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Solid rocket engine with high thrust ratio and manufacturing method thereof

A solid rocket, high-thrust technology, applied in rocket engine devices, machines/engines, mechanical equipment, etc., can solve problems such as small thrust ratio, and achieve the effect of improving total thrust, simplifying manufacturing process, and large thrust ratio

Active Publication Date: 2015-10-28
HUBEI SANJIANG AEROSPACE JIANGHE CHEM TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] The technical problem to be solved by the present invention is to provide a solid rocket motor with a large thrust ratio and its manufacturing method, which can solve the problem of a small thrust ratio, provide a large thrust ratio, work smoothly, and have reliable structure and performance

Method used

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  • Solid rocket engine with high thrust ratio and manufacturing method thereof
  • Solid rocket engine with high thrust ratio and manufacturing method thereof
  • Solid rocket engine with high thrust ratio and manufacturing method thereof

Examples

Experimental program
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Effect test

Embodiment 1

[0033] Such as figure 1 , figure 2 with image 3 As shown, a solid rocket motor with a high thrust ratio includes a combustion chamber casing 1, a heat insulating layer 2 is pasted on the inner surface of the combustion chamber casing 1, and a heat insulating sleeve 3 is bonded to the outer surface of the grain 4 and forms a joint with the grain. Overall, the charge column 4 with the heat insulating sleeve 3 is installed in the combustion chamber shell 1 with the heat insulating layer 2 in a free-loading manner, and the outlet end of the combustion chamber shell 1 is installed with a nozzle 5;

[0034] The grain 4 includes a booster-level three-arm grain 4-1 and a cruise-level end-fired grain 4-2, and the booster-level three-arm grain 4-1 and the cruise-level end-fire grain 4-2 are connected in series to form a Whole drug column;

[0035] The booster-level three-arm grain 4-1 and the cruise-level end-burning grain 4-2 are BOH four-component propellant grains with the same ...

Embodiment 2

[0042] A preparation method of the above-mentioned solid rocket motor with high thrust ratio, the method comprises the following steps:

[0043] 1) Adhesive heat insulation layer in combustion chamber shell 1 to manufacture heat insulation sleeve 3;

[0044] 2) Treat the inner surface of the heat insulation sleeve 3 and paint the butyl hydroxy lining;

[0045] 3) Install the heat insulating sleeve 3 prepared in step 2) in the combustion chamber shell 1 with the heat insulating layer 2;

[0046] 4) Molding of the grain 4: Install the mold for forming the three-armed grain 4-1 on the heat insulating sleeve 3, pour the same formula of butylated hydroxyl four-component propellant into the heat insulating sleeve 3 and the mold, and vulcanize and form under normal pressure , remove the mold;

[0047] 5) install nozzle 5;

[0048] Promptly make the solid rocket motor of described high thrust ratio.

[0049] In step 4), the vulcanization temperature is 50-60 degrees Celsius.

[0...

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Abstract

A solid rocket engine with a high thrust ratio comprises a combustion chamber shell. A heat insulated layer is pasted to the inner surface of the combustion chamber shell. A heat insulated sleeve is bonded to the outer surface of a grain and forms a whole with the grain. The grain with the heat insulated sleeve is arranged in the combustion chamber shell with the heat insulated layer in a free-filling mode. A spray pipe is arranged at the outlet end of the combustion chamber shell. The grain comprises a booster-stage three-arm type grain body and a cruising-stage end-burning grain body which are connected in series to form the integrated grain. The booster-stage three-arm type grain body and the cruising-stage end-burning grain body are grain bodies for four-component hydroxy-terminated polyb propellants of the same formula. By means of the solid rocket engine with the high thrust ratio and a manufacturing method thereof, the problem of a small thrust ratio can be solved, the high thrust ratio can be provided, working is table, and the structure and performance are reliable.

Description

technical field [0001] The invention relates to the technical field of solid rocket motors, in particular to a solid rocket motor with a large thrust ratio and a manufacturing method thereof. Background technique [0002] In the design of small tactical missiles, solid rocket motors are used as power sources. In order to improve tactical performance, single-chamber dual-thrust structures are usually used, including booster stages and cruise stages. After the main charge of the combustion chamber is reliably ignited, it continues to burn to generate a predetermined thrust. The booster stage has a large thrust and short working time to provide the main thrust for missile launch; the cruise stage has a long working time and relatively stable thrust to provide power for the cruise flight of the missile. source. With the overall development of missiles, the thrust ratio between the booster stage and the cruise stage is required to be further increased to more than 7, which bring...

Claims

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Application Information

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IPC IPC(8): F02K9/34F02K9/10F02K9/28
Inventor 陈永钊陈曦余永春刘浚榕史丰雨肖利利吕磊吴刚王菲
Owner HUBEI SANJIANG AEROSPACE JIANGHE CHEM TECH
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