CN103522555A - Integrated forming manufacturing method of I-shaped beam made from composite material - Google Patents
Integrated forming manufacturing method of I-shaped beam made from composite material Download PDFInfo
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- CN103522555A CN103522555A CN201310507643.0A CN201310507643A CN103522555A CN 103522555 A CN103522555 A CN 103522555A CN 201310507643 A CN201310507643 A CN 201310507643A CN 103522555 A CN103522555 A CN 103522555A
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- mould
- fiber cloth
- shaped beam
- die
- composite
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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
- 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
- B29C70/345—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 matched moulds
Abstract
The invention discloses an integrated forming manufacturing method of an I-shaped beam made from a composite material. The method comprises the following steps: I, preparing a die; II, clipping, impregnating and overlaying fiber cloth; III, laminating the fiber cloth in the die; IV, hot-pressing and curing the laminated fiber cloth through a hot-press and the die; and V, opening the die. The method provided by the invention has the following advantages that material damage caused by punching connection and low connecting strength between a flange and a web caused by gluing connection are overcome when the flange and the web of the split type I-shaped beam made from the composite material obtained by existing manufacturing method are combined and connected, and the integral strength of the I-shaped beam made from the composite material is improved.
Description
Technical field
The invention belongs to field of compound material, be specifically related to a kind of global formation manufacture method of composite I-shaped beam.
Background technology
At present, the manufacture method of composite I-shaped beam is first by the method for dull and stereotyped mold pressing, prepare respectively its upper and lower plate face (being called wing plate) and middle plate face (being called web), then the method connecting by bolt or viscose glue, wing plate and web are carried out to being connected each other, obtain composite I-shaped beam.Because wing plate and the web of this I-beam is first to prepare respectively, and then link together, wing plate and web belong to split-type structural on structural form, are not monolithic constructions.
The subject matter that the wing plate of composite I-shaped beam and web are bolted is: this connected mode must be punched in the wing plate of composite I-shaped beam and web, and drilling technology will destroy the intensity of composite I-shaped beam.
The subject matter that the wing plate of composite I-shaped beam is connected by viscose glue with web is: under the stretching or shear loads strengthening outside, owing to having obvious interface between the wing plate of composite and web, and adhesive strength is often inadequate, in the abutting edge (interface) of wing plate and web, be easy to rupture.
Summary of the invention
Technical problem to be solved by this invention is just to provide a kind of global formation manufacture method of composite I-shaped beam, it can overcome material damage that existing split-type structural composite I-shaped beam causes because punching connects and connect the defects such as bonding strength is low between the wing plate that causes and web, the intensity of reinforced composite I-beam because of viscose glue.
Technical problem to be solved by this invention is to realize by such technical scheme, and it includes following steps:
The preparation of step 1, mould
Mould is comprised of 4 Die and mould plates, is respectively upper and lower, left and right Die and mould plate;
The cutting out of step 2, fiber cloth, impregnation and lamination
Composite material fibre cloth is cut out by 2 kinds of sizes, and the fiber cloth after cutting out is fully dipped after resin, according to composite I-shaped beam stand under load direction, carries out fiber cloth lamination, has obtained dipping 4 fiber cloth laminations under resin, hygrometric state;
After to upper and lower, left and right Die and mould plate smearing release agent, the fiber cloth lamination under 4 hygrometric states is placed on respectively to the position that mould is corresponding;
Step 4, by hot press and mould, fiber cloth lamination is carried out to hot-press solidifying.
After step 4, the upper and lower, left and right Die and mould plate of decorporating, just obtains the composite I-shaped beam of global formation.
Owing to having adopted technique scheme, the composite fiber plate (being web) in the middle of the upper and lower composite fiber plate (being wing plate) of this I-beam and I-beam is a monolithic construction, between the wing plate of I-beam and web, there is no interface.From I-beam fiber characteristics, wing plate and the fiber between web of composite I-shaped beam are continuous, and this makes the intensity of composite I-shaped beam higher than the intensity of the I-beam of the split-type structural being obtained by existing composite I-shaped beam manufacture method.
The present invention has advantages of as follows: due to composite I-shaped beam global formation, do not need punching or bonding, while having avoided split type composite I-shaped beam wing plate that existing manufacture method obtains and web to be connected, because punching connects the material damage cause and to connect between the wing plate that causes and web bonding strength low because of viscose glue, improved the bulk strength of composite I-shaped beam.
Accompanying drawing explanation
Accompanying drawing of the present invention is described as follows:
Fig. 1 is whole mould structure of the present invention and composite I-shaped beam shaping schematic view;
In figure: 1. mold plate; 2. bed die plate; 3. left Die and mould plate; 4. right Die and mould plate; 5. fiber cloth lamination.
The specific embodiment
Below in conjunction with drawings and Examples, the invention will be further described:
The present invention includes following steps:
The preparation of step 1, mould
As shown in Figure 1, mould is comprised of 4 Die and mould plates, is respectively mold plate 1, bed die plate 2, left Die and mould plate 3 and right Die and mould plate 4;
The cutting out of step 2, fiber cloth, impregnation and lamination
Composite material fibre cloth is cut out by 2 kinds of sizes, the fiber cloth that a kind of dimensions is wing plate, the fiber cloth that another kind of dimensions is web; Fiber cloth after cutting out is fully dipped after resin, according to composite I-shaped beam stand under load direction, carried out fiber cloth lamination, obtained dipping 4 fiber cloth laminations under resin, hygrometric state;
As shown in Figure 1, after mold plate 1, bed die plate 2, left Die and mould plate 3 and right Die and mould plate 4 smearing release agents, the fiber cloth lamination 5 under 4 hygrometric states is placed on respectively to the position that mould is corresponding;
Step 4, by hot press and mould, fiber cloth lamination is carried out to hot-press solidifying;
In hot-press solidifying process, briquetting pressure is 110MPa, and forming temperature is 120 ℃, and pressurize and hardening time are 12 hours;
After step 4, the upper and lower, left and right Die and mould plate of decorporating, just obtains the composite I-shaped beam of global formation.
In this method invention, the wing plate of I-beam and web are made in I-beam compression molding process simultaneously, and wing plate and the web of the composite I-shaped beam obtaining are monolithic constructions, and the fiber between wing plate and web is continuous.And the upper and lower seamed edge that this I-beam is prepared the left and right Die and mould plate of mould can be designed as the chamferings of different sizes, between the wing plate that makes the I-beam that obtains and web, there is the knuckle of different sizes.In general, this knuckle is larger, and the stress of wing plate and web transition position is concentrated less, and the intensity of corresponding I-beam is higher.
Claims (1)
1. a global formation manufacture method for composite I-shaped beam, is characterized in that, includes following steps:
The preparation of step 1, mould
Mould is comprised of 4 Die and mould plates, is respectively upper and lower, left and right Die and mould plate;
The cutting out of step 2, fiber cloth, impregnation and lamination
Composite material fibre cloth is cut out by 2 kinds of sizes, and the fiber cloth after cutting out is fully dipped after resin, according to composite I-shaped beam stand under load direction, carries out fiber cloth lamination, has obtained dipping 4 fiber cloth laminations under resin, hygrometric state;
Step 3, fiber cloth are stacked in mould and place
After to upper and lower, left and right Die and mould plate smearing release agent, the fiber cloth lamination under 4 hygrometric states is placed on respectively to the position that mould is corresponding;
Step 4, by hot press and mould, fiber cloth lamination is carried out to hot-press solidifying;
Step 5, die sinking
After step 4, the upper and lower, left and right Die and mould plate of decorporating, just obtains the composite I-shaped beam of global formation.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310507643.0A CN103522555B (en) | 2013-10-25 | 2013-10-25 | A kind of global formation manufacture method of composite I-shaped beam |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310507643.0A CN103522555B (en) | 2013-10-25 | 2013-10-25 | A kind of global formation manufacture method of composite I-shaped beam |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN103522555A true CN103522555A (en) | 2014-01-22 |
| CN103522555B CN103522555B (en) | 2016-05-25 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201310507643.0A Expired - Fee Related CN103522555B (en) | 2013-10-25 | 2013-10-25 | A kind of global formation manufacture method of composite I-shaped beam |
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| CN (1) | CN103522555B (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107399092A (en) * | 2017-09-04 | 2017-11-28 | 江西洪都航空工业集团有限责任公司 | A kind of preparation facilities of composite I-shaped beam and preparation method thereof |
| CN108953978A (en) * | 2018-06-19 | 2018-12-07 | 哈尔滨工程大学 | A kind of composite material truss and preparation method thereof of H-type web member and the assembly of rectangular chord member |
| CN109927316A (en) * | 2019-04-01 | 2019-06-25 | 苏州华特时代碳纤维有限公司 | A kind of batch forming method of composite material I-shaped beam |
| CN110103489A (en) * | 2019-06-14 | 2019-08-09 | 哈尔滨工业大学 | A kind of melting adhered forming method of High Performance Thermoplastic Composites I-beam |
| CN112606271A (en) * | 2020-12-14 | 2021-04-06 | 陕西天翌天线股份有限公司 | I-beam compression molding die and using method thereof |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4379798A (en) * | 1981-01-12 | 1983-04-12 | Mcdonnell Douglas Corporation | Integral woven reinforcement for structural components |
| US4789594A (en) * | 1987-04-15 | 1988-12-06 | The Boeing Company | Method of forming composite radius fillers |
| JPS6475226A (en) * | 1987-09-16 | 1989-03-20 | Mitsubishi Heavy Ind Ltd | Fiber structural body for reinforcement of joint part of beam material made of composite and its manufacture |
| CN101394988A (en) * | 2006-03-15 | 2009-03-25 | 东丽株式会社 | Process for manufacturing preform and apparatus therefor |
| CN102026798A (en) * | 2008-05-16 | 2011-04-20 | 波音公司 | Reinforced stiffeners and method for making the same |
| CN202248527U (en) * | 2011-09-13 | 2012-05-30 | 福建省龙岩龙能粉煤灰综合利用有限公司 | I-shaped bamboo-based sectional bar made of pulverized-coal ash |
| CN202686489U (en) * | 2012-08-20 | 2013-01-23 | 武琳 | Once roller forming H-shaped beam |
| CN202719360U (en) * | 2011-12-17 | 2013-02-06 | 欧创塑料建材(浙江)有限公司 | Polyurethane composite transverse H-shaped section and shaping system |
-
2013
- 2013-10-25 CN CN201310507643.0A patent/CN103522555B/en not_active Expired - Fee Related
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4379798A (en) * | 1981-01-12 | 1983-04-12 | Mcdonnell Douglas Corporation | Integral woven reinforcement for structural components |
| US4789594A (en) * | 1987-04-15 | 1988-12-06 | The Boeing Company | Method of forming composite radius fillers |
| JPS6475226A (en) * | 1987-09-16 | 1989-03-20 | Mitsubishi Heavy Ind Ltd | Fiber structural body for reinforcement of joint part of beam material made of composite and its manufacture |
| CN101394988A (en) * | 2006-03-15 | 2009-03-25 | 东丽株式会社 | Process for manufacturing preform and apparatus therefor |
| CN102026798A (en) * | 2008-05-16 | 2011-04-20 | 波音公司 | Reinforced stiffeners and method for making the same |
| CN202248527U (en) * | 2011-09-13 | 2012-05-30 | 福建省龙岩龙能粉煤灰综合利用有限公司 | I-shaped bamboo-based sectional bar made of pulverized-coal ash |
| CN202719360U (en) * | 2011-12-17 | 2013-02-06 | 欧创塑料建材(浙江)有限公司 | Polyurethane composite transverse H-shaped section and shaping system |
| CN202686489U (en) * | 2012-08-20 | 2013-01-23 | 武琳 | Once roller forming H-shaped beam |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107399092A (en) * | 2017-09-04 | 2017-11-28 | 江西洪都航空工业集团有限责任公司 | A kind of preparation facilities of composite I-shaped beam and preparation method thereof |
| CN107399092B (en) * | 2017-09-04 | 2019-09-13 | 江西洪都航空工业集团有限责任公司 | A kind of preparation facilities and preparation method thereof of composite material I-shaped beam |
| CN108953978A (en) * | 2018-06-19 | 2018-12-07 | 哈尔滨工程大学 | A kind of composite material truss and preparation method thereof of H-type web member and the assembly of rectangular chord member |
| CN109927316A (en) * | 2019-04-01 | 2019-06-25 | 苏州华特时代碳纤维有限公司 | A kind of batch forming method of composite material I-shaped beam |
| CN110103489A (en) * | 2019-06-14 | 2019-08-09 | 哈尔滨工业大学 | A kind of melting adhered forming method of High Performance Thermoplastic Composites I-beam |
| CN110103489B (en) * | 2019-06-14 | 2021-04-20 | 哈尔滨工业大学 | Fusion bonding forming method for high-performance thermoplastic composite material I-beam |
| CN112606271A (en) * | 2020-12-14 | 2021-04-06 | 陕西天翌天线股份有限公司 | I-beam compression molding die and using method thereof |
Also Published As
| Publication number | Publication date |
|---|---|
| CN103522555B (en) | 2016-05-25 |
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Granted publication date: 20160525 Termination date: 20191025 |