CN109263088A - A kind of composite material integral formed method with holes - Google Patents
A kind of composite material integral formed method with holes Download PDFInfo
- Publication number
- CN109263088A CN109263088A CN201811282993.0A CN201811282993A CN109263088A CN 109263088 A CN109263088 A CN 109263088A CN 201811282993 A CN201811282993 A CN 201811282993A CN 109263088 A CN109263088 A CN 109263088A
- Authority
- CN
- China
- Prior art keywords
- layer
- laid
- main material
- sleeve
- fiber filament
- 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.)
- Granted
Links
- 239000002131 composite material Substances 0.000 title claims abstract description 30
- 238000000034 method Methods 0.000 title claims abstract description 14
- 239000000463 material Substances 0.000 claims abstract description 39
- 239000000835 fiber Substances 0.000 claims abstract description 34
- 238000000465 moulding Methods 0.000 claims description 11
- 230000035929 gnawing Effects 0.000 claims description 7
- 206010006514 bruxism Diseases 0.000 claims description 6
- 210000003781 tooth socket Anatomy 0.000 claims description 6
- 238000004080 punching Methods 0.000 claims description 4
- 239000007788 liquid Substances 0.000 claims description 3
- 238000004519 manufacturing process Methods 0.000 description 6
- 238000005553 drilling Methods 0.000 description 3
- 238000007906 compression Methods 0.000 description 2
- RYGMFSIKBFXOCR-UHFFFAOYSA-N Copper Chemical compound [Cu] RYGMFSIKBFXOCR-UHFFFAOYSA-N 0.000 description 1
- 239000000853 adhesive Substances 0.000 description 1
- 230000001070 adhesive effect Effects 0.000 description 1
- 238000005452 bending Methods 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 238000009954 braiding Methods 0.000 description 1
- 230000006835 compression Effects 0.000 description 1
- 238000000748 compression moulding Methods 0.000 description 1
- 230000008602 contraction Effects 0.000 description 1
- 229910052802 copper Inorganic materials 0.000 description 1
- 239000010949 copper Substances 0.000 description 1
- 230000006378 damage Effects 0.000 description 1
- 230000007423 decrease Effects 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 239000004744 fabric Substances 0.000 description 1
- 238000005755 formation reaction Methods 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 230000006641 stabilisation Effects 0.000 description 1
- 238000011105 stabilization Methods 0.000 description 1
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
- B29C70/38—Automated lay-up, e.g. using robots, laying filaments according to predetermined patterns
-
- 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
- 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
- B29C70/28—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
- B29C70/38—Automated lay-up, e.g. using robots, laying filaments according to predetermined patterns
- B29C70/382—Automated fiber placement [AFP]
-
- 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
Abstract
The invention discloses a kind of composite material integral formed methods with holes, including main material, fiber filament and sleeve, are first laid with first layer main material, then first layer fiber filament is laid on first layer main material；Then second layer main material is laid on the filametntary top of first layer, the part being broken at hole then will be located in first layer fiber filament and is laid on the top surface of second layer main material behind the hole on second layer main material, is then laid with second layer fiber filament；Then third layer main material is laid on the filametntary top of the second layer, and so on；After the completion of the last layer main material is laid with, it is pressed and molded, pass through composite material structural member integral forming process, guarantee that broken fiber filaments are less, the aperture for the composite material structural member produced possesses lower stress state under certain condition, it solves the outlet splitting of conventional borehole, is cross-woven laying and further enhances the intensity in hole, and reduce the probability of composite material layering in the place in hole.
Description
Technical field
The present invention relates to a kind of forming method of composite material, especially a kind of composite material integral formed method with holes.
Background technique
In composite material element manufacturing process, the molding of the production in common hole, conventional holes generallys use drilling via formations, due to
The special fiber of composite material exists, and the manufacture craft of drilling will lead to fiber and be destroyed, and is easy to appear layering around drilling, out
The problems such as mouth splitting, causes the strength and stiffness in hole to decline, directly influence the intensity, rigidity, stabilization of composite material structural member
Property.It especially embodies and becomes apparent on the composite material structural member of unidirectional fibre, the hole of unidirectional fibrous composite materials structural member
Serious destruction around hole can be directly resulted in.Traditional handicraft usually adds copper sheathing at the punching in composite material structural member hole, to protect
Shield composite material structural member will not be destroyed further during use, but effect is not significant.
Summary of the invention
Technical assignment of the invention be for the above the deficiencies in the prior art, and provide a kind of band hole composite material one at
Type method.
The technical solution adopted by the present invention to solve the technical problems is: a kind of composite material integral formed method with holes,
Including main material, fiber filament and sleeve, specific production step are as follows:
Step 1: punching on every layer of main material, then selects sleeve corresponding with aperture；
Step 2: it is laid with first layer main material, then ready sleeve is inserted in the hole, then by first layer fiber filament
It is laid on first layer main material；
Step 3: being laid on the filametntary top of first layer for second layer main material, then by position in first layer fiber filament
The part being broken at hole is laid on the top surface of second layer main material behind the hole on second layer main material, is then laid with the
Bilaminar fiber silk；
Step 4: being laid on the filametntary top of the second layer for third layer main material, and subsequent step is subject to step 3, according to
It is secondary to analogize；
Step 5: after the completion of the last layer main material is laid with, molding or autoclave molding or liquid molding are carried out.
It is further improved: in step 3, after second layer fiber filament is laid, the fiber filament of first layer being wrapped in second
On layer fiber filament.
It is a kind of for making the sleeve of composite material integral formed with holes, wherein the sleeve includes inner barrel and outer barrel,
The outer diameter of the inner cylinder is identical as the internal diameter of the outer cylinder, and the inner cylinder is engaged by two sections of casings with outer cylinder and formed.
Be further improved: the inner cylinder is made of interior sleeve and interior two casing, and the outer cylinder is by outer sleeve and outer two
Casing composition, is respectively equipped with grinding tooth and tooth socket, the grinding tooth is identical as the shape size of tooth socket in described sleeve pipe.
Be further improved: in the axial direction, the position of inner cylinder upper gnawing tooth and the position of outer cylinder upper gnawing tooth are arranged in a staggered manner.
Advantages of the present invention: this method is integrally formed new process by composite material structural member, in production composite material knot
The hole of needs is just produced when component, guarantees that broken fiber filaments are less, the aperture for the composite material structural member produced exists
Possess lower stress state under certain condition, sleeve has compressibility using the sleeve of the double-deck four-part form design, solves
Contraction problem after molding or material compacting is simultaneously asked with the leak adhesive problem in compression process, bending of the solution fiber at gap
Hole surrounding annulus canoe: topic solves a large amount of breakage problems of fiber caused by conventional borehole；Hole, which uses, to be integrally formed, so that
Fibrous fracture is reduced, and solves the outlet splitting of conventional borehole to a certain extent, and layering and fabric reel off raw silk from cocoons problem around hole wall；It hands over
Fork braiding, which is laid with, further enhances the intensity in hole, and reduces the probability of composite material layering in the place in hole.
Detailed description of the invention
Fig. 1 is the structural schematic diagram of sleeve of the present invention.
Specific embodiment
The present invention is described below with reference to the accompanying drawings of the specification.
As shown, it is a kind of for making the sleeve of composite material integral formed with holes, wherein the sleeve includes interior
Cylinder and outer cylinder, the outer diameter of the inner cylinder is identical as the internal diameter of the outer cylinder, and the inner cylinder engages group by two sections of casings with outer cylinder
At；The inner cylinder is made of interior sleeve 3 and interior two casing 4, and the outer cylinder is made of outer a set of 1 pipe and outer two casing 2, in institute
It states and is respectively equipped with grinding tooth 5 and tooth socket 6 on casing, the grinding tooth 5 is identical as the shape size of tooth socket 6；In the axial direction, it is nibbled on inner cylinder
The position of tooth 5 and the position of outer cylinder upper gnawing tooth 5 are arranged in a staggered manner.
A kind of composite material integral formed method with holes, including main material, fiber filament and sleeve, specific production step
Are as follows:
Step 1: punching on every layer of main material, then selects sleeve corresponding with aperture；
Step 2: it is laid with first layer main material, then ready sleeve is inserted in the hole, then by first layer fiber filament
It is laid on first layer main material；
Step 3: being laid on the filametntary top of first layer for second layer main material, then by position in first layer fiber filament
The part being broken at hole is laid on the top surface of second layer main material behind the hole on second layer main material, is then laid with the
Bilaminar fiber silk；After second layer fiber filament is laid, the fiber filament of first layer is wrapped on second layer fiber filament.
Step 4: being laid on the filametntary top of the second layer for third layer main material, and subsequent step is subject to step 3, will
The fiber filament of preceding layer passes through the part being broken at hole and is laid on later layer main material behind the hole on later layer main material
Top surface, then be laid with later layer fiber filament, and so on；
Step 5: after the completion of the last layer main material is laid with, carrying out molding or autoclave molding or liquid molding,
In compression molding, since sleeve is made of inner barrel and outer barrel, and inner cylinder is engaged by two sections of casings with outer cylinder and is formed, institute
With when being molded, sleeve can be completed to compress together with composite material, simultaneously because in the axial direction, the position of inner cylinder upper gnawing tooth
It sets and is arranged in a staggered manner with the position of outer cylinder upper gnawing tooth, so main material excessive problem of gummosis in compression.
The above description is only an embodiment of the present invention, is not intended to limit the scope of the invention, all to utilize this hair
Equivalent structure or equivalent flow shift made by bright specification and accompanying drawing content is applied directly or indirectly in other relevant skills
Art field, is included within the scope of the present invention.
Claims (5)
1. a kind of composite material integral formed method with holes, it is characterised in that: specific to make including main material, fiber filament and sleeve
Make step are as follows:
Step 1: punching on every layer of main material, then selects sleeve corresponding with aperture；
Step 2: it is laid with first layer main material, then ready sleeve is inserted in the hole, is then laid with first layer fiber filament
On first layer main material；
Step 3: being laid on the filametntary top of first layer for second layer main material, and hole then will be located in first layer fiber filament
The part of place's fracture is laid on the top surface of second layer main material, is then laid with the second layer behind the hole on second layer main material
Fiber filament；
Step 4: being laid on the filametntary top of the second layer for third layer main material, and subsequent step is subject to step 3, successively class
It pushes away；
Step 5: after the completion of the last layer main material is laid with, molding or autoclave molding or liquid molding are carried out.
2. a kind of composite material integral formed method with holes according to claim 1, it is characterised in that: in step 3,
After second layer fiber filament is laid, the fiber filament of first layer is wrapped on second layer fiber filament.
3. a kind of for making the sleeve of composite material integral formed with holes, it is characterised in that: the sleeve include inner cylinder and
Outer cylinder, the outer diameter of the inner cylinder is identical as the internal diameter of the outer cylinder, and the inner cylinder is engaged by two sections of casings with outer cylinder and formed.
4. according to claim 3 a kind of for making the sleeve of composite material integral formed with holes, it is characterised in that:
The inner cylinder is made of interior sleeve and interior two casing, and the outer cylinder is made of outer sleeve and outer two casing, in described sleeve pipe
On be respectively equipped with grinding tooth and tooth socket, the grinding tooth is identical as the shape size of tooth socket.
5. according to claim 4 a kind of for making the sleeve of composite material integral formed with holes, it is characterised in that:
In the axial direction, the position of inner cylinder upper gnawing tooth and the position of outer cylinder upper gnawing tooth are arranged in a staggered manner.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811282993.0A CN109263088B (en) | 2018-10-31 | 2018-10-31 | Integrated forming method of porous composite material |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811282993.0A CN109263088B (en) | 2018-10-31 | 2018-10-31 | Integrated forming method of porous composite material |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN109263088A true CN109263088A (en) | 2019-01-25 |
| CN109263088B CN109263088B (en) | 2023-10-31 |
Family
ID=65190965
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811282993.0A Active CN109263088B (en) | 2018-10-31 | 2018-10-31 | Integrated forming method of porous composite material |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109263088B (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110481061A (en) * | 2019-09-17 | 2019-11-22 | 中国航发沈阳发动机研究所 | A kind of method for punching of fibre reinforced composites, acoustical panel and its sound lining |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE102009004813A1 (en) * | 2009-01-13 | 2010-07-15 | Eurocopter Deutschland Gmbh | Fiber reinforced plastic panel for manufacturing lining part of aircraft, has laminated bush insert with reinforcement ring, where threads are wound around ring and embedded between lower and upper layers of panel by laminating process |
| CN103968159A (en) * | 2013-01-31 | 2014-08-06 | 天源环保有限公司 | Special environment-friendly wear-resisting pipe |
| CN205781611U (en) * | 2016-06-27 | 2016-12-07 | 方自然 | The subsection connecting structure of turbine-generator units operating oil line |
-
2018
- 2018-10-31 CN CN201811282993.0A patent/CN109263088B/en active Active
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE102009004813A1 (en) * | 2009-01-13 | 2010-07-15 | Eurocopter Deutschland Gmbh | Fiber reinforced plastic panel for manufacturing lining part of aircraft, has laminated bush insert with reinforcement ring, where threads are wound around ring and embedded between lower and upper layers of panel by laminating process |
| CN103968159A (en) * | 2013-01-31 | 2014-08-06 | 天源环保有限公司 | Special environment-friendly wear-resisting pipe |
| CN205781611U (en) * | 2016-06-27 | 2016-12-07 | 方自然 | The subsection connecting structure of turbine-generator units operating oil line |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110481061A (en) * | 2019-09-17 | 2019-11-22 | 中国航发沈阳发动机研究所 | A kind of method for punching of fibre reinforced composites, acoustical panel and its sound lining |
Also Published As
| Publication number | Publication date |
|---|---|
| CN109263088B (en) | 2023-10-31 |
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