CN106738505A - A kind of manufacture method of the composite material shaping mould with composite construction - Google Patents
A kind of manufacture method of the composite material shaping mould with composite construction Download PDFInfo
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- CN106738505A CN106738505A CN201611099889.9A CN201611099889A CN106738505A CN 106738505 A CN106738505 A CN 106738505A CN 201611099889 A CN201611099889 A CN 201611099889A CN 106738505 A CN106738505 A CN 106738505A
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- Prior art keywords
- mould
- composite material
- composite
- support
- face
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Classifications
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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
- B29C33/00—Moulds or cores; Details thereof or accessories therefor
- B29C33/38—Moulds or cores; Details thereof or accessories therefor characterised by the material or the manufacturing process
- B29C33/3842—Manufacturing moulds, e.g. shaping the mould surface by machining
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
- B23P15/00—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass
- B23P15/24—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass dies
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Manufacturing & Machinery (AREA)
- Mounting, Exchange, And Manufacturing Of Dies (AREA)
Abstract
A kind of manufacture method of the composite material shaping mould with composite construction, belongs to technical field of composite material molding, more particularly to a kind of manufacture method of the composite material shaping mould with composite construction.Low for the forming accuracy of large-scale, accurate composite material parts mould and be more expensive to manufacture the problem short with service life, the present invention carries out assembly connection according to mould digital-to-analogue, machining composite material mould rack to support；Successively piled up using increasing material manufacturing method according to die face CAD digital-to-analogues and process Mold Metal type face and type face and support assembling assembly；Roughing is carried out to the component that die face and type face are assembled with support using Digit Control Machine Tool；Die face carries out assembly connection with support by self-locking component；Mould to assembling carries out the finishing of type face, produces the composite material shaping mould with composite construction.Manufacture of the present invention suitable for the composite material shaping mould of composite construction.
Description
Technical field
The invention belongs to technical field of composite material molding, more particularly to a kind of composite shaping with composite construction
The manufacture method of mould.
Background technology
Composite with its high specific stiffness, high specific strength, lightweight, stealth it is good and antifatigue, it is anticorrosive the advantages of
It is used more and more on aircraft structure, such as Boeing B787 and Air Passenger A350 model aircrafts, and composite material parts
Manufacture be presented the trend such as size is bigger, profile is more complicated, therefore the workmanship of composite material parts is proposed higher
It is required that.Due to the curing molding feature of composite product, especially Deformation control is depended greatly on into its quality
The quality of pattern tool.
Wherein, the characteristics of carbon fibre composite mould has thermal coefficient of expansion formed precision consistent with part high, but system
Make high cost, fragile, service life it is short and exist not easy mold release and be difficult to repair the shortcomings of restrict its large-scale application.
The features such as metal material mould such as Invar steel has high temperature resistant, wear-resistant, usage cycles are long, compared to carbon fibre composite mould
Significantly, but large scale labyrinth metal die weight is excessive for long service life advantage for tool, to transport bearing capacity and
Autoclave equipment size requirement it is too high, and existing manufacture method there are problems that low precision,.Existing large scale is answered
Miscellaneous type face die manufacture is：Slab piecemeal is shaped, and die face and support are assembled and welded, piecemeal die face welding,
Die face milling roughing and finishing etc..Its medium-sized face shaping is mainly roll bending (or punching press) and shapes the fiery school shape that adds water, weldering
It is manual argon arc welding to connect.Easily occur for process such as complex curvatures slab forming, the weld seam weldings long of forming face outer
The quality problems such as shape is overproof, commissure gas leakage, it is necessary to reparation of doing over again, meanwhile, slab milling processing capacity in type face is big, high cost.Separately
On the one hand, the die face of existing method processing solidifies once processing, it is impossible to change, this is for composite material structural member
The research and development initial stage is put to no little inconvenience, it is impossible to which the resilience result according to part is repaired to die shape, can only be added again
The new mould of work.
Therefore, the complex curvatures slab shaping for easily occurring for existing metal die processing and manufacturing process controls difficult, long
The problems such as weld seam stability of the welding quality difference, and carbon fibre composite die life it is short, repair it is difficult, be more expensive to manufacture
The problems such as, need to improve existing mould manufacturing method, so as to ensure die quality while, how scientific and effective realization
The high-precision modeling of composite material mould, low cost manufacture are composite material mould designs and manufacture problem urgently to be resolved hurrily.
The content of the invention
The technical problems to be solved by the invention are directed to the forming accuracy of large-scale, accurate composite material parts mould
It is low and be more expensive to manufacture the problem short with service life, propose a kind of manufacture of the composite material shaping mould with composite construction
Method, the method effectively improves the accuracy of manufacture of composite product, improves service life, it is ensured that product quality.
A kind of manufacture method of composite material shaping mould with composite construction of the present invention, the method it is specific
Step is：
Step one, according to mould digital-to-analogue, machining composite material mould rack, and assembly connection is carried out to support；
Step 2, successively piled up using increasing material manufacturing method according to die face CAD digital-to-analogues and process Mold Metal type face
And type face and support assembling assembly；
Step 3, roughing is carried out to the component that die face and type face and support are assembled using Digit Control Machine Tool；
Step 4, die face and support carry out assembly connection by self-locking component；
Step 5, the mould to assembling carry out the finishing of type face, complete the composite shaping mould with composite construction
The manufacture of tool.
The present invention has the advantage that and beneficial effect：
1) mould of metal mold face and composite material bracket structure can shorten the manufacturing cycle of mould, reduce Making mold
Cost；
2) complex profile increasing material manufacturing can be high with disposal molding, formed precision, it is to avoid occurs in conventional fabrication process
Slab shaping control accuracy is poor, it is high to former requirement the problems such as, and avoid the type face spelling occurred in conventional fabrication process
Weldering positioning difficulty is big, and the defect that leaks air problem；
4) support can mitigate mold weight using composite, and close with Invar steel type faces thermal coefficient of expansion, reduce
Deformation between die face and support caused by thermal expansion coefficient difference；
5) self-locking structure assembling can solve metal mold face and composite material bracket connectivity problem, it is to avoid conventionally manufactured mistake
The problems such as die face assembles hardly possible and big welding job amount with support in journey；
6) composite construction mould can be modified and repair according to technological requirement to die face, it is to avoid single carbon is fine
The characteristics of die face solidification of dimension composite structure cannot change.
Brief description of the drawings
Fig. 1 is flow chart of the invention；
Fig. 2 is the carbon fibre composite support described in specific embodiment five；
Fig. 3 is the CAD model of the die face described in specific embodiment five；
Fig. 4 is the Invar steel type faces manufacture schematic diagram described in specific embodiment five；
Fig. 5 is the self-locking structure schematic diagram of die face and the support connection described in specific embodiment five；
Fig. 6 is the final horizontal tail wing root radome fairing mould schematic diagram for assembling described in specific embodiment five.
Specific embodiment
Specific embodiment one, present embodiment is illustrated with reference to Fig. 1, the one kind described in present embodiment has composite construction
Composite material shaping mould manufacture method, the method concretely comprises the following steps：
Step one, according to mould digital-to-analogue, machining composite material mould rack, and assembly connection is carried out to support；
Step 2, successively piled up using increasing material manufacturing method according to die face CAD digital-to-analogues and process Mold Metal type face
And type face and support assembling assembly；
Step 3, roughing is carried out to the component that die face and type face and support are assembled using Digit Control Machine Tool；
Step 4, die face and support carry out assembly connection by self-locking component；
Step 5, the mould to assembling carry out the finishing of type face, complete the composite shaping mould with composite construction
The manufacture of tool.
Specific embodiment two, present embodiment is to a kind of the answering with composite construction described in specific embodiment one
The manufacture method of condensation material mould is further illustrated, and increasing material manufacturing method described in step 2 includes laser gain material side
Method, electron beam increase material method and electric arc (TIG or MIG) increases material method.
Die face increasing material manufacturing method described in present embodiment includes but is not limited to laser gain material, electron beam and increases
Material, electric arc (TIG or MIG) increase the methods such as material.
If starting to process preceding designer in mould needs to change size, the CAD numbers of increasing material manufacturing program need to be only updated
Mould；For mould, local location needs to change size in process or after processing, then need the position milling in change
Unnecessary material is cut away, according to new digital-to-analogue increasing material manufacturing, then follow-up processing is carried out.
For the damage that die surface is caused in use, it is also possible to carry out repair process with reference to the above method.
Specific embodiment three, present embodiment is that have composite construction to the one kind described in specific embodiment one or two
The manufacture method of composite material shaping mould further illustrate, die face described in step 2 is carbon fiber composite
Material, Invar steel or nickel alloy.
Specific embodiment four, present embodiment is to a kind of the answering with composite construction described in specific embodiment one
The manufacture method of condensation material mould is further illustrated, and the utilization Digit Control Machine Tool described in step 3 is to die face and type
Face carries out rough machined specific method with the component that support is assembled：Using the lower surface in end mill(ing) cutter milling type face, milling axial direction
Cutting-in is less than 3mm.
Specific embodiment five, present embodiment is that have composite construction to the one kind described in specific embodiment one or four
The manufacture method of composite material shaping mould further illustrate, described in step 5 pair mould for assembling carries out type face finishing
The method of work is：End mill(ing) cutter milling is first used in die face upper surface, milling axial direction cutting-in is less than 0.8mm, bulb is then used again
Milling cutter milling is machined to the theoretical profile of mould, and mould final profile degree error is less than 0.4mm.
Specific embodiment, by taking horizontal tail wing root radome fairing shaping mould as an example, with reference to the drawings and specific embodiments to the present invention
Further illustrate：
1) as shown in Fig. 2 processing carbon fibre composite support using traditional method, and assembling company is carried out to support
Connect；
2) as shown in figure 3, the CAD model according to die face carries out layered shaping, produce every layer with computer and sweep
Path is retouched, carrying out successively stack shaping along scanning pattern goes out Invar steel type faces and Invar steel type faces with carbon fiber support assembling
The component of connection；
3) as shown in Figure 4, it is possible to use laser gain material shaping, electron beam increase material shaping, electric arc (TIG or MIG) increase material into
The methods such as shape carry out Invar steel type face manufactures, and numbering 1 is increasing material manufacturing equipment working head in figure, and label 2 is die face；
4) Fig. 5 is the self-locking structure schematic diagram that die face and support are connected, wherein numbering 3 is Invar steel mold types
Face back assembling assembly, assembly connection is carried out by the structure by die face and support, and numbering 4 is in mould carbon fiber support
Component.
5) Fig. 6 is the final horizontal tail wing root radome fairing mould schematic diagram for assembling.
6) it is such as design alteration or technique adjustment are, it is necessary to the die face to processing carries out local correction, then right
Amendment position is carried out after digital control milling reaches requirement, repeat step 3) local increasing material manufacturing shaping is carried out, finally realize the position
Profile adjustment.
In sum, the manufacture method of the composite mold for forming of the composite construction that the present invention is provided, it is possible to achieve
Accurate, the quick manufacture of the mould that profile forms are complicated, dimensional accuracy is high.
Presently preferred embodiments of the present invention is the foregoing is only, is not intended to limit the invention, it is all in essence of the invention
Any modification, equivalent and improvement made within god and principle etc., should be included within the scope of the present invention.
Claims (5)
1. a kind of manufacture method of the composite material shaping mould with composite construction, it is characterised in that the specific step of the method
Suddenly it is：
Step one, according to mould digital-to-analogue, machining composite material mould rack, and assembly connection is carried out to support；
Step 2, successively piled up using increasing material manufacturing method according to die face CAD digital-to-analogues process Mold Metal type face and
Type face and support assembling assembly；
Step 3, roughing is carried out to the component that die face and type face and support are assembled using Digit Control Machine Tool；
Step 4, die face and support carry out assembly connection by self-locking component；
Step 5, the mould to assembling carry out the finishing of type face, complete the composite material shaping mould with composite construction
Manufacture.
2. a kind of manufacture method of composite material shaping mould with composite construction according to claim 1, its feature
It is that the increasing material manufacturing method described in step 2 includes that laser gain material method, electron beam increase material method and electric arc increases material method.
3. the manufacture method of a kind of composite material shaping mould with composite construction according to claim 1 and 2, it is special
Levy and be, the die face described in step 2 is carbon fibre composite, Invar steel or nickel alloy.
4. a kind of manufacture method of composite material shaping mould with composite construction according to claim 1, its feature
It is that rough machined tool is carried out to the component that die face and type face are assembled with support using Digit Control Machine Tool described in step 3
Body method is：Using the lower surface in end mill(ing) cutter milling type face, milling axial direction cutting-in is less than 3mm.
5. the manufacture method of a kind of composite material shaping mould with composite construction according to claim 1 or 4, it is special
Levy and be, pair mould for assembling described in step 5 carries out type face method for finishing manufactured and is：End is first used in die face upper surface
Milling cutter milling, milling axial direction cutting-in is less than 0.8mm, is then machined to the theoretical profile of mould, mould with rose cutter milling again
Final profile degree error is less than 0.4mm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611099889.9A CN106738505A (en) | 2016-12-02 | 2016-12-02 | A kind of manufacture method of the composite material shaping mould with composite construction |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611099889.9A CN106738505A (en) | 2016-12-02 | 2016-12-02 | A kind of manufacture method of the composite material shaping mould with composite construction |
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| CN106738505A true CN106738505A (en) | 2017-05-31 |
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| CN201611099889.9A Pending CN106738505A (en) | 2016-12-02 | 2016-12-02 | A kind of manufacture method of the composite material shaping mould with composite construction |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108526831A (en) * | 2018-03-19 | 2018-09-14 | 中国南方航空股份有限公司 | A kind of anti-manufacture craft for being bulldozed sliding door exterior skin and repairing mold of aircraft |
| CN111483151A (en) * | 2020-04-09 | 2020-08-04 | 沈阳沈飞机械设备制造厂 | Preparation method of milling mould for airplane parts |
| KR102215966B1 (en) * | 2019-08-21 | 2021-02-16 | 한국항공우주산업 주식회사 | Apparatus for producing After Cone Fin for Helicopter |
| CN114248377A (en) * | 2021-11-09 | 2022-03-29 | 浙江抟原复合材料有限公司 | Preparation method of composite material RTM (resin transfer molding) mold |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108526831A (en) * | 2018-03-19 | 2018-09-14 | 中国南方航空股份有限公司 | A kind of anti-manufacture craft for being bulldozed sliding door exterior skin and repairing mold of aircraft |
| KR102215966B1 (en) * | 2019-08-21 | 2021-02-16 | 한국항공우주산업 주식회사 | Apparatus for producing After Cone Fin for Helicopter |
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| CN114248377A (en) * | 2021-11-09 | 2022-03-29 | 浙江抟原复合材料有限公司 | Preparation method of composite material RTM (resin transfer molding) mold |
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Application publication date: 20170531 |