CN103625040A - Composite-material and metal-material laminating structure with fiber interface for toughening and method - Google Patents
Composite-material and metal-material laminating structure with fiber interface for toughening and method Download PDFInfo
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- CN103625040A CN103625040A CN201310532821.5A CN201310532821A CN103625040A CN 103625040 A CN103625040 A CN 103625040A CN 201310532821 A CN201310532821 A CN 201310532821A CN 103625040 A CN103625040 A CN 103625040A
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Abstract
The invention provides a composite-material and metal-material laminating structure with a fiber interface for toughening. The composite-material and metal-material laminating structure uses short fiber for toughening between a composite material and a metal material. A fiber bridge is formed between the composite material and the metal material to provide additional connection. The composite-material and metal-material laminating structure provided by the invention has the advantages that through the bridging action of fiber in a crack tip area, the critical breaking strength of the materials is improved; according to experimental observation and theoretical modeling, due to the toughening of the fiber interface and the bridging action, the layering resistance and the fracture resistance of the materials can be improved, i.e., the parameters such as critical stress strength factors, critical fracture strength and critical energy release rate, the probability of layering and crack extension is reduced, and further the capabilities such as bending strength, energy absorption and impact toughness of the whole structure are improved.
Description
Technical field
The present invention relates to laminate structures, especially carbon fiber that a kind of composite and metal material form bonding well with metal aluminium, and then the ability such as the bending strength of integral material, energy absorption, the impact flexibility laminate structures and the preparation method that are improved.
Background technology
The laminated structure of current known composite-metal material, is comprised of composite layer and metal material layer.The major part of composite layer bearing load wherein; Metal material layer is mainly selected sheet metal, honeycomb or foamed material, improves tired toughness, shock resistance, thermodynamics or the acoustic function of whole laminate structures.Yet in engineering application, the bonding position of composite and metal material is often destroyed, and integrally-built performance cannot be given full play to, and affects the use of material and structure.
For composite, traditional solution be use that fibre bundle is sewed, the mode such as " Z-PIN " is fixed material from thickness direction, but the laminate structures for composite and metal material composition, fibre bundle cannot pass metal part, cause toughness reinforcing cannot the enforcement on this class thickness direction, need seek other method for toughening.
Summary of the invention
Goal of the invention: the invention provides a kind of the have laminated structure of the toughness reinforcing composite-metal material of fiber interface and method, its objective is in the laminate structures that composite in the past of solution and metal material form the toughness reinforcing problem that cannot implement on thickness direction.
Technical scheme: the present invention is achieved by the following technical solutions:
There is the laminated structure of the toughness reinforcing composite-metal material of fiber interface, it is characterized in that: one or more layers composite layer, metal material layer and fiber reinforced layer, consist of, fiber reinforced layer is arranged between composite layer and metal material layer.
Fiber reinforced layer material is used metal, carbon, glass, pottery or macromolecular material one or more microcosmic of making or nanofiber layer wherein; The fibre diameter of fiber reinforced layer is 3 nanometers to 100 micron; Fiber reinforced layer material is continuous fiber or discontinuous fibre; Fiber reinforced aspect density is for being not less than 0.5 gram every square metre to 100 grams every square metre.
Fiber reinforced layer is fibrofelt, pad or the film of random distribution.
Microcosmic or nanofiber that composite layer can be used metal, carbon, glass, pottery or macromolecular material to make; Composite layer can be used thermosetting resin or thermoplastic resin as bonding matrix.
Metal material is used one or more in the smooth surface metal material, grain surface metal material, metal foaming material, porous metal material of various geometric shapes and curvature.
Toughening layer fiber can form bridge between composite layer and metal level, improves adhesive strength and toughness; To using the structure of porous metal material, toughening layer fiber also can carry on the hole wall of porous metals, forms extra fillet Reinforced structure.
Prepare the above-mentioned method with the toughness reinforcing laminated structure of composite-metal material of fiber interface, it is characterized in that: first toughened fiber is trimmed to 2-30 mm length, afterwards low-density toughened fiber is stirred in air or liquid evenly, waits for afterwards fiber natural subsidence or manual uniform felt, pad or the film of being scattered in.
The fibrofelt of making, pad or film and thermosetting resin or thermoplastic resin are crushed to fiber reinforced layer prepreg, more together by structure, need assembled formation with material prepreg, metal material; Or fibrofelt, pad or film and composite are together made and are had fiber reinforced prepreg, then with metal material assembled formation.
Toughness reinforcingly with fiber and composite, use identical resin, co-curing moulding, process and existing layer condensation material process, without obvious difference, are cured by standard according to resin and physical dimension; Adopt co-curing technique that composite, fiber reinforced material are closely connected with metal material.
Advantageous effect: the invention provides a kind of laminated structure of the toughness reinforcing composite-metal material of fiber interface that has, it uses short fiber to carry out toughness reinforcing between composite and metal material.Between composite and metal material, form fiber " bridge ", extra connection is provided.By the bridging effect of fiber in crack tip region, improve the critical fracture strength of material.According to experimental observation and theoretical modeling, toughness reinforcing and the bridging effect of fiber interface can improve anti-layering, the fracture energy of material, be the parameters such as critical stress intensity factors, critical fracture strength, critical energy release rate, reduce the probability of layering and Crack Extension, and then improve the abilities such as integrally-built bending strength, energy absorption, impact flexibility.And, adopt the short fiber of 12 grams every square metre of 3 – to carry out toughness reinforcing, can obtain good effect, than the weight (being greater than 200 grams every square metre) of single layer fibre reinforcing material, integrally-built weight increase is very little, to material specific strength and specific stiffness, can not impact.Simultaneously, toughness reinforcingly with fiber, can use identical resin as matrix with composite or directly on material prepreg, add fiber reinforced layer, all material is used identical resin, can co-curing moulding, process and existing layer condensation material process, without obvious difference, are therefore conveniently improved in existing design basis.
Concrete beneficial effect of the present invention is:
1, the laminate structures forming with conventional composite materials-metal material is compared, and it is toughness reinforcing that the present invention uses fiber to carry out between composite and metal material.Between composite and metal material, form fiber " bridge ", extra connection is provided.By the bridging effect of fiber in crack tip region, improve the critical fracture strength of material.
2, all material of the present invention can be used identical resin, can co-curing moulding, and process and existing laminate structures process, without obvious difference, can be cured by standard according to resin and physical dimension, conveniently in existing design basis, improve.
3, the scope of application of the present invention is wider, and the laminate structures of various sizes and shape is all applicable.According to physical dimension, load level and the requirement to structure function, can carry out the design of laminate structures, select suitable fiber as carbon fiber, aramid fiber, glass fibre etc., and different metal material forms is as honeycomb, foam, section bar etc., makes the rigidity of structure, intensity and functional meeting the demands.
4, the present invention adopts the laminate structures that composite-metal material forms, and this structural fatigue toughness is better, can meet the demand of long-time military service.
accompanying drawing explanation:
Fig. 1 is the fibrofelt schematic diagram that the fiber reinforced layer of the present invention is used.
In figure: black is substrate, white is toughened fiber.
Fig. 2 is that schematic diagram is assembled/assembled to laminate structures of the present invention.
In figure: black layer is composite layer, grey porous layer is metal material layer, two-layer centre be fiber reinforced layer.
Fig. 3 is the fiber reinforced layer of the present invention bridge linking effect schematic diagram.
In figure: top black layer is composite layer, below gray layer is metal material layer, and centre is the toughness reinforcing region of fiber-bridged.
Fig. 4 is that the fiber reinforced layer of the present invention is to the toughness reinforcing schematic diagram of the fillet of porous material.
In figure: top black layer is composite layer, below colorless layer is porous metal material layer, and zone line and curve are the toughness reinforcing region of fiber fillet.
the specific embodiment:
As shown in Figure 1, the invention provides a kind of laminated structure of the toughness reinforcing composite-metal material of fiber interface that has, one or more layers composite layer, metal material layer and fiber reinforced layer, consist of, fiber reinforced layer is arranged between composite layer and metal material layer.
Fiber reinforced layer material is used metal, carbon, glass, pottery or macromolecular material one or more microcosmic of making or nanofiber layer wherein; The fibre diameter of fiber reinforced layer is 3 nanometers to 100 micron; Fiber reinforced layer material is continuous fiber or discontinuous fibre; Fiber reinforced aspect density is for being not less than 0.5 gram every square metre to 100 grams every square metre.
Fiber reinforced layer is fibrofelt, pad or the film of random distribution;
Microcosmic or nanofiber that composite layer can be used metal, carbon, glass, pottery or macromolecular material to make; Composite layer can be used thermosetting resin or thermoplastic resin as bonding matrix.
Metal material use various geometric shapes and curvature smooth surface metal material, have one or more in grain surface metal material, metal foaming material, porous metal material.
A kind of preparation method with the toughness reinforcing laminated structure of composite-metal material of fiber interface, the fibrofelt of making, pad or film and thermosetting resin or thermoplastic resin are together made to fiber reinforced layer prepreg, together by structure, need assembled formation with material prepreg, metal material again, or fibrofelt, pad or film and composite are together made and are had fiber reinforced prepreg, then with metal material assembled formation.
Toughness reinforcingly with fiber, can use identical resin as matrix with composite or directly on material prepreg, add fiber reinforced layer, all material can be used identical resin, can co-curing moulding, process and existing layer condensation material process, without obvious difference, can be cured by standard according to resin and physical dimension.Adopt co-curing technique can make composite, fiber reinforced material closely be connected with metal material.
As Fig. 1, the fibrofelt for using 6 mm length Kevlar fibers to make in figure, its density is 3 grams every square metre.Fibrofelt preparation method is: in air or liquid, stir low-density fibre to evenly, wait for afterwards natural subsidence or manual distribution.
As Fig. 2, in figure: black layer is composite layer, buffy layer is fiber reinforced layer, and gray layer is metal material layer, after laminate assembling/assembling, carries out co-curing.
As Fig. 3, in figure: top black layer is composite layer, below gray layer is metal material layer, and centre is the toughness reinforcing region of fiber-bridged.Bridging fiber is present in crack tip part until crack opening major part.
As Fig. 4, in figure: top gray layer is composite layer, below colorless layer is porous metal material layer, and middle yellow area and curve are the toughness reinforcing region of fiber fillet.Toughening layer fiber can carry on the hole wall of porous metals, forms extra " fillet is toughness reinforcing ", and then improves adhesive strength.
According to result of the test, without the laminated interface critical energy release rate of carbon fiber/epoxy resin-6061 aluminium alloy of toughening layer, it is 174 joules every square metre, adopt the laminate structures critical energy release rate of mode of the present invention toughness reinforcing the Kevlar fibrofelt of 12 grams every square metre (14 millimeters long) can reach 441 joules every square metre, critical energy release rate improves 153%, and construction weight only increases by 0.01%.The experimental result of the laminated structure of carbon fiber/epoxy resin-Alporas foamed aluminium is shown: the interface critical energy release rate without the laminated structure of carbon fiber/epoxy resin-Alporas foamed aluminium of toughening layer is 1518 joules every square metre, adopt the laminate structures critical energy release rate of mode of the present invention toughness reinforcing the Kevlar fibrofelt of 6 grams every square metre (6 millimeters long) can reach 2753 joules every square metre, critical energy release rate improves 81%, and construction weight only increases by 0.18%.Meanwhile, can improve ultimate load 36%, the total energy absorption performance 80% of laminate structures under three-point bending load.
Claims (9)
1. there is the laminated structure of the toughness reinforcing composite-metal material of fiber interface, it is characterized in that: one or more layers composite layer, metal material layer and fiber reinforced layer, consist of, fiber reinforced layer is arranged between composite layer and metal material layer.
2. according to claim 1 have a laminated structure of the toughness reinforcing composite-metal material of fiber interface, it is characterized in that: fiber reinforced layer material is used metal, carbon, glass, pottery or macromolecular material one or more microcosmic of making or nanofiber layer wherein; The fibre diameter of fiber reinforced layer is 3 nanometers to 100 micron; Fiber reinforced layer material is continuous fiber or discontinuous fibre; Fiber reinforced aspect density is for being not less than 0.5 gram every square metre to 100 grams every square metre.
3. according to claim 1 have a laminated structure of the toughness reinforcing composite-metal material of fiber interface, it is characterized in that: fiber reinforced layer is the fibrofelt of random distribution, pad or film.
4. according to claim 1 have a laminated structure of the toughness reinforcing composite-metal material of fiber interface, it is characterized in that: microcosmic or nanofiber that composite layer can be used metal, carbon, glass, pottery or macromolecular material to make; Composite layer can be used thermosetting resin or thermoplastic resin as bonding matrix.
5. according to claim 1 have a laminated structure of the toughness reinforcing composite-metal material of fiber interface, it is characterized in that: metal material is used one or more in the smooth surface metal material, grain surface metal material, metal foaming material, porous metal material of various geometric shapes and curvature.
6. according to claim 1 have a laminated structure of the toughness reinforcing composite-metal material of fiber interface, it is characterized in that: toughening layer fiber can form bridge between composite layer and metal level, improves adhesive strength and toughness; To using the structure of porous metal material, toughening layer fiber also can carry on the hole wall of porous metals, forms extra fillet Reinforced structure.
7. prepare the method with the toughness reinforcing laminated structure of composite-metal material of fiber interface claimed in claim 1, it is characterized in that: first toughened fiber is trimmed to 2-30 mm length, afterwards low-density toughened fiber is stirred in air or liquid evenly, waits for afterwards fiber natural subsidence or manual uniform felt, pad or the film of being scattered in.
8. the preparation method with the toughness reinforcing laminated structure of composite-metal material of fiber interface according to claim 7, it is characterized in that: the fibrofelt of making, pad or film and thermosetting resin or thermoplastic resin are crushed to fiber reinforced layer prepreg, more together by structure, need assembled formation with material prepreg, metal material; Or fibrofelt, pad or film and composite are together made and are had fiber reinforced prepreg, then with metal material assembled formation.
9. the preparation method with the toughness reinforcing laminated structure of composite-metal material of fiber interface according to claim 7; it is characterized in that: toughness reinforcingly with fiber and composite, use identical resin; co-curing moulding; process and existing layer condensation material process, without obvious difference, are cured by standard according to resin and physical dimension; Adopt co-curing technique that composite, fiber reinforced material are closely connected with metal material.
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106273902A (en) * | 2016-08-05 | 2017-01-04 | 深圳航天科技创新研究院 | A kind of aluminium foam sandwich structural composite material and preparation method thereof |
| CN112223860A (en) * | 2020-09-24 | 2021-01-15 | 哈尔滨工程大学 | Composite board for ocean platform living area enclosure wall and preparation method thereof |
| CN112895474A (en) * | 2019-12-03 | 2021-06-04 | 中国商用飞机有限责任公司 | Method for connecting fiber reinforced thermoplastic composite material and metal |
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| CN101992566A (en) * | 2009-08-20 | 2011-03-30 | 西门子公司 | Fiber reinforced plastic-structure and method to produce the fiber reinforced plastic-structure |
| WO2012116261A1 (en) * | 2011-02-24 | 2012-08-30 | Toray Industries, Inc. | Reinforced interphase and bonded structures thereof |
| US20130052897A1 (en) * | 2011-08-29 | 2013-02-28 | Cytec Technology Corp. | Interlaminar toughening of thermoplastics |
| CN102991009A (en) * | 2012-11-16 | 2013-03-27 | 中国航空工业集团公司北京航空材料研究院 | Interlayer toughening carbon fiber-metal layer plywood |
| CN103158852A (en) * | 2013-03-01 | 2013-06-19 | 溧阳市科技开发中心 | Fuselage with sandwich structure |
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2013
- 2013-11-04 CN CN201310532821.5A patent/CN103625040A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101992566A (en) * | 2009-08-20 | 2011-03-30 | 西门子公司 | Fiber reinforced plastic-structure and method to produce the fiber reinforced plastic-structure |
| WO2012116261A1 (en) * | 2011-02-24 | 2012-08-30 | Toray Industries, Inc. | Reinforced interphase and bonded structures thereof |
| US20130052897A1 (en) * | 2011-08-29 | 2013-02-28 | Cytec Technology Corp. | Interlaminar toughening of thermoplastics |
| CN102991009A (en) * | 2012-11-16 | 2013-03-27 | 中国航空工业集团公司北京航空材料研究院 | Interlayer toughening carbon fiber-metal layer plywood |
| CN103158852A (en) * | 2013-03-01 | 2013-06-19 | 溧阳市科技开发中心 | Fuselage with sandwich structure |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN106273902A (en) * | 2016-08-05 | 2017-01-04 | 深圳航天科技创新研究院 | A kind of aluminium foam sandwich structural composite material and preparation method thereof |
| CN106273902B (en) * | 2016-08-05 | 2018-08-07 | 深圳航天科技创新研究院 | A kind of aluminium foam sandwich structural composite material and preparation method thereof |
| CN112895474A (en) * | 2019-12-03 | 2021-06-04 | 中国商用飞机有限责任公司 | Method for connecting fiber reinforced thermoplastic composite material and metal |
| CN112223860A (en) * | 2020-09-24 | 2021-01-15 | 哈尔滨工程大学 | Composite board for ocean platform living area enclosure wall and preparation method thereof |
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Application publication date: 20140312 |