CN100363546C - Method for sewing fibrous composite material and its sandwiched structure - Google Patents
Method for sewing fibrous composite material and its sandwiched structure Download PDFInfo
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- CN100363546C CN100363546C CNB2003101134842A CN200310113484A CN100363546C CN 100363546 C CN100363546 C CN 100363546C CN B2003101134842 A CNB2003101134842 A CN B2003101134842A CN 200310113484 A CN200310113484 A CN 200310113484A CN 100363546 C CN100363546 C CN 100363546C
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Abstract
The present invention relates to a sewing method for fibrous composites and sandwich structures thereof. The method comprises the following steps: a sewing machine and sewing threads are adopted for stitch sewing sites needing to be sewn in fibrous composites and the sandwich structures thereof. The method is characterized in that sewing stitches adopt wave type stitches, wherein, the sewing needle pitch a of the wave type stitches is from 0.2 to 10 centimeters, the row spacing b of the sewing stitches is from 0.2 to 10 centimeters, the sewing length c of one wave type stitch is from 0.2 to 10 centimeters, and the sewing height d of a wave type stitch peak is from 0.2 to 10 centimeters. The method enhances the impact and damage resistance of fibrous composites, strengthens the exhaustion and damage tolerance of the fibrous composites and reduces integral manufacturing cost and weight. The method makes advanced composites applied better in various fields. Especially, the method makes the performance of the advanced composites accord with applications in aircrafts of airplanes, spacecraft, etc., and in the field of communications and transportation and materiel facility.
Description
Technical field
The present invention relates to the sewing method of relevant fibrous composite and relevant sandwich, particularly relate to the used fibrous composite of forming by continuous fibers and resin matrix such as be used for aircraft, spacecraft aircraft, communications and transportation, construction material and weaponry and the sewing method of sandwich thereof.
Background technology
Generally require fibrous composite to have (a) very high specific strength and very big specific modulus, can make structure reduce quality significantly; (b) heterogeneous body and anisotropy make fibrous composite have designability, make fiber composite structure reach optimal design better according to design feature; (c) good fatigue resistance: differently in the fibrous composite slow down with interface energy and stop crackle to further expand, thereby postpone the generation of fatigue rupture; (d) moulding process is good, easily part, co-curing and the all-in-one-piece structure of any profile of moulding; (e) good DIMENSIONAL STABILITY, and THERMAL EXPANSION COEFFICIENT OF FIBER COMPOSITES still is adjustable.As a kind of new material that has function and architectural characteristic concurrently, these unique advantages of fibrous composite can make it just be widely used in every field, and have become one of four macrostructure materials of running neck and neck with aluminium alloy, titanium alloy and steel in the aircaft configuration.American lockheed for example. LMT announces that F-35 composite consumption will reach 30%, and wherein major part will be a fibrous composite; Calendar year 2001, Boeing announced Unmanned Combat Aerial Vehicle X-45 composite consumption: X-45A composite consumption is 45%, and following type of production X-45B composite will reach more than 90%, and wherein major part also all is a fibrous composite.The ratio of 21 century aircaft configuration employing fibrous composite will account for 1/3, make the weight ratio eighties of last century of aircaft configuration reduce 30%.Fibrous composite will adopt composite sewing process and resin transfer forming technique etc. so that it is used for the main stress member, alleviate aircaft configuration weight on the one hand, reduce the finished parts number on the other hand, reduce cost, and shorten the manufacturing cycle.
Yet manufacturing cost accounting example is maximum in the fiber composite component totle drilling cost, and therefore low-cost moulding manufacturing technology is present development priority.Trend both domestic and external in recent years is development liquid condition shaping composite material for weaving technology, the i.e. manufacturing technology of " affording to use ".Mainly comprise composite material for weaving and resin transfer moulding liquid condition shaping technology etc.By braiding, make preform, and liquid condition shaping such as liquid state infiltration and resin transfer molding through compile, knitting, woven, sewing etc., cost made in one piece is reduced, the interlayer enhancing, and reach the purpose of loss of weight.
In order to improve the interlaminar strength of fibrous composite, reduce the delamination failure of interlayer, improve the shock resistance damage ability of fibrous composite, strengthen fatigue and damage tolerance, cost made in one piece is reduced, reach the purpose of loss of weight, the method for employing has: (a) select for use high strain fiber and high tenacity resin to improve the boundary strength of laminate, but the fibrous composite cost is too high; (b) adopt advanced more composite engineering and process design method, this will be subjected to the restriction of composite material manufacturing technology itself development up till now unavoidably; (c) adopt interlayer to insert the technology of high tenacity material and particle, strengthen the Interleaving technology as interlayer, technology itself is comparatively complicated, though integral body strengthens to some extent, still can have the problems referred to above equally at the interlayer that is not enhanced; (d) along the enhancing of thickness direction, that is to say on the thickness direction of composite structure and increase reinforcing fiber materials, to improve anti-vertical resolution, increase interlaminar strength, as composite suturing skill (Stitching) and three-dimensional fiber braiding (3-D Weaving) technology, introduced as document 1 " L.K.Jain; etc; On the Effects ofStitching in CFRPs-II.Mode II Delamination Toughness; Composites Sciences andTechnology; Vo158 (1998), 829-837 ".The three-dimensional fiber knitting skill does not have the damage of the plane fibers that the fiber suturing skill produces, but can make the aggregation block that has big matrix in the structure during PROCESS FOR TREATMENT; With two-dimensional phase like veneer structure relatively, the plane mechanical property reduces significantly, and plane fibers fracture and resin hole is arranged when adopting the fiber suturing skill, still different suture ways can compensate its defect.
The elder generation fibrous composite stitching be with the dry state fiber (as cord fabric, tricot etc.) or prepreg (as by carbon fiber, glass fibre, boron fibre, aramid fiber, silicon carbide fibre and mutual assorted fibre and epoxy resin, phenolic resins, mylar, the bismaleimide peace, the inferior peace of polyamides, thermoplastic resin is formed by combining) and sandwich get togather according to certain shop layer sequential layer, use carbon fiber then, glass fibre, aramid fiber, boron fibre, twice-laid yarn such as silicon carbide fibre with industrial sewing machine or domestic sewing machine or quilting machine people along direction perpendicular to the shop layer plane, generally speaking be thickness direction, pass up and down according to certain technological parameter, and the sewing mode that in the laminate plane, moves along a certain direction.What adopt basically at present in the world is that straight line is sewed up form, shown in Fig. 1 .1.
Straight line is sewed up the breakdown strength that can improve interlayer to a certain extent, but the interior performance of the face that has but reduced fibrous composite and sandwich thereof, as tension, resistance to compression and bending rigidity and tension, resistance to compression and the bending strength etc. of material have been reduced, introduced as document 2 " A.P.Mourtiz; Flexural Properties of Stitched GRPLaminates, Composites A, Vol27; 1996,523-530 ".Sew up in order to improve straight line that performance in the face that form causes for fibrous composite and sandwich thereof reduces and the raising degree of interlaminar failure intensity, in the hope of reaching the industrial applications level.
The domestic fibrous composite of continuous fibers and resin matrix composition and the suturing skill industrial applications of sandwich thereof of still not carrying out.In addition, sew up this mode at common wave and only be suitable for nonwoven adhesive interlining cloth, CN2327709Y patent for example, but still be not used in the used fibrous composite of forming by continuous fibers and resin matrix of aircraft, communications and transportation, construction material and weaponrys such as aircraft, spacecraft.
Summary of the invention
The objective of the invention is to: (1) sews up in order to improve straight line that performance in the face that form causes for fibrous composite and sandwich thereof reduces and the raising degree of interlaminar failure intensity, so that bring into play the application of advanced composite material better, particularly use in aircraft such as aircraft, spacecraft, communications and transportation and weaponry field in each field; (2) in order to improve the elegant in appearance of suture on the panel; (3) improve the firm degree and the anti-fracture energy of suture, make that to be sewn knot more stable on the whole, and and on the non-rectilinear any 3 remain straight line; In order to improve the interlaminar strength of fibrous composite, reduce the delamination failure of interlayer, improve the shock resistance damage ability of fibrous composite, strengthen fatigue and damage tolerance, cost made in one piece is reduced, reach the purpose of loss of weight, thereby a kind of have performance is good, elegant in appearance in the tenacity excellent, face the fibrous composite that is applicable to industrial applications and the sewing method of sandwich material thereof are provided.
The objective of the invention is to realize by the following technical solutions:
The invention provides the sewing method of a kind of fibrous composite and sandwich thereof, comprising: adopt Sewing machines and suture, the place that needs to sew up on fibrous composite is sewed up; It is characterized in that: described stitching cabling form adopts waveform form cabling, and wherein waveform form cabling sewing needle is 0.2-10 centimetre apart from a; Sewing up cabling line-spacing b is 0.2--10 centimetre; A waveform cabling stitch length c is 0.2-10 centimetre; The height d that waveform is walked the suturing with thread management peak is 0.2-10 centimetre.
Described Sewing machines comprises: machinery or automatical stitching robot are sewed up in domestic sewing machine, industry.
Described suture comprises: the suture of all kinds of synthetic fiber sutures such as carbon fiber, glass fibre, boron fibre, aramid fiber and cotton fiber, flax fibre, silk fiber or all kinds of natural fabrics.
Described fibrous composite comprises: the fibrous composite of thermoplastic resin such as thermosetting resin such as carbon fiber, glass fibre, boron fibre, aramid fiber, silicon carbide fibre and assorted fibre reinforced epoxy thereof, phenolic resins, mylar, BMI, polyimides and polyether-ether-ketone, PEKK, polyether-ketone, polyether sulfone, PEI, polyphenylene sulfide, or and the corresponding sandwich of above-mentioned material.
The sewing method of a kind of fibrous composite provided by the invention and sandwich thereof, be applicable to the stitching of advanced composite material and relevant sandwich (containing comb core, foam core material etc.) material, such as the stitching of field material therefors such as aerospace flight vehicle, traffic transport industry (for example car industry, shipbuilding industry etc.), petrochemical industry (for example recovery tower, reactive tank jar etc.), (for example corrugated tile, building prefabrication assembly), weaponry, mining industry, stationery sports goods.
Advantage of the present invention:
Adopt waveform form cabling of the present invention, material after sewing up on fibrous composite and the sandwich thereof, because the interlaminar strength of fibrous composite is improved, reduced the delamination failure of interlayer, improve the shock resistance damage ability of fibrous composite, strengthen fatigue and damage tolerance, cost made in one piece is reduced, and reach the purpose of loss of weight, bring into play the application of advanced composite material in each field better, its performance particularly reaches the application that meets in aircraft such as aircraft, spacecraft, communications and transportation and weaponry field.Relevant performance indications see Table 1, reach the needs of commercial Application as seen from Table 1 fully.
Because the present invention adopts wave to sew up form, changed the direction of sewing up form, make the track of sewing up the suture needle walking become curve by straight line, one, elegant in appearance, two, any 3 on the curve have formed that to be similar to mathematical Atria point stable, make that to be sewn knot more stable on the whole, and and on the non-rectilinear any 3 remain straight line; Three, sew up with straight line and compare, increased substantially the anti-fracture energy of fibrous composite, and with the reduction homogenising of performance in the fibrous composite face.
The mechanical property table that table 1 is relevant
| Performance indications | Wave is sewed up | Straight line is sewed up |
| Stretch modulus 1(Mpa) | 145.14 | 125.377 |
| Bending modulus 2(Mpa) | 120.84 | 105.61 |
| I type fracture toughness 3(KJ/m) | 0.90 | 0.63 |
| II type fracture toughness 4(KJ/m) | 2.27 | 1.64 |
Annotate: 1-is obtained by static stretching experiment; 2-is obtained by static three-point bending experiment; 3-is obtained by static I type fracture experiment; 4-is obtained by static II type fracture experiment.
Description of drawings
Fig. 1 .1 represents that the suture of the straight line of employing stitching is at present arranged schematic diagram in the world
The suture that Fig. 2 (a) composite undaform of the present invention is sewed up is arranged (schematic top plan view)
The suture that Fig. 2 (b) composite undaform of the present invention is sewed up is arranged (A-A generalized section)
The lock-stitch schematic diagram of Fig. 3 composite of the present invention
The wave of Fig. 4 composite of the present invention is sewed up the relative dimensions schematic diagram
The drawing explanation
1-composite 2-sews up cabling
3-syringe needle line 4-bobbin thread
A is the sewing needle distance, and b is the of suture line distance, and c is a stitch length, and d is for sewing up width
The specific embodiment
With reference to figure 2-4, employing be common small-sized household Sewing machines (the Toyota board household small-size Sewing machines that the subordinate's of group company of Japanese Toyota Japanese AISIN Jinggong Co., Ltd produces), and aramid fiber (trade mark of du pont company is Kevlar
29 aramid fiber), the fibrous composite of desiring to make is: carbon-fibre reinforced epoxy resin is the composite 1 of matrix; The laminate that this composite 1 is formed by the multilayer laying; Use domestic sewing machine, carried out the stitching cabling 2 of wave form thereon, wherein sewing needle is 4mm apart from a, of suture line is two kinds of 5mm and 10mm apart from b, and stitch length c is 7mm, and sewing up width d is 2mm, described stitching cabling adopts lock-stitch, as shown in Figure 3, and syringe needle line 3 and bobbin thread 4.Through static stretching experiment, static state and dynamic three-point bending experiment, static and dynamic fracture experiment, as shown in table 1, proved that wave lock-stitch of the present invention is sewn on raising fracture toughness, the improvement face interior mechanics performance far better than the straight line of present international popular, reached the purpose of fibrous composite Strengthening and Toughening, very big prospect has been arranged in the industrial applications of composite.
What adopt is common industrial sewing machine, and carbon fiber, and the fibrous composite of desiring to make is: glass fibre-reinforced phenolic resin is the composite 1 of matrix; The laminate that this composite 1 is formed by the multilayer laying; Use domestic sewing machine, carried out the stitching cabling 2 of wave form thereon, wherein sewing needle is 10mm apart from a, of suture line is two kinds of 1mm and 8mm apart from b, stitch length c is two kinds of 0.2mm or 10mm, sewing up height d is 0.2mm or 10mm (as shown in Figure 3), and described stitching cabling adopts lock-stitch (as shown in Figure 4).Through the Compound Material Engineering theory analysis, wave lock-stitch of the present invention can increase substantially the toughness of fibrous composite and along the rigidity of thickness direction, realized that fibrous composite strengthens toughness reinforcing purpose, can be used for fibrous composite and strengthen toughness reinforcing suitability for industrialized production.
What adopt is the automatical stitching robot, and glass fibre, and the fibrous composite of desiring to make is: aramid fiber strengthens the inferior peace of polyamides and is the composite of matrix; This composite is earlier the dry state aramid fiber to be sewed up, and then adopts RTM technology that the inferior peace of polyamides resin is fused in the dry state aramid fiber of having sewed up; Use domestic sewing machine, carried out the stitching cabling of wave form on the dry state fiber, wherein sewing needle is 0.2mm apart from a, of suture line is two kinds of 5mm and 10mm apart from b, stitch length c is two kinds of 3mm and 6mm, and sewing up height d is 5mm, and described stitching cabling adopts lock-stitch.Through the numerical simulation study analysis, wave lock-stitch of the present invention can increase substantially the toughness of fibrous composite and along the rigidity of thickness direction, realized that fibrous composite strengthens toughness reinforcing purpose, can be used for fibrous composite and strengthen toughness reinforcing suitability for industrialized production.
What adopt is common small-sized household Sewing machines (homemade), and aramid fiber (trade mark of du pont company is Kevlar
29 aramid fiber), the fibrous composite sandwich of desiring to make is: the frp honeycomb structure, its panel is the fibrous composite of glass fiber reinforced epoxy resin matrix, and fuse is the composite of carbon fiber reinforced epoxy resin-based body, adopts the good epoxyn of compatibility; Use domestic sewing machine, carried out the stitching cabling of wave form thereon, wherein sewing needle is 6mm apart from a, and of suture line is two kinds of 3mm and 6mm apart from b, and stitch length c is 5mm, and sewing up width d is 4mm, and described stitching cabling adopts the wave lock-stitch.Analyze after deliberation, wave lock-stitch of the present invention than the straight line of present international popular be sewn to the fracture toughness that improves fibrous composite sandwich, improve on its whole face interior mechanics performance far better, reached the purpose of fibrous composite sandwich Strengthening and Toughening, very big prospect has been arranged in the industrial applications of composite material sandwich structure.
Claims (5)
1. one kind is suitable for the method that fibrous composite and sandwich thereof are sewed up, and comprising: adopt Sewing machines and suture, suturing with thread management is walked in the place that needs to sew up on fibrous composite and sandwich thereof; It is characterized in that: the described cabling form of walking suturing with thread management adopts waveform form cabling, and wherein waveform form cabling sewing needle is 0.2-10 centimetre apart from a; Sewing up cabling line-spacing b is 0.2-10 centimetre; A waveform cabling stitch length c is 0.2-10 centimetre; The height d that waveform is walked the suturing with thread management peak is 0.2-10 centimetre.
2. by the described method that is suitable for the composite stitching of claim 1, it is characterized in that: described stitching cabling adopts the wave lock-stitch.
3. by the described method that is suitable for the composite stitching of claim 1, it is characterized in that: described Sewing machines comprises domestic sewing machine, industrial sewing machine or automatical stitching robot.
4. by the described method that is suitable for the composite stitching of claim 1, it is characterized in that: described suture is: carbon fiber suture, glass fibre suture or aramid fiber suture.
5. by the described method that is suitable for the composite stitching of claim 1, it is characterized in that: the laminate that described composite is formed by multilayer carbon-fibre reinforced epoxy resin laying; Or
The laminate that described composite is formed by compound glass fiber reinforcement phenolic resins laying; Or
Described composite is made by following technology: earlier the dry state aramid fiber is sewed up, then adopt RTM technology to be fused in the dry state aramid fiber of having sewed up the inferior peace of polyamides resin or the frp honeycomb structure, the panel of described frp honeycomb structure is the fibrous composite of glass fiber reinforced epoxy resin matrix, and fuse is the composite of carbon fiber reinforced epoxy resin-based body.
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| CNB2003101134842A CN100363546C (en) | 2003-11-12 | 2003-11-12 | Method for sewing fibrous composite material and its sandwiched structure |
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| CNB2003101134842A CN100363546C (en) | 2003-11-12 | 2003-11-12 | Method for sewing fibrous composite material and its sandwiched structure |
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| CN100363546C true CN100363546C (en) | 2008-01-23 |
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| CN110039792A (en) * | 2018-11-22 | 2019-07-23 | 阜宁云逸航空复合材料有限公司 | The cellular production method and device of continuous fiber reinforcement side wall |
| CN110438668B (en) * | 2019-07-10 | 2021-06-22 | 南京铁道职业技术学院 | Split type traction seam laying device |
| CN111421843B (en) * | 2020-03-31 | 2021-08-03 | 成都飞机工业（集团）有限责任公司 | Composite material sewing method |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4357193A (en) * | 1979-05-21 | 1982-11-02 | Rockwell International Corporation | Method of fabricating a composite structure |
| US4445951A (en) * | 1981-07-01 | 1984-05-01 | Rolls-Royce Limited | Method of manufacturing composite materials |
| CN1046004A (en) * | 1989-03-31 | 1990-10-10 | 纳幕尔杜邦公司 | Stitchbonded nonmoven fabric |
| CN2247186Y (en) * | 1996-06-13 | 1997-02-12 | 谢永波 | Non-woven pile bonded lining fabric |
| CN2327709Y (en) * | 1998-04-23 | 1999-07-07 | 湖北省荆州市红枫衬布有限公司 | Non-woven linings with waved suture |
| US6179945B1 (en) * | 1998-12-30 | 2001-01-30 | Owens Corning Fiberglas Technology, Inc. | Process for filament winding composite workpieces |
| CN1394739A (en) * | 1996-12-31 | 2003-02-05 | 欧文斯-康宁玻璃纤维西班牙有限公司 | Composite fabric |
-
2003
- 2003-11-12 CN CNB2003101134842A patent/CN100363546C/en not_active Expired - Fee Related
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4357193A (en) * | 1979-05-21 | 1982-11-02 | Rockwell International Corporation | Method of fabricating a composite structure |
| US4445951A (en) * | 1981-07-01 | 1984-05-01 | Rolls-Royce Limited | Method of manufacturing composite materials |
| CN1046004A (en) * | 1989-03-31 | 1990-10-10 | 纳幕尔杜邦公司 | Stitchbonded nonmoven fabric |
| CN2247186Y (en) * | 1996-06-13 | 1997-02-12 | 谢永波 | Non-woven pile bonded lining fabric |
| CN1394739A (en) * | 1996-12-31 | 2003-02-05 | 欧文斯-康宁玻璃纤维西班牙有限公司 | Composite fabric |
| CN2327709Y (en) * | 1998-04-23 | 1999-07-07 | 湖北省荆州市红枫衬布有限公司 | Non-woven linings with waved suture |
| US6179945B1 (en) * | 1998-12-30 | 2001-01-30 | Owens Corning Fiberglas Technology, Inc. | Process for filament winding composite workpieces |
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