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Resin-based premix and rocket engine housing synchronous thermal-curing and adhesion method

A rocket engine and premix technology, applied in chemical instruments and methods, lamination, layered products, etc., can solve the problems of rocket engine normal operation risk, rocket engine shell risk increase, and accelerated gas heat, etc., to achieve The effect of firm and reliable bonding, good heat insulation, and easy process

Active Publication Date: 2015-09-02
HUBEI INST OF AEROSPACE CHEMOTECHNOLOGY
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

There are three disadvantages of this molding method: one is that the resin-based premix is ​​first cured and then bonded with the rocket engine shell, forming and bonding are divided into two or more steps, and the production efficiency is low; the other is that the resin-based premix is ​​cured The elongation rate of the prefabricated part formed after that is generally less than 10%. The adverse consequence of direct bonding with the rocket engine shell is that a large bond stress is generated, which brings risks to the normal operation of the rocket engine.
The third is that the thermal conductivity of the prefabricated part cured by the resin-based premix is ​​higher than that of the rubber insulation layer. Directly bonding with the rocket engine shell will accelerate the conduction of gas heat to the wall of the rocket engine shell, and the rocket engine shell will be burned. Increased risk of wearing

Method used

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Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0023] The materials to be bonded are (1) solid rocket motor steel casing; (2) resin-based premix made of resin-impregnated ablation-resistant fibers and inorganic high-temperature-resistant solid fillers. The preparation method is as follows: commercially available thermosetting The resin is formulated with ethyl acetate to form 100 parts of glue with a concentration of 50-60%, and then 5-10 parts of ablation-resistant fibers such as carbon fibers, aramid fibers, high-silica fibers, etc., and 10-30 parts of high-temperature resistant solid fillers such as Calcium oxide, magnesium oxide, vermiculite, etc. are added to the thermosetting resin glue, fully stirred to make it evenly mixed, and set aside.

[0024] The bonding material is heat-vulcanized Chemlock 238 binder and heat-vulcanized EPDM rubber compound. The preparation method is as follows: 100 parts of EPDM raw rubber is masticated 4-5 times on an open mill, and then carbon black 1 -5 parts, white carbon black 10-40 par...

Embodiment 2

[0033] The materials to be bonded are (1) the aluminum casing of the solid rocket motor, (2) a resin-based premix made of resin-impregnated ablation-resistant fibers and inorganic high-temperature-resistant solid fillers. The preparation method is as follows: commercially available thermosetting The resin is formulated with ethyl acetate to form 100 parts of glue with a concentration of 50-60%, and then 5-10 parts of ablation-resistant fibers such as carbon fibers, aramid fibers, high-silica fibers, etc., and 10-30 parts of high-temperature resistant solid fillers such as Calcium oxide, magnesium oxide, vermiculite, etc. are added to the thermosetting resin glue, fully stirred to make it evenly mixed, and set aside.

[0034]The bonding material is thermal vulcanization adhesive AS101-4-A and thermal vulcanization EPDM rubber compound. The preparation method of adhesive AS101-4-A is as follows: mix 100 parts of Chemlock 238 adhesive with 10-20 parts of EPDM raw rubber, stir eve...

Embodiment 3

[0043] The material to be bonded is (1) solid rocket motor carbon fiber material shell, (2) resin-based premix made of resin-impregnated ablation-resistant fibers and inorganic high-temperature-resistant solid fillers. The preparation method is as follows: the commercially available thermosetting resin is prepared into 100 parts of glue with a concentration of 50-60% with ethyl acetate, and then 5-10 parts of ablation-resistant fibers such as carbon fiber, aramid fiber, high silica fiber, etc. and Add 10-30 parts of high-temperature-resistant solid fillers such as calcium oxide, magnesium oxide, and vermiculite into the thermosetting resin glue, stir well to make it evenly mixed, and set aside.

[0044] The binder is heat-vulcanized self-made binder AS106-2 and heat-vulcanized nitrile rubber compound. The preparation method of self-made adhesive AS106-2 is as follows: mix 100 parts of Chemlock 238 adhesive with 20-30 parts of raw nitrile rubber, and stir evenly. The preparati...

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Abstract

The invention relates to a resin-based premix and rocket engine housing synchronous thermal-curing and adhesion method, which comprises that a hot vulcanization type mixing rubber sheet coated with an adhesive is placed inside a rocket engine housing and is expanded so as to adhere to the rocket engine housing; and a resin-based premix pressed into a sheet is placed inside the rocket engine housing and is expanded so as to adhered to the hot vulcanization type mixing rubber sheet, such that the premix prepared by adopting the resin as the matrix material and adding the organic or inorganic filler and the rocket engine housing can be subjected to the synchronous one-time thermal-curing molding. The method of the present invention has the following advantages that: the direction adhesion between the resin-based premix and the rocket engine housing is reduced so as to produce the high adhesion stress and reduce the rocket engine housing wall surface temperature increasing rate, the adhesion is reliable, the strength is high, and the process is easy to perform.

Description

technical field [0001] The invention relates to a method for synchronous thermosetting bonding of a resin-based premixed material and a rocket motor shell, and belongs to the field of molding technology of thermal protection materials for solid rocket motors. Background technique [0002] In order to prevent the high-temperature gas from damaging the structural integrity of the rocket motor shell during operation, the solid rocket motor needs to bond a certain thickness of heat insulating layer on the inner surface of the rocket motor shell. The commonly used heat insulating layer is rubber elastomer material, but for the air-breathing For rocket engines, due to the serious erosion of gas particles, the pure rubber insulation layer cannot meet the thermal protection requirements, and a material with high ablation resistance and erosion resistance is required, such as resin-impregnated fiber fabric material or resin-impregnated ablation-resistant fiber and inorganic High-temp...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B32B37/02B32B37/06B32B37/10B32B25/08B32B25/14B32B25/16B32B25/20B32B7/12
Inventor 王江陈春娟张宏雷彭正贵赵志祥詹穹隋琦
Owner HUBEI INST OF AEROSPACE CHEMOTECHNOLOGY
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