CN102991009B - Interlayer toughening carbon fiber-metal layer plywood - Google Patents
Interlayer toughening carbon fiber-metal layer plywood Download PDFInfo
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- CN102991009B CN102991009B CN201210465130.3A CN201210465130A CN102991009B CN 102991009 B CN102991009 B CN 102991009B CN 201210465130 A CN201210465130 A CN 201210465130A CN 102991009 B CN102991009 B CN 102991009B
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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
The invention belongs to fiber metal laminate structures manufacture technology of composite material field, relate to a kind of carbon fiber-metal laminate of interlayer toughened.
Background technology
Fiber metal laminate is the novel hybrid buildup structural composite material of a class, be referred to as FML(Fiber-Metal Laminate in the world) laminate, its Typical Representative is aluminium alloy-aramid fiber laminated composite materials laminate, be called ARALL(ARAamid-ALuminum Laminate in the world), and aluminium alloy-glass fibre laminated composite materials laminate, be called GLARE(GLAss-Reinforce aluminum in the world).Bibliography (Vogelesang, L., Development of a New Hybrid Material (ARALL) for AircraftStructure, Ind.Eng.Chem.Prod.Res.Dev., 1983, pp.492-496) and U.S. patent Nos (US.5,039,571, US.5,547,735 and US.5,219,629) preparation method of FML laminated composite materials laminate has all been studied in great detail, mechanical property and advantage and potential application.At present, GLARE is applied on the upper fuselage shell structural of A380 aircraft in large area, is a significant innovative point of A380 aircraft materials technology.
At present, FML composite both domestic and external is all selected nonconducting aramid fiber or glass fibre etc. and is not selected to have the carbon fiber of better mechanical property and interface performance as enhancing, toughening material, its reason is that the potential difference of the metal material such as carbon fiber and aluminium, titanium, steel will form electrochemical corrosion, affect Long-Time Service and the military service performance of this material, finally cause the structural failure of laminate structures and the manufacture of aeronautic structure cannot be applied to.
Summary of the invention
The object of the invention is to propose a kind of high-performance carbon fibre prepreg that uses as reinforcement, and there is not the carbon fiber-metal laminate of the interlayer toughened of galvanic corrosion problems.
Technical scheme of the present invention is that described carbon fiber-metal laminate at least comprises double layer of metal laminate and one deck carbon fiber prepreg, and between carbon fiber prepreg and plymetal, all sandwich one deck surface density is 15 ~ 20g/m
2, thickness be the nylon nonwoven fabrics of 30 ~ 40 μm as toughness reinforcing/separation layer, wherein nylon molecular weight is 4 ~ 6, and fibre diameter is 10 ~ 15 μm.The layup sequence of laminate is plymetal-toughness reinforcing/separation layer-carbon fiber prepreg-toughness reinforcing/separation layer-plymetal, the rest may be inferred for the order that stacks of the carbon fiber-metal laminate of other more multi-layered number, after the paving of complete layer plywood, autoclave forming process is utilized to solidify the carbon fiber-metal laminate obtaining interlayer toughened.
Fibre reinforcement in described carbon fiber prepreg is T300 grade carbon fiber or T700 grade carbon fiber or T800 grade carbon fiber.
Matrix resin in described carbon fiber prepreg is high-toughness epoxy resin.
Described plymetal is aramid aluminiumlaminates or titanium alloy laminate or steel alloy laminate.
Described toughness reinforcing/separation layer nylon nonwoven fabrics thermal plastic high polymer used is nylon 6 or nylon66 fiber or nylon 1010.
Advantage of the present invention selects the thermoplastic nylon non-woven fabrics with high porosity as interlayer toughened/separation layer, resin matrix is made can infiltration to occur smoothly in toughness reinforcing/separation layer and infiltrate in hot-forming process, but toughness reinforcing/separation layer and matrix resin do not occur to dissolve and phase-splitting, still maintain complete nonwoven fabric construct form.And then, the three-dimensional net structure forming non-Polymerization induced phase separation is mutually run through by nylon nonwoven fabrics and matrix resin, play the effect of interlayer toughened, cut off the contact between carbon fiber reinforcement and plymetal simultaneously, serve electrochemistry iris action, eliminate the galvanic corrosion problems caused due to the existence of potential difference between carbon fiber reinforcement and plymetal, make the carbon fiber with excellent mechanical performance can be used for preparing fiber metal Test of Laminate Composites.
Accompanying drawing explanation
Fig. 1 is the carbon fiber-metal laminate structural representation of interlayer toughened of the present invention, in figure: 1 is plymetal, and 2 is toughness reinforcing/separation layers, and 3 is carbon fiber prepregs.
Detailed description of the invention
As shown in Figure 1, described carbon fiber-metal laminate at least comprises double layer of metal laminate 1 and one deck carbon fiber prepreg 3, and between carbon fiber prepreg and plymetal, all sandwich one deck surface density is 15 ~ 20g/m
2, thickness be the nylon nonwoven fabrics of 30 ~ 40 μm as toughness reinforcing/separation layer 2, wherein nylon molecular weight is 4 ~ 60,000, and fibre diameter is 10 ~ 15 μm.The layup sequence of laminate is plymetal-toughness reinforcing/separation layer-carbon fiber prepreg-toughness reinforcing/separation layer-plymetal, the rest may be inferred for the order that stacks of the carbon fiber-metal laminate of other more multi-layered number, after the paving of complete layer plywood, autoclave forming process is utilized to solidify the carbon fiber-metal laminate obtaining interlayer toughened.
Its preparation method is as follows:
A) surface texturing, solvent scouring degrease, pickling and anodization are carried out to plymetal;
B), in being dissolved by epoxy resin-base used for carbon fiber prepreg in solvent, the epoxy resin primer that weight resin content is 40% ~ 50% is formulated as;
C) at brushing one deck epoxy resin primer of the plymetal surface uniform after surface treatment, dry 6h ~ 8h at 40 DEG C ~ 60 DEG C, after solvent volatilization, primer thickness is 15 μm ~ 20 μm;
D) one side being coated with epoxy resin primer at a plymetal successively paving and plymetal equidimension toughness reinforcing/separation layer, carbon fiber epoxy prepreg, toughness reinforcing/separation layer, by one side and the above-mentioned the superiors of the plymetal of another equidimension coating primer toughness reinforcing/separation layer fits, and completes the paving prefabrication process of carbon fiber-metal laminate;
E) the laminate precast body completing paving is enclosed vacuum bag, in autoclave, complete carbon fiber-metal laminate that solidification obtains interlayer toughened.
Below by embodiment, the present invention is described in further details.
Embodiment 1:
Method according to HB/Z 197-1991 prescribed by standard carries out surface texturing, degrease, pickling and anodization to aramid aluminiumlaminates.At brushing one deck epoxy resin primer of the aramid aluminiumlaminates surface uniform after surface treatment, dry 6h at 60 DEG C, after solvent volatilization, primer thickness is 15 μm.Nylon 6 non-woven fabrics, T300 grade carbon fiber epoxy prepreg, nylon 6 non-woven fabrics of the one side being coated with epoxy resin primer at an aramid aluminiumlaminates paving and aramid aluminiumlaminates equidimension successively, the one side of the aramid aluminiumlaminates of another equidimension coating epoxy resin primer is fitted with nylon 6 non-woven fabrics of the above-mentioned the superiors, complete the paving prefabrication process of carbon fiber-metal laminate, the laminate precast body completing paving is enclosed vacuum bag, in autoclave, completes carbon fiber-metal laminate that solidification obtains interlayer toughened.
Embodiment 2:
Method according to HB/Z 197-1991 prescribed by standard carries out surface texturing, degrease, pickling and anodization to titanium alloy laminate.At brushing one deck epoxy resin primer of the titanium alloy laminate surface uniform after surface treatment, dry 8h at 40 DEG C, after solvent volatilization, primer thickness is 15 μm.Nylon66 fiber non-woven fabrics, T700 grade carbon fiber epoxy prepreg, the nylon66 fiber non-woven fabrics of the one side being coated with epoxy resin primer at a titanium alloy laminate paving and titanium alloy laminate equidimension successively, the one side of the titanium alloy laminate of another equidimension coating epoxy resin primer is fitted with the nylon66 fiber non-woven fabrics of the above-mentioned the superiors, complete the paving prefabrication process of carbon fiber-metal laminate, the laminate precast body completing paving is enclosed vacuum bag, in autoclave, completes carbon fiber-metal laminate that solidification obtains interlayer toughened.
Embodiment 3:
Method alloy steel laminate according to HB/Z 197-1991 prescribed by standard carries out surface texturing, degrease, pickling and anodization.At brushing one deck epoxy resin primer of the steel alloy laminate surface uniform after surface treatment, dry 7h at 50 DEG C, after solvent volatilization, primer thickness is 20 μm.Nylon 1010 non-woven fabrics, T700 grade carbon fiber epoxy prepreg, the nylon 1010 non-woven fabrics of the one side being coated with epoxy resin primer at an opening and closing gold steel laminate paving and steel alloy laminate equidimension successively, the one side of the steel alloy laminate of another equidimension coating epoxy resin primer is fitted with the nylon 1010 non-woven fabrics of the above-mentioned the superiors, complete the paving prefabrication process of carbon fiber-metal laminate, the laminate precast body completing paving is enclosed vacuum bag, in autoclave, completes carbon fiber-metal laminate that solidification obtains interlayer toughened.
Embodiment 4:
Method according to HB/Z 197-1991 prescribed by standard carries out surface texturing, degrease, pickling and anodization to aramid aluminiumlaminates.At brushing one deck epoxy resin primer of the aramid aluminiumlaminates surface uniform after surface treatment, dry 6h at 60 DEG C, after solvent volatilization, primer thickness is 20 μm.Nylon66 fiber non-woven fabrics, T800 grade carbon fiber epoxy prepreg, the nylon66 fiber non-woven fabrics of the one side being coated with epoxy resin primer at an aramid aluminiumlaminates paving and aramid aluminiumlaminates equidimension successively, the one side of the aramid aluminiumlaminates of another equidimension coating epoxy resin primer is fitted with the nylon66 fiber non-woven fabrics of the above-mentioned the superiors, complete the paving prefabrication process of carbon fiber-metal laminate, the laminate precast body completing paving is enclosed vacuum bag, in autoclave, completes carbon fiber-metal laminate that solidification obtains interlayer toughened.
Embodiment 5:
Method alloy steel laminate according to HB/Z 197-1991 prescribed by standard carries out surface texturing, degrease, pickling and anodization.At brushing one deck epoxy resin primer of the steel alloy laminate surface uniform after surface treatment, dry 7h at 50 DEG C, after solvent volatilization, primer thickness is 20 μm.Nylon 6 non-woven fabrics, T300 grade carbon fiber epoxy prepreg, nylon 6 non-woven fabrics of the one side being coated with epoxy resin primer at an opening and closing gold steel laminate paving and steel alloy laminate equidimension successively, the one side of the steel alloy laminate of another equidimension coating epoxy resin primer is fitted with nylon 6 non-woven fabrics of the above-mentioned the superiors, complete the paving prefabrication process of carbon fiber-metal laminate, the laminate precast body completing paving is enclosed vacuum bag, in autoclave, completes carbon fiber-metal laminate that solidification obtains interlayer toughened.
Embodiment 6:
Method according to HB/Z 197-1991 prescribed by standard carries out surface texturing, degrease, pickling and anodization to titanium alloy laminate.At brushing one deck epoxy resin primer of the titanium alloy laminate surface uniform after surface treatment, dry 8h at 40 DEG C, after solvent volatilization, primer thickness is 15 μm.Nylon 1010 non-woven fabrics, T300 grade carbon fiber epoxy prepreg, the nylon 1010 non-woven fabrics of the one side being coated with epoxy resin primer at a titanium alloy laminate paving and titanium alloy laminate equidimension successively, the one side of the titanium alloy laminate of another equidimension coating epoxy resin primer is fitted with the nylon 1010 non-woven fabrics of the above-mentioned the superiors, complete the paving prefabrication process of carbon fiber-metal laminate, the laminate precast body completing paving is enclosed vacuum bag, in autoclave, completes carbon fiber-metal laminate that solidification obtains interlayer toughened.
Claims (5)
1. carbon fiber-the metal laminate of an interlayer toughened, it is characterized in that, described carbon fiber-metal laminate at least comprises double layer of metal laminate and one deck carbon fiber prepreg, and between carbon fiber prepreg and plymetal, all sandwich one deck surface density is 15 ~ 20g/m
2, thickness be the nylon nonwoven fabrics of 30 ~ 40 μm as toughness reinforcing/separation layer, wherein nylon molecular weight is 4 ~ 60,000, and fibre diameter is 10 ~ 15 μm; The layup sequence of laminate is plymetal-toughness reinforcing/separation layer-carbon fiber prepreg-toughness reinforcing/separation layer-plymetal, the rest may be inferred for the order that stacks of the carbon fiber-metal laminate of other more multi-layered number, after the paving of complete layer plywood, autoclave forming process is utilized to solidify the carbon fiber-metal laminate obtaining interlayer toughened.
2. carbon fiber-the metal laminate of a kind of interlayer toughened as claimed in claim 1, is characterized in that, the fibre reinforcement in described carbon fiber prepreg is T300 grade carbon fiber or T700 grade carbon fiber or T800 grade carbon fiber.
3. carbon fiber-the metal laminate of a kind of interlayer toughened as claimed in claim 1, is characterized in that, the matrix resin in described carbon fiber prepreg is high-toughness epoxy resin.
4. carbon fiber-the metal laminate of a kind of interlayer toughened as claimed in claim 1, is characterized in that, described plymetal is aramid aluminiumlaminates or titanium alloy laminate or steel alloy laminate.
5. carbon fiber-the metal laminate of a kind of interlayer toughened as claimed in claim 1, is characterized in that, described toughness reinforcing/separation layer nylon nonwoven fabrics thermal plastic high polymer used is nylon 6 or nylon66 fiber or nylon 1010.
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| CN103625040A (en) * | 2013-11-04 | 2014-03-12 | 孙直 | Composite-material and metal-material laminating structure with fiber interface for toughening and method |
| CN104985180B (en) * | 2015-07-31 | 2017-08-18 | 中国航空工业集团公司北京航空制造工程研究所 | A kind of intermetallic compound and preparation method thereof and equipment |
| CN106079688A (en) * | 2016-06-02 | 2016-11-09 | 廊坊市高瓷新材料科技有限公司 | Reinforced structure and its preparation method |
| CN106521805B (en) * | 2017-01-13 | 2018-11-06 | 中国航空工业集团公司北京航空材料研究院 | A kind of preparation method of conduction-toughening melt-blown compound nonwoven cloth |
| CN108595754A (en) * | 2018-03-20 | 2018-09-28 | 南京航空航天大学 | The emulation mode of interlayer toughened composite laminated plate |
| EP3925773A4 (en) * | 2019-02-13 | 2022-11-16 | Sekisui Chemical Co., Ltd. | Layered sheet |
| JP7173299B2 (en) * | 2019-04-02 | 2022-11-16 | 日本製鉄株式会社 | Metal-carbon fiber reinforced resin material composite and method for producing metal-carbon fiber reinforced resin material composite |
| CN111391421A (en) * | 2020-02-25 | 2020-07-10 | 长安大学 | Carbon fiber and metal composite structure and preparation method thereof |
| CN111376547B (en) * | 2020-04-15 | 2021-06-15 | 燕山大学 | Preparation process of fiber reinforced metal composite board |
| CN112848544B (en) * | 2021-01-14 | 2023-03-31 | 中车青岛四方机车车辆股份有限公司 | Fiber metal laminated plate and preparation method thereof |
| TWI781780B (en) * | 2021-10-01 | 2022-10-21 | 永虹先進材料股份有限公司 | Thermoplastic carbon fiber composite structure and method of making the same |
| CN113833713A (en) * | 2021-10-18 | 2021-12-24 | 浙江昊达气动科技有限公司 | Thin cylinder |
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| US5039571A (en) * | 1987-10-14 | 1991-08-13 | Akzo Nv | Metal-resin laminate reinforced with S2-glass fibres |
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| CN102505355A (en) * | 2011-11-15 | 2012-06-20 | 中国航空工业集团公司北京航空材料研究院 | Toughening material of composite material and preparation method toughening material |
| CN102702683A (en) * | 2012-06-04 | 2012-10-03 | 中国航空工业集团公司北京航空材料研究院 | Epoxy resin for prepreg and preparation method thereof |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN1923506B (en) * | 2006-07-19 | 2010-08-04 | 中国航空工业第一集团公司北京航空材料研究院 | Toughening composite material lamination board and method for making same |
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| US5039571A (en) * | 1987-10-14 | 1991-08-13 | Akzo Nv | Metal-resin laminate reinforced with S2-glass fibres |
| CN1950200A (en) * | 2004-02-10 | 2007-04-18 | 波音公司 | Aluminum-fiber laminate |
| CN102505355A (en) * | 2011-11-15 | 2012-06-20 | 中国航空工业集团公司北京航空材料研究院 | Toughening material of composite material and preparation method toughening material |
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