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Benzoxazine resin/ethylene-propylene-diene rubber composite heat insulating layer and preparation method thereof

A technology of EPDM rubber and benzoxazine, which is applied in the field of solid rocket motor heat insulation, can solve the problems of not being able to significantly improve the ablation resistance

Active Publication Date: 2020-02-07
SHANGHAI AEROSPACE CHEM ENG INST
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] However, since the EPDM rubber-based insulation layer was widely used in the 1980s, purely relying on the technical progress of ablation-resistant fillers / fibers and flame retardants cannot significantly improve its ablation resistance, and the linear ablation rate is 0.07mm Between / s~0.20mm / s

Method used

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  • Benzoxazine resin/ethylene-propylene-diene rubber composite heat insulating layer and preparation method thereof
  • Benzoxazine resin/ethylene-propylene-diene rubber composite heat insulating layer and preparation method thereof

Examples

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preparation example Construction

[0048] The embodiment of the present invention also provides a method for preparing a benzoxazine resin / EPDM composite thermal insulation layer, comprising the following steps:

[0049] Step 1. According to the raw material ratio of the benzoxazine resin / EPDM composite insulation layer provided in the above-mentioned embodiment, the raw materials are weighed;

[0050] Specifically, for the detailed introduction and effect of the ratio of raw materials, please refer to the above-mentioned embodiment of the ratio of raw materials, and will not be repeated here;

[0051] Step 2, first carry out mastication on the weighed EPDM rubber, and then add the weighed solid filler to knead to obtain the kneaded product;

[0052] Specifically, the second step in the embodiment of the present invention can be masticated and mixed on equipment such as an internal mixer, a two-roller machine or a three-roller machine. Conditions, preferably at 50°C to 70°C during mixing;

[0053] Step 3, add...

Embodiment example 1

[0064] The benzoxazine resin / EPDM composite thermal insulation layer provided in this embodiment has raw material components of 100 parts by mass of EPDM rubber, 60 parts by mass of benzoxazine resin, 10 parts by mass of aramid fiber, two 10 parts by mass of silicon oxide, 2 parts by mass of silicon carbide, 3 parts by mass of (2-chloroethyl) phosphate, 2 parts by mass of melamine polyphosphate, 3 parts by mass of dibutyl sebacate, 2 parts by mass of KH550, 1 part by mass of sulfur parts by mass, 0.6 parts by mass of 2-methylimidazole, 3 parts by mass of dicumyl peroxide, and 3 parts by antimony trioxide, the composite thermal insulation layer has a tensile strength of 7MPa-9MPa and an elongation at break of 150%. The line ablation rate is 0.03mm / s, and the density is 1.08g / cm 3 , the hardness is 88, and the bonding strength with the metal is 3.2MPa. The macro pictures before and after the ablation experiment are as follows: figure 1 As shown, the SEM pictures are as figur...

Embodiment example 2

[0071] The benzoxazine resin / EPDM composite insulation layer provided in this implementation case is composed of 100 parts by mass of EPDM rubber, 40 parts by mass of benzoxazine resin, 10 parts by mass of aramid pulp, 15 parts by mass of silicon dioxide, 5 parts by mass of zirconium boride, 5 parts by mass of (2-chloroethyl) phosphate, 5 parts by mass of bromodichloromethane, 3 parts by mass of dibutyl sebacate, 2 parts by mass of KH5502, 2 parts by mass of sulfur parts by mass, 0.2 parts by mass of 2-methylimidazole, 1.5 parts by mass of dicumyl peroxide, and 2 parts by mass of antimony trioxide, the tensile strength of the composite thermal insulation layer is 7MPa-9MPa, and the elongation at break is 232%. , the line ablation rate is 0.04mm / s, and the density is 1.08g / cm 3 , the hardness is 90, and the bonding strength with metal is 3.6MPa.

[0072] The preparation method of the benzoxazine resin / EPDM rubber composite insulation layer material in this implementation case ...

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Abstract

The invention relates to a benzoxazine resin / ethylene-propylene-diene rubber composite heat insulating layer and a preparation method thereof and belongs to the technical field of heat insulation of solid rocket engines. Raw materials of the composite heat insulating layer comprise the following components in parts by mass: 100 parts of ethylene-propylene-diene rubber, 30-100 parts of benzoxazineresin, 10-15 parts of ablation-resistant fibers, 3-30 parts of solid packing, 6 -12 parts of flame-retardant system, 2-5 parts of process additives and 4.5-9 parts of vulcanization system, wherein thevulcanization system comprises a vulcanizing agent, a co-vulcanizing catalyst and an accelerant, the vulcanizing agent is at least one of sulfur, dicumyl peroxide and benzoyl peroxide, and the co-vulcanizing catalyst is 2-methylimidazole or 4-methylimidazole. The heat insulating layer not only has the favorable heat, mechanical and process properties of an ethylene-propylene-diene rubber heat insulating layer and good compatibility with various propellants and shell materials, but also has high char yield and ablation resistance (the linear ablation rate is 0.02-0.06 mm / s).

Description

technical field [0001] The invention belongs to the technical field of thermal insulation of solid rocket motors, and relates to a benzoxazine resin / EPDM composite thermal insulation layer and a preparation method thereof. Background technique [0002] The heat insulation layer of solid rocket motor is a layer of heat insulation layer material bonded between the inner surface of the shell and the propellant. When the engine is working, the heat insulation material is continuously decomposed and ablated to take away most of the heat to ease the transmission of high temperature gas to the shell. Heat, to prevent the casing from reaching temperatures that endanger the structural integrity of the engine, thereby ensuring the normal operation of the engine. With the use of high-energy propellants and the design of high specific impulse engines in modern warfare, the temperature and pressure of the engine combustion chamber will be further increased compared with ordinary engines,...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): C08L23/16C08L79/04C08L77/10C08K13/02C08K3/36C08K5/521C08K5/3492C08K3/22
CPCC08L23/16C08L2205/03C08L2205/16C08L79/04C08L77/10C08K13/02C08K3/36C08K5/521C08K5/34928C08K3/2279
Inventor 楼阳詹国柱宋洪标温彦威左海丽吴广黄洪勇沈伟民
Owner SHANGHAI AEROSPACE CHEM ENG INST
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