CN103009638B - For the interlaminar improvement technique of the composite laminated plate of unmanned aerial vehicle body, wing - Google Patents
For the interlaminar improvement technique of the composite laminated plate of unmanned aerial vehicle body, wing Download PDFInfo
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- CN103009638B CN103009638B CN201210544263.XA CN201210544263A CN103009638B CN 103009638 B CN103009638 B CN 103009638B CN 201210544263 A CN201210544263 A CN 201210544263A CN 103009638 B CN103009638 B CN 103009638B
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Abstract
The invention discloses a kind of interlaminar improvement technique of the composite laminated plate for unmanned aerial vehicle body, wing, it comprises the following steps: 1) utilize pultrusion molding process to prepare carbon fiber enhancement resin base composite material pin; 2) foam preform that carbon fiber-containing strengthens polymer matrix composites pin is prepared; 3) the carbon fiber enhancement resin base composite material pin in foam preform is implanted the composite laminated plate being used for unmanned aerial vehicle body, wing; 4) Mechanics Performance Testing is carried out to composite laminated plate after implantation carbon fiber enhancement resin base composite material pin.Utilize this technique can improve the anti-low velocity impact ability of unmanned plane laminated composite plate structures, the especially anti-interlaminar shear strength of composite laminated plate reinforced structure, for the lightweight of composite laminated plate and cost degradation are taken a firm foundation.
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 for unmanned fuselage, wing and the interlaminar improvement technique thereof that have 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 (Fiberreinforcedresinmatrixcomposites) has been widely used in aerospace structural member.But, due to the restriction of the structure and the technique such as splicing, co-curing that are subject to traditional classical composite laminated plate (Classiccompositelaminate), cause the interlayer of composite laminated plate weak, therefore the interlaminar fracture toughness (Interlaminarfracturetoughness) of composite laminated plate and impact injury tolerance limit (Impactdamagetolerance) general lower, limit its application on aerospace flight vehicle main force support structure.
At present, for composite laminated plate interlaminar improvement mainly by sewing process, this sewing process has the preformed member of 3D fibre structure with the manufacture that a lot of laying to be united by a seam of the yarn of high tensile.But this technique can cause following damage to precast body: the dislocation of fibre beakage, fiber, fiber bending, resin-rich area, suture distortion, micro-crack, compacting.In addition, the composite bed of material board structure part used in existing unmanned plane exists obviously not enough, and as shock resistance is more weak, 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 for unmanned fuselage, wing that can effectively solve the problem.This technique combines with traditional prepreg-autoclave technique, by Z-direction (vertically) pin implant layer board structure, enhance the anti-low velocity impact ability of composite laminated plate, especially the anti-interlaminar shear strength of composite laminated plate reinforced structure, for the lightweight of laminated composite plate structures and the cost degradation of composite application are taken a firm foundation.
Interlaminar improvement technique for the composite laminated plate of unmanned fuselage, wing in the present invention includes following steps:
1) adopt the carbon fiber identical with unmanned plane composite structure and resin material, and utilize pultrusion molding process to prepare carbon fiber enhancement resin base composite material pin;
2) foam preform that carbon fiber-containing strengthens polymer matrix composites pin is prepared;
3) the carbon fiber enhancement resin base composite material pin in foam preform is implanted the composite laminated plate being used for unmanned aerial vehicle body, wing;
4) Mechanics Performance Testing is carried out to the composite laminated plate after implantation carbon fiber enhancement resin base composite material pin.
In above-mentioned steps 3) in utilize the method for autoclave method that 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 the foam preform containing carbon fibre composite pin is placed on uncured laminate need toughness reinforcing position, put vacuum bag again, along with the rising of temperature, the preimpregnation laminate of laminate softens gradually, foam preform melts routed gradually simultaneously, to transfer in the laminate of laminate under the pressure effect that carbon fibre composite pin is produced at autoclave, after cured, laminate is taken out from autoclave, cuts off unnecessary foam and carbon fibre composite pin with diamant.
In above-mentioned steps 3) in utilize ultrasonic assistant embedded technology that carbon fiber enhancement resin base composite material pin is implanted to the reinforced structure of composite laminated plate and the connecting portion of wallboard.
Described ultrasonic assistant embedded technology utilizes special ultrasound applicator by between the laminate of the foam preform press-in laminate in foam preform, ultrasonic wave in ultrasound applicator drives rifle cephalic tentacle to carry out dither, reduce the active force embedding foam preform and need, the heat that vibration produces makes the resin of foam preform soften, and is easy to the transfer of foam preform.
In above-mentioned steps 3) in utilize the manual mode implanted that independent for carbon fiber enhancement resin base composite material pin is implanted to the reinforced structure of composite laminated plate and the connecting portion of wallboard.
Above-mentioned steps 1) in pultrusion molding process be by supply put supply continuous fiber filament enter steeping vat, in steeping vat, pin base is made to be combined with fiber filament fixing, enter into intensification mould from steeping vat fiber filament out together with pin base to be cured, and wind up to store and to transport with the form of package.
Before fiber filament is by dipping tank, preheating is carried out to fiber filament, heat dipping tank simultaneously and regulate resin temperature in dipping tank can reduce the viscosity of resin.
The carbon fiber enhancement resin base composite material strengthening 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 ㎜.
Both the deficiency of the sewing process of current extensive use can have been made up after utilizing the interlaminar improvement technique in the present invention, the fabric precast body of interlaminar improvement can be provided for popular at present resin transfer molding (RTM), vacuum assisted resin transfer molding shaping (VARTM) technique again, therefore become the focus of domestic and international composite circle research.
Interlaminar improvement technique in the present invention improves the anti-low velocity impact ability of unmanned plane composite laminated plate, especially the anti-interlaminar shear strength of composite laminated plate reinforced structure, for the lightweight of laminated composite plate structures and cost degradation are taken a firm foundation.
Accompanying drawing explanation
Fig. 1 is the process chart of composite laminated plate interlaminar improvement in the present invention.
Fig. 2 is the schematic flow sheet of the pultrusion molding process of composite pin in the present invention.
Fig. 3 is the structural representation of the preformed foam part in the present invention.
Fig. 4 is the schematic diagram of autoclave implantation step in the present invention.
Fig. 5 is the schematic diagram of ultrasonic wave implantation step in the present invention.
Detailed description of the invention
Below in conjunction with accompanying drawing, the specific embodiment in the present invention is elaborated.
Following steps are included for the technique of the interlaminar improvement of the composite laminated plate of unmanned fuselage, wing in the present invention:
1) preparation of material, equipment
The determination of the manufacture of the buying of the mainly buying of Unidirectional fibre bundle, mold materials in this step, the building of pultrusion molding process device, mould, basic resin system, technological parameter.In the present invention is the pin (general diameter is between 0.15mm ~ 1.5mm) that a kind of diameter is very little containing carbon fiber reinforced polymer composites pin, the pin base of applicable different composite material layer plywood was selected before preparation, the diameter of pin base has: Ф 0.4mm, Ф 0.6mm, Ф 0.8mm, Ф 1.0mm, Ф 1.2mm.Consumption by controlling carbon fiber in subsequent technique makes different composite pins, and controls the glue content of composite pin, as table 1:
Pin diameter table is prepared during table 135% 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, pultrusion molding process is adopted to make containing carbon fiber reinforced polymer composites pin, specifically put 1 by supply and continuous print fiber filament 7 is provided, this fiber filament 7 enters steeping vat 3 through fibre guide device 2, in steeping vat 3, pin base 8 is made to be combined with fiber filament 7 fixing, to enter in intensification mould 4 together with pin base 8 from steeping vat 3 fiber filament 7 out and be cured, coiler device 6 is entered again by the traction of draw-gear 5, wound up with the form of package by coiler device 6, so that storage and transport.
Separately, in order to improve the speed of pultrusion, can carry out preheating before fiber filament 7 is by dipping tank 3 to fiber filament 7, suitably heating dipping tank 3 regulates the resin temperature in dipping tank 3 simultaneously, to reduce the viscosity of resin, increase pin base 8 is adhesively fixed with fiber filament 7.In addition, also can at pin base 8 when meeting certain rigidity, just reel when not exclusively solidifying in intensification mould 4, again whole package is put into warming box until completion of cure, although one Post RDBMS operation that this method is many, but pultrusion speed can be improved, reduce tractive force requirement and mould requirement simultaneously.
3) containing the preparation of the foam preform of composite pin
In the process of embeding layer plywood, flexing is there is for preventing carbon fibre composite pin, first the carbon fibre composite pin of reel around storage is cut, and before the implanted prepreg of carbon fibre composite pin or foam preform, utilize process tool, the carbon fibre composite pin after solidification is processed into the cone of certain angle by polishing motor, bistrique etc., as shown in Figure 3, with the resistance reduced when being implanted to laminate and the damage reduced fiber filament in laminate.Carbon fibre composite pin after processing is implanted in foam with certain density orthogonal and obtains foam preform.
Foam for implanting carbon fibre composite pin is combined by bi-material, be respectively low density foam and Midst density foam, wherein low density foam is placed in upper strata, play a supporting role before embedding carbon fibre composite pin, can melt when autoclave or ultrasonic assistant embed routed simultaneously gradually, carbon fibre composite pin is transferred to downwards in prepreg laminate.Midst density foam is placed in lower floor, prevents carbon fibre composite pin from bending when stressed.Wherein, low density foam and Midst density foam can be identical material, as polyurethane foamed material.Also can be unlike material, as EPE, polyphenyl foam, polyethylene, phenol formaldehyde foam etc.
4) by carbon fibre composite pin composite implant material laminate
Carbon fibre composite pin is inserted in unmanned plane composite laminated plate and forms 3D network fibres structure, can be used for carrying out interlaminar improvement to dry state fiber preform and prepreg.This step can be completed by two kinds of methods, and one is single implantation, carbon fibre composite pin is one by one embedded respectively in uncured laminate 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 prepreg of laminate or the laminate of dry fabric laying.Another kind is integral embedded type, namely introduces foam preform, is embedded in the composite laminated plate of unmanned aerial vehicle body, wing by some carbon fibre composite pins simultaneously.Can adopt two kinds of diverse ways when embed wholly, wherein a kind of is the method utilizing autoclave method, and another kind is ultrasonic assistant embedded technology.Below distinct methods carbon fibre composite pin being implanted unmanned plane composite laminated plate is described in detail.
A) manual implantation
This manual mode implanted generally uses in the experimental stage, is embedded in the laminate of prepreg by independent for carbon fibre composite pin, shapingly prepares carbon fibre composite pin unmanned plane wallboard.The method can complete in two steps, and a step adopts low temperature prepregs material, utilizes Shen Fei company SUAV apparatus for production line, adopts that negative pressure of vacuum is shaping prepares carbon fibre composite pin unmanned plane wallboard; Another step is warm prepreg in adopting, and utilizes the big-and-middle-sized unmanned plane apparatus for production line of Shen Fei company, and manual implantation prepares carbon fibre composite pin unmanned plane wallboard.
B) autoclave is implanted
It is by carbon fibre composite pin embed wholly that autoclave is implanted, realize particular by autoclave forming process, as shown in Figure 4, specifically the foam preform containing carbon fibre composite pin is placed on uncured laminate and needs toughness reinforcing position, put vacuum bag again, along with the rising of temperature, the preimpregnation laminate of laminate softens gradually, foam preform melts routed gradually simultaneously, to transfer in the laminate of laminate under the pressure effect that carbon fibre composite pin is produced at autoclave, after cured, laminate is taken out from autoclave, unnecessary foam and carbon fibre composite pin is cut off with diamant, be enhanced laminated composite.This method is suitable for plane layer plywood.
In addition, when autoclave forming process, because the pressure ratio needed in the process of embedding carbon fibre composite pin is larger, therefore foam preform can add layer of metal plate or silicane rubber plate, thus changed by pressure, promote the embedment pressure of carbon fibre composite pin, control the thickness of upper strata low density foam layer simultaneously, resistance when carbon fibre composite pin is shifted to laminate by foam preform reduces.
C) ultrasonic assistant
Utilize special ultrasound applicator by between the laminate of the foam preform press-in laminate in foam preform, ultrasonic wave in ultrasound applicator can drive rifle cephalic tentacle to carry out dither, reduce the active force embedding foam preform and need, the heat that vibration produces can also make the resin of foam preform soften, and is easy to the transfer of foam preform.This method is different from utilizing the method for autoclave, is just removed by unnecessary foam preform before composite laminated plate solidification.As shown in Figure 5, finally by strengthen after prepreg put into heat riser solidify namely obtain tool carbon fibre composite pin strengthen laminated composite.In addition, need between foam preform and uncured laminate to place one deck polytetrafluorethylecoatings coatings fabric before embedding, its effect to prevent carbon fibre composite pin in laminate from toppling over because of stressed.
5) test report, analysis and numerical modeling
Utilize pendulum to carry out hitting 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 shooting by micro-imaging technique, record carbon fibre composite pin is to the failure mode of bonding property between toughness reinforcing between laminate, plate-muscle simultaneously.
In sum, not only can improve the interlaminar fracture toughness between laminate by above-mentioned technique, the structural design scope of unmanned plane composite laminated plate can also be promoted, also can be the direction that composite structure interconnection technique provides new simultaneously.
Claims (9)
1., for an interlaminar improvement technique for the composite laminated plate of unmanned aerial vehicle body, wing, comprise the following steps:
1) adopt the carbon fiber identical with unmanned plane composite structure and resin material, and utilize pultrusion molding process to prepare carbon fiber enhancement resin base composite material pin;
2) foam preform that carbon fiber-containing strengthens polymer matrix composites pin is prepared;
3) the carbon fiber enhancement resin base composite material pin in foam preform is implanted the composite laminated plate being used for unmanned aerial vehicle body, wing,
Described foam preform is to be laid in the plate body on described composite laminated plate, it comprises lower floor's low density foam and upper strata Midst density foam, and implant in the position being covered in the toughness reinforcing position of needs of described foam preform the described carbon fiber enhancement resin base composite material pin after solidification having the cone being processed into certain angle, carrying out described step 3) implantation time, described foam preform is laid on uncured described composite laminated plate and carries out temperature-pressure, described foam preform melts routed gradually, under the effect of the pressure, described carbon fiber enhancement resin base composite material pin is made to transfer in the laminate of described composite laminated plate,
4) Mechanics Performance Testing is carried out to the composite laminated plate after implantation carbon fiber enhancement resin base composite material pin.
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 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. the interlaminar improvement technique of the composite laminated plate for unmanned aerial vehicle body, wing according to claim 2, it is characterized in that: the method for described autoclave method the foam preform containing carbon fibre composite pin is placed on uncured laminate need toughness reinforcing position, put vacuum bag again, along with the rising of temperature, the preimpregnation laminate of laminate softens gradually, simultaneously foam preform melts routed gradually, will transfer in the laminate of laminate under the pressure effect that carbon fibre composite pin is produced at autoclave.
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 ultrasonic assistant embedded technology that 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: described ultrasonic assistant embedded technology utilizes special ultrasound applicator by between the laminate of the foam preform press-in laminate in foam preform, ultrasonic wave in ultrasound applicator drives rifle cephalic tentacle to carry out dither, reduce the active force embedding foam preform and need, the heat that vibration produces makes the resin of foam preform soften, and is easy to the transfer of foam preform.
6. the interlaminar improvement technique of the composite laminated plate for unmanned aerial vehicle body, wing as claimed in any of claims 2 to 5, it is characterized in that: above-mentioned steps 1) in pultrusion molding process be by supply put supply continuous fiber filament enter steeping vat, in steeping vat, pin base is made to be combined with fiber filament fixing, enter into intensification mould from steeping vat fiber filament out together with pin base to be cured, and wind up to store and to transport with the form of package.
7. the interlaminar improvement technique of the composite laminated plate for unmanned aerial vehicle body, wing according to claim 6, it is characterized in that: before fiber filament is by dipping tank, preheating is carried out to fiber filament, heat dipping tank simultaneously and regulate resin temperature in dipping tank can reduce the viscosity of resin.
8. the interlaminar improvement technique of the composite laminated plate for unmanned aerial vehicle body, wing according to claim 1, is characterized in that: the carbon fiber enhancement resin base composite material strengthening 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.
9. the interlaminar improvement technique of the composite laminated plate for unmanned aerial vehicle body, wing according to claim 1, 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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| 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 |
| 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 |
| 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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