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Preparation method of thermoplastic polyimide-based composite material structure member (cover)

A technology of polyimide-based and composite materials, which is applied in the field of preparing skin components from resin-based composite materials, and can solve problems such as difficulty in preparing high-density products, difficulty in removing solvents from small molecules, and high manufacturing costs. , to achieve the effect of low manufacturing cost, short molding cycle and good toughness

Active Publication Date: 2010-06-16
CHENGDU AIRCRAFT INDUSTRY GROUP +1
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, the introduction of solvent will lead to the difficulty of solvent removal and the release of small molecules during the molding process, making it difficult to prepare high-density products
Leading to high manufacturing costs, large-scale application is limited

Method used

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Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0024] At 100g / m 2 Spread 2 0.001mm thermoplastic polyimide films on top and bottom of T300 carbon fiber 1k plain cloth, fiber / film=80 / 20. For 2mm thick parts, 14 layers are required. Thermoplastic polyimide film and carbon fiber and glass fiber braid layer are layered in turn. Put the layered carbon fiber (carbon cloth) and thermoplastic polyimide film into the skin part of the mold cavity of the cover part, and add the thermoplastic polyimide-based chopped fiber to the mold cavity reinforcement part Composite material NDJ-901-C30 powder (30% chopped carbon fiber content, 0.05mm fiber length), mold clamping. After heating in a mold press at 400°C for 0.5 hours, pressurize it at a pressure of 100MPa for 5 minutes, and cool to 200°C for demolding. The density of the cover can be 1600kg / m 3 , The tensile strength is 800MPa, and the total molding time is 35 minutes.

Embodiment 2

[0026] The glass cloth can be SW280-100 of Nanjing Fiberglass Research and Design Institute. At 400g / m 2 Spread one piece of 0.250mm thermoplastic polyimide film on and between the bottom of the glass cloth, fiber / film=20 / 80. For 2mm thick parts, 7 layers are required. The film and the carbon fiber and glass fiber braid are layered in turn. Put the layered glass cloth and thermoplastic polyimide film mixture into the skin part of the part mold cavity, and add the thermoplastic polyimide-based chopped fiber composite material to the part of the part mold cavity reinforcement NDJ-901-G30 powder (30% chopped glass fiber content, 10.0mm fiber length), mold clamping. After heating in a mold press at 300°C for 1 hour, pressurize it at a pressure of 10 MPa for 10 minutes, and cool to 200°C for demolding. The density of the prepared composite material is 1600kg / m 3 , The tensile strength is 600MPa, and the total molding time is 70 minutes.

Embodiment 3

[0028] Lay the T300 carbon fiber 12K wire flat at 280g / m 2 Spread 1 piece of 0.1mm thermoplastic polyimide film on and under the carbon fiber, fiber / film=50 / 50. For 2mm thick parts, 11 layers can be laid. The film and the carbon fiber and glass fiber braid are layered in turn. Put the layered carbon fiber and thermoplastic polyimide film into the skin part of the mold cavity of the part, and add 40 pieces of thermoplastic polyimide-based chopped fiber composite material NDJ-901-ECG to the reinforcement part of the mold cavity Material (the content of chopped glass fiber and carbon fiber are 15% and 25%, and the fiber length is 1.00mm), and then the mold is closed. After heating for 0.8 hours in a mold press at 360°C, pressurize at a pressure of 25MPa for 7 minutes, and cool to 200°C for demolding. The density of the prepared composite material is 1500kg / m 3 , The tensile strength is 800MPa, and the total molding time is 55 minutes.

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Abstract

The invention provides a preparation method of a thermoplastic polyimide-based composite material structure member (cover), which can be used for obviously improving the density and the toughness of products and forming an integrated skin cover member in one step. The method of the invention is realized by the following technical scheme comprising the steps of: at least laying one thermoplastic polyimide film the thickness of which is at least 0.001mm on the upper surface and the lower surface of carbon fiber or glass fiber fabric, and successively laminating the fiber fabric and the thermoplastic polyimide film in proportion; putting the laminated multilayer fiber fabric and the thermoplastic polyimide film into the skin part of a cover member mold cavity; adding thermoplastic polyimide-based chopped fiber composite material powder or granules at the reinforcing rib part of the mold cavity, and assembling the mold; after heating for 0.5-1 hour at300-400 DEG C on a molding press, applying 10-100MPa pressure , and keeping the pressure for 5-10 minutes; and then, cooling below 200 DEG C for demolding. The invention does not need to introduce solvents and has short cycle and low cost. The skin cover has light weight, high strength and high temperature resistance.

Description

Technical field [0001] The invention relates to a method for preparing a skin member by using a resin-based composite material, in particular to a method for preparing an aircraft cover structure using a thermoplastic polyimide-based composite material. Background technique [0002] The improvement of the performance of aircrafts and other aircraft depends on the material to a considerable extent. Among the ten key technical problems affecting the manufacture of large aircraft, advanced composite material technology has become one of the biggest technical obstacles to the development of large passenger aircraft projects in my country. The driving force of the use of composite materials is to reduce weight, while having a high modulus / weight ratio and strength / weight ratio. The first 787 produced by the Boeing Company of the United States, whose composite materials account for 50% of the total structural mass, is the world's first large-scale commercial airliner with composite wi...

Claims

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Application Information

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IPC IPC(8): B29C43/20B29C43/58
Inventor 肖娟黄培彭兴国王晓东吴步根高彬
Owner CHENGDU AIRCRAFT INDUSTRY GROUP
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