CN103192528A - Method for co-curing and co-moulding titanium alloy and composite material part - Google Patents
Method for co-curing and co-moulding titanium alloy and composite material part Download PDFInfo
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- CN103192528A CN103192528A CN2013101461848A CN201310146184A CN103192528A CN 103192528 A CN103192528 A CN 103192528A CN 2013101461848 A CN2013101461848 A CN 2013101461848A CN 201310146184 A CN201310146184 A CN 201310146184A CN 103192528 A CN103192528 A CN 103192528A
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Abstract
The invention belongs to the technology for co-curing a composite material and a titanium alloy plate, and relates to a method for co-curing and co-moulding titanium alloy and a composite material part. According to the invention, due to application of a metal pressing mould fixture, co-curing and co-moulding of a titanium alloy plate and high-temperature carbon fibre prepreg are realized; the problem of being low in cementing quality of the titanium alloy plate and the composite material part because of over-high curvature is avoided; the quality stability of products is increased; furthermore, a gel mould J-99B and an expansion gel mould J-94 are used in a combined manner; the clearance of the adhesive surface is also filled while the adhesive quality is increased; the clearance generation possibility of the adhesive surface is avoided; simultaneously, connection is realized without a metal connecting part; the weight of the product is reduced; the intensity of the product is ensured; and the service life of the product is increased.
Description
Technical field
The invention belongs to composite and titanium alloy sheet co-curing technology, relate to the method for a kind of titanium alloy and the moulding of composite material element co-curing.
Background technology
At present, composite is widely used in the manufacturing of helicopter structure part.Because design requirement, indivedual composite material elements need have carrying high temperature, shock proof characteristic, and for satisfying this design requirement, the bonding titanium alloy plate of composite material element surface reaches the characteristic demand.Therefore, the bonding quality of titanium alloy plate and composite material element is the index of reflection composite material element local surfaces high temperature resistance.So the technique for sticking method affect of composite material element surface and titanium alloy plate part high temperature resistance, shock proof characteristic.
The process that traditional metal sheet and composite material element surface are bonding:
1. normal temperature bonded process
For preventing the distortion of composite regelate, generally use normal temperature glue to carry out bonding to metal sheet and composite material element surface
This method bonding quality poor stability, splicing face intensity is low.
2. normal temperature glue riveting method
Because normal temperature glueds joint and to make the glue-joint strength of metal sheet and composite material element surface not high, carrying out after normal temperature gluedd joint, the use holdfast of loosing core is strengthened being connected to metal sheet and composite material element
This method causes certain damage to composite material surface, and using rivet to increase product weight influences product service life simultaneously.Simultaneously, be subjected to the influence of product structure and rivet instructions for use, this method can't be used at the deep camber composite material element, the development of restriction composite material element forming technique.
Summary of the invention
It is little to the objective of the invention is to propose a kind of composite material surface damage, and product weight is light, and can be applicable to the forming method of deep camber titanium alloy and composite material element co-curing.
Technical solution of the present invention is,
1) preparation co-curing frock
According to the requirement of product digital-to-analogue, make the co-curing frock, the frock material therefor is aluminium or steel, tool structure is upper and lower pressing mold;
2) the shop layer solidifies
At first, according to product requirement, carry out composite material element shop layer, after shop layer operation finished, glued joint shop, surface glued membrane J-99B at composite material element shop layer, titanium alloy sheet after the pickling is gluedd joint face in 8 hours, spray primer J-100, glued joint regional area interpolation expansion glued membrane J-94 on the surperficial glued membrane J-99B at composite material element shop layer, titanium alloy sheet is placed on composite material element surface;
3) curing molding
Solidification of hot-press tank, variations in temperature is: first intermediate temperature setting: 135 ℃ ± 5 ℃ of temperature, constant temperature 1 hour, back hot setting: 180 ℃ ± 5 ℃ of temperature, constant temperature 2.5 hours, maximum 2 ℃/minute of heating rate, 3 ℃/minute of rate of temperature fall, are come out of the stove below 40 ℃ at release below 60 ℃.
Described composite material element is the high-temperature carbon fiber prepreg.
The advantage that the present invention has and beneficial effect, the present invention uses the metal stamping and pressing frock, realize the co-curing moulding of titanium alloy plate and high-temperature carbon fiber prepreg, avoided the titanium alloy plate because of the influence that curvature is excessive and the composite material element bonding quality is not high, improved constant product quality.Glued membrane J-99B and expansion glued membrane J-94's is used in combination in addition, when having promoted bonding quality, also fill glueing joint the face gap, avoided splicing face the possibility in gap to occur, simultaneously do not use metal connecting piece to connect and reduced product weight, guarantee product strength, improved product service life.
Description of drawings
Fig. 1 is high-temperature carbon fiber preimpregnation cloth and titanium alloy plate splicing face structural representation among the present invention.
Among the figure, 1. high-temperature carbon fiber prepreg, 2. expansion glued membrane J-94,3. glued membrane J-99B, 4. titanium alloy plate
The specific embodiment
1) preparation co-curing frock
According to the requirement of product digital-to-analogue, make the co-curing frock, the frock material therefor is aluminium or steel, tool structure is upper and lower pressing mold;
2) titanium alloy plate preparation
3) shop layer and matched moulds
At first, according to the product structure requirement, carry out composite material element 1 shop layer, after shop layer operation finished, glued joint shop, surface glued membrane 2(J-99B at composite material element 1 shop layer), with the spray of the titanium alloy sheet 4 splicing faces after pickling primer J-100, layer glueds joint a surperficial glued membrane 2(J-99B in composite material element 1 shop) go up regional area (glued joint the relatively large zone of the curvature of face, area size is corresponding with the relatively large zone of curvature) interpolation expansion glued membrane 3(J-94), after titanium alloy sheet 4 is placed on composite material element surface, upper and lower pressing mold is carried out matched moulds.
Working environment is: operate temperature in air conditioning room: 18-24 ℃, humidity: 40-65%, clean dustless.
1) curing and cleaning
Solidification of hot-press tank, variations in temperature is: first intermediate temperature setting (middle temperature 135 ℃ ± 5 ℃, 1 hour), back hot setting (high temperature 180 ℃ ± 5 ℃, 2 hours+30 minutes), maximum 2 ℃/minute of heating rate, 3 ℃/minute of rate of temperature fall, release below 60 ℃, come out of the stove the back cleaning product surface of coming out of the stove below 40 ℃.
Embodiment
At first, according to certain product structure requirement, carry out composite material element shop layer, after finishing 5 floor height temperature carbon fiber prepregs shop layer operation (being of a size of 500 ㎜ * 500 ㎜), glued joint shop, surface glued membrane J-99B(at composite material element shop layer and be of a size of 300 ㎜ * 300 ㎜), with the spray of the titanium alloy sheet splicing face after pickling primer J-100, glued joint regional area (the R angle is greater than 9 zones) interpolation expansion glued membrane J-94 (being of a size of 200 ㎜ * 200 ㎜) on the surperficial glued membrane J-99B at composite material element shop layer, after titanium alloy sheet is placed on composite material element surface, will go up, dip mold carries out matched moulds.
Claims (2)
1. the method for a titanium alloy and the moulding of composite material element co-curing is characterized in that,
1) preparation co-curing frock
According to the requirement of product digital-to-analogue, make the co-curing frock, the frock material therefor is aluminium or steel, tool structure is upper and lower pressing mold;
2) the shop layer solidifies
At first, according to product requirement, carry out composite material element shop layer, after shop layer operation finished, glued joint shop, surface glued membrane J-99B at composite material element shop layer, titanium alloy sheet after the pickling is gluedd joint face in 8 hours, spray primer J-100, glued joint regional area interpolation expansion glued membrane J-94 on the surperficial glued membrane J-99B at composite material element shop layer, titanium alloy sheet is placed on composite material element surface;
3) curing molding
Solidification of hot-press tank, variations in temperature is: first intermediate temperature setting: 135 ℃ ± 5 ℃ of temperature, constant temperature 1 hour, back hot setting: 180 ℃ ± 5 ℃ of temperature, constant temperature 2.5 hours, maximum 2 ℃/minute of heating rate, 3 ℃/minute of rate of temperature fall, are come out of the stove below 40 ℃ at release below 60 ℃.
2. the method for a kind of titanium alloy according to claim 1 and the moulding of composite material element co-curing is characterized in that, described composite material element is the high-temperature carbon fiber prepreg.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN201310146184.8A CN103192528B (en) | 2013-04-24 | 2013-04-24 | Method for co-curing and co-moulding titanium alloy and composite material part |
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| CN201310146184.8A CN103192528B (en) | 2013-04-24 | 2013-04-24 | Method for co-curing and co-moulding titanium alloy and composite material part |
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| CN103192528A true CN103192528A (en) | 2013-07-10 |
| CN103192528B CN103192528B (en) | 2015-05-27 |
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Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104339504A (en) * | 2013-08-05 | 2015-02-11 | 哈尔滨飞机工业集团有限责任公司 | Method for eliminating sinking of R corner of front edge of side end plate |
| CN105799162A (en) * | 2016-04-18 | 2016-07-27 | 江西洪都航空工业集团有限责任公司 | Application method of protective film-shaped primer of aluminum alloy cementing surface |
| CN107856315A (en) * | 2017-10-30 | 2018-03-30 | 江苏恒神股份有限公司 | A kind of flexible pressure control adhesive technology |
| CN108099223A (en) * | 2017-12-27 | 2018-06-01 | 沈阳浦利尔科技有限公司 | Composite material/metallic stacked structure multiple tube co-curing manufacturing method |
| CN108749265A (en) * | 2018-04-27 | 2018-11-06 | 中铝材料应用研究院有限公司 | A kind of connection method at automobile steel aluminium combination covering flange position |
| CN109291459A (en) * | 2018-08-02 | 2019-02-01 | 哈尔滨飞机工业集团有限责任公司 | Composite plys process |
| CN110067797A (en) * | 2019-04-23 | 2019-07-30 | 四川九洲电器集团有限责任公司 | A method of it is glued towards airborne thin wall metalwork and nonmetal parts |
| CN112157966A (en) * | 2020-09-29 | 2021-01-01 | 首钢集团有限公司 | Fiber reinforced metal material composite board |
| CN114683558A (en) * | 2022-04-06 | 2022-07-01 | 航天海鹰(镇江)特种材料有限公司 | Gluing method for metal wrapping edges of composite material blades |
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| CN1746021A (en) * | 2004-09-09 | 2006-03-15 | 航天特种材料及应用研究所 | Reinforced fibre metal laminated composite materials and production thereof |
| US20070074737A1 (en) * | 2005-09-30 | 2007-04-05 | Airbus Espana, S.L. | Method of surface treatment of composite material structures with atmospheric plasma beams |
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Cited By (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104339504A (en) * | 2013-08-05 | 2015-02-11 | 哈尔滨飞机工业集团有限责任公司 | Method for eliminating sinking of R corner of front edge of side end plate |
| CN104339504B (en) * | 2013-08-05 | 2017-07-25 | 哈尔滨飞机工业集团有限责任公司 | The removing method of side end panel leading edge R corner recess |
| CN105799162A (en) * | 2016-04-18 | 2016-07-27 | 江西洪都航空工业集团有限责任公司 | Application method of protective film-shaped primer of aluminum alloy cementing surface |
| CN105799162B (en) * | 2016-04-18 | 2017-09-08 | 江西洪都航空工业集团有限责任公司 | A kind of aluminium alloy glue surfaces protect the application method of membranaceous primer |
| CN107856315A (en) * | 2017-10-30 | 2018-03-30 | 江苏恒神股份有限公司 | A kind of flexible pressure control adhesive technology |
| CN108099223A (en) * | 2017-12-27 | 2018-06-01 | 沈阳浦利尔科技有限公司 | Composite material/metallic stacked structure multiple tube co-curing manufacturing method |
| CN108749265A (en) * | 2018-04-27 | 2018-11-06 | 中铝材料应用研究院有限公司 | A kind of connection method at automobile steel aluminium combination covering flange position |
| CN109291459A (en) * | 2018-08-02 | 2019-02-01 | 哈尔滨飞机工业集团有限责任公司 | Composite plys process |
| CN110067797A (en) * | 2019-04-23 | 2019-07-30 | 四川九洲电器集团有限责任公司 | A method of it is glued towards airborne thin wall metalwork and nonmetal parts |
| CN110067797B (en) * | 2019-04-23 | 2020-09-08 | 四川九洲电器集团有限责任公司 | Method for adhering airborne thin-wall metal piece and non-metal piece |
| CN112157966A (en) * | 2020-09-29 | 2021-01-01 | 首钢集团有限公司 | Fiber reinforced metal material composite board |
| CN114683558A (en) * | 2022-04-06 | 2022-07-01 | 航天海鹰(镇江)特种材料有限公司 | Gluing method for metal wrapping edges of composite material blades |
| CN114683558B (en) * | 2022-04-06 | 2023-10-03 | 航天海鹰(镇江)特种材料有限公司 | Cementing method for metal edge-covering of composite material blade |
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| CN103192528B (en) | 2015-05-27 |
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