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Solid rocket engine propellant lining layer material and preparation method thereof

A solid rocket and propellant technology, applied in the directions of adhesives, adhesive additives, non-polymer adhesive additives, etc., can solve the problems of serious migration performance and high polarity of nitrate plasticizers, and achieve migration inhibition performance, low Polarity, effect of broadening method

Active Publication Date: 2016-02-10
HUBEI INST OF AEROSPACE CHEMOTECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0005] The purpose of the invention is to solve the problem that the propellant liner material for the existing solid rocket motor has high polarity, and the migration performance of the nitrate plasticizer is serious when it contacts with the NEPE composite propellant, and a kind of low polarity is provided. A propellant liner material for solid rocket motors that can effectively inhibit the migration of polar plasticizers and improve the safety and reliability of NEPE solid rocket motors

Method used

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Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0033] Put 10g of azido-terminated polybutadiene and 0.15g of dioctyl sebacate into a dry beaker, mix well and add 2g of carbon black. After mixing evenly, add 0.62g of dipropynyl succinate and 0.05g of cuprous acetate as a process aid, and mix evenly. Then vacuum poured into tetrafluoroethylene mold, 50 o Curing at C for 6 days to obtain the lining material for solid rocket motors. The obtained liner material and H 2 The contact angle is 100 at O5 seconds o , the contact angle at 1 minute is 95 o .

Embodiment 2

[0035] Put 20g of azido-terminated polybutadiene and 0.2g of dioctyl adipate into a dry beaker, then add 4g of silicon dioxide, mix well and add 1.06g of trimethylolpropane triplyne ether, 0.16 g process additive tris(triphenylphosphine) cuprous bromide, and mix well. Then vacuum poured into tetrafluoroethylene mold, 50 o Curing at C for 6 days to obtain the lining material for solid rocket motors. The liner material 20 o Under C, the mechanical tensile strength is 0.54MPa, and the elongation is 212%.

Embodiment 3

[0037] Put 10g of azido-terminated polybutadiene and 0.1g of dibutyl phthalate into a dry beaker, mix well and add 1.5g of boron powder. After mixing evenly, add 0.3g tripynylamine, process additive 0.02g 5-nitrotetrazolium cuprous, and mix evenly, then vacuum pour into tetrafluoroethylene mold, 60 o Curing at C for 6 days to obtain the lining material for solid rocket motors. The resulting liner material 25 o C Soaked in glycerol triacetate for 96 hours, the mass weight gain rate was <2%.

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Abstract

The present invention relates to a solid rocket engine propellant lining layer material and a preparation method thereof, and belongs to the field of solid rocket engine lining layer material preparation. According to the present invention, azido-terminated polybutadiene is adopted as a polymer prepolymer, a multi-alkynyl compound is adopted as a curing agent, a plasticizer, a solid filler and a process auxiliary agent are added, and an inter-azido / alkynyl click chemistry reaction is used to prepare the triazole five-membered ring cross-linked low-polarity polybutadiene lining layer material, such that the migration performance of the polar nitrate plasticizer of the NEPE composite propellant in the lining layer material is effectively inhibited; and the obtained solid rocket engine propellant lining layer material can be subjected to curing molding within the temperature of 50-70 DEG C, the reaction conditions are mild, the obtained lining layer material has low polarity, the disadvantages of the propellant lining layer material preparation through the cross-linking of polyurethane and polybutadiene are overcome, and the propellant lining layer material preparation method is broadened.

Description

technical field [0001] The invention belongs to the field of preparation of a lining material for a solid rocket motor, and in particular relates to a propellant lining material for a solid rocket motor and a preparation method thereof. Background technique [0002] The propellant liner is a viscoelastic substance that firmly bonds the propellant grain and the thermal insulation layer. It is an indispensable and important part of the shell-bonded solid rocket motor. Its function is to meet the bonding strength of the propellant and the thermal insulation layer , to ensure the smooth combustion of the propellant. In addition, the propellant lining also has functions such as limiting the burning surface, reducing interfacial stress, and absorbing part of vibration energy. [0003] With the development of solid rocket motor technology, nitrate plasticized polyether (NEPE) high-energy solid composite propellant has become a research hotspot. Compared with the traditional hydro...

Claims

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Application Information

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IPC IPC(8): C09J147/00C09J11/06
Inventor 庞爱民翟进贤杨荣杰尹华丽桑丽鹏王玉罗国勤王爱红李东峰
Owner HUBEI INST OF AEROSPACE CHEMOTECH
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