CN103496173A - Manufacturing method of composite material laminated plate with holes - Google Patents
Manufacturing method of composite material laminated plate with holes Download PDFInfo
- Publication number
- CN103496173A CN103496173A CN201310411498.6A CN201310411498A CN103496173A CN 103496173 A CN103496173 A CN 103496173A CN 201310411498 A CN201310411498 A CN 201310411498A CN 103496173 A CN103496173 A CN 103496173A
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- China
- Prior art keywords
- fiber cloth
- plate
- laminated plate
- mould
- pin
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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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- 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
-
- 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 manufacturing method of a composite material laminated plate with holes. The manufacturing method comprises the following steps: a step I of forming through holes in upper and lower mould boards, manufacturing pins with corresponding dimensions corresponding to the through holes of the mould boards, wherein one end of each of the pins is a flat end, and the other end of each of the pins is machined with chamfer, and the flat end of each of the pins is inserted into the lower mould board; a step II of manufacturing and gum dipping of fiber cloths; a step III of coating a de-molding agent on the upper and lower mould boards and the pins, laminating the fiber cloths under a semi-dried state according to a preset fiber direction of the composite material laminated plate, and enabling fibers in each layer of the filter cloths to bypass pins in the lower mould board during laminating; a step IV of compounding the mould boards to carry hot-pressing and curing; and a step V of opening a mould. The manufacturing method disclosed by the invention has the advantage that fibers at holes of the composite material laminated plate are retained and reasonably distributed near the holes of the composite material laminated plate, so that strength of the composite material laminated plate with holes is far greater than that of a composite material laminated plate with holes obtained by an existing hole-making method.
Description
Technical field
The present invention relates to composite, be specifically related to the pertusate composite laminated plate manufacture method of a kind of tool.
Background technology
Composite laminated plate (or housing), because of process limitation, can not be accomplished the size needed and reach the shape needed in a lot of situations.Therefore, often need to carry out connection each other to them.The main method that composite laminated plate connects is by screw or pin, and these screws or pin are installed, and the hole with screw or pin cooperation must be arranged in composite laminated plate.
At present, the common preparation method of the pertusate composite laminated plate of tool adopts machining process: first by compression-moulding methods, prepare composite laminated plate, then the composite laminated plate obtained is holed or the machining such as punching, obtained the hole needed.Chinese Patent Application No. is 201210399254.6, name is called " the carbon-fiber-reinforcomposite composite material layer plywood of controlling based on drill thrust is without the layering boring method " and discloses " in drill bit drilling carbon-fiber-reinforcomposite composite material layer plywood process; the drilling axial force of controlling drill bit is less than boring layering critical thrust value Fa all the time ", and this method has been avoided the boring lamination defect of carbon-fiber-reinforcomposite composite material layer plywood.China Patent No. is 201010132202.5 to disclose a kind of " fibrous composite aircraft target ship laser accurate method for drilling and its device ", adopt the laser without contact method for drilling, the problems such as the wire drawing that while having overcome the employing bit bore, drill thrust causes, layering, fibrous fracture, cutting residual stress and deformation.
The problem that the method for drilling of existing composite laminated plate exists is, the fiber at composite hole place is cut off, and reduced composite laminated plate and the intensity of the composite structure that is assembled into.Existing composite laminated plate method for drilling also causes hole edge wire drawing, layering equivalent damage to destroy, the intensity of the composite structure that has also reduced composite laminated plate and be assembled into, make near the hole of composite laminated plate and hole the Dangerous Place that becomes that whole composite laminated plate and composite structure fracture destroy.
Summary of the invention
The fiber that technical problem to be solved by this invention just is to provide a kind of composite hole place be not cut off, can maintain composite laminated plate and composite structure intensity, the pertusate composite laminated plate manufacture method of tool.
Solve the problems of the technologies described above, the present invention includes
Step 1, mould preparation
Offer through hole on upper and lower Die and mould plate; The through hole of corresponding Die and mould plate is made the pin of corresponding size; One end of pin is tack, other end chamfering; Pin tack one end is inserted in the bed die plate;
The making of step 2, fiber cloth and impregnation
Fiber cloth is cut out to suitable dimension according to the mould size, then fiber cloth is fully dipped to resin, the fiber cloth of having dipped resin is dried to processing;
To upper and lower Die and mould plate and pin smearing release agent; By partly drying fiber cloth under state by default composite laminated plate machine direction, carry out laying on the bed die plate, during laying, allow the fiber in every layer of fiber cloth walk around the pin in the bed die plate;
Step 4, Die and mould plate matched moulds carry out hot-press solidifying
After the reliable laminating of each passing at pin layer fiber cloth, the mold plate that closes, and allow the pin in the bed die plate insert reliably in the corresponding aperture in the mold plate; Mold integral is put into to flat-bed press, the fiber cloth lamination is carried out to the hot-press solidifying processing;
Step 5, die sinking
The straight pin of first decorporating in mould, then open mould, obtains the pertusate composite laminated plate of tool.
Owing to having adopted technique scheme, the fiber at hole place is distributed in around hole continuously, makes to have high intensity near the hole of composite laminated plate.The present invention has advantages of as follows: the fiber at composite laminated plate hole place is retained, and reasonably be distributed near the hole of composite laminated plate the intensity of the pertusate composite laminated plate of tool that the intensity that makes the pertusate composite laminated plate of tool obtains much larger than existing method for drilling.
The accompanying drawing explanation
Accompanying drawing of the present invention is described as follows:
The structural representation that Fig. 1 is upper and lower Die and mould plate of the present invention;
Fig. 2 is the schematic diagram of fiber cloth between upper and lower template.
In figure: 1. mold plate; 2. bed die plate; 3. pin; 4. fiber cloth.
The specific embodiment
Below in conjunction with drawings and Examples, the invention will be further described:
The present invention includes
Step 1, mould preparation
As shown in Figure 1, on mold plate 1, bed die plate 2, offer an exhausting hole, the through hole of corresponding Die and mould plate is made the pin 3 of corresponding size, one end of pin 3 is tack, large chamfered is made in other end end, makes fiber easily walk around straight pin, and pin tack one end is inserted in bed die plate 2; The size of pin 3, shape and determining positions size, shape and the position of hole of composite laminated plate, the hole of composite laminated plate is determined according to actual service condition;
The making of step 2, fiber cloth and impregnation
Fiber cloth is cut out to suitable dimension according to the mould size, then fiber cloth is fully dipped to resin, the fiber cloth of having dipped resin is dried to processing; This fiber cloth can be the fiber cloth (fiber cloth of quadrature) that latitude is arranged, and can be also the fiber cloth (unidirectional fiber cloth) without latitude, the optional glass fabric of fiber cloth or carbon cloth; Dip the optional epoxy resin of resin used or phenolic resins etc.;
To upper and lower Die and mould plate and pin smearing release agent; As shown in Figure 2, partly drying fiber cloth 4 under state by default composite laminated plate machine direction, carry out laying on bed die plate 2, during laying, allow the fiber in every layer of fiber cloth 4 walk around the pin 3 in bed die plate 2;
Step 4, Die and mould plate matched moulds carry out hot-press solidifying
After the reliable laminating of each passing at pin layer fiber cloth, close with the mold plate with the pin corresponding aperture; While closing the mold plate, note allowing the pin in the bed die plate insert reliably in the through hole of mold plate; Mold integral is put into to flat-bed press the fiber cloth lamination is carried out to the hot-press solidifying processing, forming temperature is 120 ℃.Briquetting pressure is 110Mpa, and pressurize and hardening time are 12 hours;
Step 5, die sinking
The straight pin of first decorporating after the composite lay solidified forming in mould, then open mould, obtain fiber around pore size distribution, the pertusate composite laminated plate of tool.
Claims (2)
1. the pertusate composite laminated plate manufacture method of tool, is characterized in that, comprises the following steps:
Step 1, mould preparation
Offer through hole on upper and lower Die and mould plate; The through hole of corresponding Die and mould plate is made the pin of corresponding size; One end of pin is tack, other end chamfering; Pin tack one end is inserted in the bed die plate;
The making of step 2, fiber cloth and impregnation
Fiber cloth is cut out to suitable dimension according to the mould size, then fiber cloth is fully dipped to resin, the fiber cloth of having dipped resin is dried to processing;
Step 3, fiber cloth lamination
To upper and lower Die and mould plate and pin smearing release agent; By partly drying fiber cloth under state by default composite laminated plate machine direction, carry out laying on the bed die plate, during laying, allow the fiber in every layer of fiber cloth walk around the pin in the bed die plate;
Step 4, Die and mould plate matched moulds carry out hot-press solidifying
After the reliable laminating of each passing at pin layer fiber cloth, the mold plate that closes, and allow the pin in the bed die plate insert reliably in the corresponding aperture in the mold plate; Mold integral is put into to flat-bed press, the fiber cloth lamination is carried out to the hot-press solidifying processing;
Step 5, die sinking
The straight pin of first decorporating in mould, then open mould, obtains the pertusate composite laminated plate of tool.
2. the pertusate composite laminated plate manufacture method of tool according to claim 1, is characterized in that, described fiber cloth is the fiber cloth of latitude to be arranged or without the fiber cloth of latitude.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310411498.6A CN103496173B (en) | 2013-09-11 | 2013-09-11 | A kind of have pertusate composite laminated plate manufacture method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310411498.6A CN103496173B (en) | 2013-09-11 | 2013-09-11 | A kind of have pertusate composite laminated plate manufacture method |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN103496173A true CN103496173A (en) | 2014-01-08 |
| CN103496173B CN103496173B (en) | 2016-06-08 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201310411498.6A Expired - Fee Related CN103496173B (en) | 2013-09-11 | 2013-09-11 | A kind of have pertusate composite laminated plate manufacture method |
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Cited By (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105479771A (en) * | 2015-12-30 | 2016-04-13 | 吉林大学 | Manufacturing method for carbon fiber composite plate and self-punching riveting die and method for carbon fiber composite plate and aluminum alloy plate |
| CN105479770A (en) * | 2015-12-30 | 2016-04-13 | 吉林大学 | Preparing method of carbon fiber composite board and non-rivet riveting die and method of carbon fiber composite board and aluminum alloy board |
| CN106273219A (en) * | 2016-08-19 | 2017-01-04 | 福州福耀模具科技有限公司 | Production technology and the process units thereof of adnexa directly it is molded on fibre board |
| CN107379597A (en) * | 2017-09-08 | 2017-11-24 | 上海伊瑟卫浴有限公司 | A kind of production method of step-in type bathtub |
| CN109501326A (en) * | 2018-11-13 | 2019-03-22 | 贵州大自然科技股份有限公司 | A kind of identification method and device of palm fiber elastic material |
| CN110103487A (en) * | 2019-05-16 | 2019-08-09 | 沈阳飞机工业（集团）有限公司 | A kind of process forming Z-section composite material parts |
| CN110249126A (en) * | 2016-12-28 | 2019-09-17 | 维斯塔斯风力系统有限公司 | For wind turbine rotor blade to be connected to the connector and correlation technique of rotor hub |
| 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 |
| CN110588020A (en) * | 2019-08-22 | 2019-12-20 | 成都飞机工业（集团）有限责任公司 | Automatic tape laying method for hexagonal hole of composite material |
| CN111016218A (en) * | 2019-12-31 | 2020-04-17 | 北玻院(滕州)复合材料有限公司 | Preparation method of composite material lifting lug and composite material lifting lug |
| CN111618940A (en) * | 2020-06-05 | 2020-09-04 | 万丰飞机工业有限公司 | Novel civil aircraft wing maintenance cover hole drilling tool manufacturing process |
| CN113084931A (en) * | 2021-03-31 | 2021-07-09 | 五冶集团上海有限公司 | Method for cutting furnace hole fiber product |
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| GB2168647A (en) * | 1984-12-07 | 1986-06-25 | Smith H R | Fibre reinforced polymer articles |
| EP1382436A1 (en) * | 2002-07-19 | 2004-01-21 | Vincent Duqueine | Method for moulding a composite article and moulding apparatus for carrying out said method |
| CN101870172A (en) * | 2010-06-09 | 2010-10-27 | 哈尔滨工业大学 | Preparation mould of carbon fiber composite material casing of airplane and aircraft and forming method thereof |
| WO2012143190A1 (en) * | 2011-04-19 | 2012-10-26 | Nijhuis Willem Aloysius | Multi-layer laminate structure with reversible bonding |
-
2013
- 2013-09-11 CN CN201310411498.6A patent/CN103496173B/en not_active Expired - Fee Related
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2168647A (en) * | 1984-12-07 | 1986-06-25 | Smith H R | Fibre reinforced polymer articles |
| EP1382436A1 (en) * | 2002-07-19 | 2004-01-21 | Vincent Duqueine | Method for moulding a composite article and moulding apparatus for carrying out said method |
| CN101870172A (en) * | 2010-06-09 | 2010-10-27 | 哈尔滨工业大学 | Preparation mould of carbon fiber composite material casing of airplane and aircraft and forming method thereof |
| WO2012143190A1 (en) * | 2011-04-19 | 2012-10-26 | Nijhuis Willem Aloysius | Multi-layer laminate structure with reversible bonding |
Cited By (18)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105479771A (en) * | 2015-12-30 | 2016-04-13 | 吉林大学 | Manufacturing method for carbon fiber composite plate and self-punching riveting die and method for carbon fiber composite plate and aluminum alloy plate |
| CN105479770A (en) * | 2015-12-30 | 2016-04-13 | 吉林大学 | Preparing method of carbon fiber composite board and non-rivet riveting die and method of carbon fiber composite board and aluminum alloy board |
| CN105479771B (en) * | 2015-12-30 | 2017-09-26 | 吉林大学 | The preparation method of carbon fibre composite plate and its self-piercing riveting mould and method with aluminium alloy plate |
| CN106273219A (en) * | 2016-08-19 | 2017-01-04 | 福州福耀模具科技有限公司 | Production technology and the process units thereof of adnexa directly it is molded on fibre board |
| CN110249126B (en) * | 2016-12-28 | 2021-08-13 | 维斯塔斯风力系统有限公司 | Joint for connecting a wind turbine rotor blade to a rotor hub and related method |
| CN110249126A (en) * | 2016-12-28 | 2019-09-17 | 维斯塔斯风力系统有限公司 | For wind turbine rotor blade to be connected to the connector and correlation technique of rotor hub |
| US11022093B2 (en) | 2016-12-28 | 2021-06-01 | Vestas Wind Systems A/S | Joint for connecting a wind turbine rotor blade to a rotor hub and associated methods |
| CN107379597A (en) * | 2017-09-08 | 2017-11-24 | 上海伊瑟卫浴有限公司 | A kind of production method of step-in type bathtub |
| CN109501326A (en) * | 2018-11-13 | 2019-03-22 | 贵州大自然科技股份有限公司 | A kind of identification method and device of palm fiber elastic material |
| CN110103487B (en) * | 2019-05-16 | 2021-05-18 | 沈阳飞机工业（集团）有限公司 | Process method for forming composite material part with Z-shaped section |
| CN110103487A (en) * | 2019-05-16 | 2019-08-09 | 沈阳飞机工业（集团）有限公司 | A kind of process forming Z-section composite material parts |
| CN110588020A (en) * | 2019-08-22 | 2019-12-20 | 成都飞机工业（集团）有限责任公司 | Automatic tape laying method for hexagonal hole of composite material |
| 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 |
| CN111016218A (en) * | 2019-12-31 | 2020-04-17 | 北玻院(滕州)复合材料有限公司 | Preparation method of composite material lifting lug and composite material lifting lug |
| CN111016218B (en) * | 2019-12-31 | 2021-08-17 | 北玻院(滕州)复合材料有限公司 | Preparation method of composite material lifting lug and composite material lifting lug |
| CN111618940A (en) * | 2020-06-05 | 2020-09-04 | 万丰飞机工业有限公司 | Novel civil aircraft wing maintenance cover hole drilling tool manufacturing process |
| CN111618940B (en) * | 2020-06-05 | 2022-02-08 | 浙江万丰飞机制造有限公司 | Novel civil aircraft wing maintenance cover hole drilling tool manufacturing process |
| CN113084931A (en) * | 2021-03-31 | 2021-07-09 | 五冶集团上海有限公司 | Method for cutting furnace hole fiber product |
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| CN103496173B (en) | 2016-06-08 |
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