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A kind of synthetic method of chemically degradable propellant curing accelerator

A curing accelerator and chemical degradation technology, applied in the field of synthesis of chemically degradable propellant curing accelerator, can solve the problems of uncurable test formula, insufficient cross-linking density, loss of activity of hydroxyl groups, etc., and achieve safe synthesis route and post-processing The method is simple and the product yield is high

Active Publication Date: 2018-10-12
HUBEI INST OF AEROSPACE CHEMOTECHNOLOGY
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, since AP has a certain solubility in the binder and can be ionized in the binder, the ionized NH 4 + Form a complex structure similar to hydrogen bonds with the adhesive, making the hydroxyl group inactive and unable to react with the curing agent, resulting in the failure of the test formulation to cure
Even after curing, due to the presence of a large amount of AP, the NH bound to the hydroxyl 4 + The number is large, and a considerable number of hydroxyl groups are covered by NH 4 + complexed, and the complexed NH 4 + It also forms a crown ether-like structure with the curled PEG segment in the adhesive, resulting in insufficient cross-linking density and a low degree of cross-linking in the network structure, resulting in softening at higher temperatures

Method used

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  • A kind of synthetic method of chemically degradable propellant curing accelerator
  • A kind of synthetic method of chemically degradable propellant curing accelerator
  • A kind of synthetic method of chemically degradable propellant curing accelerator

Examples

Experimental program
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Effect test

Embodiment 1

[0052] Synthesis of embodiment 1 polyethylene glycol monomethyl ether acrylate / acrylonitrile / 3-butene-1-amine / hydroxyethyl acrylate copolymer:

[0053] Weighing 100g (0.25mol) molecular weight is the polyethylene glycol monomethyl ether acrylate of 400, the acrylonitrile of 106g (2mol), 27g (0.38mol) 3-butene-1-amine, 29g (0.25mol) acrylic acid- Add 2-hydroxyethyl ester, 400g of acetone, 0.5g of AIBN, and 2g of mercaptoethanol into the Erlenmeyer flask, mix well, and set aside.

[0054] Weigh 220g of the above mixed solution and 0.1g of AIBN into a four-neck flask equipped with a condenser, tail gas receiving device and stirring, control the temperature at 80±5°C and heat to reflux, and react for 1.5h to remove the remaining mixed solution Slowly add it dropwise into a four-necked bottle, and finish dropping after 3 hours. After the dropwise addition, control the reaction temperature at 85±5°C and keep it warm for 5 hours, then stop heating.

[0055] The solvent was distilled...

Embodiment 2

[0057] Synthesis of embodiment 2 polyethylene glycol monobutyl ether acrylate / acrylonitrile / 3-butene-1-amine / butyl acrylate copolymer:

[0058] Weighing 100g (0.2mol) molecular weight is 500 polyethylene glycol monobutyl ether ester, the acrylonitrile of 96g (1.8mol), 21.4g (0.3mol) 3-butene-1-amine, 38.4g (0.3mol) ) Butyl acrylate, 400g of acetone, 0.5g of AIBN, and 3g of mercaptoethanol were added to the Erlenmeyer flask, fully mixed, and set aside.

[0059] Weigh 230g of the above mixed solution and 0.1g of AIBN into a four-neck flask equipped with a condenser, tail gas receiving device and stirring, control the temperature at 75±5°C and heat to reflux, and react for 1.5h to remove the remaining mixed solution Slowly add it dropwise into the four-necked bottle, and finish dropping it in 3.5 hours. After the dropwise addition, control the reaction temperature at 80±5°C and keep it warm for 5 hours, then stop heating.

[0060] The solvent was distilled off under reduced pres...

Embodiment 3

[0062] Synthesis of embodiment 3 polyethylene glycol monomethyl ether acrylate / acrylonitrile / allylamine / ethyl acrylate copolymer:

[0063] Weighing 200g (0.25mol) molecular weight is the polyethylene glycol monomethyl ether acrylate of 800, the acrylonitrile of 106g (2mol), 22.4g (0.4mol) allylamine, 30g (0.3mol) ethyl acrylate, 600g acetone, Add 0.8g of ABVN and 3.8g of mercaptoethanol into the Erlenmeyer flask, mix well, and set aside.

[0064] Weigh 320g of the above mixed solution and 0.2g of ABVN into a four-neck flask equipped with a condenser and equipped with an exhaust gas receiving device and stirring, control the temperature at 80±5°C and heat to reflux. After 2 hours of reaction, the remaining mixed solution is slowly Add it dropwise into a four-necked bottle, and finish dropping after 4 hours. After the dropwise addition, control the reaction temperature at 85±5°C and keep it warm for 5 hours, then stop heating.

[0065] The solvent was distilled off under reduce...

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Abstract

The invention relates to a synthetic method for an accelerator used for accelerating curing of a chemically degradable propellant. The synthetic method employs an acrylic acid polyethylene glycol single-terminal ether ester compound series, acrylate and a derivative thereof, an enamine compound, acrylonitrile and the like as reactants, an azo substance as an initiator, lower fatty esters like acetone and ethyl acetate as solvents and a mercaptoalcohol substance as a molecular weight regulating agent, and utilizes low-temperature reflux polymerization to synthesize the accelerator used for accelerating curing of the chemically degradable propellant. The synthetic method for the accelerator has the characteristics of short synthesis time, a high raw material utilization rate, a safe synthesis approach, simple post-treatment approach and high yield of the synthesized accelerator.

Description

technical field [0001] The invention relates to a synthesis method of a chemically degradable propellant curing accelerator. The chemically degradable propellant curing accelerator synthesized by the method is mainly used to accelerate the curing of the chemically degradable propellant. Background technique [0002] Solid rocket motors have a certain storage and service life due to their own component characteristics. Due to the use and storage of solid rocket motors in different environments, their performance can no longer meet the original index requirements and have differences. Some The performance of the solid propellant may deteriorate, and it must be decommissioned, which leads to the destruction and reuse of solid propellants after their service life expires. With the decommissioning of a large number of weapons and ammunition, the pressure on the destruction and disposal of abandoned ammunition has increased dramatically. With the increasing awareness of environm...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): C08F290/06C08F220/44C08F226/02C08F220/28C08F220/18
Inventor 王锐肖金武杜芳黄凌杨伯涵罗薇李延波
Owner HUBEI INST OF AEROSPACE CHEMOTECHNOLOGY