CN103009638A - Interlaminar enhancement process for composite laminated plate for fuselage and airfoils of unmanned plane - Google Patents
Interlaminar enhancement process for composite laminated plate for fuselage and airfoils of unmanned plane Download PDFInfo
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- CN103009638A CN103009638A CN201210544263XA CN201210544263A CN103009638A CN 103009638 A CN103009638 A CN 103009638A CN 201210544263X A CN201210544263X A CN 201210544263XA CN 201210544263 A CN201210544263 A CN 201210544263A CN 103009638 A CN103009638 A CN 103009638A
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Abstract
The invention discloses an interlaminar enhancement process for a composite laminated plate for a fuselage and airfoils of an unmanned plane. The interlaminar enhancement process comprises the following steps of: (1) preparing carbon fiber-reinforced resin matrix composite pins by utilizing a pultrusion molding process; (2) preparing a foam preform containing the carbon fiber-reinforced resin matrix composite pins; (3) implanting the carbon fiber-reinforced resin matrix composite pins in the foam preform into the composite laminated plate for the fuselage and the airfoils of the unmanned plane; and (4) testing mechanical properties of the composite laminated plate after the carbon fiber-reinforced resin matrix composite pins are implanted. By utilizing the process, the anti-low speed impact capability of the structure of the composite laminated plate for the unmanned plane, in particular the anti-interlaminar shearing strength of a stiffened structure of the composite laminated plate can be improved, and a solid foundation is laid for realizing light weight and low cost of the composite laminated plate.
Description
Technical field
The present invention relates to a kind of composite laminated plate for unmanned fuselage, wing, more particularly, relate to a kind of composite laminated plate and interlaminar improvement technique thereof of being used for unmanned fuselage, wing that has more anti-low velocity impact ability and anti-interlaminar shear strength.
Background technology
In recent years, along with application study deeply and the development of forming technique, fiber-reinforced resin matrix compound material (Fiber reinforced resin matrix composites) has been widely used in aerospace structural member.Yet, owing to be subject to the restriction of the techniques such as the structure of traditional classical composite laminated plate (Classic composite laminate) and splicing, co-curing, cause the interlayer of composite laminated plate weak, therefore interlayer faults toughness (Interlaminar fracture toughness) and the impact injury tolerance limit (Impact damage tolerance) of composite laminated plate are generally lower, have limited its application on the aerospace flight vehicle main force support structure.
At present, being used for the composite laminated plate interlaminar improvement mainly is by sewing process, and this sewing process is with the yarn of high tensile the manufacturing that unites by a seam of a lot of layings to be had the preformed member of 3D fibre structure.But this technique can cause following damage to precast body: fibre beakage, fiber dislocation, fiber bending, resin-rich area, suture distortion, micro-crack, compacting.In addition, the composite bed of material board structure spare that uses in the existing unmanned plane exists obviously not enough, as shock resistance a little less than, layering etc. appears in reinforcement-wallboard interface.。
Summary of the invention
The object of the present invention is to provide a kind of interlaminar improvement technique (Z-pin technique) of the composite laminated plate that is used for unmanned fuselage, wing that can effectively address the above problem.This technique combines with traditional prepreg-autoclave technique, with Z-direction (vertically) pin implant layer board structure, strengthened the anti-low velocity impact ability of composite laminated plate, especially the anti-interlaminar shear strength of composite laminated plate reinforced structure is for the cost degradation that lightweight and the composite of laminated composite plate structures are used is taken a firm foundation.
The interlaminar improvement technique that is used for the composite laminated plate of unmanned fuselage, wing among the present invention includes following steps:
1) adopt with the unmanned plane composite structure in identical carbon fiber and resin material, and utilize pultrusion molding process to prepare the carbon fiber enhancement resin base composite material pin;
2) the preparation carbon fiber-containing strengthens the foam preform of polymer matrix composites pin;
3) the carbon fiber enhancement resin base composite material pin in the foam preform is implanted the composite laminated plate that is used for unmanned aerial vehicle body, wing;
4) composite laminated plate behind the implantation carbon fiber enhancement resin base composite material pin is carried out Mechanics Performance Testing.
In above-mentioned steps 3) in utilize the method for autoclave method that the carbon fiber enhancement resin base composite material pin is implanted to the reinforced structure of composite laminated plate and the connecting portion of wallboard.
The method of described autoclave method is that the foam preform that will contain the carbon fibre composite pin is placed on the uncured toughness reinforcing position of laminate needs, put again vacuum bag, rising along with temperature, the preimpregnation laminate of laminate is softening gradually, foam preform melts routed gradually simultaneously, the carbon fibre composite pin will be transferred in the laminate of laminate under the pressure-acting that autoclave produces, after cured, laminate is taken out from autoclave, cut off unnecessary foam and carbon fibre composite pin with diamant.
In above-mentioned steps 3) in utilize the auxiliary embedded technology of ultrasonic wave that the carbon fiber enhancement resin base composite material pin is implanted to the reinforced structure of composite laminated plate and the connecting portion of wallboard.
The ultrasound applicator of the auxiliary embedded technology utilization special use of described ultrasonic wave is pressed into the foam preform in the foam preform between the laminate of laminate, ultrasonic wave in the ultrasound applicator drives the rifle cephalic tentacle and carries out dither, reduce and embed the active force that foam preform needs, the heat of generation of vibration makes the resin of foam preform softening, is easy to the transfer of foam preform.
In above-mentioned steps 3) in utilize the manual mode of the implanting reinforced structure that is implanted to composite laminated plate that the carbon fiber enhancement resin base composite material pin is independent and the connecting portion of wallboard.
Above-mentioned steps 1) pultrusion molding process in is to put the continuous fiber filament of supply by supply to enter steeping vat, it is fixing that the pin base is combined with fiber filament, enter into the intensification mould from steeping vat fiber filament out together with the pin base and be cured, and wind up in order to store and transport with the form of package.
Before fiber filament is by dipping tank, fiber filament is carried out preheating, heat simultaneously dipping tank and regulate the viscosity that the interior resin temperature of dipping tank can reduce resin.
The carbon fiber enhancement resin base composite material that strengthens the polymer matrix composites pin for the preparation of carbon fiber-containing is SiC/ bismaleimide resin, T650/ bismaleimide resin, T300/ epoxy, T300/ bismaleimide resin, P100/ epoxy or S glass/epoxy.
Described carbon fiber-containing strengthens the diameter of polymer matrix composites pin between 0.15 ㎜～1.5 ㎜.
Utilize the deficiency that both can remedy the sewing process of current extensive use after the interlaminar improvement technique among the present invention, the fabric precast body of interlaminar improvement can be provided for present popular resin transfer molding (RTM), vacuum-assisted resin transfer molded (VARTM) technique again, therefore become the focus of domestic and international composite circle research.
Interlaminar improvement technique among the present invention has improved the anti-low velocity impact ability of unmanned plane composite laminated plate, especially the anti-interlaminar shear strength of composite laminated plate reinforced structure is for lightweight and the cost degradation of laminated composite plate structures are taken a firm foundation.
Description of drawings
Fig. 1 is the process chart of composite laminated plate interlaminar improvement among the present invention.
Fig. 2 is the schematic flow sheet of the pultrusion molding process of composite pin among the present invention.
Fig. 3 is the structural representation of the preformed foam part among the present invention.
Fig. 4 is the schematic diagram of autoclave implantation step among the present invention.
Fig. 5 is the schematic diagram of ultrasonic wave implantation step among the present invention.
The specific embodiment
Below in conjunction with accompanying drawing the specific embodiment among the present invention is elaborated.
The technique of interlaminar improvement that is used for the composite laminated plate of unmanned fuselage, wing among the present invention includes following steps:
1) preparation of material, equipment
Mainly be the determining of manufacturing, basic resin system, technological parameter of the building of buying, pultrusion molding process device, the mould of buying, the mold materials of Unidirectional fiber tow in this step.The charcoal fiber-reinforced resin matrix compound material pin that contains among the present invention is the very little pin of a kind of diameter (general diameter is between 0.15mm～1.5mm), before preparation, select the pin base that is fit to different composite material layer plywood, the diameter of pin base has: Ф 0.4mm, Ф 0.6mm, Ф 0.8mm, Ф 1.0mm, Ф 1.2mm.In subsequent technique, make different composite pins by the consumption of control carbon fiber, and the glue content of control composite pin, such as table 1:
Prepare pin diameter table during table 1 35% glue content
| 3K carbon fiber radical | Root | 1 | 2 | 3 | 4 | 5 |
| The diameter of pin base | mm | 0.4 | 0.6 | 0.8 | 1.0 | 1.2 |
| The diameter of composite pin (Z-pin) | mm | 0.51 | .72 | .88 | 1.14 | 1.24 |
Carbon fiber enhancement resin base composite material for the preparation of pin can be SiC/ bismaleimide resin, T650/ bismaleimide resin, T300/ epoxy, T300/ bismaleimide resin, P100/ epoxy, S glass/epoxy, and the material of pin base can be titanium alloy, stainless steel, aluminium alloy etc.
2) preparation of carbon fibre composite pin
As shown in Figure 2, adopt pultrusion molding process to make and contain charcoal fiber-reinforced resin matrix compound material pin, specifically put 1 by supply continuous fiber filament 7 is provided, this fiber filament 7 enters steeping vat 3 through fibre guide device 2, in steeping vat 3, make pin base 8 fixing with fiber filament 7 combinations, enter in the intensification mould 4 together with pin base 8 from steeping vat 3 fiber filament 7 out and to be cured, traction by draw-gear 5 enters coiler device 6 again, wound up by the form of coiler device 6 with package, in order to store and transportation.
In addition, in order to improve the speed of pultrusion, can carry out preheating by dipping tank 3 is front to fiber filament 7 at fiber filament 7, suitably heating dipping tank 3 is regulated resin temperature in the dipping tank 3 simultaneously, to reduce the viscosity of resin, increase being adhesively fixed of pin base 8 and fiber filament 7.In addition, also can satisfy in the situation of certain rigidity at pin base 8, in the situation of intensification mould 4 interior incomplete curing, just reel, again whole package is put into warming box until completion of cure, although this method is many together after curing process, but can improve pultrusion speed, reduce simultaneously tractive force requirement and mould requirement.
3) contain the preparation of the foam preform of composite pin
For preventing that the carbon fibre composite pin from the process of embeding layer plywood flexing occuring, the carbon fibre composite pin of first former coiling being stored cuts, and before the implanted prepreg of carbon fibre composite pin or foam preform, utilize process tool, polishing motor, bistrique etc. the carbon fibre composite pin after solidifying to be processed into the cone of certain angle, resistance when as shown in Figure 3, being implanted to laminate with reduction and reduce damage to fiber filament in the laminate.Carbon fibre composite pin after the processing implanted in the foam with certain density quadrature obtain the foam prefabricated component.
The foam that is used for implantation carbon fibre composite pin is combined by bi-material, be respectively low density foam and middle density foam, wherein low density foam places the upper strata, before embedding the carbon fibre composite pin, play a supporting role, while can melt routed when autoclave or the auxiliary embedding of ultrasonic wave gradually, and the carbon fibre composite pin is transferred to downwards in the prepreg laminate.Middle density foam places lower floor, prevents that the carbon fibre composite pin from bending in stressed situation.Wherein, low density foam and middle density foam can be identical material, such as polyurethane foamed material.Also can be unlike material, such as EPE, polyphenyl foam, polyethylene, phenol formaldehyde foam etc.
4) with carbon fibre composite pin composite implant material laminate
The carbon fibre composite pin is inserted into formation 3D network fibres structure in the unmanned plane composite laminated plate, can be used for dry state fiber preform and prepreg are carried out interlaminar improvement.This step can be finished by two kinds of methods, and a kind of is single implantation, and the carbon fibre composite pin embeds respectively in the uncured laminate one by one exactly.The mode that the mode of this single implantation can adopt manual mode or ail gun to inject at a high speed is embedded in the laminate of the prepreg of laminate or dry fabric laying.Another kind is integral embedded type, has namely introduced the foam prefabricated component, and some carbon fibre composite pins are embedded in the composite laminated plate of unmanned aerial vehicle body, wing simultaneously.Can adopt two kinds of diverse ways when embed wholly, wherein a kind of is the method for utilizing the autoclave method, and another kind is the auxiliary embedded technology of ultrasonic wave.The below describes in detail the distinct methods of the carbon fibre composite pin being implanted the unmanned plane composite laminated plate.
A) the manual implantation
This manual mode of implanting is generally used in the experimental stage, and in the laminate that is embedded into prepreg that the carbon fibre composite pin is independent, moulding prepares carbon fibre composite pin unmanned plane wallboard.The method can be finished in two steps, and a step is to adopt the low temperature prepreg, utilizes god to fly company's SUAV apparatus for production line, adopts the negative pressure of vacuum moulding to prepare carbon fibre composite pin unmanned plane wallboard; Another step is warm prepreg in adopting, and utilizes god to fly the big-and-middle-sized unmanned plane apparatus for production line of company, the manual preparation carbon fibre composite pin unmanned plane wallboard of implanting.
B) autoclave is implanted
It is with carbon fibre composite pin embed wholly that autoclave is implanted, specifically realize by autoclave forming process, as shown in Figure 4, the foam preform that specifically will contain the carbon fibre composite pin is placed on the uncured toughness reinforcing position of laminate needs, put again vacuum bag, rising along with temperature, the preimpregnation laminate of laminate is softening gradually, foam preform melts routed gradually simultaneously, the carbon fibre composite pin will be transferred in the laminate of laminate under the pressure-acting that autoclave produces, after cured, laminate is taken out from autoclave, cut off unnecessary foam and carbon fibre composite pin with diamant, laminated composite is enhanced.This method is suitable for the plane layer plywood.
In addition, when autoclave forming process, because the pressure ratio that needs in the process that embeds the carbon fibre composite pin is larger, therefore can add layer of metal plate or silicane rubber plate on the foam preform, thereby change by pressure, promote the embedment pressure of carbon fibre composite pin, control simultaneously the thickness of upper strata low density foam layer, the resistance when the carbon fibre composite pin is shifted to laminate by foam preform reduces.
C) ultrasonic wave is auxiliary
Utilize special-purpose ultrasound applicator the foam preform in the foam preform to be pressed between the laminate of laminate, ultrasonic wave in the ultrasound applicator can drive the rifle cephalic tentacle and carry out dither, reduce and embed the active force that foam preform needs, the heat of generation of vibration can also make the resin of foam preform softening, is easy to the transfer of foam preform.This method is different from the method for utilizing autoclave, just unnecessary foam prefabricated component is removed before composite laminated plate solidifies.As shown in Figure 5, the prepreg after will strengthening is at last put into heat riser and is solidified and namely obtain tool carbon fibre composite pin and strengthen laminated composite.In addition, need to place one deck polytetrafluorethylecoatings coatings fabric between foam prefabricated component and uncured laminate before embedding, its effect is can prevent that the carbon fibre composite pin is toppled over because of stressed in the laminate when cutting off unnecessary foam prefabricated component with diamant.
5) test report, analysis and numerical modeling
Utilize pendulum to hit test and make the interlaminal toughness of composite laminated plate and the switching performance of plate-muscle structure by above-mentioned technique, carry out material object by micro-imaging technique simultaneously and take, record carbon fibre composite pin is to the failure mode of bonding property between toughness reinforcing between laminate, plate-muscle.
In sum, not only can improve interlayer faults toughness between laminate by above-mentioned technique, can also promote the structural design scope of unmanned plane composite laminated plate, also can be the composite structure interconnection technique simultaneously a new direction is provided.
Claims (10)
1. be used for the interlaminar improvement technique of the composite laminated plate of unmanned aerial vehicle body, wing, may further comprise the steps:
1) adopt with the unmanned plane composite structure in identical carbon fiber and resin material, and utilize pultrusion molding process to prepare the carbon fiber enhancement resin base composite material pin;
2) the preparation carbon fiber-containing strengthens the foam preform of polymer matrix composites pin;
3) the carbon fiber enhancement resin base composite material pin in the foam preform is implanted the composite laminated plate that is used for unmanned aerial vehicle body, wing;
4) composite laminated plate behind the implantation carbon fiber enhancement resin base composite material pin is carried out Mechanics Performance Testing.
2. the interlaminar improvement technique of the composite laminated plate for unmanned aerial vehicle body, wing according to claim 1 is characterized in that: in above-mentioned steps 3) in utilize the method for autoclave method that the carbon fiber enhancement resin base composite material pin is implanted to the reinforced structure of composite laminated plate and the connecting portion of wallboard.
3. according to claim 2 for unmanned aerial vehicle body, the interlaminar improvement technique of the composite laminated plate of wing, it is characterized in that: the method for described autoclave method is that the foam preform that will contain the carbon fibre composite pin is placed on the uncured toughness reinforcing position of laminate needs, put again vacuum bag, rising along with temperature, the preimpregnation laminate of laminate is softening gradually, foam preform melts routed gradually simultaneously, the carbon fibre composite pin will be transferred in the laminate of laminate under the pressure-acting that autoclave produces, after cured, laminate is taken out from autoclave, cut off unnecessary foam and carbon fibre composite pin with diamant.
4. the interlaminar improvement technique of the composite laminated plate for unmanned aerial vehicle body, wing according to claim 1 is characterized in that: in above-mentioned steps 3) in utilize the auxiliary embedded technology of ultrasonic wave that the carbon fiber enhancement resin base composite material pin is implanted to the reinforced structure of composite laminated plate and the connecting portion of wallboard.
5. the interlaminar improvement technique of the composite laminated plate for unmanned aerial vehicle body, wing according to claim 4, it is characterized in that: the ultrasound applicator of the auxiliary embedded technology utilization special use of described ultrasonic wave is pressed into the foam preform in the foam preform between the laminate of laminate, ultrasonic wave in the ultrasound applicator drives the rifle cephalic tentacle and carries out dither, reduce and embed the active force that foam preform needs, the heat of generation of vibration makes the resin of foam preform softening, is easy to the transfer of foam preform.
6. the interlaminar improvement technique of the composite laminated plate for unmanned aerial vehicle body, wing according to claim 1 is characterized in that: in above-mentioned steps 3) in utilize the manual mode of the implanting reinforced structure that is implanted to composite laminated plate that the carbon fiber enhancement resin base composite material pin is independent and the connecting portion of wallboard.
7. the interlaminar improvement technique of the described composite laminated plate for unmanned aerial vehicle body, wing of any one in 6 according to claim 2, it is characterized in that: the pultrusion molding process above-mentioned steps 1) is to put the continuous fiber filament of supply by supply to enter steeping vat, it is fixing that the pin base is combined with fiber filament, enter into the intensification mould from steeping vat fiber filament out together with the pin base and be cured, and wind up in order to store and transport with the form of package.
8. the interlaminar improvement technique of the composite laminated plate for unmanned aerial vehicle body, wing according to claim 7, it is characterized in that: before fiber filament is by dipping tank, fiber filament is carried out preheating, heat simultaneously dipping tank and regulate the viscosity that the interior resin temperature of dipping tank can reduce resin.
9. the interlaminar improvement technique of the composite laminated plate for unmanned aerial vehicle body, wing according to claim 1, it is characterized in that: the carbon fiber enhancement resin base composite material that strengthens the polymer matrix composites pin for the preparation of carbon fiber-containing is SiC/ bismaleimide resin, T650/ bismaleimide resin, T300/ epoxy, T300/ bismaleimide resin, P100/ epoxy or S glass/epoxy.
10. the interlaminar improvement technique of the composite laminated plate for unmanned aerial vehicle body, wing according to claim 1, it is characterized in that: described carbon fiber-containing strengthens the diameter of polymer matrix composites pin between 0.15 ㎜～1.5 ㎜.
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| CN104647776A (en) * | 2015-01-23 | 2015-05-27 | 南京航空航天大学 | Z-pin reinforced composite material stiffened wall plate structure and forming method thereof |
| CN105196563A (en) * | 2015-10-09 | 2015-12-30 | 南京航空航天大学 | Z-pin reinforced composite grid structure and manufacturing method thereof |
| CN107908151A (en) * | 2017-12-18 | 2018-04-13 | 哈尔滨工业大学（威海） | A kind of Z PIN contact pins control system and interpolating method |
| CN109291461A (en) * | 2018-11-07 | 2019-02-01 | 西安交通大学 | A kind of fine stick enhancing continuous fiber reinforced composite materials increasing material manufacturing method of interlayer |
| CN111113927A (en) * | 2018-11-01 | 2020-05-08 | 洛阳尖端技术研究院 | Forming method of Z-pin reinforced composite material structural member |
| CN111169053A (en) * | 2018-11-09 | 2020-05-19 | 洛阳尖端技术研究院 | Forming method of three-dimensional reinforced composite material |
| CN111251627A (en) * | 2020-01-22 | 2020-06-09 | 西北工业大学 | Method for improving interlayer strength effect of Z-pin reinforced composite material |
| CN113665782A (en) * | 2021-09-24 | 2021-11-19 | 肇庆市海特复合材料技术研究院 | Composite material unmanned aerial vehicle bonding structure and bonding method thereof |
| CN115195160A (en) * | 2022-07-07 | 2022-10-18 | 湖南弘辉科技有限公司 | Method for paving, sewing and compression molding metal piece and composite material |
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|---|---|---|---|---|
| CN104647776A (en) * | 2015-01-23 | 2015-05-27 | 南京航空航天大学 | Z-pin reinforced composite material stiffened wall plate structure and forming method thereof |
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| CN109291461A (en) * | 2018-11-07 | 2019-02-01 | 西安交通大学 | A kind of fine stick enhancing continuous fiber reinforced composite materials increasing material manufacturing method of interlayer |
| CN111169053A (en) * | 2018-11-09 | 2020-05-19 | 洛阳尖端技术研究院 | Forming method of three-dimensional reinforced composite material |
| CN111251627A (en) * | 2020-01-22 | 2020-06-09 | 西北工业大学 | Method for improving interlayer strength effect of Z-pin reinforced composite material |
| CN113665782A (en) * | 2021-09-24 | 2021-11-19 | 肇庆市海特复合材料技术研究院 | Composite material unmanned aerial vehicle bonding structure and bonding method thereof |
| CN115195160A (en) * | 2022-07-07 | 2022-10-18 | 湖南弘辉科技有限公司 | Method for paving, sewing and compression molding metal piece and composite material |
| CN115195160B (en) * | 2022-07-07 | 2023-11-03 | 湖南弘辉科技有限公司 | Method for stitching and compression molding of metal piece and composite material layer |
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