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A kind of polyimide composite gas cylinder and preparation method thereof

A composite material and polyimide technology, applied in the field of composite materials, can solve the problems of difficult control of curing process, complicated process, and reduction of burst pressure of gas cylinders.

Active Publication Date: 2021-03-09
AEROSPACE INST OF ADVANCED MATERIALS & PROCESSING TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Applying it to composite gas cylinders is an idea to solve the weak high-temperature bearing capacity of existing materials. However, during the research process, it was found that due to the high curing temperature of polyimide, the thermal expansion of the metal liner and the composite material is obviously inconsistent. At the same time Its curing process is difficult to control. During the reaction process, it needs to go through multiple stages such as solvent volatilization, amidation, imidization, cross-linking and curing. The whole process is relatively complicated, and there are many process parameters that need to be controlled.
In addition, high temperature resistant polyimide resin is only suitable for the solution winding process. Polyimide resin contains solvent, which needs to be removed after winding. After removing the solvent, the fiber will shrink, and the fiber will buckle after curing. Reduce the burst pressure of gas cylinders and affect the bearing strength

Method used

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Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0070] After sandblasting the stainless steel metal liner, use alcohol to remove surface impurities and oil stains, install the metal liner on the winding machine, and spread 0.1mm polyimide film on the outer surface of the metal liner. The preparation method of the polyimide film is as follows: 100 parts of YH-550 polyimide and 10 parts of Vespel thermoplastic polyimide are added to 250 parts of N,N-dimethylacetamide (DMAC) (boiling point 166°C ), stirred at 115°C for 3h, after the mixture was uniform and completely dissolved, then 1 part of polystyrene oligomer (thermal decomposition temperature 325°C) and 0.1 part of chopped carbon fiber with a length of 50 microns were ultrasonically mixed, and the solution method was used to Coat the prepared glue solution on the segregation paper according to the predetermined thickness, bake it at 60°C for 0.5h, attach the isolation film, and make a glue film with a thickness of 0.1mm.

[0071] Then take two shafts of T1000 carbon fiber...

Embodiment 2

[0076] Buffer layer preparation: Add 100 parts of YH-550 polyimide and 20 parts of Vespel thermoplastic polyimide to 250 parts of N,N-dimethylacetamide (DMAC), stir at 115°C for 3 hours, and wait until the mixture is uniform After completely dissolving, add 1 part of polystyrene oligomer and 0.1 part of chopped carbon fiber with a length of 50 microns and ultrasonically mix evenly, and use the solution method to coat the prepared glue on the segregation paper with a predetermined thickness. Baking at ℃h for 0.5h, attaching a separator to make a film with a thickness of 0.1mm.

[0077] The rest of the steps are the same as in Example 1. The obtained high temperature and high pressure resistant polyimide composite gas cylinder is subjected to a room temperature water pressure burst test and a high temperature withstand pressure test, and the performance is similar to that of Example 1.

Embodiment 3

[0079] Except that the polystyrene oligomer was 3 parts, the preparation of the remaining film was the same as in Example 2, and a film of 0.1 mm was obtained.

[0080] The rest of the steps are the same as in Example 1. The obtained high temperature and high pressure resistant polyimide composite gas cylinder is subjected to a room temperature water pressure burst test and a high temperature withstand pressure test, and the performance is similar to that of Example 1.

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Abstract

The invention provides a polyimide composite material gas cylinder and a preparation method thereof. The gas cylinder consists of a metal inner liner and a composite material shell. The composite material shell consists of a buffer layer and a winding layer. The buffer layer is a polyimide glue film. The winding layer is a fiber bundle impregnated with polyimide resin. The buffer layer is adheredto the outer surface of the metal inner liner. The winding layer alternately winds the outer layer of the buffer layer in an order of H-Z-H-Z-...-H-Z-H, wherein the H is circumferential winding and the Z is spiral winding. The buffer layer and the winding layer are co-cured to obtain the composite material shell. According to the invention, the polyimide glue film buffer layer is introduced between the metal inner liner and the polyimide winding layer. The polyimide composite material gas cylinder is designed based on double functions of bonding and thermal stress buffering, and so the flue film can achieve in-situ foaming at a high curing temperature, the high toughness of the glue film can achieve good bonding between the composite material and the metal structure, the peeling strength is improved, potential corrosion can be acoided, and the thermal stress matching between the metal inner liner and the composite material during a high temperature curing and cooling process of the resin can be enhanced.

Description

technical field [0001] The invention relates to a polyimide composite gas cylinder and a preparation method thereof, belonging to the technical field of composite materials. Background technique [0002] With the rapid development of aerospace technology, missiles and aircraft are developing in the direction of high speed, long-distance, and structural and functional integration. The flight speed of missiles and aircraft can reach Ma3-4, and some even break through Ma6. The problem of aerodynamic heating makes the projectile structure face an increasingly harsh working environment. The high temperature environment also limits the application of many commonly used subsonic projectile structural materials such as aluminum alloy and epoxy composite materials. In order to further adapt to the large load of the aircraft Due to the multiple requirements of ammunition volume and long range of missiles, the structure of the missile body needs to be further reduced in weight. [000...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F17C1/06F17C13/00B29C70/68B29C53/56
CPCB29C53/56B29C70/68F17C1/06F17C13/002F17C2203/012F17C2209/2163F17C2209/232F17C2221/014F17C2223/0123
Inventor 柯红军徐铁峰王国勇张维军
Owner AEROSPACE INST OF ADVANCED MATERIALS & PROCESSING TECH