CN108544766A - A kind of carbon fibre composite Wing structure and its it is coated with forming method - Google Patents
A kind of carbon fibre composite Wing structure and its it is coated with forming method Download PDFInfo
- Publication number
- CN108544766A CN108544766A CN201810239429.4A CN201810239429A CN108544766A CN 108544766 A CN108544766 A CN 108544766A CN 201810239429 A CN201810239429 A CN 201810239429A CN 108544766 A CN108544766 A CN 108544766A
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- China
- Prior art keywords
- fender
- coated
- carbon fibre
- fibre composite
- ontology
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- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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Classifications
-
- 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
- B29C70/342—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 using isostatic pressure
-
- 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
- B29C70/06—Fibrous reinforcements only
- B29C70/10—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres
- B29C70/16—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres using fibres of substantial or continuous length
- B29C70/22—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres using fibres of substantial or continuous length oriented in at least two directions forming a two dimensional structure
- B29C70/228—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres using fibres of substantial or continuous length oriented in at least two directions forming a two dimensional structure the structure being stacked in parallel layers with fibres of adjacent layers crossing at substantial angles
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29L—INDEXING SCHEME ASSOCIATED WITH SUBCLASS B29C, RELATING TO PARTICULAR ARTICLES
- B29L2031/00—Other particular articles
- B29L2031/30—Vehicles, e.g. ships or aircraft, or body parts thereof
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Composite Materials (AREA)
- Mechanical Engineering (AREA)
- Textile Engineering (AREA)
- Laminated Bodies (AREA)
- Reinforced Plastic Materials (AREA)
- Moulding By Coating Moulds (AREA)
Abstract
The invention discloses a kind of carbon fibre composite Wing structure and its it is coated with forming method, it is characterised in that：Wing structure includes fender ontology, and one end is connected with fender mounting base on the fender ontology, is equipped with fender accessory mounting plate with equipped with the opposite a side in fender mounting base one end, fender is equipped on the fender ontology and reinforces area.Carbon fibre composite Wing structure of the present invention and its it is coated with forming method, Wing structure meets performance requirements, lightweight requirements, actual operation requirements and moulding process requirement, and the fender produced is specifically light-weight, and intensity is high, it is corrosion-resistant, it is damping good the advantages that.Using autoclave forming process, the carbon fiber product of higher quality and performance has been obtained, conventional metals fender has been compared using the fender of this method production, light weight effect is apparent, has preferable application prospect.
Description
Technical field
The invention belongs to automobile technical field, more specifically to a kind of carbon fibre composite Wing structure and
It is coated with forming method.
Background technology
As environmental issue and energy problem are more and more prominent, automotive light weight technology design has become more and more important.Vapour
Vehicle light-weight design can improve power performance, economy, the feature of environmental protection, comfort.Carbon fibre composite is due to its lightweight
The features such as high-strength, corrosion-resistant, antifatigue, designability is strong, it has also become the critical material of automotive light weight technology design alternative；But it is common
The carbon fibre composite fender of technique is unsatisfactory for intensity requirement, therefore one kind is needed reasonably to be coated with forming method to meet production
Product resist recessed strength and stiffness requirement.
Invention content
Present invention aim to address problems of the existing technology, provide a kind of structural strength height, performance is good, lightweight
Carbon fibre composite Wing structure and its be coated with forming method.
To achieve the goals above, the technical solution that the present invention takes is：This carbon fibre composite wing provided
Daughter board structure, including fender ontology, one end is connected with fender mounting base on the fender ontology, and equipped with wing
The opposite a side in plate mounting base one end is equipped with fender accessory mounting plate, and fender is equipped on the fender ontology and is reinforced
Area.
To keep above-mentioned technical proposal more detailed and specific, the present invention also provides optimization technique sides further below
Case, to obtain satisfied practical function：
The fender ontology, fender accessory mounting plate and fender mounting base are all made of carbon fibre composite system
At the fender accessory mounting plate and fender mounting base are fixed on by gluing knot mode on the fender ontology.
Carbon fibre composite Wing structure is coated with forming method, which is characterized in that includes the following steps：
1) prepare carbon fibre composite prepreg；
2) prepreg is cut and integral is coated with shape；Mold pre-treatment；
3) the prepreg layering after cutting is coated on mould surface from level to level；
4) outside is coated with vacuum bag, vacuumize process after prepreg is coated with；
5) whole after being coated with to be sent into autoclave heat-pressure curing；
6) cooling and demolding is handled；
7) by step 1) to daughter board ontology, fender accessory mounting plate and fender mounting base 6) is produced, by fender
Accessory mounting plate and fender mounting base gluing knot are fixed on fender ontology.
- 0.1Mpa is evacuated in step 4).
Step 5) hot pressing pressure tank is 0.4-0.6Mpa, heats 70-90 DEG C and maintains 30 minutes, then is warming up to 120-140 DEG C
It maintains 120 minutes.
Compared with prior art, the present invention haing the following advantages：Carbon fibre composite Wing structure of the present invention and its
It is coated with forming method, Wing structure, which meets performance requirements, lightweight requirements, actual operation requirements and moulding process, to be wanted
Ask, the fender produced is specifically light-weight, and intensity is high, corrosion-resistant, it is damping good the advantages that.Using autoclave forming process,
The carbon fiber product of higher quality and performance has been obtained, conventional metals fender has been compared using the fender of this method production, gently
Quantification effect is apparent, has preferable application prospect.
Description of the drawings
The content expressed by the attached drawing to this specification and the label in figure are briefly described below：
Fig. 1 is carbon fibre composite Wing structure schematic diagram of the present invention；
Fig. 2 is fender mounting base structural schematic diagram of the present invention；
Fig. 3 is fender accessory mounting plate structural schematic diagram of the present invention；
Fig. 4 is that fender ontology of the present invention and fender reinforcement area's laying are successively decreased schematic diagram；
Fig. 5 is carbon fibre composite fender forming parts process flow chart.
In figure label for：1, fender ontology, 2, fender reinforce area, 3, fender mounting base, 4, fender auxiliary peace
Loading board.
Specific implementation mode
Below against attached drawing, by the description of the embodiment, making to the specific implementation mode of the present invention further details of
Explanation.
Carbon fibre composite Wing structure of the present invention, as shown in Figure 1, including fender ontology 1, fender ontology 1
Upper one end is connected with fender mounting base 3, pacifies with fender auxiliary is equipped with equipped with the opposite a side in 3 one end of fender mounting base
Loading board 4 is equipped with fender reinforcement area 2 on fender ontology 1.Fender in carbon fibre composite Wing structure of the present invention
Ontology 1, fender accessory mounting plate 4 and fender mounting base 3 are all made of carbon fibre composite and are made.
Carbon fibre composite Wing structure of the present invention is coated with forming method, and step as shown in Figure 5 prepares carbon fiber
Material prepreg；Prepreg is cut into and is coated with shape；Mold pre-treatment；Prepreg layering after cutting is spread from level to level
It overlays on mould surface；Outside is coated with vacuum bag, vacuumize process after prepreg is coated with；Whole autoclave of being sent into adds after being coated with
Hot cure under pressure；Cooling and demolding processing；Fender ontology 1, fender auxiliary installation in carbon fibre composite Wing structure
Plate 4 and fender mounting base 3 are all made of carbon fibre composite and are made by above-mentioned steps, fender accessory mounting plate 4 and wing
Plate mounting base 3 is fixed on by gluing knot mode on fender ontology 1.Fender ontology 1, fender accessory mounting plate 4 and the wing
Its material of daughter board mounting base 3 is all made of carbon fiber prepreg by different angle laying, is molded using autoclave process
Structure, production process use automatic blanking machine fabric dividing, and manual laying, good product quality, performance are high.
In the present invention, each part is coated with using middle layer as symmetrical centre both sides laying angle symmetrical.
- 0.1Mpa is evacuated in step 4).
Step 5) hot pressing pressure tank is 0.4-0.6Mpa, heats 70-90 DEG C and maintains 30 minutes, then is warming up to 120-140 DEG C
It maintains 120 minutes.Autoclave forming process, high temperature, the molding of the high pressure field of force, product quality and performance higher.In entire curing time
Between, to ensure Product Process stability and lasting monitoring, the measuring temperature time interval for recording each thermocouple is no more than 10 points
Clock.
Carbon fibre composite Wing structure of the present invention, fender ontology 1 are reinforced needing laying to mend at area 2 with fender
By force, laying is done according to the design principle of laminate transition region to successively decrease.
Fender mounting base 3 is fixed on using gluing knot mode on fender ontology 1 with fender accessory mounting plate 4.It adopts
The Wing structure made of this method compares conventional metals fender, and 45% or more loss of weight, light weight effect is apparent.
The present invention provides a kind of composition embodiment of carbon fibre composite Wing structure.
Fender ontology 1 is coated with 12 layers, and wherein carbon fiber prepreg one-way tape thickness in monolayer is 0.145mm, 11 layers；Carbon fiber
Tie up plain weave prepreg woven cloth thickness in monolayer 0.21mm, 1 layer, total 1.805mm.
0 ° of direction is coated with 4 layers, accounts for total layer：33.33%.
45 ° of directions are coated with 2 layers, account for total layer：16.67%.
- 45 ° of directions are coated with 2 layers, account for total layer：16.67%.
90 ° of directions are coated with 3 layers, account for total layer：25%.
0/90 ° of direction Woven glass cloth is coated with 1 layer, accounts for total layer：8.33%.
Fender reinforced region 2 is coated with 17 layers, and wherein carbon fiber prepreg one-way tape thickness in monolayer is 0.145mm, 16 layers；
Carbon fiber plain weave prepreg woven cloth thickness in monolayer 0.21mm, 1 layer, total 2.53mm.
0 ° of direction is coated with 4 layers, accounts for total layer：23.53%.
45 ° of directions are coated with 4 layers, account for total layer：23.53%.
- 45 ° of directions are coated with 4 layers, account for total layer：23.53%.
90 ° of directions are coated with 4 layers, account for total layer：23.53%.
0/90 ° of direction Woven glass cloth is coated with 1 layer, accounts for total layer：5.88%.
Fig. 4 is that fender ontology and fender reinforce area's laying and successively decrease schematic diagram, and it is 17 floor, wing that fender, which reinforces area 2,
Plate ontology 1 is 12 layers, and fender reinforces area 2 to 1 transition junction of fender ontology and successively decreases laying in step type, as far as possible uniformly
It is distributed the layer that successively decreases.Table 1 is that fender ontology 1 reinforces the distribution of 2 each floor of area, laying angle and thickness with fender.
Fender ontology (1) and fender reinforced region (2)
Table 1
Fig. 2 is fender mounting base structural schematic diagram, and fender mounting base 3 is coated with 14 layers, wherein carbon fibre initial rinse material list
To band thickness in monolayer be 0.145mm, 14 layers, total 2.03mm.
0 ° of direction is coated with 4 layers, accounts for total layer：28.57%.
45 ° of directions are coated with 4 layers, account for total layer：28.57%.
- 45 ° of directions are coated with 4 layers, account for total layer：28.57%.
90 ° of directions are coated with 2 layers, account for total layer：14.29%.
Table 2 is that the present embodiment fender mounting base 3 is paved into each layer angle and thickness.
Fender mounting base (3)
Table 2
Fig. 3 is that fender accessory mounting plate fender accessory mounting plate 4 is coated with 12 layers, wherein carbon fiber prepreg one-way tape
Thickness in monolayer is 0.145mm, 12 layers, total 1.74mm.
0 ° of direction is coated with 6 layers, accounts for total layer：50%.
45 ° of directions are coated with 2 layers, account for total layer：16.67%.
- 45 ° of directions are coated with 2 layers, account for total layer：16.67%.
90 ° of directions are coated with 2 layers, account for total layer：16.67%.
Fender accessory mounting plate
Table 3
Carbon fibre composite Wing structure of the present invention and its it is coated with forming method, during laying, using entirety
Be coated with, i.e., by prepreg cut it is integral be coated with shape, set on paving face 1 and be coated with origin 3 and be coated with direction 4, by setting
It is coated with angle and carries out laying.Entirety, which is coated with, follows laying angle symmetry principle as far as possible, it then follows ± 45 ° principle occur in pairs, abide by
Follow equidirectional layer number avoids product from deforming and turn round no more than 60% principle of total number of plies to enhance reinforcing plate structural strength
The defects of bent.
It is that patch die face is coated with 1 outer surface of fender ontology, that layer contacted with metal die is patch die face；With
Fender outermost boundary is coated with boundary extension 5mm again as engineering boundary, for ease of later-stage secondary processing, is technique boundary.
Piece surface builds out coordinate origin.Fender ontology 1 and fender mounting base 3 are axial for 0 ° of side of being coated with fender ontology 1
To fender accessory mounting plate 4 is coated with direction using fender accessory mounting plate 4Z to as 0 °.Using automatic blanking machine fabric dividing,
Manual laying, using prepreg die press technology for forming, autoclave forming process, high temperature, the molding of the high pressure field of force, product quality and property
It can higher.
Operating mode and performance requirement are actually used according to fender, the general norm of material Lay up design is answered in conjunction with carbon fiber, is needed
It is designed to isotropism.Meeting performance requirements, lightweight requirements, actual operation requirements and molding work by CAE analysis
In the case that skill requires, and meet the electrochemical corrosion requirement of surface and metalwork, product is avoided to deform and distort
Defect is coated with using whole.
Carbon fibre composite Wing structure of the present invention and its it is coated with forming method, Wing structure meets properties
It is required that, lightweight requirements, actual operation requirements and moulding process requirement, the fender produced is specifically light-weight, and intensity is high, resistance to
Corrosion, it is damping good the advantages that.Using autoclave forming process, the carbon fiber product of higher quality and performance has been obtained, has been used
The fender of this method production compares conventional metals fender, and 45% or more loss of weight, light weight effect is apparent, has and preferably answers
Use foreground.
Above in conjunction with attached drawing, the present invention is exemplarily described, it is clear that the present invention implements not by above-mentioned side
The limitation of formula, if the improvement of the various unsubstantialities of inventive concept and technical scheme of the present invention progress is used, or without
It improves and the design of the present invention and technical solution is directly applied into other occasions, within protection scope of the present invention.
Claims (5)
1. a kind of carbon fibre composite Wing structure, it is characterised in that：Including fender ontology, on the fender ontology
One end is connected with fender mounting base, pacifies with fender auxiliary is equipped with equipped with the opposite a side in fender mounting base one end
Loading board is equipped with fender reinforcement area on the fender ontology.
2. carbon fibre composite Wing structure described in accordance with the claim 1, it is characterised in that：The fender ontology,
Fender accessory mounting plate and fender mounting base are all made of carbon fibre composite and are made, the fender accessory mounting plate and
Fender mounting base is fixed on by gluing knot mode on the fender ontology.
3. a kind of carbon fibre composite Wing structure as claimed in claim 2 is coated with forming method, which is characterized in that packet
Include following steps：
1) prepare carbon fibre composite prepreg；
2) prepreg is cut and integral is coated with shape；Mold pre-treatment；
3) the prepreg layering after cutting is coated on mould surface from level to level；
4) outside is coated with vacuum bag, vacuumize process after prepreg is coated with；
5) whole after being coated with to be sent into autoclave heat-pressure curing；
6) cooling and demolding is handled；
7) fender is assisted to daughter board ontology, fender accessory mounting plate and fender mounting base 6) is produced by step 1)
Mounting plate and fender mounting base gluing knot are fixed on fender ontology.
4. carbon fibre composite Wing structure described in accordance with the claim 3 is coated with forming method, it is characterised in that：Step
4) -0.1Mpa is evacuated in.
5. carbon fibre composite Wing structure is coated with forming method according to claim 4, it is characterised in that：Step
5) hot pressing pressure tank is 0.4-0.6Mpa, heats 70-90 DEG C and maintains 30 minutes, then is warming up to 120-140 DEG C and maintains 120 minutes.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810239429.4A CN108544766A (en) | 2018-03-22 | 2018-03-22 | A kind of carbon fibre composite Wing structure and its it is coated with forming method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810239429.4A CN108544766A (en) | 2018-03-22 | 2018-03-22 | A kind of carbon fibre composite Wing structure and its it is coated with forming method |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN108544766A true CN108544766A (en) | 2018-09-18 |
Family
ID=63516990
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810239429.4A Pending CN108544766A (en) | 2018-03-22 | 2018-03-22 | A kind of carbon fibre composite Wing structure and its it is coated with forming method |
Country Status (1)
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| CN (1) | CN108544766A (en) |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110920643A (en) * | 2019-12-18 | 2020-03-27 | 常州市新创智能科技有限公司 | Plate body structure for guide plate |
| CN111055928A (en) * | 2019-11-29 | 2020-04-24 | 中国第一汽车股份有限公司 | Novel carbon fiber material fender and flagpole fixed knot construct |
| CN112123805A (en) * | 2020-08-27 | 2020-12-25 | 常州启赋安泰复合材料科技有限公司 | Paving and forming method of composite fender with safety protection function |
| CN113858652A (en) * | 2021-08-26 | 2021-12-31 | 中航复合材料有限责任公司 | Edge covering structure and process without folds for composite material skirt board of railway vehicle equipment compartment |
| CN114643678A (en) * | 2020-12-17 | 2022-06-21 | 东风(十堰)林泓汽车配套件有限公司 | Production method of vehicle fender |
| CN117428631A (en) * | 2023-11-23 | 2024-01-23 | 浙江铭博汽车部件股份有限公司 | Manufacturing method of high-strength light-weight vehicle fender |
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| CN106584882A (en) * | 2016-11-29 | 2017-04-26 | 中广核俊尔新材料有限公司 | High-speed motor car equipment compartment beam made of carbon fiber composite and manufacturing method of high-speed motor car equipment compartment beam |
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| CN111055928A (en) * | 2019-11-29 | 2020-04-24 | 中国第一汽车股份有限公司 | Novel carbon fiber material fender and flagpole fixed knot construct |
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| CN112123805A (en) * | 2020-08-27 | 2020-12-25 | 常州启赋安泰复合材料科技有限公司 | Paving and forming method of composite fender with safety protection function |
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| CN113858652A (en) * | 2021-08-26 | 2021-12-31 | 中航复合材料有限责任公司 | Edge covering structure and process without folds for composite material skirt board of railway vehicle equipment compartment |
| CN113858652B (en) * | 2021-08-26 | 2023-06-16 | 中航复合材料有限责任公司 | Non-fold edge wrapping structure and process for composite material apron board of equipment compartment of railway vehicle |
| CN117428631A (en) * | 2023-11-23 | 2024-01-23 | 浙江铭博汽车部件股份有限公司 | Manufacturing method of high-strength light-weight vehicle fender |
| CN117428631B (en) * | 2023-11-23 | 2024-04-02 | 浙江铭博汽车部件股份有限公司 | Manufacturing method of high-strength light-weight vehicle fender |
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Application publication date: 20180918 |