CN105946303A - Interlaminar-toughened laminated composite material and preparation method thereof - Google Patents
Interlaminar-toughened laminated composite material and preparation method thereof Download PDFInfo
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- CN105946303A CN105946303A CN201610272688.8A CN201610272688A CN105946303A CN 105946303 A CN105946303 A CN 105946303A CN 201610272688 A CN201610272688 A CN 201610272688A CN 105946303 A CN105946303 A CN 105946303A
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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
- B32B5/00—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts
- B32B5/02—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by structural features of a fibrous or filamentary layer
- B32B5/12—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by structural features of a fibrous or filamentary layer characterised by the relative arrangement of fibres or filaments of different layers, e.g. the fibres or filaments being parallel or perpendicular to each other
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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
- B32B3/00—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar form; Layered products having particular features of form
- B32B3/02—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar form; Layered products having particular features of form characterised by features of form at particular places, e.g. in edge regions
- B32B3/08—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar form; Layered products having particular features of form characterised by features of form at particular places, e.g. in edge regions characterised by added members at particular parts
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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
- B32B3/00—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar form; Layered products having particular features of form
- B32B3/26—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar form; Layered products having particular features of form characterised by a particular shape of the outline of the cross-section of a continuous layer; characterised by a layer with cavities or internal voids ; characterised by an apertured layer
- B32B3/266—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar form; Layered products having particular features of form characterised by a particular shape of the outline of the cross-section of a continuous layer; characterised by a layer with cavities or internal voids ; characterised by an apertured layer characterised by an apertured layer, the apertures going through the whole thickness of the layer, e.g. expanded metal, perforated layer, slit layer regular cells B32B3/12
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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
- B32B33/00—Layered products characterised by particular properties or particular surface features, e.g. particular surface coatings; Layered products designed for particular purposes not covered by another single class
-
- 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
- B32B38/00—Ancillary operations in connection with laminating processes
- B32B38/16—Drying; Softening; Cleaning
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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
- B32B5/00—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts
- B32B5/22—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by the presence of two or more layers which are next to each other and are fibrous, filamentary, formed of particles or foamed
- B32B5/24—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by the presence of two or more layers which are next to each other and are fibrous, filamentary, formed of particles or foamed one layer being a fibrous or filamentary layer
- B32B5/26—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by the presence of two or more layers which are next to each other and are fibrous, filamentary, formed of particles or foamed one layer being a fibrous or filamentary layer another layer next to it also being fibrous or filamentary
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- D—TEXTILES; PAPER
- D03—WEAVING
- D03D—WOVEN FABRICS; METHODS OF WEAVING; LOOMS
- D03D15/00—Woven fabrics characterised by the material, structure or properties of the fibres, filaments, yarns, threads or other warp or weft elements used
-
- 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
- B32B2037/1072—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 using a fluid jet
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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
- B32B2307/00—Properties of the layers or laminate
- B32B2307/50—Properties of the layers or laminate having particular mechanical properties
- B32B2307/558—Impact strength, toughness
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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
- B32B2307/00—Properties of the layers or laminate
- B32B2307/50—Properties of the layers or laminate having particular mechanical properties
- B32B2307/582—Tearability
- B32B2307/5825—Tear resistant
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- D—TEXTILES; PAPER
- D10—INDEXING SCHEME ASSOCIATED WITH SUBLASSES OF SECTION D, RELATING TO TEXTILES
- D10B—INDEXING SCHEME ASSOCIATED WITH SUBLASSES OF SECTION D, RELATING TO TEXTILES
- D10B2101/00—Inorganic fibres
- D10B2101/02—Inorganic fibres based on oxides or oxide ceramics, e.g. silicates
- D10B2101/06—Glass
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- D—TEXTILES; PAPER
- D10—INDEXING SCHEME ASSOCIATED WITH SUBLASSES OF SECTION D, RELATING TO TEXTILES
- D10B—INDEXING SCHEME ASSOCIATED WITH SUBLASSES OF SECTION D, RELATING TO TEXTILES
- D10B2201/00—Cellulose-based fibres, e.g. vegetable fibres
- D10B2201/01—Natural vegetable fibres
- D10B2201/08—Ramie
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- D—TEXTILES; PAPER
- D10—INDEXING SCHEME ASSOCIATED WITH SUBLASSES OF SECTION D, RELATING TO TEXTILES
- D10B—INDEXING SCHEME ASSOCIATED WITH SUBLASSES OF SECTION D, RELATING TO TEXTILES
- D10B2201/00—Cellulose-based fibres, e.g. vegetable fibres
- D10B2201/01—Natural vegetable fibres
- D10B2201/10—Bamboo
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- D—TEXTILES; PAPER
- D10—INDEXING SCHEME ASSOCIATED WITH SUBLASSES OF SECTION D, RELATING TO TEXTILES
- D10B—INDEXING SCHEME ASSOCIATED WITH SUBLASSES OF SECTION D, RELATING TO TEXTILES
- D10B2331/00—Fibres made from polymers obtained otherwise than by reactions only involving carbon-to-carbon unsaturated bonds, e.g. polycondensation products
- D10B2331/02—Fibres made from polymers obtained otherwise than by reactions only involving carbon-to-carbon unsaturated bonds, e.g. polycondensation products polyamides
Abstract
The invention discloses an interlaminar-toughened laminated composite material and a preparation method thereof. The laminated composite material comprises in-plane laminated fabrics and interlaminar XY-direction and Z-direction staples. According to the invention, staples with certain length and diameter are uniformly pre-laid according to a certain density among the laminated fabrics; the laminated fabrics are clamped with a metal supporting net; a spunlace treatment is applied, wherein high-pressure micro-flows with certain diameter and pressure intensity are applied to the laminated fabrics; during the spunlace treatment process, water flows interact with the fiber and metal supporting net, such that scattering and agitation are generated, and the interlaminar staples are subjected to displacement, interweaving and combination; with the existence of intermediate gaps among the fabrics, part of the staples enter the intermediate gaps and form a Z-direction structure; after curing, the interlaminar-toughened laminated composite material containing interlaminar and Z-direction staples is obtained. With the method provided by the invention, the I/II mixed interlaminar fracture toughness of the laminated composite material can be improved, and in-plane performance loss is low.
Description
Technical field
The invention belongs to laminated composite material interlayer toughened technical field, be specifically related to the stacking composite wood of a kind of interlayer toughened
Material structure and preparation method.
Background technology
In laminated composite material machining manufacture, strengthen the interlayer mechanical property of laminated composite material mainly from substrate
Modified and fibre structure designs two aspects to be carried out, and its primary motivitation is the impact and not of performance in reducing opposite to greatest extent
On the premise of the complexity of increase method, promote the overall mechanical property of laminated composite material to greatest extent.Knot at fiber
Structure design aspect, current laminated composite material precast body interlayer toughened method mainly has Z-Pins, acupuncture, suturing skill,
But all there is certain limitation with not enough in these technology, be mainly reflected in following some: 1) be all to use rigid media to carry out
The introducing of interlaminar short fiber, the process of puncture forms mechanical shock to the principal fibers of stacking precast body and repeatedly tears, thus
Cause the destruction of fiber in face；2) " resolution " of face intrinsic toughening is low, can not well carry out local small area
Toughness reinforcing；3) production efficiency is relatively low, and especially acupuncture and Z-Pins is not suitable for large-scale batch production occasion；4) right
The toughness reinforcing of interlaminar fracture toughness is focused primarily under I fracture mode, seldom combines II fracture mode and carries out toughness reinforcing.Therefore,
Need the piercing method during the interlayer toughened to laminated composite material precast body badly innovate and study.
Summary of the invention
It is an object of the invention to provide a kind of interlayer toughened stacking that can improve I/II mixed type interlaminar fracture toughness to answer
Condensation material and preparation method thereof.
For reaching above-mentioned purpose, present invention employs techniques below scheme:
A kind of interlayer toughened laminated composite material, this composite includes the laminated composite material precast body of interlayer toughened, institute
State laminated composite material precast body include stacking braided fabric and be arranged at the XY in stacking braided fabric to chopped fiber
With Z-direction chopped fiber, described braided fabric the most successively lay, described XY is in uniformly to chopped fiber all
Or in part braided fabric between adjacent two layers braided fabric, described Z-direction chopped fiber is in stacking braided fabric by every layer
In the passage that the intermediate gap of braided fabric is constituted, Z-direction chopped fiber is to be layed in the short of braided fabric interlayer in advance by part
Fiber enters the intermediate gap of braided fabric with spun lacing jet and is formed, and described Z-direction is to be perpendicular to braided fabric plane
Direction.
Described braided fabric is selected from fabric, and the lay mode of braided fabric is 0 °, 45 ° ,-45 ° or 90 °,
The braiding structure of braided fabric is selected from plain weave, twill or satin weave control of two-dimensional braided body.
The kinds of fibers of described braided fabric is carbon fiber, ramee, bamboo fibre or glass fibre, and described XY is to short
The kinds of fibers of fiber and Z-direction chopped fiber is carbon fiber, glass fibre, nylon fiber or Kafra fiber.
Described XY is to chopped fiber and the 2～5 of the intermediate gap spacing of a length of described braided fabric of Z-direction chopped fiber
Times, XY is to chopped fiber and a diameter of 6～10 μm of Z-direction chopped fiber.
Described composite also includes solidifying resin matrix, and solidification resin matrix is that described in homogeneous impregnation, laminated composite material is pre-
The resin curing molding of body processed and formed.
The preparation method of above-mentioned interlayer toughened laminated composite material, comprises the following steps:
1) in stacking braided fabric interlayer lay chopped fiber；
2) through step 1) after, with torr net, stacking braided fabric is clamped；
3) through step 2) after, stacking braided fabric is carried out spun lacing process, obtains precast body；
4) by precast body curing molding.
Described step 1) in, select corresponding braided fabric kind, and by certain angle stacking lay, will during lay
The chopped fiber of certain density is laid on respective layer superimposing braid woven fabric interlayer in advance, needs to select stacking according to material property simultaneously
Whole interlayers of braided fabric or part interlayer lay chopped fiber.
It is by single water jet directive stacking braided fabric that described spun lacing processes, and makes jet body touch with braided fabric and torr net
Hit, agitate, produce scattering, make interlaminar short fiber produce displacement, interspersed, obvolvent, and make some staple fiber dimension enter braiding
Fabric intermediate gap, thus one-shot forming obtains the laminated composite material precast body of interlayer toughened.
On the basis of one-shot forming, if desired continue to increase the knitted textile layer constituting described laminated composite material precast body
Number, then the progressive mode of the braided fabric that successively adds up according to spun lacing principle employing, until it reaches required knitted textile layer
Number.
Beneficial effects of the present invention is embodied in:
Interlayer toughened laminated composite material structure and preparation method are improved by the present invention, and centre is covered with the layer of chopped fiber
Folded composite carries out spun lacing, by chopped fiber effect all directions in laminated composite material micro structure, makes stacking composite wood
Material produce interlayer XY to Z-direction chopped fiber, reduce between tradition stacking composite layer in toughing ways prefabricated simultaneously
The damage that the principal fibers of body causes.
The laminated composite material precast body more for the braided fabric number of plies uses successively cumulative toughness reinforcing mode, it is possible to increase
The interlayer toughened effect of precast body.
The present invention compared with prior art, has an advantage in that:
1) the interlayer toughened laminated composite material integrality performance of the structure that the present invention proposes is excellent, and its preparation method flow process
Clearly, succinctly, it is simple to industrialized production.
2) present invention carries out interlayer toughened based on spun lacing, when jet sprays behind laminated composite material precast body surface, penetrates
Stream can enter along fabric gap, improves toughening efficiency and resolution, utilizes jet that chopped fiber band is entered stacking and be combined
All directions in prefabricated bulk microstructure, make laminated composite material precast body produce interlayer XY to Z-direction chopped fiber,
Not only increase I mode Ⅱ fracture toughness of composite, II mode Ⅱ fracture toughness is also increased simultaneously, make material
Material possesses the ability of opposing I/II type mixing interlayer faults.
3) present invention interlayer toughened based on spun lacing method, compares the interlayer toughened method of tradition laminated composite material, does not has
Having the principal fibers to laminated composite material precast body produce rigid mechanical impact and repeatedly tear, therefore, the present invention is based on water
The interlayer toughened method of thorn can reduce the damage causing laminated composite material precast body.
Accompanying drawing explanation
Fig. 1 is the fabric construction schematic diagram being covered with interlaminar short fiber；
Fig. 2 is spun lacing systematic schematic diagram；
Fig. 3 is laminated composite material precast body spun lacing process schematic；
Fig. 4 is structural representation after laminated composite material precast body spun lacing interlayer toughened；
In figure: 1 is ground floor fabric, 2 is second layer fabric, and 3 is third layer fabric, and 4 is chopped fiber, and 5 is interlayer
Laying the laminated fabric of chopped fiber, 6 is intermediate gap, and 7 is the fine current of high pressure, and 8 is water needle head, and 9 is computer control
System processed, 10 is water pump, and 11 is water tank, and 12 is metal support net, and 13 is Z-direction link enhancement carbon fiber；A、B、
C is respectively the intermediate gap of the three, the two, one layer of fabric.
Detailed description of the invention
The present invention will be further described with embodiment below in conjunction with the accompanying drawings.
1) the spun lacing interlayer method for toughening of laminated composite material:
For the microstructure of stacking Carbon fibe precast body, as shown in Figure 1, it can be seen that stacking Carbon fibe precast body exists
Thickness direction exists and is made up of every layer of XY intermediate gap 6 at the principal fibers fiber of charcoal cloth (i.e. weave) intertexture
Passage, for typical communicating pipe porous media structure.
See Fig. 2, during when high pressure fine current 7 directive and through stacking Carbon fibe precast body, fluid and principal fibers and gold
Belong to torr net 12 to collide, agitate, multidirectional scattering occur, communicating pipe porous media structure is formed the distribution of multiple jet,
Fig. 3, it is shown that some staple fiber dimension 4 (carbon fibers) that charcoal cloth interlayer is laid issue in multidirectional jet action
Raw displacement, interspersed and obvolvent, simultaneously because the existence of intermediate gap 6, it is prefabricated that chopped fiber 4 can enter into stacking Carbon fibe
In B, C gap of body, form Z-direction link enhancement carbon fiber 13 (i.e. Z-direction interlayer connects chopped fiber), so that
Stacking Carbon fibe precast body becomes an entirety, improves the Z-direction interlayer bonding strength of stacking Carbon fibe precast body.Meanwhile,
Interlayer remains with XY to chopped fiber, and described XY is to the bearing of trend for charcoal cloth plane.
2) the spun lacing interlayer method for toughening towards laminated composite material realizes
1. in order to realize laminated composite material spun lacing method for toughening process, need to be by the spun lacing method towards laminated composite material
System, as in figure 2 it is shown, mainly include computer control system 9, water needle head 8, water tank 11, and high-pressure hydraulic pump 10.
2. as it is shown in figure 1, prepare chopped fiber (carbon fiber) in advance, before carrying out spun lacing and be toughness reinforcing, by chopped fiber with necessarily
The density (laying density of chopped fiber for example, 2～10g/m2.) uniform spreading is located at adjacent charcoal cloth interlayer, chopped fiber is permissible
It is that each interlayer is laid, or selects some interlayer to lay as required.With metal support net 12, stacking charcoal cloth is entered
Row clamping, in order to the realization of spun lacing process, ensures that the XY of charcoal cloth spun lacing is to uniform force simultaneously.
3. in laminated composite material spun lacing interlayer toughing ways, the spun lacing system shown in Fig. 2 is utilized, by fine for high pressure water
Flow 7 directive stacking Carbon fibe precast bodies, carry out spun lacing toughing ways.Spun lacing interlayer method for toughening at laminated composite material
In, by the microstructure after toughness reinforcing of the stacking Carbon fibe precast body spun lacing, as shown in Figure 4, it can be seen that at stacking charcoal
Adding Z-direction interlayer between layers in fiber preform structure and connect chopped fiber, these connect chopped fiber and make stacking
The generation between layers of charcoal cloth connects, and interlayer exists a number of XY to chopped fiber simultaneously.
4. in laminated composite material spun lacing interlayer toughing ways, if the charcoal cloth number of plies is more, layering spun lacing can be used
Mode, first carries out the spun lacing process of part number of plies charcoal cloth, adds remaining charcoal layer of cloth the most again and lays chopped fiber simultaneously, with
Improve the uniformity of spun lacing.
5. in the spun lacing interlayer method for toughening of laminated composite material, (liquid drugs injection is exactly the high pressure that water needle head penetrates to liquid drugs injection
Fine current) impact outermost charcoal cloth surface time, liquid drugs injection and fiber and ask net to collide, formation jet flow field, these
Jet to the active force of charcoal cloth with distance, jet pressure and the direction of water needle head to outermost charcoal cloth, and water needle head structure
The difference of parameter etc. and different, adjust these parameters and can change jet flow field distribution.
6. in the spun lacing interlayer method for toughening of laminated composite material, change interlayer and lay chopped fiber density, chopped fiber
Length and thickness and the braiding structure of charcoal cloth can change Z-direction interlayer in the microstructure of stacking Carbon fibe precast body
Connect distributed architecture and the quantity of chopped fiber, thus change the bonding strength that between Z-direction stacking charcoal cloth, interlayer connects.
3) the precast body application resin obtained after above-mentioned spun lacing interlayer toughened transmission curing is obtained interlayer toughened stacking
Composite.
4) applicating example and effect explanation
Select 4 layers of plain weave carbon cloth (eastern beautiful 3k carbon cloth) 0 ° of lay, each adjacent interlayer lay short carbon fiber, short
Carbon fiber length 5mm, diameter 6～10 μm, laying density is 2g/m2, spun lacing parameter: liquid drugs injection diameter d=0.1mm,
Spun lacing pressure P=1.5MPa, the liquid drugs injection speed of travel=5mm/s；Application above method obtains spun lacing toughness reinforcing stacking composite wood
Material precast body, finally application vacuum-assisted resin transfer method obtains the toughness reinforcing laminated composite material of spun lacing, and wherein resin is
EPOLAM 2040 epoxy resin (Lars company of Beijing section).
Test result indicate that: compared to directly mixing chopped fiber fluid and spray to the precast body method for toughening of stacking carbon cloth, this
Owing to there is a large amount of chopped fiber on the interlayer of precast body i.e. X/Y plane in method, and in terms of the fracture toughness of material, by
In the difference of cracks can spread mode, Z-direction fiber has directly work to I mode Ⅱ fracture toughness improving laminated composite material
Then obvious to improving II mode Ⅱ fracture toughness effect to chopped fiber with, XY, so while interlayer XY to Z-direction
Exist while chopped fiber, not only increase I mode Ⅱ fracture toughness of composite, simultaneously tough to II type interlayer faults
Property also increases, and enhances material fracture toughness under complex working condition, and the engineering adaptability making material is higher.
It is suitable for outside carbon removal cloth, prefabricated by the stacking that such as ramee, bamboo fibre or glass fibre are constituted
Body.Chopped fiber, in addition to using carbon fiber, also can use other fibers being used for increasing bonding strength, such as, glass fibers
Dimension, nylon fiber or Kafra fiber.
The present invention is directed in stacking braiding precast body the principal fibers gap (intermediate gap) in each layer of fabric and every layer
The typical communicating pipe porous media structure that the interlayer spacings of fabric is formed, utilizes high pressure fine current across-layer superimposing braid to knit pre-
Body processed, forms the distribution of various jet in communicating pipe porous media structure, and interlaminar short fiber issues in multidirectional jet action
Raw displacement, interspersed and obvolvent, simultaneously because the existence of intermediate gap, chopped fiber can enter in the gap of stacking precast body,
Form the reinforcing fiber that Z-direction connects, so that stacking braiding precast body becomes an entirety, improve stacking braiding pre-
The Z-direction interlayer bonding strength of body processed.
The spun lacing interlayer method for toughening that the present invention uses, compares the interlayer toughened method of tradition laminated composite material, the most right
The principal fibers of laminated composite material precast body produces rigid mechanical impact and repeatedly tears, therefore, and hydroentangled layer of the present invention
Between method for toughening can reduce the damage that laminated composite material precast body is caused.Due to interlayer XY to Z-direction chopped fiber
Existence, not only increase I mode Ⅱ fracture toughness of composite, II mode Ⅱ fracture toughness carried simultaneously
Height, makes material possess the ability of opposing I/II type mixing interlayer faults.
The present invention is by analyzing the spun lacing know-why of stacking composite preform, using spun lacing technology as interlayer toughened side
Method, builds the spun lacing interlayer method for toughening towards laminated composite material, on this basis, utilizes the fine current of high pressure by layer
Folded fabric interlaminar short fiber effect enters in the Z-direction gap of laminated composite material, it is achieved laminated composite material precast body spun lacing
Interlayer toughened process.
Claims (9)
1. an interlayer toughened laminated composite material, it is characterised in that: this composite includes that the stacking of interlayer toughened is multiple
Condensation material precast body, described laminated composite material precast body includes stacking braided fabric and is arranged in stacking braided fabric
XY to chopped fiber and Z-direction chopped fiber, described braided fabric the most successively lay, described XY is to chopped fiber
Being in all or part of braided fabric between adjacent two layers braided fabric uniformly, described Z-direction chopped fiber is in stacking and compiles
In the passage being made up of the intermediate gap of every layer of braided fabric in woven fabric, described Z-direction is to be perpendicular to braided fabric plane
Direction.
A kind of interlayer toughened laminated composite material, it is characterised in that: described braided fabric
Lay mode be 0 °, 45 ° ,-45 ° or 90 °, the braiding structure of braided fabric is selected from plain weave, twill or satin weave
Control of two-dimensional braided body.
A kind of interlayer toughened laminated composite material, it is characterised in that: described braided fabric
Kinds of fibers be carbon fiber, ramee, bamboo fibre or glass fibre, described XY is to the short fibre of chopped fiber and Z-direction
The kinds of fibers of dimension is carbon fiber, glass fibre, nylon fiber or Kafra fiber.
A kind of interlayer toughened laminated composite material, it is characterised in that: described XY is to short
2～5 times of the intermediate gap spacing of a length of described braided fabric of fiber and Z-direction chopped fiber, XY to chopped fiber with
And a diameter of 6～10 μm of Z-direction chopped fiber.
A kind of interlayer toughened laminated composite material, it is characterised in that: described composite
Also including solidifying resin matrix, solidification resin matrix is that described in homogeneous impregnation, the resin of laminated composite material precast body is solidified into
Type and formed.
6. the method preparing interlayer toughened laminated composite material as claimed in claim 1, it is characterised in that: include
Following steps:
1) in stacking braided fabric interlayer lay chopped fiber；
2) through step 1) after, with torr net, stacking braided fabric is clamped；
3) through step 2) after, stacking braided fabric is carried out spun lacing process, obtains precast body；
4) by precast body curing molding.
Method the most according to claim 6, it is characterised in that: described step 1) in, select corresponding braiding
Fabric types, and by certain angle stacking lay, during lay, the chopped fiber of certain density is laid in advance corresponding stacking
Braided fabric interlayer, needs to select whole interlayers of stacking braided fabric or part interlayer to lay short according to material property simultaneously
Fiber.
Method the most according to claim 6, it is characterised in that: it is by single water jet directive that described spun lacing processes
Stacking braided fabric, makes jet body collide with braided fabric and torr net, agitate, produces scattering, make interlaminar short fiber produce
Raw displacement, interspersed, obvolvent, and make some staple fiber dimension enter braided fabric intermediate gap, thus one-shot forming obtains interlayer
Toughness reinforcing laminated composite material precast body.
Method the most according to claim 8, it is characterised in that: on the basis of one-shot forming, if desired continue
Increase the braided fabric number of plies constituting described laminated composite material precast body, then use the progressive side of the braided fabric that successively adds up
Formula, until it reaches the required braided fabric number of plies.
Priority Applications (1)
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| CN107379363A (en) * | 2017-09-13 | 2017-11-24 | 温振刚 | The moulding process of Polymer concrete pipeline |
| CN107599273A (en) * | 2017-09-13 | 2018-01-19 | 山东省呈祥电工电气有限公司 | Enhancing by polymer Prestressed concrete cylinder pipe road moulding process |
| CN107696624A (en) * | 2017-10-11 | 2018-02-16 | 摩登大道时尚集团股份有限公司 | A kind of seamless suture texture with antibacterial functions |
| CN107754449A (en) * | 2017-10-21 | 2018-03-06 | 浙江华基环保科技有限公司 | A kind of complex nonwoven filtering material and preparation method thereof |
| CN107935430A (en) * | 2017-12-29 | 2018-04-20 | 长沙紫宸科技开发有限公司 | A kind of flexible fiber brambles rope for production of construction materials |
| CN112976610A (en) * | 2021-02-07 | 2021-06-18 | 西安交通大学 | Manufacturing method of carbon fiber column lattice truss sandwich structure |
| WO2022193591A1 (en) * | 2021-03-15 | 2022-09-22 | 江南大学 | Transversely woven fully formed helmet shell preform, preparation method, and helmet shell thereof |
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Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN107379363A (en) * | 2017-09-13 | 2017-11-24 | 温振刚 | The moulding process of Polymer concrete pipeline |
| CN107599273A (en) * | 2017-09-13 | 2018-01-19 | 山东省呈祥电工电气有限公司 | Enhancing by polymer Prestressed concrete cylinder pipe road moulding process |
| CN107379363B (en) * | 2017-09-13 | 2020-06-02 | 梁新业 | Forming process of polymer concrete pipeline |
| CN107696624A (en) * | 2017-10-11 | 2018-02-16 | 摩登大道时尚集团股份有限公司 | A kind of seamless suture texture with antibacterial functions |
| CN107754449A (en) * | 2017-10-21 | 2018-03-06 | 浙江华基环保科技有限公司 | A kind of complex nonwoven filtering material and preparation method thereof |
| CN107935430A (en) * | 2017-12-29 | 2018-04-20 | 长沙紫宸科技开发有限公司 | A kind of flexible fiber brambles rope for production of construction materials |
| CN112976610A (en) * | 2021-02-07 | 2021-06-18 | 西安交通大学 | Manufacturing method of carbon fiber column lattice truss sandwich structure |
| WO2022193591A1 (en) * | 2021-03-15 | 2022-09-22 | 江南大学 | Transversely woven fully formed helmet shell preform, preparation method, and helmet shell thereof |
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