CN110524910A - A kind of VARTM technique composite material mould and its manufacturing method - Google Patents
A kind of VARTM technique composite material mould and its manufacturing method Download PDFInfo
- Publication number
- CN110524910A CN110524910A CN201910864824.6A CN201910864824A CN110524910A CN 110524910 A CN110524910 A CN 110524910A CN 201910864824 A CN201910864824 A CN 201910864824A CN 110524910 A CN110524910 A CN 110524910A
- Authority
- CN
- China
- Prior art keywords
- composite material
- panel
- support unit
- material mould
- bearing rib
- Prior art date
- 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.)
- Pending
Links
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
- B29C70/40—Shaping or impregnating by compression not applied
- B29C70/42—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles
- B29C70/46—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles using matched moulds, e.g. for deforming sheet moulding compounds [SMC] or prepregs
- B29C70/48—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles using matched moulds, e.g. for deforming sheet moulding compounds [SMC] or prepregs and impregnating the reinforcements in the closed mould, e.g. resin transfer moulding [RTM], e.g. by vacuum
-
- 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
Landscapes
- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Composite Materials (AREA)
- Mechanical Engineering (AREA)
- Moulding By Coating Moulds (AREA)
- Laminated Bodies (AREA)
Abstract
The invention discloses a kind of VARTM technique composite material moulds and preparation method thereof, belong to composite material mould field.VARTM technique composite material mould preparation method of the present invention, support frame is separately manufactured with panel, entirety is connected to become using mechanical means, so as to greatly shorten mold manufacturing time, and mold installation, convenient disassembly, the demand that regular change mold design is needed especially suitable for large product design initial stage, has saved time, cost and parking space.Composite material mould of the present invention, support unit length is adjustable, and size is unrestricted, is particularly suitable for VARTM technique and prepares large-scale composite material component.The advantages such as molding is simple in addition, the mold also has, convenient disassembly, and manufacturing cost is low.
Description
Technical field
The invention belongs to composite material mould field, in particular to a kind of VARTM technique composite material mould and its system
Preparation Method.
Background technique
VARTM(vacuum assisted resin transfer molding) it is a kind of for producing the laminated of fibre reinforced plastics (FRP) product
Technique, such process requirement are laid with form in die surface.VARTM is often metal die and composite material mould with mold
Tool.Traditional metal die precision height, dimensionally stable, service life are long, but its manufacturing cycle is long, at high cost, and weight is larger, installation
Transport difficult.Common composite material mould generally uses hand pasting forming, and integrated support skeleton is built in forming process and guarantees mould
Has rigidity, hand paste has the frp layer of reinforcing rib on skeleton, forms after solidification by surface finish work.But hand paste process
Time is longer, die surface state unsightly, and form rear mold former material can not dismantle recycling.
Summary of the invention
Technical problem to be solved by the invention is to provide a kind of VARTM composite material mould and its manufacturing methods.
In order to solve the above technical problems, the invention adopts the following technical scheme:
A kind of VARTM technique composite material mould preparation method, step include:
1) braced frame is prepared comprising two longitudinal stocks；
2) according to composite element shape, fiber-reinforced resin matrix compound material panel is prepared；
3) support unit is prepared, by two bearing ribs and no less than two connecting shafts are constituted；The bearing rib, by fiber
Reinforced resin based composites are made, and upper surface is matched with panel lower surface, and thickness direction is provided with through-hole；The connecting shaft is put
It is placed in the corresponding through-hole of two bearing rib thickness directions, for adjusting and fixing the relative position of the two；
4) according to composite element size and weight, the spacing of support unit quantity and its two bearing ribs is determined；
5) longitudinal stock of placement braced frame, installation support unit, bearing rib and braced frame is removably
It is fixedly connected；Panel is placed on above support unit, and is removably fixedly connected with bearing rib；
6) surface encapsulation layer is prepared in panel surface.
VARTM technique composite material mould preparation method of the present invention, it is characterised in that: the adjacent supports list
Member shares a bearing rib, and the connecting shaft of each support unit is no less than three.
VARTM technique composite material mould preparation method of the present invention, it is characterised in that: the panel is by muti-piece
The splicing of fiber-reinforced resin matrix compound material plate is made, stitching portion encapsulation process.
VARTM technique composite material mould preparation method of the present invention, it is characterised in that: the bearing rib by
Upper and lower piecemeal is made.
VARTM technique composite material mould preparation method of the present invention, it is characterised in that: described to prepare supporting rib
Fibre reinforced materials used in plate (2) and panel (4) includes carbon fiber, glass fibre and aramid fiber.
Composite material mould of the present invention, including panel and support frame, it is characterised in that: further include face seal
Layer；The support frame is mainly made of braced frame and at least one support unit；The braced frame includes two longitudinal directions
Stock；The support unit, by two bearing ribs and no less than two connecting shafts are constituted；The bearing rib, is increased by fiber
Strong polymer matrix composites are made, and upper surface is matched with panel lower surface, and thickness direction is provided with through-hole；The connecting shaft is placed
In the corresponding through-hole of two bearing rib thickness directions, for adjusting and fixing the relative position of the two；The panel is by fibre
Dimension reinforced resin based composites are made；The support unit between braced frame and panel, bearing rib respectively with
Longitudinal stock of braced frame is removably fixedly connected with panel.
Composite material mould of the present invention, it is characterised in that: one bearing rib of the adjacent supports units shared,
The connecting shaft of each support unit is no less than three.
Composite material mould of the present invention, it is characterised in that: the panel (4) is split type structure.
Composite material mould of the present invention, it is characterised in that: the bearing rib (2) is two-piece unit formula structure.
VARTM technique composite material mould preparation method of the present invention, support frame is separately manufactured with panel,
Entirety is connected to become using mechanical means, it is special so as to greatly shorten mold manufacturing time, and mold installation, convenient disassembly
The demand that regular change mold design Shi Yongyu not be needed large product design initial stage, it is empty to have saved time, cost and storage
Between.Composite material mould of the present invention, support unit length is adjustable, and size is unrestricted, is particularly suitable for VARTM technique
Prepare large-scale composite material component.The advantages such as molding is simple in addition, the mold also has, convenient disassembly, and manufacturing cost is low.
Detailed description of the invention
Composite material mould structural schematic diagram in Fig. 1 first embodiment of the invention
Fig. 2 connecting axle structure schematic diagram
Composite material mould structural schematic diagram in Fig. 3 second embodiment of the invention
Bearing rib structural schematic diagram in Fig. 4 second embodiment of the invention
Bearing rib structural schematic diagram in Fig. 5 third embodiment of the invention
Wherein: 1- braced frame, 2- bearing rib, 3- connecting shaft, 4- panel, 5- surface encapsulation layer.
Specific embodiment
Invention will be further described below with reference to example, but not as to the present invention relates to the limits of technical solution
System.
Embodiment 1
The composite material mould of the present embodiment, as shown in Figure 1, including braced frame 1, support unit, panel 4 and surface encapsulation layer
5.Braced frame 1 is an integral structure, long 5.3m, wide 2m, is formed by two vertical four horizontal six roots of sensation square steel pipe weldeds, wherein longitudinal
Steel pipe is placed on the top of lateral steel pipe, and steel pipe is uniformly distributed along longitudinal direction for lateral steel pipe, and longitudinal steel pipe is located at the both ends of lateral steel pipe.
Support unit is made of two bearing ribs 2 and three connecting shafts 3.Bearing rib 2, by the epoxy resin of 20mm thickness
Base carbon fibre enhancing composite panel is made, and the bottom face profile of end shape and panel 4 matches, in its two sides and interposition
It sets, through-thickness respectively opens a through-hole, respectively opens the square groove of 60mm × 60mm in its two sides lower end.Connecting shaft 3 is by a spiral shell
Line steel pipe and four fastening nut compositions, as shown in Fig. 2, screw-thread steel pipe range 700mm, thread segment is arranged in both ends, respectively long 50mm.
In support unit, two 2 spacing of bearing rib are 480mm, and the fixed company of connecting shaft 3 of left, center, right is located at by three
It connects.
Panel 4 is an integral structure, and is 15mm thickness epoxy resin-matrix glass fibre reinforced composion, upper surface and need
Composite element lower surface is prepared to match.
Surface encapsulation layer 5 is 3mm thickness carbamide paint.
The composite material mould of the present embodiment, including 8 support units.Braced frame 1 is placed in the bottom；8 supports
Unit is distributed in the top of braced frame 1, and the longitudinal rod of braced frame 1 passes through in the square groove of 2 lower end two sides of bearing rib；Face
Plate 4 is placed on above support unit, is fixedly connected by metal connecting piece with bearing rib 2；Surface encapsulation layer 5 is located at panel 4
Upper surface.
Manufacturing the present embodiment composite material mould, specific step is as follows:
1) braced frame 1 is built.The square steel tube for choosing 60mm × 60mm is prepared into two root long 5.3m, and the stock of four root long 2m will
Four lateral stocks uniformly arrange placement, wherein the outer wall spacing 5.3m of two end transverse direction stocks, longitudinal stock are placed on transverse direction
Braced frame 1 is made by welding in the top of stock, two outer wall spacing 2m.
2) according to composite element shape need to be prepared, by the thick 15mm's being prepared by epoxy resin and glass fibre
Composite panel is cut to panel 4, and installation cone shaped countersink is reserved in face.
3) it is prepared into the composite material flat plate of thick 20mm by epoxy resin and carbon fiber, according to 4 underside shape of panel, cuts out
Composite material flat plate is cut, bearing rib 2, the reserved installation cone shaped countersink of thickness direction are prepared into；In its two sides and middle position, edge
Thickness direction respectively opens a through-hole.
4) support unit is prepared.Three connecting shafts 3 are individually positioned between two bearing ribs 2 in corresponding through-hole,
By adjusting the fastening nut at 3 both ends of connecting shaft, making the distance between two bearing ribs 2 is 480mm.Preparation 8 same branch
Support unit.
5) 8 support units are distributed in 1 top of braced frame, the longitudinal rod of braced frame 1 passes through 2 lower end of bearing rib
In the square groove of two sides.Support unit is bolted with braced frame 1.
6) panel 4 is placed on above support unit, passes through L-type metal connecting piece and reserved installation cone shaped countersink and branch
Support gusset 2 links together.
7) surface encapsulation layer 5 is prepared.Entire 4 upper surface of panel sprays 3mm thickness carbamide paint, is surface encapsulation layer after solidification
5, then complete the preparation of the present embodiment composite material mould.
Embodiment 2
The composite material mould of the present embodiment, as shown in figure 3, including braced frame 1, support unit, panel 4 and surface encapsulation layer
5。
Braced frame 1 is an integral structure, long 5m, wide 2m, is formed by connecting by two vertical four horizontal six roots of sensation angle steel bolt of long stem,
In, sole bar angle stock is placed on the top of lateral angle steel stock, and angle steel stock is uniformly distributed along longitudinal direction for lateral angle steel stock, longitudinal angle
Steel stock is located at the both ends of lateral angle steel stock.
Support unit difference from Example 1 is: the two sides and middle position of bearing rib 2, through-thickness are each
Through-hole there are two opening, the wheelbase 20mm of the two through hole, as shown in Figure 4；Three connecting shafts 3, respectively by 2 two sides of bearing rib and
The through-hole in middle position connects two bearing ribs 2.
Panel 4 is split type structure, is composed of eight pieces of 20mm thickness resin base glass fibre reinforced composite materials, upper surface
Match with composite element lower surface need to be prepared.
Surface encapsulation layer 5 is 2mm thickness vinyl esters gel coating resin.
The composite material mould of the present embodiment, one bearing rib 2 of adjacent supports units shared.
The step difference from Example 1 of manufacture the present embodiment composite material mould is:
After eight pieces of panels 4 are connect by metal connecting piece with bearing rib 2 respectively, epoxy sealing is used in 4 stitching portion of panel
Gluing knot fills and leads up processing；Solidification rear surface processing is smooth and sprays vinyl esters gel coating resin, forms surface encapsulation layer after solidification
5；Check its air-tightness, i.e. the composite material mould for being suitable for the application of VARTM technique is completed in preparation after air-tightness is up to standard.
Embodiment 3
Difference from Example 1 is: bearing rib 2 is made of upper and lower two parts, and the two is by thinly metallic plane and bolt
Connection, as shown in Figure 5.
The composite material mould of the present embodiment is not necessarily to when forming the composite element of different structure by bearing rib 2
All replacements need to only replace its top half, so as to play the purpose for saving material.
Embodiment 4
Difference from Example 1 is: bearing rib 2 is Varying-thickness structure, progressive additive from top to bottom, thus increase its with
The bonding strength of braced frame 1.
Claims (9)
1. a kind of VARTM technique composite material mould preparation method, step include:
1) braced frame (1) is prepared comprising two longitudinal stocks；
2) according to composite element shape, fiber-reinforced resin matrix compound material panel (4) are prepared；
3) support unit is prepared, by two bearing ribs (2) and no less than two connecting shafts (3) are constituted；The bearing rib
(2), it is made of fiber-reinforced resin matrix compound material, upper surface is matched with panel (4) lower surface, and thickness direction is provided with logical
Hole；The connecting shaft (3) is placed in the corresponding through-hole of two bearing rib (2) thickness directions, for adjusting and fixing the two
Relative position；
4) according to composite element size and weight, the spacing of support unit quantity and its two bearing ribs (2) is determined；
5) braced frame (1) is placed, support unit is installed, longitudinal stock of bearing rib (2) and braced frame (1) is with removable
The mode unloaded is fixedly connected；Panel (4) is placed on above support unit, and removably solid with bearing rib (2)
Fixed connection；
6) surface encapsulation layer (5) are prepared on panel (4) surface.
2. VARTM technique composite material mould preparation method according to claim 1, it is characterised in that: described adjacent
Support unit shares a bearing rib (2), and the connecting shaft (3) of each support unit is no less than three.
3. VARTM technique composite material mould preparation method according to claim 1, it is characterised in that: the panel
(4) it is made of the splicing of muti-piece fiber-reinforced resin matrix compound material plate, stitching portion encapsulation process.
4. VARTM technique composite material mould preparation method according to claim 1, it is characterised in that: the support
Gusset (2) is made of upper and lower piecemeal.
5. VARTM technique composite material mould preparation method according to claim 1, it is characterised in that: the preparation
Fibre reinforced materials used in bearing rib (2) and panel (4) includes carbon fiber, glass fibre and aramid fiber.
6. the composite material mould that one kind is prepared method according to claim 1, including panel and support frame, feature exist
In: it further include surface encapsulation layer (5)；The support frame is mainly made of braced frame (1) and at least one support unit；Institute
Stating braced frame (1) includes two longitudinal stocks；The support unit is connected by two bearing ribs (2) and no less than two
Axis (3) is constituted；The bearing rib (2), is made of fiber-reinforced resin matrix compound material, upper surface and panel (4) following table
Face matching, thickness direction are provided with through-hole；The connecting shaft (3) is placed in the corresponding through-hole of two bearing rib (2) thickness directions
In, for adjusting and fixing the relative position of the two；；The panel (4) is made of fiber-reinforced resin matrix compound material；It is described
Support unit is located between braced frame (1) and panel (4), bearing rib (2) longitudinal stock with braced frame (1) respectively
It is removably fixedly connected with panel (4).
7. the composite material mould of method preparation according to claim 6, it is characterised in that: the adjacent supports units shared
The connecting shaft (3) of one bearing rib (2), each support unit is no less than three.
8. the composite material mould of method preparation according to claim 6, it is characterised in that: the panel (4) is split type
Structure.
9. the composite material mould of method preparation according to claim 6, it is characterised in that: the bearing rib (2) is upper
Lower split type structure.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910864824.6A CN110524910A (en) | 2019-09-09 | 2019-09-09 | A kind of VARTM technique composite material mould and its manufacturing method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910864824.6A CN110524910A (en) | 2019-09-09 | 2019-09-09 | A kind of VARTM technique composite material mould and its manufacturing method |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN110524910A true CN110524910A (en) | 2019-12-03 |
Family
ID=68668542
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910864824.6A Pending CN110524910A (en) | 2019-09-09 | 2019-09-09 | A kind of VARTM technique composite material mould and its manufacturing method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN110524910A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113021955A (en) * | 2021-02-04 | 2021-06-25 | 浙江吉利控股集团有限公司 | Forming die of composite beam and manufacturing method of composite beam |
| CN114800958A (en) * | 2022-04-28 | 2022-07-29 | 宁波曙翔新材料股份有限公司 | Large-scale composite product forming die |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2847712A (en) * | 1952-11-10 | 1958-08-19 | Bristol Aircraft Ltd | Method of molding ribbed structures from thermosetting resin and fibrous material |
| CN101232985A (en) * | 2005-07-27 | 2008-07-30 | 三菱重工业株式会社 | RTM process |
| CN101448631A (en) * | 2006-03-20 | 2009-06-03 | 欧洲航空防务及航天公司Eads法国 | Method of producing stiffened panels made of a composite and panels thus produced |
| CN101695871A (en) * | 2009-11-12 | 2010-04-21 | 江苏九鼎新材料股份有限公司 | Large wind force blade and manufacturing process thereof |
| CN105751409A (en) * | 2016-05-05 | 2016-07-13 | 沈阳中航迈瑞特工业有限公司 | Manufacturing method of carbon fiber composite material part mold |
| CN108215249A (en) * | 2017-12-21 | 2018-06-29 | 吉林大学 | A kind of composite laminated plate makes mold |
| CN108453642A (en) * | 2017-02-20 | 2018-08-28 | 波音公司 | With the tool assembly that panel is used together and the method for supporting panel by tool assembly |
-
2019
- 2019-09-09 CN CN201910864824.6A patent/CN110524910A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2847712A (en) * | 1952-11-10 | 1958-08-19 | Bristol Aircraft Ltd | Method of molding ribbed structures from thermosetting resin and fibrous material |
| CN101232985A (en) * | 2005-07-27 | 2008-07-30 | 三菱重工业株式会社 | RTM process |
| CN101448631A (en) * | 2006-03-20 | 2009-06-03 | 欧洲航空防务及航天公司Eads法国 | Method of producing stiffened panels made of a composite and panels thus produced |
| CN101695871A (en) * | 2009-11-12 | 2010-04-21 | 江苏九鼎新材料股份有限公司 | Large wind force blade and manufacturing process thereof |
| CN105751409A (en) * | 2016-05-05 | 2016-07-13 | 沈阳中航迈瑞特工业有限公司 | Manufacturing method of carbon fiber composite material part mold |
| CN108453642A (en) * | 2017-02-20 | 2018-08-28 | 波音公司 | With the tool assembly that panel is used together and the method for supporting panel by tool assembly |
| CN108215249A (en) * | 2017-12-21 | 2018-06-29 | 吉林大学 | A kind of composite laminated plate makes mold |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113021955A (en) * | 2021-02-04 | 2021-06-25 | 浙江吉利控股集团有限公司 | Forming die of composite beam and manufacturing method of composite beam |
| CN114800958A (en) * | 2022-04-28 | 2022-07-29 | 宁波曙翔新材料股份有限公司 | Large-scale composite product forming die |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| EP2403708B1 (en) | Method for manufacturing wind turbine blades | |
| CN103342167A (en) | Method for making scaled composite material wing model | |
| CN108590163A (en) | A kind of integrated molding aluminum alloy building template | |
| CN100441860C (en) | Vane for vertical shaft wind-driven generator and its making process | |
| CN110524910A (en) | A kind of VARTM technique composite material mould and its manufacturing method | |
| CN102806617B (en) | Die for integrally forming I-shaped reinforcement composite material wall plate | |
| CN107199713A (en) | A kind of high-quality forming method of composite material bracket | |
| CN201942405U (en) | Front plate for escalators | |
| CN109353026A (en) | It is a kind of to manufacture the mold and method for emitting shape Composite Material Stiffened Panel | |
| CN109177226A (en) | A kind of molding die and its forming method of approximation enclosed construction composite material casing | |
| CN202498144U (en) | Detachable-type composite material forming die | |
| US11104424B2 (en) | Strut for the landing gear of an aircraft | |
| CN209738315U (en) | Modular-design composite material mold | |
| CN105082661B (en) | Method for whole forming of aluminum honeycomb sandwich structure of carbon panel | |
| CN107718603A (en) | A kind of HSM manufacturing process of the armed lever of carbon fiber mechanical arm | |
| CN205889647U (en) | Satellite combined material load tube formwork utensil based on automatic fiber placement forming technology | |
| CN103010321B (en) | A kind of lightweight flat bed trailer car body and manufacture method thereof | |
| CN111016223A (en) | Detachable combined tool for manufacturing lining-free composite material storage box | |
| CN104960733B (en) | Built-up pallet | |
| CN203626231U (en) | Steel form for concrete pouring | |
| CN211543866U (en) | Composite material partition frame structure for aircraft wing trailing edge | |
| CN207901478U (en) | A kind of lightweight unmanned plane main landing gear composite joint making mold | |
| CN101391490B (en) | Continuous spiral laying forming method without mold for resin based composite material fin | |
| CN208978073U (en) | It is a kind of for manufacturing the master mold of composite material mould | |
| CN208181192U (en) | Structural member and its automobile for automobile |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20191203 |
|
| WD01 | Invention patent application deemed withdrawn after publication |