CN107471678A - A kind of multi-cavity composite joint integral formation method - Google Patents
A kind of multi-cavity composite joint integral formation method Download PDFInfo
- Publication number
- CN107471678A CN107471678A CN201710542249.9A CN201710542249A CN107471678A CN 107471678 A CN107471678 A CN 107471678A CN 201710542249 A CN201710542249 A CN 201710542249A CN 107471678 A CN107471678 A CN 107471678A
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- CN
- China
- Prior art keywords
- composite joint
- cavity
- formation method
- integral formation
- cavity composite
- 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.)
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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
-
- 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
- B29C33/40—Plastics, e.g. foam or rubber
- B29C33/405—Elastomers, e.g. rubber
-
- 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
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Composite Materials (AREA)
- Manufacturing & Machinery (AREA)
- Casting Or Compression Moulding Of Plastics Or The Like (AREA)
Abstract
The present invention a kind of multi-cavity composite joint integral formation method is disclosed, be molded using assembling die, assembling die includes multiple cavities mould, lateral mass mould, upper cover plate and lower cover, first by prepreg in cavity mold laying；It will be assembled in after cavity mold pre-compacted after the completion of paving on lower cover, rear paving edge strip part filled up using unidirectional pre-immersion material；After pre-compacted, assembling lateral mass mould blending bolt locks upper and lower cover plate, is locked after being completed and lays auxiliary material, bag vacuumizes, at a certain temperature curing molding, obtains multi-cavity composite joint.The technical effects of the invention are that：Use the combination die that silicon rubber is coated with cavity mold, multi-cavity composite joint is realized using prepreg to be integrally formed, compared with the joint of conventional metals shaping, in the case where realizing joint weight saving, the rigidity and intensity index of joint will not be reduced, and composite joint is corrosion-resistant, also in the absence of the risk of fatigue rupture.
Description
Technical field
The present invention relates to a kind of multi-cavity composite joint to be integrally formed manufacturing process.
Background technology
Compared to traditional metal material, carbon fibre composite has density low but specific strength and specific modulus height, corrosion resistant
The advantages that losing, be antifatigue, is widely used in fields such as track traffic, Aero-Space, marine settings at present.As primary load bearing
The metal joint of part, is manufactured using composite, not only can effectively reduce part weight, joint fatigue can also be avoided to fail
Risk.Further, since joint is cavity type structure, autoclave forming process is difficult to product and is integrally formed.
The content of the invention
The invention provides a kind of multi-cavity composite joint integral formation method, multi-cavity composite joint can be realized
It is integrally formed, solves the problems, such as that using prepreg multi-cavity composite joint can not be integrally formed.
Technical scheme provided by the invention is：
A kind of multi-cavity composite joint integral formation method, is molded using assembling die, and assembling die includes multiple cavities mould
Tool, lateral mass mould, upper cover plate and lower cover, first by prepreg in cavity mold laying；By the cavity mould after the completion of paving
It is assembled in after tool pre-compacted on lower cover, rear paving edge strip part is filled up using unidirectional pre-immersion material；After pre-compacted, lateral mass mould is assembled
Have blending bolt and lock upper and lower cover plate, locked after being completed and lay auxiliary material, bag vacuumizes, at a certain temperature
Curing molding, obtain multi-cavity composite joint.
Further, described composite is glass fibre or carbon fiber prepreg；
Further, described prepreg is high-temp epoxy or span prepreg, and resin content is 35% ~ 42%；
Further, described shaping mould is that cavity combines modular form with lateral mass；
Further, the thick soft modes of 5-8mm are coated with described cavity mold；
Further, described joint cavity is 8 to 10 symmetrical.
Further, described curing cycle is vacuum bag pressure, and 180 DEG C are molded.
The technical effects of the invention are that：It is real using prepreg using the combination die that silicon rubber is coated with cavity mold
Show multi-cavity composite joint to be integrally formed, compared with the joint of conventional metals shaping, realize joint weight saving
In the case of, the rigidity and intensity index of joint will not be reduced, and composite joint is corrosion-resistant, also in the absence of the wind of fatigue rupture
Danger.
Brief description of the drawings
Fig. 1 is that multi-cavity composite joint of the embodiment of the present invention is integrally formed mould schematic diagram, and it does not note upper cover plate（With lower cover
Plate is identical）；
Wherein：1-2 is lateral mass mould, and 6-11 is cavity mold, has cladding soft mode in 6-11 cavity molds.
Fig. 2 is multi-cavity composite joint schematic diagram；
Wherein：1 is cavity portion, totally 10 cavitys, and 2 be edge strip part.
Embodiment
The preferred embodiment that the invention will now be described in detail with reference to the accompanying drawings.
Such as Fig. 1（Do not show upper cover plate）, shown in Fig. 2, it is integrally formed that the present embodiment provides a kind of multi-cavity composite joint
Manufacturing process, it is molded using assembling die, assembling die includes multiple cavities mould, lateral mass mould, upper cover plate and lower cover, first
First by prepreg in cavity mold laying；It will be assembled on lower cover, use after cavity mold pre-compacted after the completion of paving
Unidirectional pre-immersion material fills up rear paving edge strip part；After pre-compacted, assembling lateral mass mould blending bolt locks upper and lower cover plate, assembling
After the completion of lock and lay auxiliary material, bag vacuumizes, at a certain temperature curing molding, obtains multi-cavity composite and connects
Head.
Described composite is glass fibre or carbon fiber prepreg；Prepreg is high-temp epoxy or span prepreg,
Resin content is 35% ~ 42%；Shaping mould is that cavity combines modular form with lateral mass；The thick soft modes of 5-8mm are coated with cavity mold；
Joint cavity is 8 to 10 symmetrical.Curing cycle is vacuum bag pressure, and 180 DEG C are molded.
A kind of multi-cavity composite joint, it is integrally formed by above-mentioned manufacturing process obtained.
The beneficial effect of the present embodiment is：A kind of integrally formed manufacturing process of multi-cavity composite joint of the present embodiment and
Gained composite joint, the joint manufactured relative to traditional metal materials have light weight, intensity high, corrosion-resistant, antifatigue
The advantages that destruction.And it is made for composite material integral formed, not only reliability is high, it is thus also avoided that composite product piecemeal group
The cost input of the fastener brought and assembly tooling is filled, reduces cost.
Claims (10)
1. a kind of multi-cavity composite joint integral formation method, it is characterised in that be molded using assembling die, assembling die bag
Include multiple cavities mould, lateral mass mould, upper cover plate and lower cover, first by prepreg in cavity mold laying；Paving is complete
It is assembled in after cavity mold pre-compacted after on lower cover, rear paving edge strip part is filled up using unidirectional pre-immersion material；Pre-compacted
Afterwards, assembling lateral mass mould blending bolt and lock upper and lower cover plate, locked after being completed and lay auxiliary material, bag vacuumizes,
Curing molding at a certain temperature, obtain multi-cavity composite joint.
A kind of 2. multi-cavity composite joint integral formation method as described in claims 1, it is characterised in that described chamber
Soft mode is coated with mould.
A kind of 3. multi-cavity composite joint integral formation method as described in claims 2, it is characterised in that soft mode thickness
At least above equal to 5mm.
4. a kind of multi-cavity composite joint integral formation method as described in claims 2, it is characterised in that described consolidates
It is 180 DEG C to change temperature.
5. as a kind of multi-cavity composite joint integral formation method as described in claims 4, it is characterised in that pre-compacted
Technique is normal-temperature vacuum pre-compacted or Vacuum Heat precompressed, and temperature is not more than 75 DEG C.
6. a kind of multi-cavity composite joint integral formation method as described in claims 1, it is characterised in that edge strip uses
Unidirectional pre-immersion material and Fabric prereg mixing laying.
7. a kind of multi-cavity composite joint integral formation method as described in claims 1, it is characterised in that locking is completed
Mould, only need during bag to use airfelt and vacuum bag, vacuum bag pressure, solidification completed in curing oven.
8. a kind of multi-cavity composite joint integral formation method as described in claims 1-7, it is characterised in that described multiple
Condensation material is epoxy or bismaleimide resin system carbon fiber prepreg.
A kind of 9. multi-cavity composite joint integral formation method as described in claims 8, it is characterised in that the resin
Content is 35% ~ 42%.
10. a kind of multi-cavity composite joint, it is characterised in that the integral formation method as described in claim 1-9 is made.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710542249.9A CN107471678A (en) | 2017-07-05 | 2017-07-05 | A kind of multi-cavity composite joint integral formation method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710542249.9A CN107471678A (en) | 2017-07-05 | 2017-07-05 | A kind of multi-cavity composite joint integral formation method |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN107471678A true CN107471678A (en) | 2017-12-15 |
Family
ID=60595459
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710542249.9A Pending CN107471678A (en) | 2017-07-05 | 2017-07-05 | A kind of multi-cavity composite joint integral formation method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN107471678A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109130244A (en) * | 2018-10-31 | 2019-01-04 | 山西平阳重工机械有限责任公司 | A kind of molding die and forming method of depth chamber multiwindow composite product |
| CN111823610A (en) * | 2020-07-14 | 2020-10-27 | 中车青岛四方机车车辆股份有限公司 | Preparation method of composite material car body apron board |
| CN112032233A (en) * | 2020-08-17 | 2020-12-04 | 西安交通大学 | High-specific energy-absorbing bionic composite material structure and manufacturing method thereof |
Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103660311A (en) * | 2013-11-29 | 2014-03-26 | 北京卫星制造厂 | Integral forming method of changeable-thickness complex-structure composite connector |
-
2017
- 2017-07-05 CN CN201710542249.9A patent/CN107471678A/en active Pending
Patent Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103660311A (en) * | 2013-11-29 | 2014-03-26 | 北京卫星制造厂 | Integral forming method of changeable-thickness complex-structure composite connector |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109130244A (en) * | 2018-10-31 | 2019-01-04 | 山西平阳重工机械有限责任公司 | A kind of molding die and forming method of depth chamber multiwindow composite product |
| CN111823610A (en) * | 2020-07-14 | 2020-10-27 | 中车青岛四方机车车辆股份有限公司 | Preparation method of composite material car body apron board |
| CN112032233A (en) * | 2020-08-17 | 2020-12-04 | 西安交通大学 | High-specific energy-absorbing bionic composite material structure and manufacturing method thereof |
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Application publication date: 20171215 |