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Process for pre-compacting prepreg overlay of resin-based composite material

A technology of composite materials and prepregs, applied in lamination, lamination devices, lamination auxiliary operations, etc., can solve problems such as large wrinkles

Active Publication Date: 2010-06-09
AVIC BEIJING INST OF AERONAUTICAL MATERIALS
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] The present invention is designed to solve the problems existing in the above-mentioned prior art and provides a resin-based composite material prepreg layup pre-compacting process, and its purpose is to solve the traditional method for special-shaped hyperboloid large-thickness prepreg layup The problem of local large wrinkles in the pre-compacting process can evenly distribute the layer size error on the entire surface of the workpiece instead of accumulating in a certain local area, so that there will be no obvious wrinkles on the surface of the workpiece, and the curing process can be ensured. Integrity and uniformity of finished parts

Method used

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  • Process for pre-compacting prepreg overlay of resin-based composite material
  • Process for pre-compacting prepreg overlay of resin-based composite material
  • Process for pre-compacting prepreg overlay of resin-based composite material

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0016] Choose the uniform pressure transmission layer as barbed wire mesh, the wire diameter is 0.5mm, and the hole is 2mm square, lay it on the surface of the hyperbolic male mold, then spread the PTFE cloth and air felt, use the vacuum bag and sealing tape to seal and pump Vacuum, stay at room temperature for 10 minutes and then open the vacuum bag. Lay the skin material according to the requirements of the drawings. The skin material is SW-280A / 3218. After laying 6 layers, then lay the non-porous film, iron wire uniform pressure transmission layer, PTFE cloth and air felt in turn, and use vacuum bag After sealing with the sealing tape, vacuumize, push into the autoclave, vacuumize at room temperature and raise the temperature to the mold temperature of 70°C±5°C, open the can and push out the mold after 30 minutes of heat preservation, keep the vacuum until the mold temperature is lower than 40°C, open Vacuum bag. The comparison of its pre-compacted quality with that of the...

Embodiment 2

[0020] The uniform pressure-transmitting layer is selected as Nomex paper honeycomb, the grade is NH-1-1.83-48, which is a hexagon with a cell side length of 2.75mm, a density of 48kg / m3, and a honeycomb thickness of 2mm to 3mm. Lay the skin material according to the requirements of the drawings. The mold is a hyperboloid female mold, and the skin material is T700 / 3234. After laying 16 layers according to the angle, then lay the non-porous film, the honeycomb uniform pressure transmission layer, and the PTFE cloth in sequence. and air felt, use vacuum bags and sealing strips to seal and vacuumize, push into the autoclave, vacuumize at room temperature and heat up to the mold temperature of 70°C±5°C, open the can and push out the mold after 30 minutes of heat preservation, keep the vacuum, wait for the mold If the temperature is lower than 40°C, open the vacuum bag. The comparison of its pre-compacted quality with that of the traditional pre-compacted surface without a uniform ...

Embodiment 3

[0024] The uniform pressure transmission layer is selected as a copper wire mesh, the diameter of the copper wire is 0.3mm, and the hole grid is 2.5mm square. Cut the uniform pressure transmission layer according to the unfolded shape of the wing leading edge radome mold. According to the requirements of the drawings, lay up the radome material. The material is QW280 / 5528. After laying 12 layers, then lay the non-porous film, copper wire uniform pressure transmission layer, PTFE cloth and air felt in turn, and use vacuum bag and seal After sealing the rubber strip, vacuumize it, push it into the oven, heat it up to the mold temperature of 100°C±5°C by vacuuming at room temperature, and keep it warm for 10 minutes, then push out the mold and keep the vacuum. When the mold temperature is lower than 60°C, open the vacuum bag. The comparison of its pre-compacted quality with that of the traditional pre-compacted surface without a uniform pressure-transmitting layer is shown in Tab...

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Abstract

The invention relates to a process for pre-compacting the prepreg overlay of a resin-based composite material. Auxiliary materials of the process are a non-porous or porous isolating membrane, a piece of tetrafluoroethylene cloth and a piece of breathable felt in sequence and are sealed with a sealing joint strip and a vacuum bag or a rubber bag. The process is characterized in that: a flexible porous uniform pressure transfer layer is added between the isolating membrane and the tetrafluoroethylene cloth or between the tetrafluoroethylene cloth and the breathable felt in the auxiliary materials of the process and is 0.1 to 3 mm thick; and the area of a single pore of the flexible porous uniform pressure transfer layer is 0.25 to 100 sq. mm. The technical scheme of the invention, comparedwith the prior art, solves the problem of large partial folds produced in the pre-compacting process of the special prepreg overlay with double curved surfaces and in large thickness in a conventional method, and can uniformly distribute the error of the external dimension of the overlay on the entire surface of a work piece but not accumulate the error at a certain partial region, so that no obvious fold is produced on the surface of the work piece to ensure the integrity and uniformity of the cured work piece.

Description

technical field [0001] The invention relates to a resin-based composite material prepreg layer pre-compacting process, which belongs to the technical field of composite material processing. Background technique [0002] The current research and application of new materials and new processes has always been one of the main contents of high-tech. Advanced resin-based composite materials have excellent performance, and have been widely used in various equipment, and have achieved obvious benefits. Advanced resin matrix composites are mainly composed of reinforcing fibers and resin matrix, such as carbon fiber, quartz fiber, E and S glass fiber, aramid fiber, high molecular weight polyethylene fiber and fiber ceramic fiber, etc. Various thermosetting and thermoplastic resins such as horse, cyanate, polyimide, polyether ether ketone, etc. Prepreg refers to the sheet-like material formed by fiber impregnation resin, which is the main raw material of high-performance resin-based ...

Claims

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Application Information

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IPC IPC(8): B32B37/10B32B38/08
Inventor 蔡良元白树成温磊张华崔溢陈梦怡杨明姜健王清海刘京林刘梦媛
Owner AVIC BEIJING INST OF AERONAUTICAL MATERIALS
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