CN106926481A - A kind of forming method of filament carbon fibre component - Google Patents
A kind of forming method of filament carbon fibre component Download PDFInfo
- Publication number
- CN106926481A CN106926481A CN201710078349.0A CN201710078349A CN106926481A CN 106926481 A CN106926481 A CN 106926481A CN 201710078349 A CN201710078349 A CN 201710078349A CN 106926481 A CN106926481 A CN 106926481A
- Authority
- CN
- China
- Prior art keywords
- carbon fibre
- exemplar
- filament
- carbon fiber
- component
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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
- B29C70/40—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
- B29C70/44—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles using isostatic pressure, e.g. pressure difference-moulding, vacuum bag-moulding, autoclave-moulding or expanding rubber-moulding
- B29C70/443—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles using isostatic pressure, e.g. pressure difference-moulding, vacuum bag-moulding, autoclave-moulding or expanding rubber-moulding and impregnating by vacuum or injection
-
- 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
- B29L2031/3076—Aircrafts
- B29L2031/3085—Wings
Landscapes
- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Composite Materials (AREA)
- Mechanical Engineering (AREA)
- Moulding By Coating Moulds (AREA)
- Road Paving Structures (AREA)
Abstract
The present invention relates to a kind of forming method of filament carbon fibre component, belong to manufacture technology of composite material.The present invention includes carbon fiber exemplar and flexible die, and flexible die is combined by unvulcanized rubber layer and carbon fibre fabric, finally by rigidly playing mould and flexible die matched moulds, molds filament fiber component.The present invention can produce thickness and meet the requirements, the accurate large thick-wall filament carbon fibre component in assembly type face, reduce the scrappage of product.
Description
Technical field
The invention belongs to manufacture technology of composite material, it is related to a kind of forming method of filament carbon fibre component, particularly flies
The forming method of machine wing flap C-type beam.
Background technology
Filament carbon fibre component is a kind of typical composite laminate, and traditional vacuum-bag process technique cannot ensure
Thickness and fitting surface after filament carbon fibre molding component meet drawing requirement, further, since process program is limited, the part is only
Vacuum-bag process technique can be used, it is impossible to use wide variety of upper and lower rigid die matched moulds moulding process.So, it is badly in need of finding
A kind of vacuum-bag process method of flexible die and rigid die matched moulds.
The content of the invention
The purpose of the present invention is：By making carbon fiber exemplar, further make flexible die, then by property mould with it is firm
Mould matched moulds under property, and filament carbon fibre prepreg is shaped to by filament carbon fibre component by vacuum-bag process technique, it is ensured that
The required precision of component.
The technical scheme is that：
The invention provides a kind of forming method of filament carbon fibre component, comprise the following steps：
The first step, by vacuum-bag process technique by carbon fibre fabric prepreg make carbon fiber exemplar；
Second step, carbon fiber exemplar is attached on the lower mould of rigidity；
3rd step, carbon fibre fabric prepreg and the overlapping paving of half finished rubber layer are formed many on carbon fiber exemplar
Rotating fields, are shaped to flexible die by vacuum-bag process technique by the rubber combined sandwich construction of carbon fiber afterwards；
4th step, flexible die and carbon fiber exemplar are removed, the paving filament carbon fibre prepreg on mould under rigidity；
It is 5th step, by the lower mould matched moulds of flexible die and rigidity and by vacuum-bag process technique that filament carbon fibre is pre-
Leaching material is shaped to filament carbon fibre component.
Further, filament carbon fibre component is beam type component, and carbon fiber exemplar is beam type exemplar.
Further, filament carbon fibre component is aircraft flap C-type beam, and carbon fiber exemplar is C-type beam exemplar.
Filament carbon fibre in the present invention is known carbon fiber one-way band.
The beneficial effects of the invention are as follows：
The present invention can produce thickness and meet the requirements, the accurate large thick-wall filament carbon fibre component in assembly type face, reduce
The scrappage of product.
Brief description of the drawings
Fig. 1 is carbon fiber exemplar schematic diagram of mating formation；
Fig. 2 is wing flap C-type beam schematic diagram of mating formation；
1- rigidity lower mould, 2- exemplars, 3-C types beam, 4- flexible dies.
Specific embodiment
Specific embodiment of the invention is described in further details below：
There is provided a kind of forming method of filament carbon fibre component, comprise the following steps：
The first step, by vacuum-bag process technique by carbon fibre fabric prepreg make carbon fiber exemplar；
Second step, carbon fiber exemplar is attached on the lower mould of rigidity；
3rd step, carbon fibre fabric prepreg and the overlapping paving of half finished rubber layer are formed many on carbon fiber exemplar
Rotating fields, are shaped to flexible die by vacuum-bag process technique by the rubber combined sandwich construction of carbon fiber afterwards；
4th step, flexible die and carbon fiber exemplar are removed, the paving filament carbon fibre prepreg on mould under rigidity；
It is 5th step, by the lower mould matched moulds of flexible die and rigidity and by vacuum-bag process technique that filament carbon fibre is pre-
Leaching material is shaped to filament carbon fibre component.
Further, filament carbon fibre component is beam type component, and carbon fiber exemplar is beam type exemplar.
Further, filament carbon fibre component is aircraft flap C-type beam, and carbon fiber exemplar is C-type beam exemplar.
Filament carbon fibre in the present invention is known carbon fiber one-way band.
Claims (3)
1. a kind of forming method of filament carbon fibre component, comprises the following steps：
The first step, by vacuum-bag process technique by carbon fibre fabric prepreg make carbon fiber exemplar；
Second step, carbon fiber exemplar is attached on the lower mould of rigidity；
3rd step, carbon fibre fabric prepreg and the overlapping paving of half finished rubber layer are formed into multilayer knot on carbon fiber exemplar
Structure, is shaped to flexible die by vacuum-bag process technique by the rubber combined sandwich construction of carbon fiber afterwards；
4th step, flexible die and carbon fiber exemplar are removed, the paving filament carbon fibre prepreg on mould under rigidity；
5th step, by the lower mould matched moulds of flexible die and rigidity, and by vacuum-bag process technique by filament carbon fibre prepreg
It is shaped to filament carbon fibre component.
2. the forming method of a kind of filament carbon fibre component according to claim 1, it is characterised in that：Filament carbon fibre structure
Part is beam type component, and carbon fiber exemplar is beam type exemplar.
3. the forming method of a kind of filament carbon fibre component according to claim 1, it is characterised in that：Filament carbon fibre structure
Part is aircraft flap C-type beam, and carbon fiber exemplar is C-type beam exemplar.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710078349.0A CN106926481A (en) | 2017-02-14 | 2017-02-14 | A kind of forming method of filament carbon fibre component |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710078349.0A CN106926481A (en) | 2017-02-14 | 2017-02-14 | A kind of forming method of filament carbon fibre component |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN106926481A true CN106926481A (en) | 2017-07-07 |
Family
ID=59423164
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710078349.0A Pending CN106926481A (en) | 2017-02-14 | 2017-02-14 | A kind of forming method of filament carbon fibre component |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106926481A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107696522A (en) * | 2017-09-29 | 2018-02-16 | 江西昌河航空工业有限公司 | A kind of carbon fibre fabric method for forming parts at band R angles |
| CN114347508A (en) * | 2021-12-31 | 2022-04-15 | 辽宁通用航空研究院 | Preparation process of carbon fiber composite material airplane longitudinal member |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101134368A (en) * | 2006-08-30 | 2008-03-05 | 航天材料及工艺研究所 | Thermoplasticity composite sheet material winded with composite fiber and technique of preparing the same |
| CN101391488A (en) * | 2008-08-22 | 2009-03-25 | 成都飞机工业（集团）有限责任公司 | Curing formation method for non-flat plate composite product and shaping mould |
| CN102514210A (en) * | 2011-12-12 | 2012-06-27 | 天津工业大学 | Moulding method of composite material prefabricated component |
| CN104162996A (en) * | 2014-06-30 | 2014-11-26 | 江苏恒神纤维材料有限公司 | A manufacturing process of a carbon-fibre composite material U-shaped part |
| CN105984154A (en) * | 2016-06-14 | 2016-10-05 | 沈阳飞机工业（集团）有限公司 | Forming method of U-shaped beam type composite part |
-
2017
- 2017-02-14 CN CN201710078349.0A patent/CN106926481A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101134368A (en) * | 2006-08-30 | 2008-03-05 | 航天材料及工艺研究所 | Thermoplasticity composite sheet material winded with composite fiber and technique of preparing the same |
| CN101391488A (en) * | 2008-08-22 | 2009-03-25 | 成都飞机工业（集团）有限责任公司 | Curing formation method for non-flat plate composite product and shaping mould |
| CN102514210A (en) * | 2011-12-12 | 2012-06-27 | 天津工业大学 | Moulding method of composite material prefabricated component |
| CN104162996A (en) * | 2014-06-30 | 2014-11-26 | 江苏恒神纤维材料有限公司 | A manufacturing process of a carbon-fibre composite material U-shaped part |
| CN105984154A (en) * | 2016-06-14 | 2016-10-05 | 沈阳飞机工业（集团）有限公司 | Forming method of U-shaped beam type composite part |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107696522A (en) * | 2017-09-29 | 2018-02-16 | 江西昌河航空工业有限公司 | A kind of carbon fibre fabric method for forming parts at band R angles |
| CN114347508A (en) * | 2021-12-31 | 2022-04-15 | 辽宁通用航空研究院 | Preparation process of carbon fiber composite material airplane longitudinal member |
| CN114347508B (en) * | 2021-12-31 | 2024-08-06 | 辽宁通用航空研究院 | Preparation process of carbon fiber composite aircraft longitudinal member |
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| SE01 | Entry into force of request for substantive examination | ||
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| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20170707 |
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| RJ01 | Rejection of invention patent application after publication |