CN102501389A - 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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- CN102501389A CN102501389A CN2011103623369A CN201110362336A CN102501389A CN 102501389 A CN102501389 A CN 102501389A CN 2011103623369 A CN2011103623369 A CN 2011103623369A CN 201110362336 A CN201110362336 A CN 201110362336A CN 102501389 A CN102501389 A CN 102501389A
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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 the processing of polymer matrix composites technical field, relate to the method that the hot slippage of a kind of interlayer prepares the composite lay structure.
Background technology
The autoclave molding technology is the conventional process techniques of prepreg laminated composite materials shaping structures.This method has special advantages when moulding large-area flat-plate class formation, thereby is widely used in the industry manufacturing 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 development of aviation and aerospace technology, the autoclave molding technology is day by day challenged in the leading position in composite material forming field.On the one hand, the hydroelectric resources consumption of equipment investment that autoclave is high and later stage flood tide etc. has caused the composite cost of this prepared high, its economy is had a greatly reduced quality, thereby impelled the formation of industrial quarters " cost degradation manufacturing " theory.On the other hand, under the leading of " cost degradation manufacturing " theory, the new designer trends of cost degradation design also becoming gradually, the integration design then is the important directions of low-cost design.In integration designs,, make that when the structural member total number that constitutes aircraft reduced, the volume of single-piece and complexity were all in improve because of needs reach the primary demand that the structural member function realizes property.And will make the single-piece of large and complex structure the time, it is awkward that autoclave technology just seems, thereby be badly in need of new technology and upgrade alternative.
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 with the wallboard being I type or its general conventional variant C type (containing the different C type of local curvature) of representative, with the U type of frame, Liang Wei representative, are the V-type of representative with the leading edge; And be the L type of representative with the stringer that plays booster action, Z type, Ω type and π type etc.When concrete process implementing, in order to accomplish the manufacturing of the complex large-sized wallboard of integration, tend to adopt second bonding, glued joint or the technology of co-curing altogether, and the prerequisite of accomplishing these technologies is exactly to want prefabricated semi-solid preparation or complete above-mentioned simple structure of solidifying earlier.Thereby the prefabricated or preparation of these simple structures just becomes the key that realizes manufacturing.
Carrying out traditionally when on die face or die cavity, carrying out the technology of paving, because the comprehensive function of prepreg self rigidity and process implementing method, even if the simple member in some cross sections, the quality in arc transition district also is difficult to assurance.This mainly is because in prepreg paving process; The prepreg that self has certain rigidity is difficult to guarantee compacting fully on mold cavity with certain curvature or profile because of conventional pressure (like 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 the turning outside form rich resin region and the inboard fiber fold that forms, cause the mechanical characteristic deterioration of product 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 prolonged process cycle, has reduced manufacturing efficient.
Summary of the invention
The objective of the invention is: propose a kind of can overcome in traditional autoclave technology cause cross section simple product corner quality deterioration problem because of not tight paving; Make to be stacked in to produce the hot slippage of interlayer in the closed mould and reach excipient that the hot slippage of a kind of interlayer that the paving of loaded down with trivial details and inefficient turning is converted into the hot sliding deformation of interlayer after the dull and stereotyped paving prepares the method for composite lay structure.
Technical scheme of the present invention is: the operating procedure of this method is following:
(1) confirms the sliding deformation temperature and time; Resin viscosity-temperature curve in the test prepreg; The temperature spot that on this curve, finds viscosity to equal (100 ± 5) handkerchief second is designated as T, and it is t that the curing degree of Constant Temperature Detection resin under temperature T, record curing degree improve 10% time point; Then the temperature of sliding deformation is (T ± 5) degree centigrade, and the sliding deformation time is (t ± 5) minute;
(2) laminate panel paving, by preset shop sequence of layer, the paving prepreg forms laminate panel;
(3) forming packaging body, is the minute surface symmetrical centre with the laminate panel, presses the order of laminate panel-separation layer-air-permeable layer-ductile layer and accomplishes the encapsulation to laminate panel; The separation layer glass fabric of polytetrafluoroethylene (PTFE) that has been preimpregnation wherein; Thickness is 0.05 millimeter to 1.0 millimeters, and air-permeable layer is the adhesive-bonded fabric of polyesters, surface density be 50 the gram every square metre to 200 the gram every square metre; Ductile layer is for having superplastic rubber or aluminium foil, and elongation is greater than 300%; The assembly that encapsulation finishes is called packaging body;
(4) sliding deformation in the closed mould; Packaging body is heated in baking oven (T ± 5) degree centigrade; Put into the closed mould that conforms to shape of product; Injecting gas or high temperature resistant deep fat form the air pressure or the hydraulic pressure of 0.25 MPa to 0.45 MPa, make packaging body in (t ± 5) minute, fit tightly the completion excipient with mould;
(5) the curing and the demoulding that the original curing process of prepreg is accomplished laminated construction are pressed in the curing and the demoulding, form final structure.
Described composite lay structural section comprises I type, C type, U type, V-type, L type, Z type, Ω type and π type.
The prepreg of described composition laminated construction is the continuous fiber prepreg; Resin in the prepreg is a thermosetting resin; Thermosetting resin is: epoxy resin, bimaleimide resin, thermoset polyimide resin, benzoxazine colophony, unsaturated polyester resin, phenolic resins or cyanate ester resin, the percentage by weight of resin is 33% to 38% in the prepreg.
Solidification process carries out in not needing the auxiliary general firing equipment of pressure, and this kind equipment comprises that with heating wire or oil be the heat radiation baking oven and the electromagnetic heater box of 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, security of products is improved in the zone of moulding arc corners in high quality.
The second, earlier simple cross sectional shape is reduced into the plane in this method, and then thermal deformation.This method is with respect to the directly paving on die face of traditional autoclave technology, has efficient height, characteristics simple to operate.
The 3rd, this method can break away from the autoclave that involves great expense and in general firing equipments such as baking oven, be cured, and has low cost, adaptable characteristics, is applicable to suitability for industrialized production.
The present invention utilizes the resin Composition viscosity after heating in the prepreg synusia of forming 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 external pressures such as air pressure or hydraulic pressure, make to be stacked in the purpose that produces interlayer slip in the closed mould and reach excipient.
The specific embodiment
Explain further details in the face of the present invention down.The present invention is the method that the hot slippage of a kind of interlayer prepares the composite lay structure, it is characterized in that the operating procedure of this method is following:
(1) confirms the sliding deformation temperature and time; From prepreg or from suppliers, obtain the resin Composition the prepreg, test resin temperature-viscosity curve, the temperature spot that on this curve, finds viscosity to equal (100 ± 5) handkerchief second is designated as T; The curing degree of Constant Temperature Detection resin under temperature T; It is t that the record curing degree improves 10% time point, and then the temperature of sliding deformation is (T ± 5) degree centigrade, and the sliding deformation time is (t ± 5) minute;
(2) laminate panel paving, by preset shop sequence of layer, the paving prepreg forms laminate panel;
(3) forming packaging body, is the minute surface symmetrical centre with the laminate panel, presses the order of laminate panel-separation layer-air-permeable layer-ductile layer and accomplishes the encapsulation to laminate panel; The separation layer glass fabric of polytetrafluoroethylene (PTFE) that has been preimpregnation wherein; Thickness is 0.05 millimeter to 1.0 millimeters, and air-permeable layer is the adhesive-bonded fabric of polyesters, surface density be 50 the gram every square metre to 200 the gram every square metre; Ductile layer is for having superplastic rubber or aluminium foil, and elongation is greater than 300%; The assembly that encapsulation finishes is called packaging body;
(4) sliding deformation in the closed mould; Packaging body is heated in baking oven (T ± 5) degree centigrade; Put into the closed mould that conforms to shape of product; Injecting gas or liquid form the air pressure or the hydraulic pressure of 0.25 MPa to 0.45 MPa, make packaging body in (t ± 5) minute, fit tightly the completion excipient with mould;
(5) the curing and the demoulding that the original curing process of prepreg is accomplished laminated construction are pressed in the curing and the demoulding, form final structure.
The simple cross section that relates among the present invention comprises I type, C type, U type, V-type, L type; Z type, Ω type and π type, the prepreg of described composition laminated construction is the continuous fiber prepreg, the resin in the prepreg is a 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 the T300/5228A epoxy prepreg
The used raw material of preparation C type wallboard are the T300/5228A epoxy prepreg among this embodiment.According to the temperature-viscosity curve of 5228A resin, it is 90 degrees centigrade that this resin viscosity in temperature-rise period is reduced to (100 ± 5) handkerchief second pairing temperature spot, is 80 fens kinds in the 90 following resin solidifications degree centigrade 10% required time of improving.The T300/5228A prepreg is pressed the template blanking earlier; Become laminate panel by the layer paving of design shop then, select for use commercial separation layer, air-permeable layer and ductile layer to accomplish encapsulation, form packaging body laminate panel; Be heated to after being evacuated to more than-0.09 MPa to packaging body (90 ± 5) degree centigrade; The working face of putting into sealing is the mould of C type, feeds gas and makes air pressure in (80 ± 5) minute, arrive 0.45 MPa, makes the plane wallboard be deformed into C type wallboard; Press the set technology of T300/5228A epoxy prepreg and accomplish curing, promptly obtain the good C type wallboard product of internal soundness after the cooling and demolding.
Embodiment 2: prepare U type beam with the T300/5228A epoxy prepreg
This embodiment and embodiment 1 are different to be that with die change be U type beam mould, and other are identical with embodiment, have obtained internal soundness and turning the second best in quality U type beam.
Embodiment 3: prepare Ω type beam with the CCF300/5228A epoxy prepreg
This embodiment is replaced by the preimpregnation of CCF300/5228A epoxy resin with the different raw material that are of embodiment 2, is Ω type beam mould with die change simultaneously.Because of the resin Composition in the preimpregnation of CCF300/5228A epoxy resin still is the 5228A resin,, obtained internal soundness and turning the second best in quality Ω type beam so other parameters among this embodiment are identical with embodiment 2.
Embodiment 4: prepare the long purlin of L type with the T700/5224 epoxy prepreg
The used raw material in the long purlin of preparation L type are the T700/5224 epoxy prepreg among this embodiment.According to the temperature-viscosity curve of 5224 resins, it is 105 degrees centigrade that this resin viscosity in temperature-rise period is reduced to (100 ± 5) handkerchief second pairing temperature spot, is 60 fens kinds in the 105 following resin solidifications degree centigrade 10% required time of improving.The T700/5224 prepreg is pressed the template blanking earlier; Become laminate panel by the layer paving of design shop then, select for use commercial separation layer, air-permeable layer and ductile layer to accomplish encapsulation, form packaging body laminate panel; Be heated to after being evacuated to more than-0.09 MPa to packaging body (90 ± 5) degree centigrade; The working face of putting into sealing is the mould of the long purlin of L type, feeds gas and makes air pressure in (60 ± 5) minute, arrive 0.35 MPa, and making plate deformation is the long purlin of L type; Press the set technology of T700/5224 epoxy prepreg and accomplish curing, promptly obtain the long purlin of the good L type of internal soundness product after the cooling and demolding.
Embodiment 5: prepare the V-type trailing edge with the T300/5224 epoxy prepreg
This embodiment is replaced by the T300/5224 epoxy prepreg with the different raw material that are of embodiment 4, is V-type trailing edge mould with die change, adopts fire-resistant hydraulic fluid to pressurize, and pressure is 0.45 MPa.Because of the resin Composition in the T300/5224 epoxy prepreg still is 5224 resins,, obtained the second best in quality V-type trailing edge in internal soundness and turning so other parameters among this embodiment are identical with embodiment 4.
Embodiment 6: with T800/III type benzoxazine colophony equipment of preimpregnated material manufacture U type frame
The used raw material of preparation U type frame are T800/ benzoxazine colophony resin prepreg material among this embodiment.According to the temperature-viscosity curve of benzoxazine colophony, it is 70 degrees centigrade that this resin viscosity in temperature-rise period is reduced to (100 ± 5) handkerchief second pairing temperature spot, is 60 fens kinds in the 70 following resin solidifications degree centigrade 10% required time of improving.T800/ benzoxazine colophony prepreg is pressed the template blanking earlier; Become laminate panel by the layer paving of design shop then, select for use commercial separation layer, air-permeable layer and ductile layer to accomplish encapsulation, form packaging body laminate panel; Be heated to after being evacuated to more than-0.09 MPa to packaging body (70 ± 5) degree centigrade; The working face of putting into sealing is the mould of U type, feeds high temperature resistant deep fat and makes pressure in (60 ± 5) minute, arrive 0.4 MPa, and making plate deformation is U type frame; Press the set technology of T800/ benzoxazine colophony prepreg and accomplish curing, promptly obtain the good U type frame product of internal soundness after the cooling and demolding.
Embodiment 7: with the long purlin of CCF300/III type benzoxazine colophony equipment of preimpregnated material manufacture π type
This embodiment is replaced by CCF300/ benzoxazine colophony prepreg with the different raw material that are of embodiment 6, die change is the long purlin of π type mould.Because of the resin Composition in the CCF300/ benzoxazine colophony prepreg still is an III type benzoxazine colophony,, obtained the long purlin of the second best in quality π type in internal soundness and turning so other parameters among this embodiment are identical with embodiment 6.
Embodiment 8: with AS4/L polyimide type resin equipment of preimpregnated material manufacture U template
The used raw material of preparation U template are AS4/L polyimide type resin prepreg among this embodiment.According to the temperature-viscosity curve of L polyimide type resin, it is 260 degrees centigrade that this resin viscosity in temperature-rise period is reduced to (100 ± 5) handkerchief second pairing temperature spot, is 30 fens kinds in the 260 following resin solidifications degree centigrade 10% required time of improving.AS4/L polyimide type resin prepreg is pressed the template blanking; Become laminate panel by the layer paving of design shop then, select for use commercial separation layer, air-permeable layer and ductile layer to accomplish encapsulation, form packaging body laminate panel; Be heated to after being evacuated to more than-0.09 MPa to packaging body (260 ± 5) degree centigrade; The working face of putting into sealing is the mould of U type, feeds high temperature resistant deep fat and makes pressure in (30 ± 5) minute, arrive 0.45 MPa, and making plate deformation is U type frame; Press the set technology of AS4/L polyimide type resin prepreg and accomplish curing, promptly obtain the good U template product of internal soundness after the cooling and demolding.
Embodiment 9: with G0827/L polyimide type resin equipment of preimpregnated material manufacture C type beam
This embodiment is replaced by G0827/L polyimide type resin prepreg with the different raw material that are of embodiment 8, is C type beam mould with die change.Because of the resin Composition in the G0827/L polyimide type resin prepreg still is the L polyimide type resin,, obtained internal soundness and turning the second best in quality C type beam so other parameters among this embodiment are identical with embodiment 8.
Embodiment 10: with the long purlin of U3160/F type bimaleimide resin equipment of preimpregnated material manufacture Z
The used raw material in the long purlin of preparation Z are U3160/F type bimaleimide resin prepreg among this embodiment.According to the temperature-viscosity curve of F type bimaleimide resin, it is 140 degrees centigrade that this resin viscosity in temperature-rise period is reduced to (100 ± 5) handkerchief second pairing temperature spot, is 40 fens kinds in the 140 following resin solidifications degree centigrade 10% required time of improving.U3160/F type bimaleimide resin prepreg is pressed the template blanking; Become laminate panel by the layer paving of design shop then, select for use commercial separation layer, air-permeable layer and ductile layer to accomplish encapsulation, form packaging body laminate panel; Be heated to after being evacuated to more than-0.09 MPa to packaging body (140 ± 5) degree centigrade; The working face of putting into sealing is the mould of Z type, feeds high temperature resistant deep fat and makes pressure in (40 ± 5) minute, arrive 0.25 MPa, and making plate deformation is the long purlin of Z type; Press the set technology of U3160/F type bimaleimide resin prepreg and accomplish curing, promptly obtain the long purlin of the good Z of internal soundness product after the cooling and demolding.
Embodiment 11: with CF3031/F type bimaleimide resin equipment of preimpregnated material manufacture V-type trailing edge
This embodiment is replaced by CF3031/F type bimaleimide resin prepreg with the different raw material that are of embodiment 10, is V-type trailing edge mould with die change.Because of the resin Composition in the CF3031/F type bimaleimide resin prepreg still is a F type bimaleimide resin,, obtained internal soundness and turning the second best in quality V-type trailing edge product so other parameters among this embodiment are identical with embodiment 8.
Claims (4)
1. the hot slippage of interlayer prepares the method for composite lay structure, it is characterized in that the operating procedure of this method is following:
(1) confirms the sliding deformation temperature and time; Resin viscosity-temperature curve in the test prepreg; The temperature spot that on this curve, finds viscosity to equal for 100 ± 5 handkerchief seconds is designated as T, and it is t that the curing degree of Constant Temperature Detection resin under temperature T, record curing degree improve 10% time point; Then the temperature of sliding deformation is T ± 5 degree centigrade, and the sliding deformation time is t ± 5 minute;
(2) laminate panel paving, by preset shop sequence of layer, the paving prepreg forms laminate panel;
(3) forming packaging body, is the minute surface symmetrical centre with the laminate panel, presses the order of laminate panel-separation layer-air-permeable layer-ductile layer and accomplishes the encapsulation to laminate panel; The separation layer glass fabric of polytetrafluoroethylene (PTFE) that has been preimpregnation wherein; Thickness is 0.05 millimeter to 1.0 millimeters, and air-permeable layer is the adhesive-bonded fabric of polyesters, surface density be 50 the gram every square metre to 200 the gram every square metre; Ductile layer is for having superplastic rubber or aluminium foil, and elongation is greater than 300%; The assembly that encapsulation finishes is called packaging body;
(4) sliding deformation in the closed mould; Packaging body is heated to T ± 5 degree centigrade in baking oven; Put into the closed mould that conforms to shape of product, injecting gas or high temperature resistant deep fat form the air pressure or the hydraulic pressure of 0.25 MPa to 0.45 MPa, and packaging body is fitted with mould in t ± 5 minute and accomplished excipient;
(5) curing and the demoulding, the curing process of pressing employed prepreg is accomplished the curing and the demoulding of laminated construction, forms final structure.
2. the hot slippage of a kind of interlayer according to claim 1 prepares the method for composite lay structure, it is characterized in that, described composite lay structural section comprises I type, C type, U type, V-type, L type, Z type, Ω type and π type.
3. the hot slippage of a kind of interlayer according to claim 1 prepares the method for composite lay structure; It is characterized in that; The prepreg of described composition laminated construction is the continuous fiber prepreg; Resin in the prepreg is a thermosetting resin, and thermosetting resin is: epoxy resin, bimaleimide resin, thermoset polyimide resin, benzoxazine colophony, unsaturated polyester resin, phenolic resins or cyanate ester resin, the percentage by weight of resin is 33% to 38% in the prepreg.
4. the hot slippage of a kind of interlayer according to claim 1 prepares the method for composite lay structure; It is characterized in that; Solidification process carries out in not needing the auxiliary general firing equipment of pressure, and this kind equipment comprises that with heating wire or oil be the heat radiation baking oven and the electromagnetic heater box of thermal source.
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| CN106346845A (en) * | 2016-08-23 | 2017-01-25 | 北京汽车集团有限公司 | Middle passage reinforcing plate, preparation method thereof and vehicle |
| CN108544767A (en) * | 2018-04-10 | 2018-09-18 | 中航复合材料有限责任公司 | A kind of forming method and forming frock of composite material J-shaped blank |
| CN110757830A (en) * | 2018-07-26 | 2020-02-07 | 中国商用飞机有限责任公司 | Thermal diaphragm forming method and preparation system of hat-shaped stringer |
| CN114801243A (en) * | 2022-04-15 | 2022-07-29 | 西安电子科技大学 | Method for actively controlling stack slip in composite material member |
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| CN106346845A (en) * | 2016-08-23 | 2017-01-25 | 北京汽车集团有限公司 | Middle passage reinforcing plate, preparation method thereof and vehicle |
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| CN110757830A (en) * | 2018-07-26 | 2020-02-07 | 中国商用飞机有限责任公司 | Thermal diaphragm forming method and preparation system of hat-shaped stringer |
| CN114801243A (en) * | 2022-04-15 | 2022-07-29 | 西安电子科技大学 | Method for actively controlling stack slip in composite material member |
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| CN102501389B (en) | 2014-05-14 |
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