CN107379725A - A kind of method and composite for improving titanium/fiber-reinforced composite laminates interface performance - Google Patents
A kind of method and composite for improving titanium/fiber-reinforced composite laminates interface performance Download PDFInfo
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- CN107379725A CN107379725A CN201710556504.5A CN201710556504A CN107379725A CN 107379725 A CN107379725 A CN 107379725A CN 201710556504 A CN201710556504 A CN 201710556504A CN 107379725 A CN107379725 A CN 107379725A
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B37/00—Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding
- B32B37/12—Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding characterised by using adhesives
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
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- B32B15/00—Layered products comprising a layer of metal
- B32B15/04—Layered products comprising a layer of metal comprising metal as the main or only constituent of a layer, which is next to another layer of the same or of a different material
- B32B15/08—Layered products comprising a layer of metal comprising metal as the main or only constituent of a layer, which is next to another layer of the same or of a different material of synthetic resin
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- B32—LAYERED PRODUCTS
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- B32B27/00—Layered products comprising a layer of synthetic resin
- B32B27/06—Layered products comprising a layer of synthetic resin as the main or only constituent of a layer, which is next to another layer of the same or of a different material
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B27/00—Layered products comprising a layer of synthetic resin
- B32B27/28—Layered products comprising a layer of synthetic resin comprising synthetic resins not wholly covered by any one of the sub-groups B32B27/30 - B32B27/42
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
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- B32B27/00—Layered products comprising a layer of synthetic resin
- B32B27/28—Layered products comprising a layer of synthetic resin comprising synthetic resins not wholly covered by any one of the sub-groups B32B27/30 - B32B27/42
- B32B27/281—Layered products comprising a layer of synthetic resin comprising synthetic resins not wholly covered by any one of the sub-groups B32B27/30 - B32B27/42 comprising polyimides
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B37/00—Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding
- B32B37/10—Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding characterised by the pressing technique, e.g. using action of vacuum or fluid pressure
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B7/00—Layered products characterised by the relation between layers; Layered products characterised by the relative orientation of features between layers, or by the relative values of a measurable parameter between layers, i.e. products comprising layers having different physical, chemical or physicochemical properties; Layered products characterised by the interconnection of layers
- B32B7/04—Interconnection of layers
- B32B7/12—Interconnection of layers using interposed adhesives or interposed materials with bonding properties
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B37/00—Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding
- B32B37/12—Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding characterised by using adhesives
- B32B2037/1269—Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding characterised by using adhesives multi-component adhesive
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B2260/00—Layered product comprising an impregnated, embedded, or bonded layer wherein the layer comprises an impregnation, embedding, or binder material
- B32B2260/02—Composition of the impregnated, bonded or embedded layer
- B32B2260/021—Fibrous or filamentary layer
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B2260/00—Layered product comprising an impregnated, embedded, or bonded layer wherein the layer comprises an impregnation, embedding, or binder material
- B32B2260/04—Impregnation, embedding, or binder material
- B32B2260/046—Synthetic resin
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B2262/00—Composition or structural features of fibres which form a fibrous or filamentary layer or are present as additives
- B32B2262/10—Inorganic fibres
- B32B2262/106—Carbon fibres, e.g. graphite fibres
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Abstract
The invention discloses a kind of method and composite for improving titanium/fiber-reinforced composite laminates interface performance, comprise the steps of：1) titanium alloy surface is surface-treated；2) CNT is evenly spread in high temperature resistant thermosetting primer resin and forms dispersion liquid, and surface treated titanium alloy surface is coated in using dispersion liquid as the primer layer of laminate, carried out paved in multi-layers with prepreg resin, form composite layered plate；3) the primer resin for disperseing CNT is evenly applied to titanium alloy surface and dried；4) titanium plate coated with primer resin bed after drying is replaced into laying with fibre-reinforced prepregs, temperature-pressure solidifies to obtain titanium/fiber-reinforced composite laminates；There is one layer of primer resin bed containing CNT between every layer of titanium plate and prepreg.The present invention can improve laminate comprehensive mechanical property and forming property, have higher engineering application value.
Description
Technical field
The present invention relates to a kind of ameliorative way of Fiber Reinforced Metal Laminates interface layer performance, especially a kind of titanium/fiber increases
The method and composite that strong composite layer board interface improves, belong to field of composite material preparation.
Background technology
It is one kind by sheet metal and fiber composite that metal-fiber is super, which to mix laminate (Super Hybrid Laminates),
After material alternating laying, the interply hybrid composites that solidify under certain temperature and pressure.Metal-fiber is super to be mixed
Laminate combines the characteristics of traditional fibre composite and metal material, has higher specific strength and specific stiffness, excellent tired
Labor performance and damage tolerance performance, these advantages cause it to be obtained a wide range of applications in aerospace industry.A new generation
Fibre reinforced titanium alloy laminate (TiGr) is resistance to by the titanium-alloy thin-plate thick 0.3mm fibre reinforced thick with 0.1-0.2mm
The prepreg alternatively laminated that high temperature thermosetting resin is formed forms, its density it is low and with prominent tension-pressure fatigue behaviour and
Higher nick break performance, the laminate have higher intensity, high damage tolerance.It both had corrosion resistance in low temperature,
And can is adapted to 170 DEG C of high temperature, and even above 170 DEG C use, and can a kind of antifatigue and with higher toughness NEW TYPE OF COMPOSITE
Material pieces, its needs for having adapted to space flight and aviation development will have good application prospect in aerospace field.
There is fiber/resin, metal/resin interface as a kind of superhybrid composite in Fiber Reinforced Metal Laminates, interface characteristics
There can be vital influence to the Physical and mechanical properties of whole laminate.Wherein, metal/resin interface is considered as weak interface,
The interface determines the combination and stress transmission of metal level and fibrous layer, has dominated combination property and the failure of Fiber Reinforced Metal Laminates
Behavior.First, the stress of metal/resin effect of the interface metal level and fibrous layer transmits effect, determines the failure mode of laminate
And intensity；Secondly, the damage accumulation of effect of the interface laminate and crack propagation course, the fracture toughness and fatigability of material are determined
Energy；Meanwhile the environment resistant and dielectric stability of effect of the interface Fiber Reinforced Metal Laminates process under arms, determine the durable of material
Performance and service life, therefore the interfacial combined function quality of Fiber Reinforced Metal Laminates plays to the performance synthesis performance of whole laminate
Vital effect.
The combination of Fiber Reinforced Metal Laminates interlayer is mainly glued, and is tied at present for improving the interface of Fiber Reinforced Metal Laminates
The method of conjunction intensity, which focuses primarily upon, to be handled metal surface, metal surface is produced certain roughness, is utilized metal
Mechanical engagement with resin adhesive layer is so as to the interface cohesion for improving metal and being glued between resin, its interfacial structure such as Fig. 1.The party
Method improves the interface bond strength of laminate to a certain extent, but there is the failure mode of a large amount of interfacial failures, because
This needs to find new thinking and interfacial failure is tried one's best to be changed into cohesional failure so as to improve the interface bond strength of laminate.
The content of the invention
The technical problems to be solved by the invention are to combine to improve laminate interface layer in original Treatment of Metal Surface
On the basis of, resin bed is strengthened, so as to provide improvement fiber metal board interface knot that is a kind of effective and being easily achieved
The method of conjunction, CNT have the excellent properties such as high-modulus, high-specific surface area and high specific strength, the counterincision in the resin matrix of interface
Line plays the role of transfer, propagation, scattered, refinement, and serves bridge joint effect in the base, in the form of itself extracts failure
To strengthen interface performance, therefore improve interface performance using CNT.
In order to solve the above-mentioned technical problem, the invention provides one kind to improve titanium/fiber-reinforced composite laminates interface
The method of performance, is comprised the steps of：
1) titanium alloy surface is surface-treated；
2) CNT is evenly spread in high temperature resistant thermosetting primer resin and forms dispersion liquid, and using dispersion liquid as
The primer layer of laminate is coated in surface treated titanium alloy surface, carries out paved in multi-layers with prepreg resin, is formed compound
Laminate, its carbon fiber layer/metal level interlayer structure include two boundary layers, are respectively：Titanium/CNT/thermosetting resin circle
Surface layer and carbon fiber/thermosetting resin boundary layer；
3) the primer resin for disperseing CNT is evenly applied to titanium alloy surface and dried；
4) titanium plate coated with primer resin bed after drying is replaced into laying with fibre-reinforced prepregs, temperature-pressure is solid
Change obtains titanium/fiber-reinforced composite laminates；There is one layer of primer tree containing CNT between every layer of titanium plate and prepreg
Lipid layer.
Described method, in the step 2), CNT is also added with prepreg resin, what is ultimately formed is compound
Laminate, its carbon fiber layer/metal level interlayer structure include two boundary layers, are respectively：Titanium/CNT/thermosetting resin circle
Surface layer and carbon fiber/carbon nanotube/thermosetting resin boundary layer.
Described method, the titanium surface treatment method in the step 1) are：Blasting treatment, anodized or spray
Anodized after sand.
Described method, the titanium/fiber-reinforced composite laminates laying structure are 2/1 structure, 3/2 structure or 4/3
The single-ply plate or cross-ply laminate of structure.
Described method, the type of CNT is the common CNT that is easily dispersed or through peracid in the step 2)
Change the functionalized carbon nano-tube of attached hydroxyl or carboxyl.
Described method, the titanium alloy can be TA1, TA2, TA18, TC4.
Described method, described primer resin are high temperature resistant thermosetting resin, including polyimides, polyether-ether-ketone.
Described method, described fibre-reinforced prepregs are carbon fiber reinforced polyether-ether-ketone resin prepreg material, carbon fiber
Strengthen polyimide resin prepreg, CNT/fibre reinforced polyimide resin prepreg.
Described method, the dosage of CNT is the 5% of resin quality in the step 2).
The composite prepared according to any described method.
The beneficial effects of the present invention are：(1), the present invention utilizes CNT itself excellent properties, using it at interface
There are transfer, propagation, scattered, refinement in resin matrix to crackle, and serve bridge joint effect in the base, with itself
Extract the form of failure improves the interface layer performance of laminate to strengthen the mechanism of interface performance, so as to improve laminate synthesis mechanics
Performance and forming property, there is higher engineering application value；(2), the present invention in the case where not changing laminate thickness to property
It can be improved, not increase laminate manufacturing cost, operating process is simple, be easily achieved and enhancing effect is effective.
Brief description of the drawings
Fig. 1 is metal level/fiber interlayer structure chart of existing laminate；
Fig. 2 is metal level/fiber interlayer structural representation of the addition CNT in primer layer laminate；
Fig. 3 is metal level/fiber interlayer structural representation of the addition CNT in prepreg；
Fig. 4 is polyether-ether-ketone resin basal plate curing process curve；
Fig. 5 is the cross-sectional scans figure that 2/1 structural polyether ether ketone resin basal plate utilizes the shooting of TM3000 ESEMs, should
Figure enlargement ratio is 100 times；
Fig. 6 is polyimide resin basal plate curing process curve；
Fig. 7 is the cross-sectional scans that 3/2 structure polyimide resin base single-ply plate utilizes the shooting of TM3000 ESEMs
Figure, the figure enlargement ratio are 80 times；
Fig. 8 is the cross-sectional scans that 3/2 structure polyimide resin base cross-ply laminate utilizes the shooting of TM3000 ESEMs
Figure, the figure enlargement ratio are 80 times；
Fig. 9 is laminate preparation flow figure.
Embodiment
Below in conjunction with specific embodiment, the present invention is described in detail.
Embodiment 1
The first step, the TA2 titanium alloy blanks for selecting 100mm × 100mm × 0.3mm, and anodized is carried out, make
TA2 titanium alloy surfaces obtain and the compound more favorable surface topography of resin hot pressing；
Second step, the common CNT of resin quality 5% is distributed in laminate primer layer polyether-ether-ketone resin, and will
Dispersion is in the titanium alloy surface Jing Guo anodic oxidation；
3rd step, selection and the carbon fiber reinforced polyether-ether-ketone resin prepreg material for cutting 100mm × 100mm × 0.125mm；
4th step, using 2/1 single-ply plate structure design, lay composite layered plate in the following order：Coat laminate primer layer
TA2 titanium alloys/unidirectional continuous carbon fibre reinforced polyether ether ketone resin prepreg material/unidirectional continuous carbon fibre reinforced polyether ether ketone tree
The TA2 titanium alloys of fat prepreg/coating laminate primer layer, because every layer of TA2 titanium alloy coats laminate primer layer in advance, so
It can all have one layer to contain 5% carbon nanotube resin glue-line between carbon fiber reinforced polyether-ether-ketone resin prepreg material；
5th step, the composite laminated plate laid is put into mould, curing process is as shown in figure 4, be warming up to 390
After DEG C, apply 1MPa pressure pressurize half an hour, when sample then being cooled into 320 DEG C, gradual unloading pressure, and cool to the furnace
Room temperature is finally cured as 100mm × 100mm × H laminate, and laminate cross-sectional scans figure is as shown in figure 5, by one layer of carbon fiber layer
And two layers of titanium alloy is formed.
6th step, after the laminate suppressed is cut using precision gas cutting machine, measure its interface performance.Wherein,
The shear strength of singly taking of sample is 30MPa, and 32% is improved compared to the laminate for being not added with CNT；Interlaminar shear strength is
60MPa, 36% is improved compared to the laminate for being not added with CNT.
Embodiment 2
The first step, the TC4 titanium alloy blanks for selecting 200mm × 200mm × 0.3mm, and anodized is carried out, make
TC4 titanium alloy surfaces obtain and the compound more favorable surface topography of resin hot pressing；
Second step, the hydroxyl carbon nano tube of resin quality 7.5% is distributed in polyimide resin, and by dispersion liquid
Coated in the titanium alloy surface Jing Guo anodic oxidation；
3rd step, selection simultaneously cut 200mm × 200mm × 0.125mm fibre reinforced polyimide resin prepregs；
4th step, using 3/2 single-ply plate structure design, lay composite layered plate in the following order：Coat laminate primer layer
TC4 titanium alloys/unidirectional continuous carbon fibre enhancing polyimide resin prepreg/unidirectional continuous carbon fibre enhancing polyimides tree
The TC4 titanium alloys of fat prepreg/coating laminate primer layer/unidirectional continuous carbon fibre enhancing polyimide resin prepreg/unidirectional
Continuous carbon fibre enhancing polyimide resin prepreg/TC4 titanium alloys, every layer of TC4 titanium alloy and fibre reinforced polyimides
There is one layer of polyimide resin glue-line containing 7.5% hydroxyl carbon nano tube between resin prepreg material；
5th step, the composite laminated plate laid is put into mould, curing process is as shown in fig. 6, every 70 points
Clock ladder-elevating temperature with after-applied 2MPa pressure, and is warming up to 320 DEG C to 280 DEG C, pressurize 2 hours, is then shut off heater switch,
Be cooled to the laminate that room temperature is finally cured as 200mm × 200mm × H under stress, laminate cross-sectional view as shown in fig. 7, comprising
Two fibre layers and three layers of titanium alloy layer.
6th step, after the laminate suppressed is cut using precision gas cutting machine, measure its interface performance.Wherein,
The shear strength of singly taking of sample is 15MPa, compared to the raising 40% for being not added with CNT；Interlaminar shear strength is 60MPa, phase
Than the raising 33% for being not added with CNT.
Embodiment 3
The first step, the TA18 titanium alloy blanks for selecting 100mm × 100mm × 0.3mm, and anodized is carried out, make
TA18 titanium alloy surfaces obtain and the compound more favorable surface topography of resin hot pressing；
Second step, the carboxylic carbon nano-tube of resin quality 5% is distributed in polyimide resin, and dispersion liquid is applied
Overlay on the titanium alloy surface by anodic oxidation；
3rd step, the carboxylic carbon nano-tube of resin quality 5% is distributed in polyimide resin, and dispersion liquid is mixed
Close in prepreg, the fibre reinforced polyimide resin prepreg containing CNT is made；
4th step, the CNT/fibre reinforced polyimide resin prepreg made from the 3rd step, and be cut to
100mm × 100mm × 0.125mm (length × width x thickness)；
5th step, using 3/2 cross-ply laminate structure design, lay composite layered plate in the following order：Coat laminate primer layer
TA18 titanium alloys/unidirectional continuous carbon fibre enhancing polyimide resin prepreg/vertical unidirectional continuous carbon fibre enhancing polyamides
The TA18 titanium alloys of imide resin prepreg/coating laminate primer layer/unidirectional continuous carbon fibre enhancing polyimide resin preimpregnation
Material/vertical unidirectional continuous carbon fibre enhancing polyimide resin prepreg/TA18 titanium alloys, every layer of TA18 titanium alloy and carbon fiber
There are one layer of polyimide resin glue-line containing 5% CNT, each layer of carbon fibre between enhancing polyimide resin prepreg
The prepreg that dimension enhancing polyimide resin is formed is all containing 5% CNT；
6th step, the composite laminated plate laid is put into mould, curing process is as shown in fig. 6, every 70 points
Clock ladder-elevating temperature with after-applied 2MPa pressure, and is warming up to 320 DEG C to 280 DEG C, pressurize 2 hours, is then shut off heater switch,
The laminate that room temperature is finally cured as 200mm × 200mm × H is cooled under stress, and cross-sectional scans figure is as shown in figure 8, include two
Layer carbon fiber layer and three layers of titanium alloy layer.
7th step, after the laminate suppressed is cut using precision gas cutting machine, measure its interface performance.Wherein,
The shear strength of singly taking of sample is 17MPa, and 65% is improved compared to the laminate for being not added with CNT；Interlaminar shear strength is
70MPa, 45% is improved compared to the laminate that CNT is not added with dispersion liquid.
It should be appreciated that for those of ordinary skills, can according to the above description be improved or converted,
And all these modifications and variations should all belong to the protection domain of appended claims of the present invention.
Claims (10)
- A kind of 1. method for improving titanium/fiber-reinforced composite laminates interface performance, it is characterised in that comprise the steps of：1) titanium alloy surface is surface-treated；2) CNT is evenly spread in high temperature resistant thermosetting primer resin and forms dispersion liquid, and using dispersion liquid as laminate Primer layer be coated in surface treated titanium alloy surface, with prepreg resin carry out paved in multi-layers, formed composite layered plate, Its carbon fiber layer/metal level interlayer structure includes two boundary layers, is respectively：Titanium/CNT/thermosetting resin boundary layer and Carbon fiber/thermosetting resin boundary layer；3) the primer resin for disperseing CNT is evenly applied to titanium alloy surface and dried；4) titanium plate coated with primer resin bed after drying is replaced into laying with fibre-reinforced prepregs, temperature-pressure solidifies To titanium/fiber-reinforced composite laminates；There is one layer of primer resin bed containing CNT between every layer of titanium plate and prepreg.
- 2. according to the method for claim 1, it is characterised in that in the step 2), be also added with prepreg resin CNT, the composite layered plate ultimately formed, its carbon fiber layer/metal level interlayer structure include two boundary layers, are respectively： Titanium/CNT/thermosetting resin boundary layer and carbon fiber/carbon nanotube/thermosetting resin boundary layer.
- 3. according to the method for claim 1, it is characterised in that the titanium surface treatment method in the step 1) is：Sandblasting Anodized after processing, anodized or sandblasting.
- 4. according to the method for claim 1, it is characterised in that the titanium/fiber-reinforced composite laminates laying structure For the single-ply plate or cross-ply laminate of 2/1 structure, 3/2 structure or 4/3 structure.
- 5. according to the method for claim 1, it is characterised in that the type of CNT is to be easily dispersed in the step 2) Common CNT or the functionalized carbon nano-tube of acidified attached hydroxyl or carboxyl.
- 6. according to the method for claim 1, it is characterised in that the titanium alloy can be TA1, TA2, TA18, TC4.
- 7. according to the method for claim 1, it is characterised in that described primer resin is high temperature resistant thermosetting resin, bag Include polyimides, polyether-ether-ketone.
- 8. according to the method for claim 1, it is characterised in that described fibre-reinforced prepregs are fibre reinforced polyethers Ether ketone resin prepreg, fibre reinforced polyimide resin prepreg, CNT/fibre reinforced polyimide resin are pre- Leaching material.
- 9. according to the method for claim 1, it is characterised in that the dosage of CNT is resin quality in the step 2) 5%.
- 10. the composite prepared according to any described methods of claim 1-9.
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Cited By (6)
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| CN109483171A (en) * | 2018-12-05 | 2019-03-19 | 西安庄信新材料科技有限公司 | A kind of construction method of titanium building materials |
| CN111020685A (en) * | 2019-11-01 | 2020-04-17 | 浙江大学 | Preparation method of fiber metal laminated plate for improving interlayer strength |
| CN111516319A (en) * | 2020-03-09 | 2020-08-11 | 广东石油化工学院 | Fiber-reinforced hybrid core material and preparation method thereof |
| CN112680956A (en) * | 2019-10-18 | 2021-04-20 | 南京理工大学 | Method for improving interface performance of fiber metal laminate |
| CN113183554A (en) * | 2021-06-08 | 2021-07-30 | 燕山大学 | Preparation method for toughening carbon fiber composite aluminum plate |
| CN113373493A (en) * | 2021-05-31 | 2021-09-10 | 南京理工大学 | Preparation method of carbon nanotube reinforced fiber metal laminate |
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| 赵艳文等: "碳纳米管/玻纤/环氧层板超声真空灌注工艺及性能研究", 《航空材料学报》 * |
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| CN109483171A (en) * | 2018-12-05 | 2019-03-19 | 西安庄信新材料科技有限公司 | A kind of construction method of titanium building materials |
| CN112680956A (en) * | 2019-10-18 | 2021-04-20 | 南京理工大学 | Method for improving interface performance of fiber metal laminate |
| CN111020685A (en) * | 2019-11-01 | 2020-04-17 | 浙江大学 | Preparation method of fiber metal laminated plate for improving interlayer strength |
| CN111020685B (en) * | 2019-11-01 | 2021-01-08 | 浙江大学 | Preparation method of fiber metal laminated plate for improving interlayer strength |
| CN111516319A (en) * | 2020-03-09 | 2020-08-11 | 广东石油化工学院 | Fiber-reinforced hybrid core material and preparation method thereof |
| CN113373493A (en) * | 2021-05-31 | 2021-09-10 | 南京理工大学 | Preparation method of carbon nanotube reinforced fiber metal laminate |
| CN113183554A (en) * | 2021-06-08 | 2021-07-30 | 燕山大学 | Preparation method for toughening carbon fiber composite aluminum plate |
| CN113183554B (en) * | 2021-06-08 | 2022-07-08 | 燕山大学 | Preparation method for toughening carbon fiber composite aluminum plate |
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