CN102501389B - Method for preparing composite material lamination structure through interlamination heat slip - Google Patents
Method for preparing composite material lamination structure through interlamination heat slip Download PDFInfo
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Abstract
The invention which belongs to the technical field of resin matrix composite material molding relates to a method for preparing a composite material lamination structure through interlamination heat slip. According to the invention, molding is reached through utilizing the easy interlamination slip characteristic of resin components which compose the prepreg sheet of a section simple lamination composite material after heating to reduce the viscosity, setting a proper temperature and a proper time and allowing the lamination to slip in an enclosed die under the driving of an external pressure of an air pressure or a hydraulic pressure. The method which is established on the basis of original physical-chemical characteristics of the prepreg allows an arc corner area to be molded in a high quality mode. Compared with traditional autoclave technologies, the method of the invention has the characteristics of high efficiency, simple operation, low cost, and strong adaptability, and is suitable for the industrialization production.
Description
Technical field
The invention belongs to processing of polymer matrix composites technical field, relate to a kind of method of preparing composite material lamination structure through interlamination heat slip.
Background technology
Autoclave molding technology is the conventional process techniques of prepreg laminated composite materials shaping structures.The method has unique advantage in the time of moulding large-area flat-plate class formation, thereby is widely used in the industry manufacture of the operation rudder face (rudder, elevator, wing flap and leading edge etc.) of large-scale wallboard (wing and fuselage wallboard) and aerospace flight vehicle by aerospace industry circle.
But along with the development of aeronautical and space technology, autoclave molding technology is day by day challenged in the leading position in composite material forming field.On the one hand, the composite cost that the hydroelectric resources consumption of the equipment investment that autoclave is high and later stage flood tide etc. has caused this technique to prepare is high, its economy is had a greatly reduced quality, thereby impelled the formation of industrial quarters " cost degradation manufacture " theory.On the other hand, under the leading of " cost degradation manufacture " theory, cost degradation design also becomes new designer trends gradually, and integration design is the important directions of low-cost design.In integration design, because reaching the primary demand of structural member merit realizability, when making to form the structural member total number minimizing of aircraft, the volume of single-piece and complexity are all improving.And will manufacture the single-piece of large and complex structure time, it is awkward that autoclave technique just seems, thereby be badly in need of new technique and upgrade and substitute.
With regard to concrete structure, the large-scale wallboard of integration and operation rudder face generally can be decomposed into simple structure, these simple structures comprise I type or its general conventional variant C type (containing the different C type of local curvature) take wallboard as representative, what represent with frame, Liang Wei is U-shaped, V-type take leading edge as representative, and to play the stringer of booster action as the L-type of representative, Z-type, Ω type and π type etc.In the time of concrete process implementing, in order to complete the manufacture of the complex large-sized wallboard of integration, tend to adopt second bonding, glued joint or the technique of co-curing altogether, and the prerequisite that completes these techniques is exactly first to want prefabricated semi-solid preparation or complete above-mentioned simple structure of solidifying.Thereby the prefabricated or preparation of these simple structures just becomes the key that realizes manufacture.
Carrying out traditionally carry out the technique of paving on die face or die cavity time, because the comprehensive function of the rigidity of prepreg self and process implementing method, even if the simple member in some cross sections, the quality in arc transition district is also difficult to guarantee.This is mainly due in prepreg paving process, the prepreg self with certain rigidity is difficult to guarantee to have completely densified in the mold cavity of certain curvature or profile because of conventional pressure (as electric iron) or mechanical pressure (automated tape-laying machine), and then in later stage pressurization (being generally 0.6 MPa to 0.7 MPa) compacting process, uncompacted corner can be under the effect of high pressure, make turning outside form resin-rich area and inner side forms fiber fold, cause the mechanical characteristic of product deteriorated and then threaten the security of aviation aircraft.In addition, have the product at turning no matter be to adopt artificial paving or mechanical paving, the speed of paving is all lower, thereby has extended process cycle, has reduced manufacture efficiency.
Summary of the invention
The object of the invention is: propose one and can overcome in traditional autoclave technique because not tight paving causes cross section simple product corner quality deterioration problem, make to be stacked in and in closed mould, produce the hot slippage of interlayer and reach excipient, the paving of loaded down with trivial details and inefficient turning is converted into the method for a kind of preparing composite material lamination structure through interlamination heat slip of the hot sliding deformation of interlayer after dull and stereotyped paving.
Technical scheme of the present invention is: the operating procedure of the method is as follows:
(1) determine sliding deformation temperature and time, resin viscosity-temperature curve in test prepreg, the temperature spot that finds viscosity to equal (100 ± 5) handkerchief 〃 second on this curve is designated as T, the curing degree of Constant Temperature Detection resin under temperature T, the time point that records curing degree raising 10% is t, the temperature of sliding deformation is (T ± 5) degree Celsius, and the sliding deformation time is (t ± 5) minute;
(2) laminate panel paving, by default laying sequence, paving prepreg, forms laminate panel;
(3) form packaging body, take laminate panel as Mirror Symmetry center, complete the encapsulation to laminate panel by the order of laminate panel-separation layer-air-permeable layer-ductile layer, the wherein separation layer glass fabric of polytetrafluoroethylene (PTFE) that has been preimpregnation, thickness is 0.05 millimeter to 1.0 millimeters, the adhesive-bonded fabric that air-permeable layer is polyesters, and surface density is 50 grams every square metre to 200 grams every square metre, ductile layer is for having superplastic rubber or aluminium foil, and elongation is greater than 300%; Encapsulate complete assembly and be called packaging body;
(4) sliding deformation in closed mould, packaging body is heated in baking oven (T ± 5) degree Celsius, put into the closed mould conforming to shape of product, injecting gas or high temperature resistant deep fat form air pressure or the hydraulic pressure of 0.25 MPa to 0.45 MPa, make packaging body fit tightly excipient with mould in (t ± 5) minute;
(5) the curing and demoulding, completes solidifying and the demoulding of laminated construction by the original curing process of prepreg, forms final structure.
Described composite lay structural section comprises I type, C type, U-shaped, V-type, L-type, Z-type, Ω type or π type.
The prepreg of described composition laminated construction is continuous fiber prepreg, resin in prepreg is thermosetting resin, thermosetting resin is: epoxy resin, bimaleimide resin, thermoset polyimide resin, benzoxazine colophony, unsaturated polyester resin, phenolic resins or cyanate ester resin, in prepreg, the percentage by weight of resin is 33% to 38%.
Solidification process carries out in the general firing equipment auxiliary without the need for pressure, and this kind equipment comprises take heating wire or oily heat radiation baking oven and electromagnetic heater box as thermal source.
Advantage and beneficial effect that the present invention has are:
First, the present invention is based upon on the basis of original prepreg physicochemical characteristics, utilize the resin Composition viscosity after heating in the prepreg synusia of simple laminated composite materials to reduce the characteristic that is easy to interlayer slip, the region of moulding arc corners in high quality, the security that improves product.
The second, in this method, first simple cross sectional shape is reduced into plane, and then thermal deformation.This method, with respect to the directly paving on die face of traditional autoclave technique, has efficiency feature high, simple to operate.
The 3rd, this method can depart from the autoclave involving great expense and be cured in the general firing equipments such as baking oven, has low cost, adaptable feature, is applicable to suitability for industrialized production.
The present invention utilizes the resin Composition viscosity after heating in the prepreg synusia that forms the simple laminated composite materials in cross section to reduce the characteristic that is easy to interlayer slip, suitable temperature and time is set, under the driving of the external pressure such as air pressure or hydraulic pressure, make to be stacked in the object that produces interlayer slip in closed mould and reach excipient.
The specific embodiment
Below the present invention is described in further details.The present invention is a kind of method of preparing composite material lamination structure through interlamination heat slip, it is characterized in that, the operating procedure of the method is as follows:
(1) determine sliding deformation temperature and time, from prepreg or from suppliers, obtain the resin Composition prepreg, test resin temperature-viscosity curve, the temperature spot that finds viscosity to equal (100 ± 5) handkerchief 〃 second on this curve is designated as T, the curing degree of Constant Temperature Detection resin under temperature T, the time point that records curing degree raising 10% is t, and the temperature of sliding deformation is (T ± 5) degree Celsius, and the sliding deformation time is (t ± 5) minute;
(2) laminate panel paving, by default laying sequence, paving prepreg, forms laminate panel;
(3) form packaging body, take laminate panel as Mirror Symmetry center, complete the encapsulation to laminate panel by the order of laminate panel-separation layer-air-permeable layer-ductile layer, the wherein separation layer glass fabric of polytetrafluoroethylene (PTFE) that has been preimpregnation, thickness is 0.05 millimeter to 1.0 millimeters, the adhesive-bonded fabric that air-permeable layer is polyesters, and surface density is 50 grams every square metre to 200 grams every square metre, ductile layer is for having superplastic rubber or aluminium foil, and elongation is greater than 300%; Encapsulate complete assembly and be called packaging body;
(4) sliding deformation in closed mould, packaging body is heated in baking oven (T ± 5) degree Celsius, put into the closed mould conforming to shape of product, injecting gas or liquid form air pressure or the hydraulic pressure of 0.25 MPa to 0.45 MPa, make packaging body fit tightly excipient with mould in (t ± 5) minute;
(5) the curing and demoulding, completes solidifying and the demoulding of laminated construction by the original curing process of prepreg, forms final structure.
The simple cross section relating in the present invention comprises I type, C type, U-shaped, V-type, L-type, Z-type, Ω type or π type, the prepreg of described composition laminated construction is continuous fiber prepreg, the resin in prepreg is thermosetting resin, thermosetting resin can be: epoxy resin, bimaleimide resin, thermoset polyimide resin, benzoxazine colophony, unsaturated polyester resin, phenolic resins or cyanate ester resin.
Embodiment
Embodiment 1: prepare C type wallboard with T300/5228A epoxy prepreg
In this embodiment, preparing C type wallboard raw material used is T300/5228A epoxy prepreg.According to the temperature-viscosity curve of 5228A resin, it is 90 degrees Celsius that this resin viscosity in temperature-rise period is reduced to (100 ± 5) handkerchief 〃 second corresponding temperature spot, is 80 points of kinds in 90 lower resin solidifications degree centigrade, the 10% required time of improving.T300/5228A prepreg is first pressed to template blanking, then become laminate panel by the paving of design laying, select commercial separation layer, air-permeable layer and ductile layer complete the encapsulation to laminate panel, form packaging body, after being evacuated to more than-0.09 MPa to packaging body, be heated to (90 ± 5) degree Celsius, the working face of putting into sealing is the mould of C type, passing into gas makes air pressure arrive 0.45 MPa in (80 ± 5) minute, make plane wallboard be deformed into C type wallboard, complete curing by the set technique of T300/5228A epoxy prepreg, after cooling and demolding, obtain the good C type wallboard product of internal soundness.
Embodiment 2: prepare U-shaped beam with T300/5228A epoxy prepreg
This embodiment is different from embodiment 1 is that by die change be U-shaped beam mould, and other are identical with embodiment, have obtained the second best in quality U-shaped beam in internal soundness and turning.
Embodiment 3: prepare Ω type beam with CCF300/5228A epoxy prepreg
This embodiment is that from the different of embodiment 2 raw material are replaced by the preimpregnation of CCF300/5228A epoxy resin, is Ω type beam mould by die change simultaneously.Because the resin Composition in the preimpregnation of CCF300/5228A epoxy resin is still 5228A resin, so other parameters in this embodiment are identical with embodiment 2, obtain internal soundness and turning the second best in quality Ω type beam.
Embodiment 4: prepare L-type with T700/5224 epoxy prepreg and grow purlin
In this embodiment, preparing the long purlin of L-type raw material used is T700/5224 epoxy prepreg.According to the temperature-viscosity curve of 5224 resins, it is 105 degrees Celsius that this resin viscosity in temperature-rise period is reduced to (100 ± 5) handkerchief 〃 second corresponding temperature spot, is 60 points of kinds in 105 lower resin solidifications degree centigrade, the 10% required time of improving.T700/5224 prepreg is first pressed to template blanking, then become laminate panel by the paving of design laying, select commercial separation layer, air-permeable layer and ductile layer complete the encapsulation to laminate panel, form packaging body, after being evacuated to more than-0.09 MPa to packaging body, be heated to (90 ± 5) degree Celsius, the working face of putting into sealing is the mould of the long purlin of L-type, passing into gas makes air pressure arrive 0.35 MPa in (60 ± 5) minute, making plate deformation is the long purlin of L-type, complete curing by the set technique of T700/5224 epoxy prepreg, after cooling and demolding, obtain the long purlin of the good L-type of internal soundness product.
Embodiment 5: prepare V-type trailing edge with T300/5224 epoxy prepreg
This embodiment is that from the different of embodiment 4 raw material are replaced by T300/5224 epoxy prepreg, is V-type trailing edge mould by die change, adopts fire-resistant hydraulic fluid to pressurize, and pressure is 0.45 MPa.Because the resin Composition in T300/5224 epoxy prepreg is still 5224 resins, so other parameters in this embodiment are identical with embodiment 4, obtain the second best in quality V-type trailing edge in internal soundness and turning.
Embodiment 6: prepare U-shaped frame with T800/III type benzoxazine colophony prepreg
In this embodiment, preparing U-shaped frame raw material used is T800/ benzoxazine colophony resin prepreg material.According to the temperature-viscosity curve of benzoxazine colophony, it is 70 degrees Celsius that this resin viscosity in temperature-rise period is reduced to (100 ± 5) handkerchief 〃 second corresponding temperature spot, is 60 points of kinds in 70 lower resin solidifications degree centigrade, the 10% required time of improving.T800/ benzoxazine colophony prepreg is first pressed to template blanking, then become laminate panel by the paving of design laying, select commercial separation layer, air-permeable layer and ductile layer complete the encapsulation to laminate panel, form packaging body, after being evacuated to more than-0.09 MPa to packaging body, be heated to (70 ± 5) degree Celsius, the working face of putting into sealing is U-shaped mould, passing into high temperature resistant deep fat makes pressure arrive 0.4 MPa in (60 ± 5) minute, making plate deformation is U-shaped frame, complete curing by the set technique of T800/ benzoxazine colophony prepreg, after cooling and demolding, obtain the good U-shaped frame product of internal soundness.
Embodiment 7: prepare π type with CCF300/III type benzoxazine colophony prepreg and grow purlin
This embodiment is that from the different of embodiment 6 raw material are replaced by CCF300/ benzoxazine colophony prepreg, is the long purlin of π type mould by die change.Because the resin Composition in CCF300/ benzoxazine colophony prepreg is still III type benzoxazine colophony, so other parameters in this embodiment are identical with embodiment 6, obtain the long purlin of the second best in quality π type in internal soundness and turning.
Embodiment 8: prepare U-shaped plate with AS4/L polyimide type resin prepreg
In this embodiment, preparing U-shaped plate raw material used is AS4/L polyimide type resin prepreg.According to the temperature-viscosity curve of L-type polyimide resin, it is 260 degrees Celsius that this resin viscosity in temperature-rise period is reduced to (100 ± 5) handkerchief 〃 second corresponding temperature spot, is 30 points of kinds in 260 lower resin solidifications degree centigrade, the 10% required time of improving.AS4/L polyimide type resin prepreg is pressed to template blanking, then become laminate panel by the paving of design laying, select commercial separation layer, air-permeable layer and ductile layer complete the encapsulation to laminate panel, form packaging body, after being evacuated to more than-0.09 MPa to packaging body, be heated to (260 ± 5) degree Celsius, the working face of putting into sealing is U-shaped mould, passing into high temperature resistant deep fat makes pressure arrive 0.45 MPa in (30 ± 5) minute, making plate deformation is U-shaped frame, complete curing by the set technique of AS4/L polyimide type resin prepreg, after cooling and demolding, obtain the good U-shaped plate product of internal soundness.
Embodiment 9: prepare C type beam with G0827/L polyimide type resin prepreg
This embodiment is that from the different of embodiment 8 raw material are replaced by G0827/L polyimide type resin prepreg, is C type beam mould by die change.Because the resin Composition in G0827/L polyimide type resin prepreg is still L-type polyimide resin, so other parameters in this embodiment are identical with embodiment 8, obtain internal soundness and turning the second best in quality C type beam.
Embodiment 10: prepare Z with U3160/F type bimaleimide resin prepreg and grow purlin
In this embodiment, preparing the long purlin of Z raw material used is U3160/F type bimaleimide resin prepreg.According to the temperature-viscosity curve of F type bimaleimide resin, it is 140 degrees Celsius that this resin viscosity in temperature-rise period is reduced to (100 ± 5) handkerchief 〃 second corresponding temperature spot, is 40 points of kinds in 140 lower resin solidifications degree centigrade, the 10% required time of improving.U3160/F type bimaleimide resin prepreg is pressed to template blanking, then become laminate panel by the paving of design laying, select commercial separation layer, air-permeable layer and ductile layer complete the encapsulation to laminate panel, form packaging body, after being evacuated to more than-0.09 MPa to packaging body, be heated to (140 ± 5) degree Celsius, the mould that the working face of putting into sealing is Z-type, passing into high temperature resistant deep fat makes pressure arrive 0.25 MPa in (40 ± 5) minute, making plate deformation is the long purlin of Z-type, complete curing by the set technique of U3160/F type bimaleimide resin prepreg, after cooling and demolding, obtain the long purlin of the good Z of internal soundness product.
Embodiment 11: prepare V-type trailing edge with CF3031/F type bimaleimide resin prepreg
This embodiment is that from the different of embodiment 10 raw material are replaced by CF3031/F type bimaleimide resin prepreg, is V-type trailing edge mould by die change.Because the resin Composition in CF3031/F type bimaleimide resin prepreg is still F type bimaleimide resin, so other parameters in this embodiment are identical with embodiment 8, obtain internal soundness and turning the second best in quality V-type trailing edge product.
Claims (4)
1. a method for preparing composite material lamination structure through interlamination heat slip, is characterized in that, the operating procedure of the method is as follows:
(1) determine sliding deformation temperature and time, resin viscosity-temperature curve in test prepreg, the temperature spot that finds viscosity to equal for 100 ± 5 handkerchief 〃 seconds on this curve is designated as T, the curing degree of Constant Temperature Detection resin under temperature T, the time point that records curing degree raising 10% is t, the temperature of sliding deformation is T ± 5 degree Celsius, and the sliding deformation time is t ± 5 minute;
(2) laminate panel paving, by default laying sequence, paving prepreg, forms laminate panel;
(3) form packaging body, take laminate panel as Mirror Symmetry center, complete the encapsulation to laminate panel by the order of laminate panel-separation layer-air-permeable layer-ductile layer, the wherein separation layer glass fabric of polytetrafluoroethylene (PTFE) that has been preimpregnation, thickness is 0.05 millimeter to 1.0 millimeters, the adhesive-bonded fabric that air-permeable layer is polyesters, and surface density is 50 grams every square metre to 200 grams every square metre, ductile layer is for having superplastic rubber or aluminium foil, and elongation is greater than 300%; Encapsulate complete assembly and be called packaging body;
(4) sliding deformation in closed mould, packaging body is heated in baking oven to T ± 5 degree Celsius, put into the closed mould conforming to shape of product, injecting gas or high temperature resistant deep fat form air pressure or the hydraulic pressure of 0.25 MPa to 0.45 MPa, packaging body in t ± 5 minute with the mould excipient of having fitted;
(5) the curing and demoulding, completes solidifying and the demoulding of laminated construction by the curing process of used prepreg, forms final structure.
2. the method for a kind of preparing composite material lamination structure through interlamination heat slip according to claim 1, is characterized in that, described composite lay structural section comprises I type, C type, U-shaped, V-type, L-type, Z-type, Ω type or π type.
3. the method for a kind of preparing composite material lamination structure through interlamination heat slip according to claim 1, it is characterized in that, the prepreg of described composition laminated construction is continuous fiber prepreg, resin in prepreg is thermosetting resin, thermosetting resin is: epoxy resin, bimaleimide resin, thermoset polyimide resin, benzoxazine colophony, unsaturated polyester resin, phenolic resins or cyanate ester resin, in prepreg, the percentage by weight of resin is 33% to 38%.
4. the method for a kind of preparing composite material lamination structure through interlamination heat slip according to claim 1, it is characterized in that, solidification process carries out in the general firing equipment auxiliary without the need for pressure, and this kind equipment comprises take heating wire or oily heat radiation baking oven and electromagnetic heater box as thermal source.
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| CN106346845B (en) * | 2016-08-23 | 2018-04-24 | 北京汽车集团有限公司 | Middle passage reinforcing plate and preparation method thereof and vehicle |
| CN108544767B (en) * | 2018-04-10 | 2020-02-11 | 中航复合材料有限责任公司 | Forming method and forming tool for J-shaped blank of composite material |
| CN110757830B (en) * | 2018-07-26 | 2022-07-26 | 中国商用飞机有限责任公司 | Thermal diaphragm forming method for hat-shaped stringer |
| CN114801243B (en) * | 2022-04-15 | 2023-04-25 | 西安电子科技大学 | Method for actively controlling slip of laminate in composite member |
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| GB2267457A (en) * | 1992-06-05 | 1993-12-08 | British Aerospace | Manufacture of components from composite material |
| EP0604298A1 (en) * | 1992-12-23 | 1994-06-29 | Eurocopter France | Composite thermoplastic blade, in particular for helicopter shrouded tail rotor, and its manufacturing process |
| GB2348163A (en) * | 1999-03-24 | 2000-09-27 | Secr Defence | A fibre-reinforced composite |
| CN101080313A (en) * | 2004-12-16 | 2007-11-28 | 斯奈克玛动力部件公司 | Densification of fibrous structures by resin transfer moulding for making thick parts of composite material |
| CN101254652A (en) * | 2007-12-28 | 2008-09-03 | 西安交通大学 | In-situ consolidation fibre laying method and device for producing resin-based compound material component |
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Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2267457A (en) * | 1992-06-05 | 1993-12-08 | British Aerospace | Manufacture of components from composite material |
| EP0604298A1 (en) * | 1992-12-23 | 1994-06-29 | Eurocopter France | Composite thermoplastic blade, in particular for helicopter shrouded tail rotor, and its manufacturing process |
| GB2348163A (en) * | 1999-03-24 | 2000-09-27 | Secr Defence | A fibre-reinforced composite |
| CN101080313A (en) * | 2004-12-16 | 2007-11-28 | 斯奈克玛动力部件公司 | Densification of fibrous structures by resin transfer moulding for making thick parts of composite material |
| CN101254652A (en) * | 2007-12-28 | 2008-09-03 | 西安交通大学 | In-situ consolidation fibre laying method and device for producing resin-based compound material component |
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