CN109263088B - Integrated forming method of porous composite material - Google Patents
Integrated forming method of porous composite material Download PDFInfo
- Publication number
- CN109263088B CN109263088B CN201811282993.0A CN201811282993A CN109263088B CN 109263088 B CN109263088 B CN 109263088B CN 201811282993 A CN201811282993 A CN 201811282993A CN 109263088 B CN109263088 B CN 109263088B
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- CN
- China
- Prior art keywords
- layer
- main material
- sleeve
- hole
- fiber
- 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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- 239000002131 composite material Substances 0.000 title claims abstract description 27
- 238000000034 method Methods 0.000 title claims abstract description 16
- 239000000835 fiber Substances 0.000 claims abstract description 43
- 239000000463 material Substances 0.000 claims abstract description 39
- 210000003781 tooth socket Anatomy 0.000 claims description 6
- 238000004519 manufacturing process Methods 0.000 claims description 4
- 239000007788 liquid Substances 0.000 claims description 3
- 238000004080 punching Methods 0.000 claims description 3
- 238000000465 moulding Methods 0.000 abstract description 7
- 238000005553 drilling Methods 0.000 abstract description 6
- 238000000748 compression moulding Methods 0.000 abstract description 2
- 238000009954 braiding Methods 0.000 abstract 1
- 239000011148 porous material Substances 0.000 abstract 1
- 238000007906 compression Methods 0.000 description 2
- 230000032798 delamination Effects 0.000 description 2
- 238000004804 winding Methods 0.000 description 2
- RYGMFSIKBFXOCR-UHFFFAOYSA-N Copper Chemical compound [Cu] RYGMFSIKBFXOCR-UHFFFAOYSA-N 0.000 description 1
- 238000005452 bending Methods 0.000 description 1
- 238000005056 compaction Methods 0.000 description 1
- 230000006835 compression Effects 0.000 description 1
- 229910052802 copper Inorganic materials 0.000 description 1
- 239000010949 copper Substances 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 239000004744 fabric Substances 0.000 description 1
- 239000003292 glue Substances 0.000 description 1
- 238000009987 spinning 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 an integral forming method of a porous composite material, which comprises a main material, fiber filaments and a sleeve, wherein a first layer of main material is paved firstly, and then the first layer of fiber filaments are paved on the first layer of main material; then, a second layer of main material is paved above the first layer of fiber yarn, then, the broken part of the first layer of fiber yarn, which is positioned at the hole, passes through the hole on the second layer of main material, is paved on the top surface of the second layer of main material, and then, the second layer of fiber yarn is paved; then a third layer of main material is paved above the second layer of fiber yarn, and so on; after the last layer of main material is paved, compression molding is carried out, fiber breakage is less through a composite material structural member integrated molding process, the manufactured open pore of the composite material structural member has a lower stress state under certain conditions, the outlet splitting of the traditional drilling hole is solved, the strength of the hole is further enhanced through cross braiding paving, and the probability of layering of the composite material is reduced at the place of the hole.
Description
Technical Field
The invention relates to a forming method of a composite material, in particular to an integral forming method of a composite material with holes.
Background
In the manufacturing process of the composite material piece, the common holes are manufactured, the conventional holes are formed by drilling, and because special fibers of the composite material exist, the drilling manufacturing process can lead to the damage of the fibers, the problems of delamination, outlet splitting and the like are easy to occur around the drilling, so that the strength and the rigidity of the holes are reduced, and the strength, the rigidity and the stability of the composite material structural member are directly influenced. Particularly, the method is more obvious on the composite material structural member of unidirectional fibers, and the holes of the unidirectional fiber composite material structural member can directly cause serious damage around the holes. The conventional process typically adds a copper sleeve to the perforated portion of the composite structural member hole to protect the composite structural member from further damage during use, but with insignificant results.
Disclosure of Invention
The technical task of the invention is to provide an integral forming method of a composite material with holes, aiming at the defects in the prior art.
The technical scheme adopted for solving the technical problems is as follows: the integral forming process of composite material with holes includes the following steps:
step one: punching holes on each layer of main material, and then selecting a sleeve corresponding to the aperture;
step two: laying a first layer of main material, inserting the prepared sleeve into the hole, and then laying a first layer of fiber yarns on the first layer of main material;
step three: paving a second layer of main material above the first layer of fiber yarns, then paving a broken part of the first layer of fiber yarns, which is positioned at the hole, on the top surface of the second layer of main material after passing through the hole on the second layer of main material, and then paving the second layer of fiber yarns;
step four: paving a third layer of main material above the second layer of fiber yarns, and performing the following steps based on the third step and the like;
step five: after the last layer of main material is laid, the material is molded, autoclave molded or liquid molded.
Further improvement: in the third step, after the second layer of fiber filaments is laid, the first layer of fiber filaments are wound on the second layer of fiber filaments.
The sleeve for manufacturing the integrated forming of the perforated composite material comprises an inner cylinder and an outer cylinder, wherein the outer diameter of the inner cylinder is the same as the inner diameter of the outer cylinder, and the inner cylinder and the outer cylinder are formed by meshing two sections of sleeves.
Further improvement: the inner cylinder consists of an inner first sleeve and an inner second sleeve, the outer cylinder consists of an outer first sleeve and an outer second sleeve, the sleeves are respectively provided with a tooth and a tooth socket, and the shape and the size of the tooth and the tooth socket are the same.
Further improvement: in the axial direction, the position of the meshing teeth on the inner cylinder is staggered with the position of the meshing teeth on the outer cylinder.
The invention has the advantages that: according to the method, through a novel integrated molding process of the composite structural member, a needed hole is manufactured when the composite structural member is manufactured, fiber breakage is less, the manufactured hole of the composite structural member has a lower stress state under a certain condition, the sleeve is of a double-layer four-section design, the compressibility of the sleeve is achieved, the shrinkage problem after compression molding or material compaction and the glue leakage problem in the compression process are solved, the bending problem of fibers at a gap is solved, and the fiber winding mode around the hole is adopted: the problem of mass fiber breakage caused by traditional drilling is solved; the holes are integrally formed, so that fiber breakage is reduced, and the problems of outlet splitting, layering around hole walls and fabric spinning of the traditional drilling holes are solved to a certain extent; cross-weave lay-up further strengthens the hole strength and reduces the probability of delamination of the composite material at the hole site.
Drawings
Fig. 1 is a schematic structural view of the sleeve of the present invention.
Detailed Description
The present invention will be described in detail below with reference to the drawings attached to the specification.
As shown in the figure, the sleeve for integrally forming the perforated composite material comprises an inner cylinder and an outer cylinder, wherein the outer diameter of the inner cylinder is the same as the inner diameter of the outer cylinder, and the inner cylinder and the outer cylinder are formed by meshing two sections of sleeves; the inner cylinder consists of an inner sleeve 3 and an inner sleeve 4, the outer cylinder consists of an outer sleeve 1 and an outer sleeve 2, the sleeves are respectively provided with a tooth 5 and a tooth socket 6, and the shape and the size of the tooth 5 are the same as those of the tooth socket 6; in the axial direction, the position of the meshing teeth 5 on the inner cylinder is staggered with the position of the meshing teeth 5 on the outer cylinder.
The integral forming process of composite material with holes includes the following steps:
step one: punching holes on each layer of main material, and then selecting a sleeve corresponding to the aperture;
step two: laying a first layer of main material, inserting the prepared sleeve into the hole, and then laying a first layer of fiber yarns on the first layer of main material;
step three: paving a second layer of main material above the first layer of fiber yarns, then paving a broken part of the first layer of fiber yarns, which is positioned at the hole, on the top surface of the second layer of main material after passing through the hole on the second layer of main material, and then paving the second layer of fiber yarns; and after the second layer of fiber yarns are paved, winding the first layer of fiber yarns on the second layer of fiber yarns.
Step four: paving a third layer of main material above the second layer of fiber yarns, taking the step three as the reference, paving the top surface of the next layer of main material after the fiber yarns of the previous layer pass through the broken parts at the holes and pass through the holes on the next layer of main material, paving the next layer of fiber yarns, and so on;
step five: after the last layer of main material is paved, the molding, autoclave molding or liquid molding is carried out, and during the molding, the sleeve consists of an inner cylinder and an outer cylinder, and the inner cylinder and the outer cylinder are meshed by two sections of sleeves, so that during the molding, the sleeve can be compressed together with the composite material, and simultaneously, the positions of the meshing teeth on the inner cylinder and the positions of the meshing teeth on the outer cylinder are staggered in the axial direction, so that the main material flows too much during the compression.
The foregoing description is only illustrative of the present invention and is not intended to limit the scope of the invention, and all equivalent structures or equivalent processes or direct or indirect application in other related technical fields are included in the scope of the present invention.
Claims (2)
1. A method for integrally forming a porous composite material is characterized by comprising the following steps of: comprises a main material, fiber filaments and a sleeve,
the sleeve comprises an inner cylinder and an outer cylinder, the outer diameter of the inner cylinder is the same as the inner diameter of the outer cylinder, the inner cylinder and the outer cylinder are both formed by meshing two sections of sleeves, the inner cylinder is formed by an inner first sleeve and an inner second sleeve, the outer cylinder is formed by an outer first sleeve and an outer second sleeve, the sleeves are respectively provided with a tooth and a tooth socket, the tooth and the tooth socket have the same shape and size, and in the axial direction, the position of the tooth on the inner cylinder and the position of the tooth on the outer cylinder are staggered;
the specific manufacturing steps are as follows:
step one: punching holes on each layer of main material, and then selecting a sleeve corresponding to the aperture;
step two: laying a first layer of main material, inserting the prepared sleeve into the hole, and then laying a first layer of fiber yarns on the first layer of main material;
step three: paving a second layer of main material above the first layer of fiber yarns, then paving a broken part of the first layer of fiber yarns, which is positioned at the hole, on the top surface of the second layer of main material after passing through the hole on the second layer of main material, and then paving the second layer of fiber yarns; step four: paving a third layer of main material above the second layer of fiber yarns, and performing the following steps based on the third step and the like;
step five: after the last layer of main material is laid, the material is molded, autoclave molded or liquid molded.
2. The method for integrally forming a perforated composite material according to claim 1, wherein: in the third step, after the second layer of fiber filaments is laid, the first layer of fiber filaments are wound on the second layer of fiber filaments.
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 CN109263088A (en) | 2019-01-25 |
| CN109263088B true 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 |
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| CN (1) | CN109263088B (en) |
Families Citing this family (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 |
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| Publication number | Publication date |
|---|---|
| CN109263088A (en) | 2019-01-25 |
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