlet channel, the end combustion solid propellants are coaxially arranged in the solid propellant shell, a constant volume cavity is formed between the front end faces of the end combustion solid propellants and the rear end face of the engine head cover, each end combustion solid propellant is provided with a plurality of axial injection holes with small diameters, the flow rate of oxidizing agents in the injection holes is high, and combustion reaction only occurs at the end faces of the end combustion solid propellants; the joint between the solid propellant shell and the engine head cover and the joint between the solid propellant shell and the spray pipe shell are respectively provided with a sealing structure, so that air impermeability of an engine is guaranteed; the heat insulating layers are arranged in the solid propellant shell and the spray pipe shell, so that thermal protection performance of the engine during operation is guaranteed. Thus, performance of the engine is improved, meanwhile the filling fraction of the engine is improved, the slenderness ratio of the engine is reduced, and the application rage of engine is widened.

Description

technical field [0001] The invention relates to the technical field of solid-liquid rocket motors, in particular to an axial injection end-combustion solid-liquid rocket motor structure. Background technique [0002] Compared with the currently widely used solid or liquid rocket motors, solid-liquid rocket motors use liquid oxidizer and solid fuel as propellants, which have the advantages of low cost, good safety, thrust adjustment and multiple starts, etc. A class of engines with great development potential. [0003] When a typical solid-liquid rocket engine is working, the oxidant enters the grain channel of the engine through the injection panel, and forms a flame layer near the side wall of the grain for combustion. The grain belongs to side combustion. Common charge shapes include round hole, star hole, wheel shape and porous shape. For the side-burning solid-liquid rocket engine, as the working time of the engine increases, the area of ​​the charge channel and the fu...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F02K9/24F02K9/44
Inventor 田辉俞南嘉李新田蔡国飙
Owner BEIHANG UNIV
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