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Interlayer toughening carbon fiber-metal layer plywood

A metal laminate and carbon fiber technology, applied in metal layered products, layered products, synthetic resin layered products, etc., can solve problems that affect the long-term use and service performance of materials, electrochemical corrosion, and cannot be applied to aerospace structure manufacturing. , to achieve the effect of eliminating the problem of electrochemical corrosion

Active Publication Date: 2013-03-27
AVIC BEIJING INST OF AERONAUTICAL MATERIALS
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  • Summary
  • Abstract
  • Description
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  • Application Information

AI Technical Summary

Problems solved by technology

[0003] At present, FML composite materials at home and abroad choose non-conductive aramid fibers or glass fibers instead of carbon fibers with better mechanical properties and interface properties as reinforcement and toughening materials. The reason is that carbon fibers are compatible with aluminum, titanium, steel The potential difference of such metal materials will form electrochemical corrosion, which will affect the long-term use and service performance of this material, and eventually lead to the structural failure of the laminated structure and cannot be applied to the manufacture of aerospace structures.

Method used

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  • Interlayer toughening carbon fiber-metal layer plywood

Examples

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Embodiment 1

[0021] According to the method stipulated in the HB / Z 197-1991 standard, the aluminum alloy laminates are subjected to surface roughening, degreasing, pickling and anodizing. Apply a layer of epoxy resin primer evenly on the surface of the aluminum alloy laminate after surface treatment, and dry at 60°C for 6 hours. After the solvent evaporates, the thickness of the primer is 15 μm. Lay nylon 6 non-woven fabric, T300 grade carbon fiber epoxy resin prepreg, and nylon 6 non-woven fabric of the same size as the aluminum alloy laminate on the side coated with epoxy resin primer. Lay the side of another aluminum alloy laminate of the same size coated with epoxy resin primer to the above-mentioned top layer of nylon 6 non-woven fabric to complete the prefabrication process of carbon fiber-metal laminates, and the paving will be completed. The laminate prefabricated body is sealed in a vacuum bag and cured in an autoclave to obtain an interlayer toughened carbon fiber-metal laminate....

Embodiment 2

[0023] According to the method stipulated in HB / Z 197-1991 standard, surface roughening, degreasing, pickling and anodizing treatment are carried out on the titanium alloy laminate. Apply a layer of epoxy resin primer evenly on the surface of the titanium alloy laminate after surface treatment, and dry at 40°C for 8 hours. After the solvent evaporates, the thickness of the primer is 15 μm. Lay nylon 66 non-woven fabric, T700 grade carbon fiber epoxy resin prepreg, and nylon 66 non-woven fabric of the same size as the titanium alloy laminate on the side of a titanium alloy laminate coated with epoxy resin primer. Lay the side of another equal-sized titanium alloy laminate coated with epoxy resin primer to the above-mentioned uppermost layer of nylon 66 non-woven fabric to complete the prefabrication process of carbon fiber-metal laminate, and the paving will be completed. The laminate prefabricated body is sealed in a vacuum bag and cured in an autoclave to obtain an interlayer...

Embodiment 3

[0025] According to the method stipulated in the HB / Z 197-1991 standard, the surface of the alloy steel laminate is roughened, degreased, pickled and anodized. Apply a layer of epoxy resin primer evenly on the surface of the alloy steel laminate after surface treatment, and dry it at 50°C for 7 hours. After the solvent evaporates, the thickness of the primer is 20 μm. Lay nylon 1010 non-woven fabric, T700 grade carbon fiber epoxy resin prepreg, and nylon 1010 non-woven fabric of the same size as the alloy steel laminate on the side of an alloy steel laminate coated with epoxy resin primer. Lay the side of another alloy steel laminate of the same size coated with epoxy resin primer to the above-mentioned top layer of nylon 1010 non-woven fabric to complete the prefabrication process of carbon fiber-metal laminates, and the paving will be completed. The laminate prefabricated body is sealed in a vacuum bag and cured in an autoclave to obtain an interlayer toughened carbon fiber-...

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Abstract

The invention belongs to the technical field of fiber-metal laminating structure composite materials, and relates to an interlayer toughening carbon fiber-metal layer plywood. The interlayer toughening carbon fiber-metal layer plywood provided by the invention takes a thermoplastic nylon non-woven fabric with high porosity as an interlayer toughening / isolating layer, a resin matrix in a hot compacting process can smoothly generate penetration and soakage in the toughening / spacer, the toughening / isolating layer and a basal body resin can not dissolve and generate phase splitting, and the complete non-woven fabric structural style is still kept; further, the nylon non-woven fabric and the basal body resin mutually penetrate so as to form a non-reaction inductive detached three-dimensional net structure, plays the role of the interlayer toughening action, simultaneously obstructs the contact of a carbon fiber strengthening body and a metal plywood, and plays the role of the electrochemistry separate action; and electro-chemical corrosion is caused between the carbon fiber strengthening body and the metal plywood because of potential difference, and the carbon fiber with the excellent mechanical property is used for preparing a fiber -metal layer plywood composite material.

Description

technical field [0001] The invention belongs to the technical field of manufacturing fiber-metal laminated structural composite materials, and relates to an interlayer toughened carbon fiber-metal laminate. Background technique [0002] Fiber-metal laminates are a new type of hybrid reinforced structural composite materials, collectively referred to as FML (Fiber-Metal Laminate) laminates internationally, and its typical representative is aluminum alloy-aramid fiber laminated composite material laminates, known internationally as It is ARALL (ARAamid-ALuminum Laminate), and aluminum alloy-glass fiber laminated composite laminate, which is called GLARE (GLAss-Reinforce aluminum) internationally. References (Vogelesang, L., Development of a New Hybrid Material (ARALL) for Aircraft Structure, Ind.Eng.Chem.Prod.Res.Dev., 1983, pp.492-496) and US invention patents (US.5,039,571, US.5,547,735 and US.5,219,629) have studied in detail the preparation method, mechanical properties, ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B32B9/04B32B15/088B32B27/12B32B27/04
Inventor 刘刚马宏毅张朋崔海超李伟东益小苏
Owner AVIC BEIJING INST OF AERONAUTICAL MATERIALS
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