CN107283871A - A kind of preparation method of thermoplastic resin matrix's carbon fiber titanium/titanium alloy layer plywood - Google Patents
A kind of preparation method of thermoplastic resin matrix's carbon fiber titanium/titanium alloy layer plywood Download PDFInfo
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- CN107283871A CN107283871A CN201710737101.0A CN201710737101A CN107283871A CN 107283871 A CN107283871 A CN 107283871A CN 201710737101 A CN201710737101 A CN 201710737101A CN 107283871 A CN107283871 A CN 107283871A
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- titanium alloy
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- prepreg
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
- B29C70/28—Shaping operations therefor
- B29C70/30—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core
- B29C70/34—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core and shaping or impregnating by compression, i.e. combined with compressing after the lay-up operation
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29B—PREPARATION OR PRETREATMENT OF THE MATERIAL TO BE SHAPED; MAKING GRANULES OR PREFORMS; RECOVERY OF PLASTICS OR OTHER CONSTITUENTS OF WASTE MATERIAL CONTAINING PLASTICS
- B29B15/00—Pretreatment of the material to be shaped, not covered by groups B29B7/00 - B29B13/00
- B29B15/08—Pretreatment of the material to be shaped, not covered by groups B29B7/00 - B29B13/00 of reinforcements or fillers
- B29B15/10—Coating or impregnating independently of the moulding or shaping step
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
- B29C70/28—Shaping operations therefor
- B29C70/54—Component parts, details or accessories; Auxiliary operations, e.g. feeding or storage of prepregs or SMC after impregnation or during ageing
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29K—INDEXING SCHEME ASSOCIATED WITH SUBCLASSES B29B, B29C OR B29D, RELATING TO MOULDING MATERIALS OR TO MATERIALS FOR MOULDS, REINFORCEMENTS, FILLERS OR PREFORMED PARTS, e.g. INSERTS
- B29K2071/00—Use of polyethers, e.g. PEEK, i.e. polyether-etherketone or PEK, i.e. polyetherketone or derivatives thereof, as moulding material
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29K—INDEXING SCHEME ASSOCIATED WITH SUBCLASSES B29B, B29C OR B29D, RELATING TO MOULDING MATERIALS OR TO MATERIALS FOR MOULDS, REINFORCEMENTS, FILLERS OR PREFORMED PARTS, e.g. INSERTS
- B29K2079/00—Use of polymers having nitrogen, with or without oxygen or carbon only, in the main chain, not provided for in groups B29K2061/00 - B29K2077/00, as moulding material
- B29K2079/08—PI, i.e. polyimides or derivatives thereof
- B29K2079/085—Thermoplastic polyimides, e.g. polyesterimides, PEI, i.e. polyetherimides, or polyamideimides; Derivatives thereof
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29K—INDEXING SCHEME ASSOCIATED WITH SUBCLASSES B29B, B29C OR B29D, RELATING TO MOULDING MATERIALS OR TO MATERIALS FOR MOULDS, REINFORCEMENTS, FILLERS OR PREFORMED PARTS, e.g. INSERTS
- B29K2081/00—Use of polymers having sulfur, with or without nitrogen, oxygen or carbon only, in the main chain, as moulding material
- B29K2081/04—Polysulfides, e.g. PPS, i.e. polyphenylene sulfide or derivatives thereof
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29K—INDEXING SCHEME ASSOCIATED WITH SUBCLASSES B29B, B29C OR B29D, RELATING TO MOULDING MATERIALS OR TO MATERIALS FOR MOULDS, REINFORCEMENTS, FILLERS OR PREFORMED PARTS, e.g. INSERTS
- B29K2305/00—Use of metals, their alloys or their compounds, as reinforcement
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Composite Materials (AREA)
- Laminated Bodies (AREA)
- Reinforced Plastic Materials (AREA)
- Moulding By Coating Moulds (AREA)
Abstract
A kind of preparation method of thermoplastic resin matrix's carbon fiber titanium/titanium alloy layer plywood, it belongs to light composite material field, the problem of titanium alloy and prepreg interface bonding effect of the invention in order to solve current fibre reinforced titanium alloy laminate TiGr is poor.The thermoplastic resin that the present invention is used includes polyether-ether-ketone (PEEK), three kinds of engineering High performance plastic resins of polyphenylene sulfide (PPS) and PEI (PEI), and coordinate film layered manner and powder infusion method, solve the problem of thermoplastic resin is poor to the dipping effect of carbon fiber.
Description
Technical field
The invention belongs to light composite material field, and in particular to a kind of thermoplastic resin matrix's carbon fiber-titanium/titanium alloy
The preparation method of laminate.
Background technology
Fiber Reinforced Metal Laminates (Fiber Metal Laminates, FMLs) are one kind by sheet metal and fiber reinforcement tree
After fat prepreg is alternately laid, the interply hybrid composites solidified under certain temperature and pressure.FMLs materials are unique
Constituted mode determine it both be different from traditional metal material also different from conventional composite, with single metal material
Compare, its light weight, endurance, corrosion-resistant, good flame resistance；Compared with Single Fiber reinforced resin composite, its damage tolerance
High, notch strength is big, shock resistance and moisture-resistant good in thermal property.Meanwhile, Fiber Reinforced Metal Laminates have stronger designability, can
Ply sequence and fiber-wall-element model are selected as needed.Therefore, fiber metal plate material has wide in fields such as Aero-Space
Application prospect.
First generation FMLs is that the aramid fiber researched and developed by TU Delft university strengthens aramid aluminiumlaminates
(AramidReinforced Aluminum Laminates, ARALL), realizes aramid aluminiumlaminates to Fiber Reinforced Metal Laminates
Across, compared with traditional aluminium alloy structure, ARALL has fatigue crack-resistant scalability good, and fracture toughness is low, peel strength compared with
Low performance, ARALL applies the small curvature component of slab construction or single-curved surface in aircaft configuration, using very limited；The second generation
FMLs glass fiber reinforcements aramid aluminiumlaminates (Glass ReinforcedAluminum Laminates, GLARE), GLARE is same
ARALL is compared, and not only residual stress state is greatly taken on a new look, and improves the compression performance and impact property of material, is reduced
The hygroscopicity of material, therefore its use scope is expanded significantly.The GLARE used on A380 fuselages reaches housing construction weight
3%, usable floor area 500m2Left and right, full machine loss of weight about 800kg altogether, while fatigue life improve 10~15 times；Third generation FMLs
Fibre reinforced aramid aluminiumlaminates (Carbon reinforced aluminum laminate, CARE), CARE has larger
Damaged deformation and very high strength and stiffness, but due to there is potential corrosion between carbon fiber and aluminium alloy, therefore in engineering
On be not used widely.Forth generation FMLs fibre reinforced titanium alloy laminates (Titanium/Graphite Hybrid
Laminates, TiGr), TiGr can not only improve the specific strength and high-temperature behavior of laminate, in the absence of potential corrosion, and have
Higher fatigue strength and higher toughness.
In addition, ARALL and GLARE laminates use the thermosetting resins such as epoxy for matrix, and conventional thermosetting resinous wood
Need to carry out heat-insulation pressure keeping to material during the solidified forming of material, constrain production efficiency.By contrast, with thermoplastic resin
The FMLs prepared for matrix can be completed in a relatively short time preparation and shape, and be remarkably improved the preparation efficiency of laminate, reduce
Its production cost.Meanwhile, thermoplastic resin matrix's high temperature resistant can meet product high-temperature service requirement, the application of thermoplastic
Make it possible FMLs recycling.
The content of the invention
The present invention is glued effect for the titanium alloy and prepreg interface that solve current fibre reinforced titanium alloy laminate TiGr
Really poor the problem of.
A kind of preparation method of thermoplastic resin matrix's carbon fiber-titanium/titanium alloy layer plywood of the present invention, including following step
Suddenly：
1) thermoplastic resin is made to infiltrate carbon fiber unidirectional cloth or carbon fiber braiding using film layered manner or powder infusion method
Cloth, prepares fibre reinforced thermoplastic resin prepreg；
2) sandblasting and silane coupler Combined Treatment or alkalescence are carried out for 0.3~0.5mm titanium/titanium alloy surface to thickness
Anodization and ultraviolet radiation graft Combined Treatment；
3) the uniform brushing releasing agent of die inside, titanium/titanium alloy that surface treated is obtained and fibre reinforced thermoplastic
Property resin prepreg material be according to laying rule laying in a mold, and in every layer of titanium/thickness is placed between titanium alloy and prepreg
0.05~0.1mm thermoplastic resin glued membranes, cover tightly mould upper cover plate；
4) mould is integrally put into hot press, 180 DEG C of holdings is warming up to using three-stage gradient-heated, i.e. first paragraph
40min, second segment is warming up to 200~300 DEG C of holding 40min, and the 3rd section is warming up to 250~370 DEG C of holding 2h, naturally cools to
Thermoplastic resin matrix's carbon fiber-titanium/titanium alloy layer plywood that thickness is 1~5mm is obtained after room temperature, the demoulding.
Compared with prior art, the present invention includes following beneficial effect：
1st, the thermoplastic resin that the present invention is used includes polyether-ether-ketone (PEEK), polyphenylene sulfide (PPS) and PEI
(PEI) three kinds of engineerings are all higher than 300 DEG C with the fusing point of High performance plastic resin, and viscosity is generally more than 100Pas during melting,
And the change of temperature influences very little on it, also possessing just because of this after its shaping has high mechanical strength, high temperature resistant, insulating properties steady
Fixed, hydrolysis, resistance to compression, it is corrosion-resistant the advantages of, therefore it is to prepare carbon fiber to the dipping effect of carbon fiber to improve thermoplastic resin
Strengthen the key of thermoplastic resin prepreg.
2nd, the film layered manner that the present invention is used, belongs to dry process prepeg process.It is thin compared with conventional wet technique
The prepreg resin content and glued membrane quality that film layer folds method preparation are easily controlled, and resin Composition volatile quantity is few, bubble rate and hole
Rate reduction by more than 30%, be avoided that causes the use of prepreg because of the stress concentration that bubble and hole are brought in use
The harm of life-span reduction, and it is small to human body and environmental hazard, and big small-scale production is applicable, and resin can be monitored at any time
Gel time, viscosity etc. can influence the factor of prepreg quality.
3rd, the powder infusion method that the present invention is used, falls within dry process prepeg process.With quick continuous production heat
Plasticity prepreg, few to fibre damage, polymer is not easily decomposed and the low advantage of production cost.
4th, the mode of titanium/titanium alloy surface processing has a lot, and single surface treatment method can not expire in most cases
Sufficient application requirement, a variety of methods, which are combined, can reach more preferable bonding effect.Single blasting treatment can produce macroroughness table
Face, titanium alloy high-temperature durability is preferable, but wet heat durability is poor.The present invention is used at blasting treatment and silane coupler joint
Manage the strong interface chemical bond that silane coupler can be good with titanium/titanium alloy formation moisture-proof on the basis of blasting treatment, prevent titanium/
The hydrolysis and corrosion in titanium alloy surface area, so that product can preserve in good time splicing for a long time, add the use longevity of gluded joint
Life, improves the durability of adhesive bonding of product.
5th, exist in single titanium/titanium alloy surface anodization one side solution unstable material, noxious material or
Volatile substances are difficult to control to component in solution, such as sodium hydroxide -- and the hydrogen peroxide in hydrogenperoxide steam generator decomposes too fast.
On the other hand the technological parameter of surface treatment is difficult accurate control, and the impurity for causing the surface attachment punching after processing can't to be washed off
Layer.In addition, if the surface after processing is glued not in time, the performance of standing time and environment butt joint can also have an impact.The present invention
Using alkaline anodization and ultraviolet radiation graft Combined Treatment, ultraviolet radiation graft can be obtained on the basis of alkaline anodization
It can ensure that its bulk properties does not change again with special construction function surface feature, grafting processing is in titanium/titanium alloy table
Face forms countless polypropylene small molecule brushes, surface is formed the mini porous structures that aperture is Nano grade, so as to improve boundary
The wetability in face, improves bonding property.
6th, thickness is placed for the corresponding thermoplastic resins of 0.05~0.1mm in the middle of every layer of titanium/titanium alloy and prepreg during laying
Glued membrane adds the gel content of titanium/titanium alloy and prepreg interface, on the one hand resin adhesive liquid is filled into surface treatment
Titanium afterwards/titanium alloy micro-roughened surface, another aspect homogenous resins compatible with prepreg resin can be tied so as to improve interface
Close intensity.
7th, mold design is detachable into the lower frame of mould four, and first unloading the lower frame of mould four in mold releasability again will be upper
Cover plate separates taking-up laminate with lower mould.Purpose is to be the mold cavity closed during in order to prevent that upper cover plate from covering because of pressure mistake
Greatly, internal temperature inequality, resin flowing do not cause freely to produce various defects inside laminate.
Brief description of the drawings
Fig. 1 is the preparation shaping method flow diagram of the present invention；
Fig. 2 is titanium/titanium alloy surface ultraviolet radiation graft polypropylene schematic diagram；
Fig. 3 is inventive die and the regular schematic diagram of laying；Wherein, 1, groove mould upper cover plate；2nd, groove under mould；3rd, titanium/
Titanium alloy；4th, thermoplastic resin glued membrane；5th, prepreg；6th, four frame；7th, hex(agonal)screw hole one；
Fig. 4 is the dimensional structure diagram of specific embodiment of the invention embodiment 1；Wherein, 3, titanium/titanium alloy；4th, it is hot
Plastic resin glued membrane；5th, prepreg；
Fig. 5 is the dimensional structure diagram of specific embodiment of the invention embodiment 2；Wherein, 3, titanium/titanium alloy；4th, it is hot
Plastic resin glued membrane；5th, prepreg.
Embodiment
Embodiment one：A kind of thermoplastic resin matrix's carbon fiber-titanium/titanium alloy layer plywood of present embodiment
Preparation method, comprises the following steps：
1) thermoplastic resin is made to infiltrate carbon fiber unidirectional cloth or carbon fiber braiding using film layered manner or powder infusion method
Cloth, prepares fibre reinforced thermoplastic resin prepreg；
2) sandblasting and silane coupler Combined Treatment or alkalescence are carried out for 0.3~0.5mm titanium/titanium alloy surface to thickness
Anodization and ultraviolet radiation graft Combined Treatment；
3) the uniform brushing releasing agent of die inside, titanium/titanium alloy that surface treated is obtained and fibre reinforced thermoplastic
Property resin prepreg material be according to laying rule laying in a mold, and in every layer of titanium/thickness is placed between titanium alloy and prepreg
0.05~0.1mm thermoplastic resin glued membranes, cover tightly mould upper cover plate；
4) mould is integrally put into hot press, 180 DEG C of holdings is warming up to using three-stage gradient-heated, i.e. first paragraph
40min, second segment is warming up to 200~300 DEG C of holding 40min, and the 3rd section is warming up to 250~370 DEG C of holding 2h, naturally cools to
Thermoplastic resin matrix's carbon fiber-titanium/titanium alloy layer plywood that thickness is 1~5mm is obtained after room temperature, the demoulding.
Embodiment two：Present embodiment from unlike embodiment one：Step 1) in film stacking
The process that method prepares fibre reinforced thermoplastic resin prepreg is：Individual layer carbon fiber unidirectional cloth or carbon fiber woven cloth and thickness
Overlapped for 0.05~0.1mm thermoplastic resin membranes, temperature be 250~370 DEG C, pressure be through sulphur under the conditions of 0.5~5MPa
Change machine hot-pressing processing, the prepreg that obtained gel content is 50~60% and thickness is 0.1~0.2mm.Other and specific embodiment party
Formula one is identical.
Embodiment three：Present embodiment from unlike embodiment one：Step 1) in powder infusion
The process that method prepares fibre reinforced thermoplastic resin prepreg is：By individual layer carbon fiber unidirectional cloth or carbon fiber woven cloth through dividing
Dissipate roller and enter the electrostatic room that left floating particle diameter for 5~15 μm of thermoplastic resin powders, be sufficiently mixed, be according to prepreg gel content
50~60% and thickness be 0.1~0.2mm standard, supplement resin above and below individual layer carbon fiber unidirectional cloth or carbon fiber woven cloth
Powder is simultaneously put into vulcanizer, is 250~370 DEG C, under conditions of pressure is 0.5~5MPa in temperature, hot pressing obtains prepreg.
It is other identical with embodiment one.
Embodiment four：Present embodiment from unlike embodiment one：Step 2) in sandblasting and silicon
Alkane coupling agent Combined Treatment process is：Titanium/titanium alloy surface acetone or ethyl ester are wiped after oil removing, using sand-blasting machine 0.8
Uniformly swept from fine sands more than 100 mesh under individual atmospheric pressure and blow titanium/titanium alloy surface, until titanium/titanium alloy surface is in matt shape,
Dried with deionized water rinsing surface, then titanium/titanium alloy is put into the glycidoxy official that volumn concentration is 1% at room temperature
It can roll into a ball and 15min is soaked in silane-water solution, be dried.It is other identical with embodiment one.
Embodiment five：Present embodiment from unlike embodiment one：Step 2) in alkaline anode
Change and ultraviolet radiation graft Combined Treatment process is：
First, cleaned after titanium/titanium alloy surface being wiped into oil removing with acetone or ethyl ester with deionized water, be put into temperature for 60 DEG C
Impregnate after 2min takes out and be washed with deionized water only in alkali lye；Wherein, alkali lye is NaOH solution, Na3PO4Solution and Na2CO3Solution
Mix, NaOH weight/mass percentage composition is Na in 4%, alkali lye in alkali lye3PO4Weight/mass percentage composition be 4%, in alkali lye
Na2CO3Weight/mass percentage composition be 2%；
2nd, it is put into acid solution and handles 2min, taking-up is washed with deionized water net；Wherein, acid solution is by HF and HNO3Mixing and
Into HNO in acid solution3Volumn concentration be 30%, HF volumn concentration is 1% in acid solution；
3rd, it is put into anodization tank liquor and handles, takes out deionized water and clean；Wherein, anodisation conditions are temperature 10~30
DEG C, 5~15V of voltage, 10~30min of time；Anodization tank liquor is by NaOH solution, EDTA solution, Na2C4H4O6Solution and
Na2SiO3Solution is mixed；The weight/mass percentage composition of NaOH in anodization tank liquor is 30%,；EDTA in anodization tank liquor
Weight/mass percentage composition be 2%, the Na in anodization tank liquor2C4H4O6Weight/mass percentage composition be 6%, in anodization tank liquor
Na2SiO3Weight/mass percentage composition be 0.5%；
4th, the titanium for handling previous step/titanium alloy room is put into the methacryloxypropyl that volumn concentration is 1% under temperature
5h is soaked in the base functional silanes aqueous solution, taking-up is dried after being cleaned with deionized water；
5th, compound concentration is 1mol/L acrylic acid aqueous solution, and nitrogen is passed through into acrylic acid aqueous solution and is removed in solution
Oxygen, then titanium/titanium alloy after step 4 is handled is put into 5min in the solution, while the uviol lamp for being 500W with power shines
Penetrate 20min.
It is other identical with embodiment one.
Embodiment six：Present embodiment from unlike embodiment one：Step 3) described in laying
Rule replaces laying with prepreg for 5/4,4/3 or 3/2 laying, i.e. titanium/titanium alloy, and keeps titanium/titanium alloy to be layered on all the time most
Outer layer；When prepreg fabric with carbon fiber one-way, then laying rule for [0 °/90 °/0 °/90 °], [0 °/90 °/0 °], [0 °/
90°].It is other identical with embodiment one.
Embodiment seven：Present embodiment from unlike embodiment one：Step 3) in mould by mould
Groove 2 is constituted under tool upper cover plate 1 and mould；
Described mould upper cover plate 1 is just placed under mould in groove 2, and groove 2 is rectangle under described mould；Groove 2 under mould
Four frames 6 it is detachable, opened hexagon socket head cap screw hole 1 for 6 four jiaos in four frames, and corresponding with hex(agonal)screw hole 1
2 four jiaos of upper surfaces of groove offer hexagon socket head cap screw hole 28 under mould, are used by hex(agonal)screw hole 1 and hex(agonal)screw hole 28
Screw fixes four frames 6；The material of groove 2 is No. 45 modifier treatment mould steel under described mould upper cover plate 1 and mould.
It is other identical with embodiment one.
Embodiment eight：Present embodiment from unlike embodiment one：Step 4) in add in three-stage
Pressurized treatments are carried out in thermal process, first paragraph is, to 70min, to apply 0.05MPa pressure since heating；Second segment be
70min~80min, applies 0.5~5MPa pressure；3rd section is the pressure for applying in 80min~150min 0.05MP；The
Four sections are the pressure for applying in 150min~200min 0.5~5MPa.It is other identical with embodiment one.
Embodiment nine：Present embodiment from unlike embodiment one：Described thermoplastic resin bag
Include polyether-ether-ketone, polyphenylene sulfide or PEI.It is other identical with embodiment one.
Embodiment ten：Present embodiment from unlike embodiment one：Described titanium/titanium alloy is
TA2, TA3, TC4 or TC6, thickness are 0.3~0.5mm.It is other identical with embodiment one.
Embodiment 11：Present embodiment from unlike embodiment one：Described thermoplastic resin
Matrix carbon fiber-titanium/titanium alloy layer plywood is forth generation FMLs fibre reinforced titanium alloy laminates (Titanium/Graphite
Hybrid Laminates,TiGr).It is other identical with embodiment one.
Embodiment 12：Present embodiment from unlike embodiment one：Described carbon fiber one-way
Cloth is laminated cloth.It is other identical with embodiment one.
Present invention is not limited only to the content of the respective embodiments described above, the group of one of them or several embodiments
Contract sample can also realize the purpose of invention.
Beneficial effects of the present invention are verified by following examples：
Embodiment 1
A kind of preparation of polyether-ether-ketone resin matrix carbon fiber-TA2 titanium layer plates of the present embodiment, is to carry out as follows
's：
The first step：Poly (ether ether ketone) film is infiltrated carbon fiber woven cloth using film layered manner, prepare fibre reinforced and gather
Ether ether ketone resin prepreg material.
It by the thickness of 300mm × 300mm carbon fiber woven cloth and same size is 0.1mm polyether-ether-ketones that detailed process, which is,
Film overlapping through temperature be 370 DEG C of pressure be 2h vulcanizer hot pressing the 1MPa times, until each carbon fiber bundle between it is seamless, tree
Fat melting is embedded into fibre bundle, and it is 0.14mm that hot pressing, which terminates measurement polyether-ether-ketone prepreg thickness, and thermogravimetric analysis measures preimpregnation
It is 58% to expect gel content, meets subsequent experimental requirement.
Second step：Sandblasting and silane coupler Combined Treatment are carried out for 0.3mm TA2 industrially pure titaniums surface to thickness.
Detailed process is to wipe TA2 surfaces acetone or ethyl ester after oil removing, is selected using sand-blasting machine under 0.8 atmospheric pressure
Uniformly swept with fine sands more than 100 mesh and blow TA2 surfaces, until TA2 surfaces are in matt shape, dried with deionized water rinsing surface,
15min is soaked in the silane coupler KH560 aqueous solution that TA2 is put into 1% at room temperature again, is dried.
3rd step：The lower frame 6 of mould four is fixed, the uniform brushing releasing agent in the inner side of groove 2, surface treated is obtained under mould
The TA2 arrived is laminated the prepreg of method preparation according to 3/2 regular laying, and in every layer of TA2 and prepreg in a mold with film
Between place thickness be 0.1mm polyether-ether-ketones glued membrane (Fig. 4), finally cover tightly mould upper cover plate 1.
4th step：Mould is integrally put into hot press, sets temperature to be 180 DEG C using Three-section type heating, i.e. first paragraph
40min is kept, second segment is warming up to 300 DEG C of holding 40min, and the 3rd section is warming up to 370 DEG C of holding 2h.
Pressure process is that it is 0.05MPa that first paragraph hot pressing, which starts to hot pressing 70min precharges staged pressure, and second segment is
Hot pressing 70min~80min pressure periods pressure is 0.8MPa, and the 3rd section is that hot pressing 80min~150min pressure release staged pressures are
0.05MPa, the 4th section is that hot pressing 150min~200min pressure periods pressure is 1Mpa.
The polyether-ether-ketone resin matrix carbon fiber-TA2 titanium layers plate thickness obtained after natural cooling, the demoulding is 1.20mm.
Described mould groove 2 under mould upper cover plate 1 and mould is constituted；
Described mould upper cover plate 1 is just placed under mould in groove 2, and groove 2 is rectangle under described mould；Groove 2 under mould
Four frames 6 it is detachable, opened hexagon socket head cap screw hole 1 for 6 four jiaos in four frames, and corresponding with hex(agonal)screw hole 1
2 four jiaos of upper surfaces of groove offer hexagon socket head cap screw hole 28 under mould, are used by hex(agonal)screw hole 1 and hex(agonal)screw hole 28
Screw fixes four frames 6；The material of groove 2 is No. 45 modifier treatment mould steel under described mould upper cover plate 1 and mould.
Embodiment 2
A kind of preparation of polyphenylene sulfide matrix carbon fiber-TC4 titanium alloy laminates
The first step：Polyphenylene sulfide is infiltrated carbon fiber unidirectional cloth (laminated cloth) using powder infusion method, prepare carbon fine
Dimension enhancing polyphenylene sulfide prepreg；
Detailed process is to use powder infusion machine that individual layer carbon fiber unidirectional cloth is entered into particle diameter for 5~15 μm through guide roller
There are the multiple scattered rollers arranged according to certain rules PPS electrostatic powders room, electrostatic room, and scattered roller disperses fiber, adsorbs PPS powder
End, a certain amount of PPS powder is supplemented above and below carbon fiber and is put into vulcanizer, through 290 DEG C of pressure 1MPa times 2h heat of temperature
Pressure obtains prepreg.It is 0.15mm through measuring PPS prepregs thickness, it is 55% that thermogravimetric analysis, which measures prepreg gel content, is met
Subsequent experimental requirement.
Second step：Thickness is carried out at alkaline anodization and ultraviolet radiation graft joint for 0.5mm TC4 titanium alloy surfaces
Reason.
Detailed process is that TC4 titanium alloy surfaces are wiped into deionized water after oil removing with acetone or ethyl ester to clean, and is put into 60 DEG C
4%NaOH, 4%Na3PO4And 2%Na2CO32min taking-up deionized waters are impregnated in alkali lye to clean, and are put into 30%HNO3And 1%HF
2min taking-up deionized waters are handled in acid solution to clean, and are put into 30%NaOH, 2%EDTA, 6%Na2C4H4O6And 0.5%Na2SiO3
Anodization tank liquor in, anodisation conditions are 25 DEG C of temperature, and voltage 10V, time 25min takes out deionized water and cleaned, then by TC4
Titanium alloy is put into the 1% silane coupler KH570 aqueous solution at room temperature soaks 5h taking-up deionized water cleaning-dryings, configuration
1mol/L acrylic acid aqueous solution is passed through nitrogen, removes the oxygen in solution, TC4 titanium alloys is put into solution 5min, simultaneously
20min is irradiated under 500W ultraviolet lights, acrylic acid is occurred polymerisation.
3rd step：The lower frame 6 of mould four is fixed, the uniform brushing releasing agent in the inner side of groove 2, surface treated is obtained under mould
The prepreg that the TC4 titanium alloys arrived are prepared with powder infusion method is according to 3/2 regular laying, wherein carbon fiber unidirectional cloth in a mold
The prepreg overlay rule being made is [0 °/90 °], and placement thickness is in the middle of every layer of TC4 titanium alloy and prepreg
0.1mmPPS glued membranes (Fig. 5), finally cover tightly mould upper cover plate 1.
4th step：Mould is integrally put into hot press, sets temperature to be 180 DEG C using Three-section type heating, i.e. first paragraph
40min is kept, second segment is warming up to 200 DEG C of holding 40min, and the 3rd section is warming up to 290 DEG C of holding 2h.
Pressure process is that it is 0.05MPa that first paragraph hot pressing, which starts to hot pressing 70min precharges staged pressure, and second segment is
Hot pressing 70min~80min pressure periods pressure is 0.8MPa, and the 3rd section is that hot pressing 80min~150min pressure release staged pressures are
0.05MPa, the 4th section is that hot pressing 150min~200min pressure periods pressure is 1Mpa.
The PPS resin matrix carbon fiber-TC4 titanium alloy layers plate thickness obtained after natural cooling, the demoulding is 1.85mm.
Described mould groove 2 under mould upper cover plate 1 and mould is constituted；
Described mould upper cover plate 1 is just placed under mould in groove 2, and groove 2 is rectangle under described mould；Groove 2 under mould
Four frames 6 it is detachable, opened hexagon socket head cap screw hole 1 for 6 four jiaos in four frames, and corresponding with hex(agonal)screw hole 1
2 four jiaos of upper surfaces of groove offer hexagon socket head cap screw hole 28 under mould, are used by hex(agonal)screw hole 1 and hex(agonal)screw hole 28
Screw fixes four frames 6；The material of groove 2 is No. 45 modifier treatment mould steel under described mould upper cover plate 1 and mould.
Claims (10)
1. a kind of preparation method of thermoplastic resin matrix's carbon fiber-titanium/titanium alloy layer plywood, it is characterised in that including following step
Suddenly：
1) thermoplastic resin is made to infiltrate carbon fiber unidirectional cloth or carbon fiber woven cloth, system using film layered manner or powder infusion method
Standby fibre reinforced thermoplastic resin prepreg；
2) sandblasting and silane coupler Combined Treatment or alkaline anode are carried out for 0.3~0.5mm titanium/titanium alloy surface to thickness
Change and ultraviolet radiation graft Combined Treatment；
3) the uniform brushing releasing agent of die inside, titanium/titanium alloy that surface treated is obtained and fibre reinforced thermoplastic resin
Fat prepreg is 0.05 according to laying rule laying in a mold, and in every layer of titanium/thickness is placed between titanium alloy and prepreg
~0.1mm thermoplastic resin glued membranes, cover tightly mould upper cover plate；
4) mould is integrally put into hot press, 180 DEG C of holding 40min is warming up to using three-stage gradient-heated, i.e. first paragraph,
Second segment is warming up to 200~300 DEG C of holding 40min, and the 3rd section is warming up to 250~370 DEG C of holding 2h, naturally cools to room temperature,
Thermoplastic resin matrix's carbon fiber-titanium/titanium alloy layer plywood that thickness is 1~5mm is obtained after the demoulding.
2. a kind of preparation method of thermoplastic resin matrix's carbon fiber-titanium/titanium alloy layer plywood according to claim 1,
It is characterized in that：Step 1) in film stacking method prepare the process of fibre reinforced thermoplastic resin prepreg and be：Monolayer carbon
One-way fiber fabric or carbon fiber woven cloth are that 0.05~0.1mm thermoplastic resin membranes overlap with thickness, temperature for 250~
370 DEG C, pressure be under the conditions of 0.5~5MPa through vulcanizer hot-pressing processing, obtained gel content be 50~60% and thickness be 0.1~
0.2mm prepreg.
3. a kind of preparation method of thermoplastic resin matrix's carbon fiber-titanium/titanium alloy layer plywood according to claim 1,
It is characterized in that：Step 1) in powder infusion method prepare the process of fibre reinforced thermoplastic resin prepreg and be：By individual layer
Carbon fiber unidirectional cloth or carbon fiber woven cloth are dispersed through roller and enter the electrostatic that left floating particle diameter for 5~15 μm of thermoplastic resin powders
Room, is sufficiently mixed, according to the standard that prepreg gel content is 50~60% and thickness is 0.1~0.2mm, in individual layer carbon fiber list
Continue to supplement toner above and below to cloth or carbon fiber woven cloth and be put into vulcanizer, be 250~370 DEG C, pressure in temperature
Under conditions of 0.5~5MPa, hot pressing obtains prepreg.
4. a kind of preparation method of thermoplastic resin matrix's carbon fiber-titanium/titanium alloy layer plywood according to claim 1,
It is characterized in that：Step 2) in sandblasting and silane coupler Combined Treatment process be：By titanium/titanium alloy surface acetone or second
Ester is wiped after oil removing, is uniformly swept from fine sands more than 100 mesh under 0.8 atmospheric pressure using sand-blasting machine and is blown titanium/titanium alloy table
Face, until titanium/titanium alloy surface is in matt shape, is dried, then titanium/titanium alloy is put into body at room temperature with deionized water rinsing surface
Product percentage composition is dried to soak 15min in the 1% glycidoxy functional silanes aqueous solution.
5. a kind of preparation method of thermoplastic resin matrix's carbon fiber-titanium/titanium alloy layer plywood according to claim 1,
It is characterized in that：Step 2) in alkaline anodization and ultraviolet radiation graft Combined Treatment process be：
First, cleaned after titanium/titanium alloy surface being wiped into oil removing with acetone or ethyl ester with deionized water, it is 60 DEG C of alkali lye to be put into temperature
Middle dipping 2min is washed with deionized water net after taking out；Wherein, alkali lye is NaOH solution, Na3PO4Solution and Na2CO3Solution is mixed
Form, NaOH weight/mass percentage composition is Na in 4%, alkali lye in alkali lye3PO4Weight/mass percentage composition be 4%, in alkali lye
Na2CO3Weight/mass percentage composition be 2%；
2nd, it is put into acid solution and handles 2min, taking-up is washed with deionized water net；Wherein, acid solution is by HF and HNO3Mix, acid
HNO in liquid3Volumn concentration be 30%, HF volumn concentration is 1% in acid solution；
3rd, it is put into anodization tank liquor and handles, takes out deionized water and clean；Wherein, anodisation conditions are 10~30 DEG C of temperature, electricity
Press 5~15V, 10~30min of time；Anodization tank liquor is by NaOH solution, EDTA solution, Na2C4H4O6Solution and Na2SiO3It is molten
Liquid is mixed；The weight/mass percentage composition of NaOH in anodization tank liquor is 30%,；The quality hundred of EDTA in anodization tank liquor
It is the Na in 2%, anodization tank liquor to divide content2C4H4O6Weight/mass percentage composition be 6%, the Na in anodization tank liquor2SiO3's
Weight/mass percentage composition is 0.5%；
4th, the titanium for handling previous step/titanium alloy room is put into the methacryloxy official that volumn concentration is 1% under temperature
It can roll into a ball and 5h is soaked in silane-water solution, taking-up is dried after being cleaned with deionized water；
5th, compound concentration is 1mol/L acrylic acid aqueous solution, and the oxygen in nitrogen removing solution is passed through into acrylic acid aqueous solution
Gas, then titanium/titanium alloy after step 4 is handled are put into 5min in the solution, while the ultra violet lamp for being 500W with power
20min。
6. a kind of preparation method of thermoplastic resin matrix's carbon fiber-titanium/titanium alloy layer plywood according to claim 1,
It is characterized in that：Step 3) described in laying rule replace paving with prepreg for 5/4,4/3 or 3/2 laying, i.e. titanium/titanium alloy
Layer, and keep titanium/titanium alloy to be layered on outermost layer all the time；When prepreg fabric with carbon fiber one-way, then prepreg machine direction
For [0 °/90 °/0 °/90 °], [0 °/90 °/0 °], [0 °/90 °].
7. a kind of preparation method of thermoplastic resin matrix's carbon fiber-titanium/titanium alloy layer plywood according to claim 1,
It is characterized in that：Step 3) in mould under mould upper cover plate (1) and mould groove (2) constitute；
Described mould upper cover plate (1) is just placed in groove under mould (2), and groove (2) is rectangle under described mould；Groove under mould
(2) four frames (6) detachably, have opened hexagon socket head cap screw hole one (7) in four frames (6) corner, and with hex(agonal)screw hole
Groove (2) corner upper surface offers hexagon socket head cap screw hole two (8) under the corresponding mould in one (7), by hex(agonal)screw hole one (7) and
Hex(agonal)screw hole two (8) is fixed by four frames (6) using screw；The material of groove (2) under described mould upper cover plate (1) and mould
For No. 45 modifier treatment mould steel.
8. a kind of preparation method of thermoplastic resin matrix's carbon fiber-titanium/titanium alloy layer plywood according to claim 1,
It is characterized in that：Step 4) in carry out pressurized treatments during three-stage gradient-heated, first paragraph be since heating to
70min, applies 0.05MPa pressure；Second segment is the pressure for applying 0.5~5MPa in 70min~80min；3rd section be
80min~150min, applies 0.05MP pressure；4th section is the pressure for applying in 150min~200min 0.5~5MPa.
9. a kind of preparation method of thermoplastic resin matrix's carbon fiber-titanium/titanium alloy layer plywood according to claim 1,
It is characterized in that：Described thermoplastic resin includes polyether-ether-ketone, polyphenylene sulfide or PEI.
10. a kind of preparation method of thermoplastic resin matrix's carbon fiber-titanium/titanium alloy layer plywood according to claim 1,
It is characterized in that：Described titanium/titanium alloy is TA2, TA3, TC4 or TC6, and thickness is 0.3~0.5mm.
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108664731A (en) * | 2018-05-11 | 2018-10-16 | 西安理工大学 | A kind of multiple dimensioned method for numerical simulation of composite material Googol motion controller |
| CN110116535A (en) * | 2019-05-27 | 2019-08-13 | 江苏君华特种工程塑料制品有限公司 | A kind of continuous CF/PEEK thermoplastic composite and preparation method thereof |
| CN111361180A (en) * | 2020-02-14 | 2020-07-03 | 大连交通大学 | Carbon fiber fine structure component and preparation method thereof |
| CN113619235A (en) * | 2021-08-16 | 2021-11-09 | 东华大学 | Fiber-reinforced thermoplastic resin-based composite material-metal sheet connecting piece and preparation method and application thereof |
| US11446885B2 (en) | 2019-02-28 | 2022-09-20 | Wuhan Research Institute Of Materials Protection | Friction-reducing and anti-wear composite material for wading kinematic pair and preparation method therefor |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5958578A (en) * | 1996-11-04 | 1999-09-28 | The Boeing Company | Hybrid laminate having improved metal-to-resin adhesion |
| JP2005306026A (en) * | 2004-03-23 | 2005-11-04 | Toray Ind Inc | Titanium-fiber reinforced plastic laminate |
| CN104191753A (en) * | 2014-08-27 | 2014-12-10 | 江苏呈飞精密合金股份有限公司 | Method for preparing continuous carbon fiber enhanced polyether-ether-ketone matrix fiber metal laminates |
| CN105799242A (en) * | 2014-12-31 | 2016-07-27 | 比亚迪股份有限公司 | Metal resin complex and preparation method thereof |
-
2017
- 2017-08-24 CN CN201710737101.0A patent/CN107283871B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5958578A (en) * | 1996-11-04 | 1999-09-28 | The Boeing Company | Hybrid laminate having improved metal-to-resin adhesion |
| JP2005306026A (en) * | 2004-03-23 | 2005-11-04 | Toray Ind Inc | Titanium-fiber reinforced plastic laminate |
| CN104191753A (en) * | 2014-08-27 | 2014-12-10 | 江苏呈飞精密合金股份有限公司 | Method for preparing continuous carbon fiber enhanced polyether-ether-ketone matrix fiber metal laminates |
| CN105799242A (en) * | 2014-12-31 | 2016-07-27 | 比亚迪股份有限公司 | Metal resin complex and preparation method thereof |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108664731A (en) * | 2018-05-11 | 2018-10-16 | 西安理工大学 | A kind of multiple dimensioned method for numerical simulation of composite material Googol motion controller |
| US11446885B2 (en) | 2019-02-28 | 2022-09-20 | Wuhan Research Institute Of Materials Protection | Friction-reducing and anti-wear composite material for wading kinematic pair and preparation method therefor |
| CN110116535A (en) * | 2019-05-27 | 2019-08-13 | 江苏君华特种工程塑料制品有限公司 | A kind of continuous CF/PEEK thermoplastic composite and preparation method thereof |
| CN111361180A (en) * | 2020-02-14 | 2020-07-03 | 大连交通大学 | Carbon fiber fine structure component and preparation method thereof |
| CN113619235A (en) * | 2021-08-16 | 2021-11-09 | 东华大学 | Fiber-reinforced thermoplastic resin-based composite material-metal sheet connecting piece and preparation method and application thereof |
| CN113619235B (en) * | 2021-08-16 | 2022-06-28 | 东华大学 | Fiber reinforced thermoplastic resin matrix composite-metal sheet connecting piece and preparation method and application thereof |
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