CN102267235A - Device and method for laying composite ribbons by using laser - Google Patents
Device and method for laying composite ribbons by using laser Download PDFInfo
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- CN102267235A CN102267235A CN2011101959892A CN201110195989A CN102267235A CN 102267235 A CN102267235 A CN 102267235A CN 2011101959892 A CN2011101959892 A CN 2011101959892A CN 201110195989 A CN201110195989 A CN 201110195989A CN 102267235 A CN102267235 A CN 102267235A
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Abstract
The invention relates to a device for laying composite ribbons by using laser, which comprises a ribbon-releasing coil, a glue spreader, a guide unit and a compression roller; in addition, the device also comprises a laser device which is arranged in a mode capable of emitting a laser beam to a bonding part of a processed component and a composite ribbon, and can carry out point-by-point scanning on a bonding surface of the composite ribbon laid on the processed component by using the laser beam, so that a photopolymerisable reaction is generated on a thin layer on the surface of a scanned area, and then the surface of the composite ribbon reaches a state of curing. According to the invention, through using a laser continuous curing process, in the process of laying a composite ribbon, the surface of the composite ribbon is subjected to point-by-point scanning by using the laser beam so as to enable the surface of the composite ribbon to reach a state of curing, and then the composite ribbon is pressed and fixed by using the compression roller, thereby forming a molded surface of a product.
Description
Technical field
The present invention relates to a kind of composite silk ribbon laying apparatus and method thereof of utilizing laser, be used for utilizing laser aid to assist and lay the composite silk ribbon that aircraft is used, belong to the laser technology application in aviation manufacturing field.
Background technology
Composite has lightweight, high strength, high-modulus, structure-function integration and integrated manufacturing system (IMS), is easy to make advantages such as large-scale component, is widely used in aerospace industry.The composite consumption has become one of important indicator of the advance of estimating aerospace vehicle, so composite use amount aboard is increasing.Along with the continuous increase of aircaft configuration size and being on the increase of aircraft composite use amount, be used to make the special equipment of composite element and technology is developed rapidly and extensive use.The automatic laying apparatus of composite is mainly used in the product parts that specific (special) requirements is arranged of industrial circles such as making Aero-Space, boats and ships, automobile.
It is the general designation that forming technique is laid in automatic tow laying forming technique and automatic arrowband that composite is laid forming technique automatically, is a kind of automated manufacturing technology that grows up on existing winding technology and automatic laying technology basis.Present automatic laying technology at first needs to make the preimpregnation band, according to shop layer direction of determining based on structure and shop layer thickness, to organize the surface that fiber preimpregnation yarn bundle (or arrowband) is routed to the target core by multivariant paving head according to certain rule more, while thermoplastic preimpregnation yarn bundle (or arrowband) in the process of deployment, and use the hold-down roller compacting, thereby form the profile of goods.At last, will lay the moulding that is heating and curing of moulding product, obtain finished product.
If use heat cure formers such as autoclave, hot press, its process cycle is long, causes cost to improve.At present, the research composite fiber is laid the direction of forming technique will cancel the heat cure molding procedure exactly, by thermoplastic fibre laying technology and thermosetting laying technology are combined with Electron beam curing technology, manufacturing time, material consumption and the energy can be significantly reduced, the good mechanical performance can also be obtained.But, Electron beam curing technology uses electron beam as thermal source, need high vacuum environment to prevent electron scattering, on machine table, a vacuum chamber with regulation space must be set, thereby influenced the flexibility ratio of processing largely, in addition, in the required pumpdown time, also seriously reduced production efficiency.
In addition, in order to guarantee that original shop layer has better caking property on preimpregnation yarn bundle (or arrowband) and the mould, and prevent bubble, guarantee product quality, process equipment that need be special when making preimpregnation yarn bundle (or arrowband), therefore, cause complex manufacturing technology, manufacturing expense to improve.
Summary of the invention
The present invention makes for solving the above-mentioned problems in the prior art point, its purpose is to provide a kind of composite silk ribbon laying apparatus and method thereof of utilizing laser, laser technology is combined with the fleece-laying technology, in composite laying process, utilize laser beam that point by point scanning is carried out on the wet fiber bundle surface with certain resin content, thereby heat the region surface that is scanned of wet fiber bundle, make it become solid state, use the hold-down roller compacting then, thereby form the profile of goods.Therefore, processing technology is simple, and shorten process time, and manufacturing cost reduces.
A kind of composite silk ribbon laying apparatus that utilizes laser provided by the invention, have the roll coil of strip of putting, glue spreader, pilot unit and pressure roller, it also comprises laser aid, it is configured to can be towards the bonding part emission laser beam of processed member and above-mentioned composite silk ribbon, the laser beam of launching by utilization carries out continual point by point scanning to the adhesive surface that is routed to the composite silk ribbon on the processed member, makes the thin layer that is scanned region surface produce photopolymerization reaction and reach solid state.
In addition, a kind of composite silk ribbon laying method that utilizes laser provided by the invention, it may further comprise the steps: put the band step, along with the rotation of putting the roll coil of strip, send above-mentioned composite silk ribbon the roll coil of strip continuously from being wound with putting of above-mentioned composite silk ribbon; The gluing step makes the glue that is coated on the glue spreader be applied on will being adhered on the side surface on the processed member of above-mentioned composite silk ribbon; The guiding step, by the above-mentioned composite silk ribbon of traction clamping mechanisms grip through gluing, and by after the guide roller channeling conduct, above-mentioned composite silk ribbon is transported between processed member and the pressure roller; Lay step, the laser beam that utilization is launched from laser aid carries out point by point scanning to the adhesive surface that is routed to the composite silk ribbon on the processed member, make the thin layer that is scanned region surface produce photopolymerization reaction and reach solid state, utilize pressure roller to carry out roll-in then, thereby just above-mentioned composite silk ribbon press solidly on the surface of processed member.
In addition, above-mentioned composite silk ribbon laying method can also comprise the shearing step, and size is sheared above-mentioned composite silk ribbon in accordance with regulations.
According to aforesaid the present invention, because this technology is used the continuous curing process of laser, do not need prepared beforehand and properly store the preimpregnation band, cancelled the manufacturing link of preimpregnation yarn bundle/band, in the manufacture process of composite element, directly make, promptly use, equipment needed thereby is simple, manufacturing process obtains simplifying, avoided because wasting phenomenon and the quality problems that the inefficacy of preimpregnation band causes, the environmental pollution that has produced when also having avoided special making preimpregnation band can effectively improve the laying process efficient of composite.Adopt the wet fiber bundle in the process of deployment, the filametntary free degree is big in the fibre bundle, can realize flexible manufacturing.And the continuous curing process of laser can be implemented in same with thermosetting compound material system and thermoplastic system and directly add the hot consolidation typing in the process of deployment, has simplified technology, has reduced cost.The continuous curing process of laser can carry out in atmosphere, does not need vacuum chamber, is not subjected to the workpiece size restrictions; The continuous curing process processing flexibility of laser is big, and the flexibility ratio height is not limited by the workpiece shape, can make complicated, meticulous part; In addition,, Wavelength of Laser absorbs because easily being scribbled the wet fiber bundle of resin, and concentration of energy, the heat-affected zone is little, rapidly to wet fiber Shu Jinhang heating, realize solidifying completely at short notice, be significantly less than electron beam processing the circulation timei of the continuous curing process of laser.Because photopolymerization reaction is based on the effect of light rather than based on the effect of heat, so only need the lower lasing light emitter of power when working.
This technology realizes the automatic laying moulding of aircraft composite element in aviation manufacturing field.
The invention has the beneficial effects as follows:
1) do not need prepared beforehand and appropriate storage preimpregnation band, manufacturing process obtains simplifying;
2) avoided because wasting phenomenon and the quality problems that the inefficacy of preimpregnation band causes the environmental pollution that has produced when also having avoided special making preimpregnation band;
3) the intrafascicular filametntary free degree of wet fiber is big, can realize flexible manufacturing;
4) the continuous curing process of laser can be implemented in same with thermosetting compound material system and thermoplastic system and directly add the hot consolidation typing in the process of deployment;
5) do not need heating system, simplified technology, reduced cost.
6) easy to operate, technological equipment is simple economy more also, is not subjected to the restriction of expensive autoclave size, also is not subjected to the restriction of relevant heat-transfer devices, can prepare the large scale product.
Description of drawings
Fig. 1 is the integrally-built schematic diagram of the composite silk ribbon laying apparatus that utilizes laser that the present invention relates to of expression.
Fig. 2 is the flow chart of the composite silk ribbon laying method that utilizes laser that the present invention relates to of expression.
Reference numeral
1 puts the roll coil of strip 2 glue spreaders 3 traction clamping devices
4 guide rollers, 5 cutting mechanisms, 6 laser aids
7 pressure rollers, 8 pressure roller driving mechanisms
9 composite silk ribbons, 10 have been laid component surface
11 processed members
The specific embodiment
Below, the preferred implementation that present invention will be described in detail with reference to the accompanying.
Fig. 1 is the integrally-built schematic diagram of the composite silk ribbon laying apparatus that utilizes laser that the present invention relates to of expression.As shown in the drawing, utilize the composite silk ribbon laying apparatus of laser to comprise: as wire-feeding part put the roll coil of strip 1, twining the composite silk ribbon, in rotation, can send the composite silk ribbon, at this, this composite silk ribbon for example can be the wet fiber bundle with certain resin content; As the glue spreader 2 of gluing part, to from the above-mentioned surface coating of putting the composite silk ribbon that the roll coil of strip 1 sends; As the traction clamping device 3 and the guide roller 4 of targeting part, the composite silk ribbon behind guiding and the clamping gluing is carried this composite silk ribbon so that stretch straightly; As the cutting mechanism 5 of cutting out section, size is sheared this composite silk ribbon in accordance with regulations; As the pressure roller driving mechanism 8 of the pressure roller 7 of laying part and this pressure roller 7 of driving, the composite silk ribbon that is used for being laid on alignedly on the processed member 11 presses solidly; And laser aid 6, being arranged to can be towards the bonding part emission laser beam of processed member 11 and composite silk ribbon 9, the laser beam of launching by utilization carries out point by point scanning to the adhesive surface that is routed to the composite silk ribbon 9 on the processed member 11, makes the thin layer that is scanned region surface produce photopolymerization reaction and reach solid state.At this, this laser aid 6 is preferred to adopt the laser beam wavelength that is sent easily to be absorbed and the lasing light emitter of concentration of energy, like this, just can heat the wet fiber surface rapidly at short notice; And this laser aid is preferably needs lower powered lasing light emitter.
Below, describe the composite silk ribbon laying method that utilizes aforesaid composite silk ribbon laying apparatus to carry out in detail.
At first, along with by motor-driven rotation of putting the roll coil of strip 1, send composite silk ribbon 9 roll coil of strip 1 continuously from being wound with putting of composite silk ribbon.This composite silk ribbon 9 is successively through glue spreader 2, traction clamping device 3 and guide roller 4, wherein, through glue spreader 2 time, is coated on glue on the glue spreader 2 and is applied on the side surface on the processed member 11 of will being adhered to of above-mentioned composite silk ribbon 9.The composite silk ribbon 9 that is gummed is by traction clamping device 3 clampings, and when being directed to roller 4 guidings, after cutting mechanism 5, is transported between processed member 11 and the pressure roller 7.
At this, at first be to align with the lower end edge of processed member 11 and be superimposed in the end of composite silk ribbon 9, between the composite silk ribbon 9 of other parts and the surface of processed member 11 a little across distance and underlapped.Then, the laser beam that utilization is penetrated from laser aid 6 carries out point by point scanning to the adhesive surface of composite silk ribbon 9, make the thin layer that is scanned region surface produce photopolymerization reaction and reach solid state, simultaneously, utilization is pressed solidly composite silk ribbon 9 on the surface of processed member 11 successively by the pressure roller that pressure roller driving mechanisms such as cylinder 8 drive.
After this processed member 11 was finished with the bonding process of composite silk ribbon 9, cutting mechanism 5 size was in accordance with regulations sheared composite silk ribbon 9.At this moment, cutting mechanism 5 requires to guarantee that fabric strip is sheared with arbitrarily angled before heating, and otch is neat, does not produce burr.
Then, repeat the aforesaid operations step, carry out the composite silk ribbon of the processed member 11 of the next one is laid operation.
Though at this preferred implementation of the present invention has been described, this embodiment is to propose as example, not delimit the scope of the invention.These new embodiments can be implemented by other multiple mode, in the scope that does not break away from main idea of the present invention, can carry out multiple omission, displacement, change.Therefore, these embodiments maybe this distortion are contained in scope of the present invention or the main idea, and are contained in the invention and its equivalency range of claims record.
Claims (4)
1. a composite silk ribbon laying apparatus that utilizes laser has the roll coil of strip of putting, glue spreader, pilot unit and pressure roller, it is characterized in that,
Also comprise laser aid, it is configured to can be towards the bonding part emission laser beam of processed member and above-mentioned composite silk ribbon, the laser beam of launching by utilization carries out point by point scanning to the adhesive surface that is routed to the composite silk ribbon on the processed member, makes the thin layer that is scanned region surface produce photopolymerization reaction and reach solid state.
2. the composite silk ribbon laying apparatus that utilizes laser according to claim 1 is characterized in that described laser beam carries out continual point by point scanning to wet fiber bundle surface.
3. a composite silk ribbon laying method that utilizes laser is characterized in that, may further comprise the steps:
Put the band step,, send above-mentioned composite silk ribbon the roll coil of strip continuously from being wound with putting of above-mentioned composite silk ribbon along with the rotation of putting the roll coil of strip;
The gluing step makes the glue that is coated on the glue spreader be applied on will being adhered on the side surface on the processed member of above-mentioned composite silk ribbon;
The guiding step, by the above-mentioned composite silk ribbon of traction clamping mechanisms grip through gluing, and by after the guide roller channeling conduct, above-mentioned composite silk ribbon is transported between processed member and the pressure roller;
Lay step, the laser beam that utilization is launched from laser aid carries out point by point scanning to the adhesive surface that is routed to the composite silk ribbon on the processed member, make the thin layer that is scanned region surface produce photopolymerization reaction and reach solid state, utilize pressure roller to carry out roll-in then, thereby just above-mentioned composite silk ribbon press solidly on the surface of processed member.
4. the composite silk ribbon laying method that utilizes laser according to claim 3 is characterized in that also comprise the shearing step, size is sheared above-mentioned composite silk ribbon in accordance with regulations.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011101959892A CN102267235A (en) | 2011-07-13 | 2011-07-13 | Device and method for laying composite ribbons by using laser |
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| Application Number | Priority Date | Filing Date | Title |
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| CN2011101959892A CN102267235A (en) | 2011-07-13 | 2011-07-13 | Device and method for laying composite ribbons by using laser |
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| CN2011101959892A Pending CN102267235A (en) | 2011-07-13 | 2011-07-13 | Device and method for laying composite ribbons by using laser |
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Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105946254A (en) * | 2016-07-14 | 2016-09-21 | 王瑛玮 | Composite material prepared through pultrusion and twining composite forming and laser curing |
| CN106182815A (en) * | 2016-07-14 | 2016-12-07 | 王瑛玮 | Pultrusion laser curing prepares composite material bar material |
| CN106182799A (en) * | 2016-07-14 | 2016-12-07 | 王瑛玮 | Lay-up molding laser curing prepares composite |
| CN106182521A (en) * | 2016-07-14 | 2016-12-07 | 王瑛玮 | Wrapping formed laser curing prepares composite |
| CN106182816A (en) * | 2016-07-14 | 2016-12-07 | 王瑛玮 | Pultrusion is wound around composite molding laser curing and prepares composite material hollow section bar |
| CN106182818A (en) * | 2016-07-14 | 2016-12-07 | 王瑛玮 | Pultrusion laser baking oven composite curing preparation abnormity composite |
| CN106182820A (en) * | 2016-07-14 | 2016-12-07 | 王瑛玮 | Pultrusion laser curing prepares composite material anchor shaft |
| CN106182819A (en) * | 2016-07-14 | 2016-12-07 | 王瑛玮 | Pultrusion laser curing prepares composite material hollow section bar |
| CN106273557A (en) * | 2016-08-22 | 2017-01-04 | 王瑛玮 | Pultrusion laser curing prepares composite |
| CN108656568A (en) * | 2018-04-23 | 2018-10-16 | 广州蓝圣智能科技有限公司 | A kind of automatic rubberizing equipment stood for automobile tail fin group on production line |
| CN115635210A (en) * | 2022-12-23 | 2023-01-24 | 湖南湘投金天钛金属股份有限公司 | TC4 titanium alloy plate surface layer high-entropy alloy modification method |
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Cited By (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106182820A (en) * | 2016-07-14 | 2016-12-07 | 王瑛玮 | Pultrusion laser curing prepares composite material anchor shaft |
| CN105946254A (en) * | 2016-07-14 | 2016-09-21 | 王瑛玮 | Composite material prepared through pultrusion and twining composite forming and laser curing |
| CN106182799A (en) * | 2016-07-14 | 2016-12-07 | 王瑛玮 | Lay-up molding laser curing prepares composite |
| CN106182521A (en) * | 2016-07-14 | 2016-12-07 | 王瑛玮 | Wrapping formed laser curing prepares composite |
| CN106182816A (en) * | 2016-07-14 | 2016-12-07 | 王瑛玮 | Pultrusion is wound around composite molding laser curing and prepares composite material hollow section bar |
| CN106182818A (en) * | 2016-07-14 | 2016-12-07 | 王瑛玮 | Pultrusion laser baking oven composite curing preparation abnormity composite |
| CN106182815A (en) * | 2016-07-14 | 2016-12-07 | 王瑛玮 | Pultrusion laser curing prepares composite material bar material |
| CN106182819A (en) * | 2016-07-14 | 2016-12-07 | 王瑛玮 | Pultrusion laser curing prepares composite material hollow section bar |
| CN105946254B (en) * | 2016-07-14 | 2019-04-16 | 安徽森德新材料科技发展有限公司 | Pultrusion winding composite molding laser curing prepares composite material |
| CN106182816B (en) * | 2016-07-14 | 2019-05-07 | 安徽森德新材料科技发展有限公司 | The method that pultrusion winding composite molding laser curing prepares composite material hollow profile |
| CN106273557A (en) * | 2016-08-22 | 2017-01-04 | 王瑛玮 | Pultrusion laser curing prepares composite |
| CN108656568A (en) * | 2018-04-23 | 2018-10-16 | 广州蓝圣智能科技有限公司 | A kind of automatic rubberizing equipment stood for automobile tail fin group on production line |
| CN115635210A (en) * | 2022-12-23 | 2023-01-24 | 湖南湘投金天钛金属股份有限公司 | TC4 titanium alloy plate surface layer high-entropy alloy modification method |
| CN115635210B (en) * | 2022-12-23 | 2023-06-23 | 湖南湘投金天钛金属股份有限公司 | TC4 titanium alloy plate surface layer high-entropy alloy modification method |
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