CN103770431A - Preparation method of nanometer adding layer-to-layer modified fiber-metal composite material - Google Patents
Preparation method of nanometer adding layer-to-layer modified fiber-metal composite material Download PDFInfo
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- CN103770431A CN103770431A CN201410007252.7A CN201410007252A CN103770431A CN 103770431 A CN103770431 A CN 103770431A CN 201410007252 A CN201410007252 A CN 201410007252A CN 103770431 A CN103770431 A CN 103770431A
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Abstract
The invention discloses a preparation method of a nanometer adding layer-to-layer modified fiber-metal composite material. The preparation method comprises the following steps: 1, performing surface treatment on metal sheets to enhance the binding strength between the metal sheets and metal plates; 2, overlaying tailored fiber presoaked fabrics against a right-angle gauge, and ironing the fiber presoaked fabrics in a radioactivity manner from the middle to the edge by an iron at 90-100 DEG C so as to extrude residual bubbles among layers, wherein the consistency of fiber directions is maintained; 3, adding proper nanometer reinforcement additives to the metal plate surfaces or the fiber plate surfaces requiring binding by a powder method or a solution method, and then alternatively overlaying the metal plates and the fiber plates, wherein the fiber direction is maintained to be vertical to the direction of calendering ribs of the metal plates in the process of overlaying; and 4, curing a fiber-metal laminated plate obtained in the step 3 in a hot press or a high-pressure kettle to obtain a finished product. The method has the advantages that the layer-to-layer strength and the breaking tenacity between the fiber layer and the metal layer are improved in the manufacture process of the fiber-metal laminated plate.
Description
Technical field
The present invention relates to a kind of preparation method of composite, be specifically related to the preparation method of modified fibre metallic composite between a kind of nanometer interpolation layer by layer.
Background technology
Aluminum alloy materials has compared with low-density and higher intensity and shock resistance, and it is also comparatively cheap to have good machinability cost.Therefore be just widely used in aerospace field since earlier 1930s.But having for example lower fatigue life and corrosion resistance of some limitation, aluminum alloy materials limits its further using value.And glass fibre and the carbon fibre composite of twentieth century four the fifties inventions have very high specific strength and specific stiffness, and there is good fatigue properties and corrosion resistance, but the outer transverse strength of this laminated composite material face and shock resistance are poor, and interlayer faying face easily produces delamination.Some shortcomings that exist in order to overcome aluminum alloy materials and fibrous composite simultaneously, in later 1970s, have been developed the fibre metal laminate material of metal material and fiber composite by TU Delft Polytechnics.This material combines the advantage of metal and fibrous composite, and has overcome its most shortcoming, is a kind of structural material that has huge applications prospect in high-tech areas such as Aero-Space, military affairs, automobiles.It is the most representative be exactly fiberglass reinforced plastics and aluminium alloy compound material: GFRP/Al laminate (commercial code GLARE), has been used on the fuselage of Air Passenger A380 at present.Although fibre metal laminate has the performance of a series of excellences, its metal level and fibrous composite layer can be combined the problem a little less than boundary strength that causes due to foreign material.
Chinese patent literature CN102516569A discloses a kind of preparation method of carbon nanotube non-woven fabric interlayer modified fiber reinforced composite materials, it enters into direct carbon nano-tube non-woven fabrics intercalation in the interlayer resin-rich area territory of fiber reinforced thermosetting resin based composites, utilizes autoclave forming process or liquid condition shaping technique according to modified composite material between the original curing process prepared layer of matrix resin.Thereby improve composite interlayer strong-malleableize performance, obtain HI high impact damage impedance and high damage tolerance.At present, also openly directly carry out the technology of the interlaminar strength of fortifying fibre metal laminate by the interlayer modified method of nanometer interpolation layer.
Summary of the invention
For the lower defect of fracture toughness between the fibrage of fibre metal laminate and metal level, technical problem to be solved by this invention is just to provide the preparation method of modified fibre metallic composite between a kind of nanometer interpolation layer by layer, it can improve the interlaminar strength between fibrage and metal level, improves interlayer faults toughness.
Method of the present invention, comprises the following steps:
1, sheet metal is carried out to surface treatment, to strengthen and the bond strength of metallic plate;
2, the fiber prepreg cloth cutting is folded against right angle gauge, kept machine direction consistent; Be radioactivity flatiron fiber prepreg cloth from centre to edge with the flatirons of 90～100 ℃ with residual bubble between extruding layer;
3,, use powder method or solwution method to add appropriate nanometer enhancing additive to the bonding metal sheet surface of needs and fiberboard surface; Then metallic plate and fiberboard alternative stacked, in lamination, note making machine direction to keep vertical with the calendering muscle direction of sheet metal;
4,, by the fibre metal laminate of step 3 gained, put in hot press or autoclave and solidify and obtain finished product.
In described step 1, metal sheet surface is treated to mechanical grinding, electrochemical corrosion, acid treatment, laser ablation or plasma spraying, and described sheet metal has aluminium alloy plate, corrosion resistant plate or titanium alloy sheet.
In described step 2, the base material of fiber prepreg cloth is glass fibre, carbon fiber, cotton fibriia or bamboo fibre.
In described step 3, it is single or multiple lift CNT, VGCF, acidifying VGCF, carbon black, Graphene or graphene oxide that nanometer strengthens additive.
In described step 3, described powder method refers to Powdered nanometer additive, adopts the sieve of suitable sizing grid, and quantitative nanometer powder Direct Uniform is sprinkled upon on wanted bonding fiberboard or metal plate.
In described step 3, described solwution method refers to the nanometer additive to Powdered, graininess or sheet, adopt ultrasonic wave to stir nanometer additive is dispersed in to organic solution as in acetone or dimethyl formamide (DMF) solution, then adding a certain amount of epoxy resin stirs, in order to ensure good dispersiveness, can be repeatedly used machinery stirs with ultrasonic wave, heating afterwards vapors away acetone or DMF, finally remaining nanometer reinforced epoxy is evenly spread upon on wanted bonding fiberboard or metallic plate.
In step 4, the described gradient heating that is cured as solidifies, and is first heated to certain temperature from room temperature and keeps certain hour to make resin softening mobile, and to reduce bubble, more than being then heated to solidification temperature, constant temperature certain hour is naturally cooling after solidifying completely.
The present invention is in the manufacturing process of fibre metal laminate, by metallic plate is carried out to surface treatment, and add appropriate nanometer additive carry out to the interlayer of fibrage and sheet metal interlayer modified, thereby improve the interlaminar strength of fibre metal laminate, improve its interlayer faults toughness.
Owing to having adopted technique scheme, the present invention has advantages of as follows: in the manufacturing process of fibre metal laminate, improved the interlaminar strength between fibrage and metal level, improved fibrage and metal interlevel fracture toughness.
The specific embodiment
Below in conjunction with embodiment, the invention will be further described:
embodiment 1:
The target of this embodiment is to manufacture the interlayer modified GFRP/Al composite laminated plate of gas-phase growth of carbon fibre (VGCF).
The material using has fiberglass reinforced plastics (GFRP) preimpregnation cloth (TOHO Tenax Co., Ltd. Dong Bangte Nike silk), aluminium 2017(TOHO HitetsuKinzoku Co., Ltd. east nation nonferrous metal) and VGCF(Showa Denko K.K. is clear and electrician).The parameter of material sees the following form:
Concrete making step is as follows:
1. 2 aluminium alloy sheets of degreasing are put in the salpeter solution that concentration is 1mol/L into acidification 24 hours, be then neutral with distilled water flushing to pH value.Oven dry surface moisture is stand-by.
2. get the GFRP preimpregnation cloth of 3 layers and fold with right angle gauge successively, guarantee the uniformity of machine direction, and use 90-100
othe flatiron of C presses to discharge the residual bubble of interlayer from middle toward surrounding.
3. measure 10g/m
2vGCF, prevent that with absorption VGCF powder it from wafting toward a small amount of alcohol of the upper sprinkling of GFRP, being zig-zag type with the sieve that size of mesh opening is approximately 70 μ m, that VGCF is sprinkled upon to GFRP is equably upper, GFRP lamination is superimposed with aluminium alloy plate and make GFRP machine direction vertical with the calendering muscle direction maintenance of aluminium sheet afterwards.The laminated layer sequence of the present embodiment is Al/ GFRP 0
o(3)/Al, i.e. each one deck aluminium sheet up and down, middle three layers of machine direction are 0
ogFRP preimpregnation cloth.
4. the GFRP/Al laminate film of folding is wrapped, then put into hot press and solidify.While solidifying, be first heated to 80 from room temperature
oc, constant temperature 30 minutes, is then heated to 130
oc, constant temperature 3 hours, naturally cooling afterwards.
Test by end breach bending (ENF), we draw through the interlaminar strength of the GFRP/Al laminate of surface acid processing and interlayer VGCF interpolation modification (does not have acid treatment than original sample, do not have VGCF to add layer) be improved significantly, II type fracture toughness has improved 385%.In addition the present embodiment has also proposed angle between the calendering muscle direction of machine direction and aluminium sheet 90
owith 0
oon the impact of II mode Ⅱ fracture toughness.Through test determination, in the time that machine direction and aluminium sheet calendering muscle is vertical, II type Fracture Toughness exceeds 15.3%-73.6% when parallel.
embodiment 2:
The target of this embodiment is to manufacture the interlayer modified CFRP/Al composite laminated plate of VGCF.
The material using has carbon fibre reinforced plastic (CFRP) preimpregnation cloth (TOHO Tenax Co., Ltd. Dong Bangte Nike silk), aluminium 2017(TOHO HitetsuKinzoku Co., Ltd. east nation nonferrous metal) and VGCF(Showa Denko K.K. is clear and electrician).The parameter of material sees the following form:
Concrete making step is as follows:
1. 2 aluminium alloy sheets of degreasing are put in the salpeter solution that concentration is 1mol/L into acidification 24 hours, be then neutral with distilled water flushing to pH value.Oven dry surface moisture is stand-by.
2. get the CFRP preimpregnation cloth of 3 layers and fold with right angle gauge successively, guarantee the uniformity of machine direction, and use 90-100
othe flatiron of C presses to discharge the residual bubble of interlayer from middle toward surrounding.
3. measure 20g/m
2vGCF, adopt ultrasonic stirrer that VGCF is dispersed in to (amount of DMF should guarantee good being dispersed in wherein of VGCF) in appropriate DMF solution, then adding a certain amount of epoxy resin (VGCF weight: weight epoxy=1:5-15) stirs with planetary mixer, reusing ultrasonic stirrer stirs, then heat DMF is vapored away, finally remaining VGCF reinforced epoxy is evenly spread upon on wanted bonding fiberboard or metallic plate, CFRP lamination is superimposed with aluminium alloy plate and make the calendering muscle direction of CFRP machine direction and aluminium sheet keep vertical afterwards.The laminated layer sequence of the present embodiment is Al/ CFRP 0
o(3)/Al, i.e. each one deck aluminium sheet up and down, middle three layers of machine direction are 0
ocFRP preimpregnation cloth.
4. the CFRP/Al laminate film of folding is wrapped, then put in autoclave and solidify.While solidifying, be first heated to 80 from room temperature
oc, constant temperature 30 minutes, is then heated to 130
oc, constant temperature 3 hours, naturally cooling afterwards.
Test by double cantilever beam (DCB), we draw through the interlaminar strength of the CFRP/Al laminate of surface acid processing and interlayer VGCF interpolation modification and are improved significantly, I type fracture toughness (does not have acid treatment than original sample, do not have VGCF to add layer) improve 41 times, the sample that does not have VGCF to add layer than processing through surface acid has improved 6.5 times.
The manufacturing process of this method invention is simple, also not high to manufacturing equipment requirement, but effect is remarkable, and it is significant for manufacturing high performance fibre metal composite.
Claims (7)
1. a preparation method for modified fibre metallic composite between nanometer interpolation layer by layer, is characterized in that, comprises the following steps:
(1) sheet metal is carried out to surface treatment, to strengthen and the bond strength of metallic plate;
(2) the fiber prepreg cloth cutting is folded against right angle gauge, kept machine direction consistent; Be radioactivity flatiron fiber prepreg cloth from centre to edge with the flatirons of 90～100 ℃ with residual bubble between extruding layer;
(3) use powder method or solwution method to add appropriate nanometer enhancing additive to the bonding metal sheet surface of needs and fiberboard surface; Then metallic plate and fiberboard alternative stacked, in lamination, note making machine direction to keep vertical with the calendering muscle direction of sheet metal;
(4), by the fibre metal laminate of step (3) gained, put in hot press or autoclave and solidify and obtain finished product.
2. the preparation method of modified fibre metallic composite between a kind of nanometer interpolation layer by layer according to claim 1, it is characterized in that: in step (1), metal sheet surface is treated to mechanical grinding, electrochemical corrosion, acid treatment, laser ablation or plasma spraying, and described sheet metal has aluminium alloy plate, corrosion resistant plate or titanium alloy sheet.
A kind of nanometer according to claim 1 add layer by layer between the preparation method of modified fibre metallic composite, it is characterized in that: stating in step (2), the base material of fiber prepreg cloth is glass fibre, carbon fiber, cotton fibriia or bamboo fibre.
4. the preparation method of modified fibre metallic composite between a kind of nanometer interpolation layer by layer according to claim 1, it is characterized in that: stating in step (3), it is single or multiple lift CNT, VGCF, acidifying VGCF, carbon black, Graphene or graphene oxide that nanometer strengthens additive.
5. the preparation method of modified fibre metallic composite between a kind of nanometer interpolation layer by layer according to claim 1, it is characterized in that: stating in step (3), described powder method refers to Powdered nanometer additive, adopt the sieve of suitable sizing grid, quantitative nanometer powder Direct Uniform is sprinkled upon on wanted bonding fiberboard or metallic plate.
6. the preparation method of modified fibre metallic composite between a kind of nanometer interpolation layer by layer according to claim 1, it is characterized in that: stating in step (3), described solwution method refers to the nanometer additive to Powdered, graininess or sheet, adopting ultrasonic wave to stir is dispersed in nanometer additive in organic solution, then adding a certain amount of epoxy resin stirs, heating afterwards vapors away acetone or DMF, finally remaining nanometer reinforced epoxy is evenly spread upon on wanted bonding fiberboard or metallic plate.
7. the preparation method of modified fibre metallic composite between a kind of nanometer interpolation layer by layer according to claim 1, it is characterized in that: in step (4), the described gradient heating that is cured as solidifies, first being heated to certain temperature from room temperature keeps certain hour to make resin softening mobile, to reduce bubble, then, more than being heated to solidification temperature, constant temperature certain hour is naturally cooling after solidifying completely.
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Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104707888A (en) * | 2014-12-26 | 2015-06-17 | 中航复合材料有限责任公司 | Lamination forming process method for fiber-metal mixed composite material |
| 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 |
| CN107234766A (en) * | 2017-06-27 | 2017-10-10 | 重庆大学 | A kind of powder lamination process method of quick preparation magnesium-based Fiber Reinforced Metal Laminates |
| CN107379725A (en) * | 2017-07-10 | 2017-11-24 | 南京航空航天大学 | A kind of method and composite for improving titanium/fiber-reinforced composite laminates interface performance |
| CN108819369A (en) * | 2018-07-06 | 2018-11-16 | 李石林 | A kind of aircraft fiber-reinforced resin matrix compound material laminate |
| CN109504053A (en) * | 2018-07-12 | 2019-03-22 | 江苏华信新材料股份有限公司 | A kind of smart card polycarbonate laser ablation film and preparation method thereof |
| CN110713611A (en) * | 2019-07-25 | 2020-01-21 | 北京汽车集团有限公司 | Interlaminar modification method of fiber reinforced composite material and fiber reinforced composite material |
| CN111231375A (en) * | 2020-01-14 | 2020-06-05 | 上海交通大学 | Hot forming and co-curing integrated forming method for CFRP/aluminum alloy composite structure |
| CN111231366A (en) * | 2020-01-14 | 2020-06-05 | 上海交通大学 | CFRP/aluminum alloy hot forming quenching aging co-curing integrated forming method |
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| CN102605208A (en) * | 2012-04-13 | 2012-07-25 | 上海交通大学 | High thermal conductivity metal-based composite material with hierarchical structure, and preparation method thereof |
| CN102825860A (en) * | 2011-06-14 | 2012-12-19 | 重庆大学 | Metal-reinforced plastic composite material part and its molding method |
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Cited By (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104707888B (en) * | 2014-12-26 | 2016-09-14 | 中航复合材料有限责任公司 | A kind of fiber metal hybrid composite part laminated forming process |
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| 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 |
| CN107234766A (en) * | 2017-06-27 | 2017-10-10 | 重庆大学 | A kind of powder lamination process method of quick preparation magnesium-based Fiber Reinforced Metal Laminates |
| CN107234766B (en) * | 2017-06-27 | 2019-12-13 | 重庆大学 | Powder laminating process method for rapidly preparing magnesium-based fiber metal laminate |
| CN107379725A (en) * | 2017-07-10 | 2017-11-24 | 南京航空航天大学 | A kind of method and composite for improving titanium/fiber-reinforced composite laminates interface performance |
| CN108819369B (en) * | 2018-07-06 | 2020-07-24 | 西安拓邦航空科技有限公司 | Fiber reinforced resin matrix composite laminated board for aircraft |
| CN108819369A (en) * | 2018-07-06 | 2018-11-16 | 李石林 | A kind of aircraft fiber-reinforced resin matrix compound material laminate |
| CN109504053A (en) * | 2018-07-12 | 2019-03-22 | 江苏华信新材料股份有限公司 | A kind of smart card polycarbonate laser ablation film and preparation method thereof |
| CN110713611A (en) * | 2019-07-25 | 2020-01-21 | 北京汽车集团有限公司 | Interlaminar modification method of fiber reinforced composite material and fiber reinforced composite material |
| CN110713611B (en) * | 2019-07-25 | 2022-04-15 | 北京汽车集团有限公司 | Interlaminar modification method of fiber reinforced composite material and fiber reinforced composite material |
| CN111231375A (en) * | 2020-01-14 | 2020-06-05 | 上海交通大学 | Hot forming and co-curing integrated forming method for CFRP/aluminum alloy composite structure |
| CN111231366A (en) * | 2020-01-14 | 2020-06-05 | 上海交通大学 | CFRP/aluminum alloy hot forming quenching aging co-curing integrated forming method |
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