CN103925267A - Composite material and metal connection structure and forming method thereof - Google Patents
Composite material and metal connection structure and forming method thereof Download PDFInfo
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- CN103925267A CN103925267A CN201410103278.1A CN201410103278A CN103925267A CN 103925267 A CN103925267 A CN 103925267A CN 201410103278 A CN201410103278 A CN 201410103278A CN 103925267 A CN103925267 A CN 103925267A
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- 229910052751 metal Inorganic materials 0.000 title claims abstract description 120
- 239000002184 metal Substances 0.000 title claims abstract description 115
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- 238000004026 adhesive bonding Methods 0.000 description 3
- 229910052796 boron Inorganic materials 0.000 description 3
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- KXGFMDJXCMQABM-UHFFFAOYSA-N 2-methoxy-6-methylphenol Chemical compound [CH]OC1=CC=CC([CH])=C1O KXGFMDJXCMQABM-UHFFFAOYSA-N 0.000 description 1
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- Laminated Bodies (AREA)
- Moulding By Coating Moulds (AREA)
Abstract
The invention relates to a composite material and metal connection structure comprising a metal connector and a composite material connector. The composite material and metal connection structure is characterized in that connected parts of the metal connector and the composite material connector are provided with thin pins; one end of every thin pin is fixedly connected to the metal connector, and the other end of every thin pin is inserted into the composite material connector. The invention further discloses a forming method of the connection structure. The forming method includes the steps of a, fixedly connecting one end of every thin pin to the metal connector; b, placing the other end of every thin pin into composite material, and not cutting off reinforcing material of fiber with the direction matching with the shape of the thin pins; c, solidifying the composite material to form. The composite material and metal connection structure and the forming method thereof have the advantages that the composite material of fiber is not cut off by the thin pins on the metal connector, the problem of hole-edge stress concentration caused by hole making is avoided, glue cracking and laminate outside layering can be suppressed, the connection structure has the advantages of both the glued structure and the mechanically connected structure, and defects in the glued structure and the mechanically connected structure are largely overcome.
Description
Technical field
Patent of the present invention relates to the Placement between a kind of dissimilar materials, the interconnection technique between especially a kind of fibre reinforced composites and metallic material.
Background technique
Compare traditional metallic material, fibre reinforced composites (comprise resin-based carbon fiber reinforced composite, resin-base glass fibre reinforced composite, resin base glass fiber reinforced composite, resin base boron fibre reinforced composite, resin base graphite fiber reinforced composite, and metal base and ceramic matric composite, Deng) there is high specific strength, high specific stiffness, high temperature resistant, corrosion-resistant, endurance, damping shock absorption is good, fail-safety is good, performance can design, anisotropy, the advantages such as multifunctionality and developability, make composite material be applied to more and more aviation, space flight, vehicle, boats and ships, building, oil, bridge, the engineering field such as wind-powered electricity generation and building.Yet, compare metallic material, fibre reinforced composites also generally have the shortcomings such as humidity resistance is poor, crushing strength is low, interlaminar strength is low, expensive, cause its substituted metal material completely.Therefore, although the application of composite material can be made into large-scale component by the mode of global formation, reduce assembling work, at some position, also need to be connected with Structural Hardware.
Composite material has different physics, chemistry and mechanical property from metal, and the connection between them belongs to dissimilar materials and connects.Traditional composite material comprises that with the technique that is connected of metal mechanical connection, splicing and the two common mixing of applying connect.Compare splicing, mechanical connection is reliable, can transmit larger load.By rational fastening piece arrange, Bolt-hole fits and fastening piece clamping force can improve metal to a certain extent and composite material machinery join strength.But the connection of metal-composite material machinery also has following shortcoming: 1) owing to having cut off composite fiber and metallic material in drilling process, cause limit, hole stress seriously to be concentrated, thereby have to increase the thickness of composite material and metal connecting piece, and then cause weight to increase; 2) use of a large amount of fastening pieces, needs a large amount of drilling and assembling work, and cost is high, the cycle is long, and has increased structure weight; 3) potential corrosion problem may be brought in fastening piece and hole; 4), because composite material is different from metal material mechanics performance, they are also different to the requirement of the assembly parameters such as screw-down torque, interference fit, but normally identical with these parameters in metal mixed construction machine linkage structure at composite material.
Compare mechanical connection, the structure weightening finish of splicing is less, and the stress of connection part is concentrated lower, and fatigue performance is good, but due to the process characteristic glueing joint, it has following shortcoming: 1) the mechanical property dispersiveness of cementing structure part is larger; 2) opposite external force is responsive; 3) danger that humidity resistance is poor, glue-line has ageing failure; 4), thereby destroy, there is to be suddenly difficult to prediction in fragility; 5) detection difficult; 6) not quick detachable.
Glue spiral shell mixes connection and overcomes shortcoming comprehensive their advantage of performance of two kinds of Placements above, but the use of fastening piece has improved the weight of cost and structure, has weakened to a certain extent the advantage of using composite material to bring.The fiber or the metal stub that by the diameter that directly embedding is cured in the prepreg members of gluded joint, are 0.2-1mm, and then curing prepreg members forms veneer, can increase the performance of the delamination of adhesive bonding of composites joint, therefore but the applied fiber of this technique or metal stub cannot embed metal, be not suitable for the linkage structure of mixing of metal and composite material.
Summary of the invention
The technical problem to be solved in the present invention is, overcome the shortcoming of the various Placements of conventional composite materials and metal, the method that the linkage structure of a kind of composite material and metal is provided and forms this linkage structure, makes composite material and metal connecting structure have higher bearing capacity and reliability.
The present invention solves the problems of the technologies described above adopted technological scheme: the linkage structure of a kind of composite material and metal, comprise metal connecting piece, composite material link, the position that is connected at metal connecting piece with composite material link, also be provided with fine needle, described fine needle one end is fixedly connected on metal connecting piece, and the other end inserts composite inner.Thereby by this fine needle structure, make the combination between metal connecting piece and composite material link more firm, reliable.
Further, described composite inner is provided with fibre reinforced materials, the position that is connected at described metal connecting piece with composite material link, and the trend of described fiber and the form fit of fine needle, form the fiber layout structure around fine needle.
Further, described fibre reinforced materials arranges multilayer, between each layer of fiber, moves towards angled, forms the staggered structure of fiber.
In addition, distance between described fine needle termination and metal connecting piece is less than or equal to composite material link at the thickness of relevant position, thereby can not pass from composite material, described fine needle is printed process engineerinies such as (laser stack shapings) and is fixed on metal connecting piece by welding, splicing, 3D.
Further, described fine needle is a plurality of, its sectional shape is circular, oval, square or rectangle, the end of one end that described fine needle is not connected with metallic interconnect is set to size and becomes large cylindricality, circle, ellipse, L shaped, T shape or hook-shape structure, thereby increases the antistripping ability of fine needle and the rigidity of linkage structure.Can there be the circle of leading of certain radius fine needle and metallic interconnect joint, thereby strengthen the strength and stiffness of fine needle.
Further, the axis of described fine needle is consistent with the normal direction of the joint of metal connecting piece, or the setting that forms an angle, and described each fine needle is the parallel or setting that forms an angle each other.
In addition, metal connecting piece can be for tabular, composite material and metal connecting structure metal and composite material can be both single bridging arrangements, the side at metal connecting piece arranges fine needle, forms linkage structure, can be also two bridging arrangements, in the relative both sides of metal connecting piece, fine needle is set respectively, two sides is all connected with composite material, or even multi-link board connecting structure, need on all faying surfaces of all metallic interconnects, produce fine needle.The faying surface of metal and composite material connecting plate can be both plane, can be also more complicated curved surface.This metal connecting piece can also be for bar-shaped, and bar-shaped metal connecting piece is provided with fine needle around this club shaped structure.Described fine needle is inserted into respectively in composite material link.
A method that forms above-mentioned linkage structure, comprises the steps,
A, is fixedly connected on fine needle one end on metal connecting piece;
B, is placed in composite inner by the fine needle the other end, and cut staple reinforcing material not, the trend of fiber and fine needle form fit;
C, is cured moulding to composite material.
Further, in a step, fine needle is fixed on metal connecting piece by process engineerinies such as welding, splicing, 3D printings; In b step, described fine needle is inserted into composite inner, is only the local detachment original position of fiber tuft in insertion process.
Further, in b step, described fiber is by laying or be wound around the junction plane place that is arranged on described link, in c step, first the fibrous structure of the laying in the composite material of making and metal connecting structure or winding is injected to curing agent, and then be placed into heating, cure under pressure moulding in heat pressing forming device.
Further, in b step, described composite material arranges multilayer, the fiber orientation of inner each layer of described multilayer materials is angled, form the staggered structure of fiber, described composite material is made by prepreg or is made by prefabricated component, correspondingly in c step, to the composite material of being made by prepreg, directly the composite material assembling and metal connecting structure are heated in heat pressing forming device, cure under pressure moulding, to the composite material of being made by prefabricated component, first the prefabricated component in the composite material assembling and metal connecting structure is injected to curing agent, and then be placed in heat pressing forming device and heated, cure under pressure moulding.
First according to the material of fine needle and link and geometrical shape, the process engineerinies such as application welding (comprising melting welding, diffusion welding, soldering etc.), splicing or 3D printing are made some fine needles on the surface of metal connecting piece, then the metal connecting piece with fine needle and composite material assembly parts according to relative position place, fixing, and guarantee fine needle to pass in the process of material prepreg or prefabricated component not cut staple and just fiber tuft part detachment original position.Finally the metal-composite material assembly parts solidifying assembling, thereby make metal and composite material glue-many fine needles connection member.Wherein prepreg refers to the also uncured fibre reinforced composites with curing agent, and prefabricated component refers to the composite fiber part of laying moulding that does not add curing agent.Wherein curing agent mainly refers to various glue and resin, hot thermosets such as epoxy resin, phenolic resin.
Need to make in metal connecting piece connection area some fine needles of arranging according to certain position and attitude, then become one with adhesive bonding of composites, these fine needles penetrate composite material, form fibre reinforced composites and metal connecting structure, and improve the bearing capacity of linkage structure.Preferably fine needle quantity, arrange relevantly with the geometry of attitude and linkage structure and material characteristics and external load, need to obtain according to test or through the analytical technology of verification experimental verification.Described external load comprises cyclic loading, random load and the impulsive load etc. of static stretch load, static compressive load, static shear load, different stress ratios.Described arranges, and the line-spacing, row that refers to fine needle is apart from, the spatial relation such as end distance, back gauge, line number, columns.Described attitude, refers to the position relationship of the relative metal connecting piece of axis of fine needle, and the attitude of each fine needle can be identical, also can be different, and the angle between each fine needle axis and link is determined according to concrete load condition.Need to be according to fine needle and metal connecting piece material and geometrical shape different, select melting welding, diffusion welding, soldering, 3D to print or the technique such as splicing goes out fine needle in metal connecting piece surface Machining.
Beneficial effect of the present invention: the fine needle on metal connecting piece does not cut off composite fiber, limit, the hole problem of stress concentration that does not have drilling to cause, thereby not only there is the effect that Z-pin and fastening piece suppress glue-line cracking and the outer layering of unclad laminate surface, and fine needle is by the cementation power with composite material, axial friction and laterally mechanicals efforts, and the glue-line on the faying surface between link together transmits the load between link, there is cementing structure and mechanical connecting structure simultaneously, and overcome to a great extent the two shortcoming, the quantity of fine needle, position and attitude can be optimized according to the feature of link shape and external load, thereby improve composite material and the metal connecting structure strength and stiffness under static and fatigue load.
Accompanying drawing explanation
Fig. 1 is glue-many fine needles long splice composition of composite material and metal.
Fig. 2 is the location diagram between fine needle and reinforcing fiber and matrix.
Fig. 3 is that fine needle is perpendicular to metal connecting piece surface.
Fig. 4 is that fine needle is tilted to composite material link.
Fig. 5 is that fine needle is tilted to metal connecting piece.
Fig. 6 is that fine needle is arranged relatively.
Fig. 7 is that fine needle is arranged dorsad.
Fig. 8 is fine needle cross arrangement.
Fig. 9 is that fine needle termination is cylindricality.
Figure 10 is that fine needle termination is spherical.
Figure 11 is that fine needle termination is for oval.
Figure 12 is that fine needle termination is dihedral.
Figure 13 is that fine needle termination is T shape.
Figure 14 is that fine needle termination is back-shaped.
Figure 15 is a sheet metal and two two bridging arrangements that composite panel forms.
Figure 16 is two sheet metals and the two bridging arrangements that composite panel forms.
Figure 17 is multi-link board connecting structure.
Figure 18 is that connection faying surface is curved surface.
Figure 19 is that the cross section of bar-shaped link faying surface is polygonal.
Figure 20 is that the cross section of bar-shaped link faying surface is circle.
Figure 21 is that fine needle is connected with metal connecting piece by the blind hole on sheet metal.
Figure 22 is that fine needle is connected with metal connecting piece by the through hole on sheet metal.
1. composite material links in figure, 2. metal connecting piece, 3. glue-line, 4. fine needle, 5. 0o fiber laying, 6.90o fiber laying, 7.45o fiber laying, 8.45o fiber laying.
Embodiment
Below in conjunction with the drawings and specific embodiments, the present invention will be further described.
The linkage structure of a kind of composite material and metal, comprise composite material link 1 and metal connecting piece 2, glue-line 3 between metal connecting piece 2 and composite material link 1, this glue-line 3 can apply in metal surface, can be also self-assembling formation in composite material link 1 solidification process.The position that is connected at metal connecting piece 2 with composite material link 1, is also provided with a plurality of fine needles 4, and fine needle 4 one end are fixedly connected on metal connecting piece 2, and the other end inserts composite material link 1 inside.
Further, described composite material 2 inside are provided with fibre reinforced materials, this fiber can be carbon fiber, glass fibre, aramid fibre, boron fiber, the materials such as graphite fiber, form resin-based carbon fiber reinforced composite, resin-base glass fibre reinforced composite, resin base glass fiber reinforced composite, resin base boron fibre reinforced composite, resin base graphite fiber reinforced composite, and the multiple fibre reinforced composites such as metal base and ceramic matric composite, the position that is connected at metal connecting piece 2 with composite material link 1, the form fit of the trend of fiber and fine needle 4, be that fiber is avoided fine needle 4, thereby form the fiber layout structure around fine needle 4.In addition, in composite material 2, fibre reinforced materials arranges multilayer, between each layer of fiber, moves towards angled, form the staggered structure of fiber, the multi-layer structures such as 0o fiber laying 5 as shown in Figure 2 of example, 90o fiber laying 6,45o fiber laying 7,45o fiber laying 8.
Distance between fine needle 4 terminations and metal connecting piece 2 is less than or equal to composite material link 1 at the thickness of relevant position, thereby the linkage structure fine needle 4 after moulding can be not outstanding by the surface of composite material link 1.Fine needle 4 is printed and is fixed on metal connecting piece 1 by welding, splicing, 3D.In structure shown in Fig. 1, composite material link 1 also can be connected with a plurality of pins 4 by glue-line 3 with metal connecting piece 2.
This glue-line 3 can transmit two shearing loads between link.A plurality of fine needles 4 that are distributed in two ends, connection area have cementation power and axial rub active force with the matrix in composite material 1, all have horizontal mechanicals efforts, as shown in Figure 2 with matrix and reinforcement (comprising fibre reinforcement) in composite material 4.Fine needle 4 not only suppresses glue-line cracking and unclad laminate surface layering outward, and and faying surface on glue-line 3 together transmit two load between link.
As shown in Fig. 3-Fig. 8, the axis of fine needle 4 can be consistent with the normal direction of the joint of metal connecting piece 2, or form an angle and be obliquely installed, and each fine needle 4 is the parallel or setting that forms an angle each other.According to the geometry of link and material characteristics and external load situation (stretching, compression or shearing, static, dynamically or circulation etc.), how much of fine needles on optimal design metallic interconnect and arrangement, comprise geometric properties (sectional shape, size, surface quality, termination shape, length etc.), position (line-spacing, row distance, back gauge, end distance etc.), quantity (line number, columns) and the attitude (fine needle axis and the angle of metallic interconnect, the relative angle of different fine needles etc.) of fine needle.The distribution of thin nail can be both regular, can be also irregular.If the regular shape of link, power transmission are even, the also rule of arranging conventionally of fine needle; If link out-of-shape or power transmission are inhomogeneous, arranging of fine needle also can be irregular.When link transmits axial tension or compressive load, fine needle is usually located at the two ends of connection area, because the interlaminar stress that the outer peeling force of the face that the glue-line at the two ends of connection area bears conventionally and composite material connecting plate bear is higher, than being easier to, occurs losing efficacy; During the interior shearing load of connection area transfer surface, the common irregular distribution of fine needle.
As shown in Fig. 9-Figure 14, the sectional shape of fine needle 4 can be circular, oval, square or rectangle, the end of one end that fine needle 4 is not connected with metallic interconnect 2 is set to size and becomes large cylindricality, circle, ellipse, L shaped, T shape or hook-shape structure, thereby increases the antistripping ability of fine needle and the rigidity of linkage structure.Can there be the circle of leading of certain radius fine needle 4 and metallic interconnect 2 joints.
Metal connecting piece 2 can be for tabular, composite material 1 can be both single bridging arrangement with metal connecting structure, as shown in Figure 1, the side at metal connecting piece 2 arranges fine needle 4, form linkage structure, also can be two bridging arrangements, as shown in Figure 15 and Figure 16, in the relative both sides of metal connecting piece 2, fine needle 4 is set respectively, two sides is all connected with composite material 1, or even multi-link board connecting structure, as shown in figure 17, need on all faying surfaces of all metallic interconnects, produce fine needle, for example equal fixing fine needle 4 in four sides of sheet metal 2.The faying surface of metal and composite material connecting plate can be both plane, as shown in Fig. 1,15-17, can be also more complicated curved surface, as shown in figure 18.This metal connecting piece 2 can also be for bar-shaped, and as shown in Figure 19,20, bar-shaped metal connecting piece is provided with fine needle 4 around this club shaped structure.Above-mentioned fine needle 4 is inserted into respectively in composite material link 1.In the linkage structure of fine needle 4 and metal connecting piece 2, also the hole of mating with fine needle profile can be set on metal connecting piece 2, fine needle 4 is embedded in metal connecting piece 2, this hole can be blind hole, as shown in figure 21, can be also through hole, as shown in figure 22, fine needle can be by glue bond in hole, also can be by being welded to connect.In addition, in the situation that being through hole, fine needle is through through hole, thereby can realize easily above-mentioned pair of bridging arrangement or multi-link board connecting structure, now the means of fixation between fine needle and metal connecting piece 2 even can not used the modes such as glue or welding, only fine needle is passed to hole, or use the interference Placement in fine needle and hole.
In addition, the invention also discloses a kind of method that forms above-mentioned linkage structure, comprise the steps,
A, is fixedly connected on fine needle 4 one end on metal connecting piece 2;
B, is placed in composite material link 1 inside by fine needle 4 the other ends, and cut staple reinforcing material not, the trend of fiber and fine needle form fit;
C, is cured moulding to composite material 1.
In a step, fine needle 4 is fixed on metal connecting piece 2 by process engineerinies such as welding, splicing, 3D printings; In b step, fine needle 4 is inserted into composite material 1 inside, is only the local detachment original position of fiber tuft in insertion process.
In b step, for fine needle 4 being arranged on to composite material 1 inside, the position of fine needle 4 is set at metallic interconnect 2, the fiber of composite material is arranged on to the junction plane place of two links by the mode of laying or being wound around, by this mode that fiber is laid or is wound around, reinforcing fiber can lay around fine needle 4 in every way, can form around fine needle 4 composite fiber structures, can carry out precise forming to the shape of link joint area, can obtain and there is good mechanical property joint structure; In c step, first the fibrous structure of the laying in the composite material of making and metal connecting structure or winding is injected to curing agent, and then be placed into heating, cure under pressure moulding in hot-press tank.The curing agent of selecting in the present embodiment is epoxy resin.
In addition, in b step, composite material 1 arranges multilayer, and the fiber orientation of described multilayer materials 1 inner each layer is angled, forms the staggered structure of fiber, and described composite material 1 is made by prepreg or made by prefabricated component.Correspondingly, in c step, be divided into two kinds of different processing modes, mode one, if composite material link 1 is made by prepreg, fine needle 4 passes according to the multilayer materials prepreg of certain laying order lay, then fix the material prepreg of different layings and the relative position of metal connecting piece 1 product, and a metal-composite material assembly parts that assemble heats in hot-press tank, cure under pressure moulding, thereby make composite material and many fine needles of metal connection member; Mode two, if composite material link 1 is made by prefabricated component, fine needle 4 is through be made into the prefabricated component of definite shape by fiber, relative position between anchoring fiber prefabricated component and metal connecting piece 2, then resin by injection, the shaping that is finally heating and curing, thus composite material and many fine needles of metal connection member made.
In addition, in a step, fine needle 4 can be some according to different angles and positional alignment at the join domain of metal connecting piece 2, perpendicular distance between fine needle 4 terminations and metallic interconnect 2 is less than composite material link 1 at the thickness of relevant position, to guarantee the termination of all fine needles 4, can not stretch out from composite material link 1, the axis of fine needle 4 is consistent with the normal direction of the joint of metal connecting piece 2, or forms an angle and be obliquely installed, and each fine needle 4 is the parallel or setting that forms an angle each other.
Claims (11)
1. the linkage structure of a composite material and metal, comprise metal connecting piece, composite material link, it is characterized in that, the position that is connected at metal connecting piece with composite material link, also be provided with fine needle, described fine needle one end is fixedly connected on metal connecting piece, and the other end inserts composite inner.
2. the linkage structure of composite material according to claim 1 and metal, it is characterized in that, described composite inner is provided with fibre reinforced materials, form fibre reinforced composites, the position that is connected at described metal connecting piece with composite material link, the trend of described fiber and the form fit of fine needle, form the fiber layout structure around fine needle.
3. the linkage structure of composite material according to claim 2 and metal, is characterized in that, described fibre reinforced materials arranges multilayer, between each layer of fiber, moves towards angled, forms the staggered structure of fiber.
4. the linkage structure of composite material according to claim 3 and metal, it is characterized in that, distance between described fine needle termination and metal connecting piece is less than or equal to composite material link at the thickness of relevant position, and described fine needle is fixed on metal connecting piece by technology such as welding, splicing, 3D printings.
5. according to the arbitrary described composite material of claim 1-4 and the linkage structure of metal, it is characterized in that, described fine needle is a plurality of, its sectional shape is circular, oval, square or rectangle, and the end of one end that described fine needle is not connected with metallic interconnect is set to size and becomes large cylindricality, circle, ellipse, L shaped, T shape or hook-shape structure.
6. the linkage structure of composite material according to claim 5 and metal, is characterized in that, the axis of described fine needle is consistent with the normal direction of the joint of metal connecting piece, or the setting that forms an angle, and described each fine needle is the parallel or setting that forms an angle each other.
7. according to the composite material described in claim 1-6 and the linkage structure of metal, it is characterized in that, described metal connecting piece is tabular or bar-shaped, tabular metal connecting piece two apparent surfaces are fixedly installed fine needle, bar-shaped metal connecting piece is provided with fine needle around this club shaped structure, and described fine needle is inserted into respectively in composite material link.
8. a method that forms linkage structure described in claim 1-7, is characterized in that, comprises the steps,
A, is fixedly connected on fine needle one end on metal connecting piece;
B, is placed in composite inner by the fine needle the other end, and cut staple reinforcing material not, the trend of fiber and fine needle form fit;
C, is cured moulding to composite material.
9. method according to claim 8, is characterized in that: in a step, fine needle is fixed on metal connecting piece by technology such as welding, splicing, 3D printings; In b step, described fine needle is inserted into composite inner, is only the local detachment original position of fiber tuft in insertion process.
10. method according to claim 8, it is characterized in that, in b step, described fiber is by laying or be wound around the junction plane place that is arranged on described link, in c step, first the fibrous structure of the laying in the composite material of making and metal connecting structure or winding is injected to curing agent, and then be placed into heating, cure under pressure moulding in heat pressing forming device.
11. according to Claim 8, 9 arbitrary described methods, it is characterized in that, in b step, described composite material arranges multilayer, the fiber orientation of inner each layer of described multilayer materials is angled, form the staggered structure of fiber, described composite material is made by prepreg or is made by prefabricated component, correspondingly in c step, to the composite material of being made by prepreg, directly the composite material assembling and metal connecting structure are heated in heat pressing forming device, cure under pressure moulding, to the composite material of being made by prefabricated component, first the prefabricated component in the composite material assembling and metal connecting structure is injected to curing agent, and then be placed in heat pressing forming device and heated, cure under pressure moulding.
Priority Applications (1)
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Cited By (15)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105172317A (en) * | 2015-09-25 | 2015-12-23 | 刘龙权 | Solidified composite and enhancing method of repairing structure and connecting structure of solidified composite |
| CN105622127A (en) * | 2015-12-29 | 2016-06-01 | 北京航空航天大学 | Connecting method for high-temperature composite component and metal component for aircraft engine |
| CN106378986A (en) * | 2016-08-29 | 2017-02-08 | 江西昌兴航空装备股份有限公司 | Metal matrix composite material and its preparation method |
| CN106515137A (en) * | 2016-09-28 | 2017-03-22 | 中航复合材料有限责任公司 | Composite material sandwich board and manufacturing method thereof |
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| CN106696118A (en) * | 2016-12-14 | 2017-05-24 | 中国航空工业集团公司基础技术研究院 | Z-direction enhancing method suitable for dry-state fiber preform |
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Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1575225A (en) * | 2001-09-14 | 2005-02-02 | 索尼株式会社 | Plastic card, plastic card producing method, hot press plate, and car producing device |
| CN1705564A (en) * | 2002-11-01 | 2005-12-07 | 贝尔直升机泰克斯特龙公司 | Method and apparatus for Z-direction reinforcement of composite laminates |
| KR20090028861A (en) * | 2007-09-17 | 2009-03-20 | 한국항공우주연구원 | Composite laminated structure reinforced with performance by pinning, composite manufacturing method, device and manufacturing method of the composite laminated structure |
| US20100258236A1 (en) * | 2007-03-23 | 2010-10-14 | United Technologies Corporation | Repair of a composite sandwich structure having a perforated skin |
| WO2010120628A1 (en) * | 2009-04-15 | 2010-10-21 | Alzeta Corporation | High temperature fiber composite burner surface |
| CN102622472A (en) * | 2012-02-27 | 2012-08-01 | 西北工业大学 | Method for analyzing load and stress distribution and stress levels of composite mechanical connection pins |
| CN102632362A (en) * | 2011-02-08 | 2012-08-15 | 波音公司 | Methods and apparatus for mechanically joining metal components and composite components |
| WO2013051809A2 (en) * | 2011-10-07 | 2013-04-11 | 한국항공우주연구원 | Z-pin patch and method for manufacturing or coupling a composite laminated structure using same |
-
2014
- 2014-03-19 CN CN201410103278.1A patent/CN103925267B/en active Active
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1575225A (en) * | 2001-09-14 | 2005-02-02 | 索尼株式会社 | Plastic card, plastic card producing method, hot press plate, and car producing device |
| CN1705564A (en) * | 2002-11-01 | 2005-12-07 | 贝尔直升机泰克斯特龙公司 | Method and apparatus for Z-direction reinforcement of composite laminates |
| US20100258236A1 (en) * | 2007-03-23 | 2010-10-14 | United Technologies Corporation | Repair of a composite sandwich structure having a perforated skin |
| KR20090028861A (en) * | 2007-09-17 | 2009-03-20 | 한국항공우주연구원 | Composite laminated structure reinforced with performance by pinning, composite manufacturing method, device and manufacturing method of the composite laminated structure |
| WO2010120628A1 (en) * | 2009-04-15 | 2010-10-21 | Alzeta Corporation | High temperature fiber composite burner surface |
| CN102632362A (en) * | 2011-02-08 | 2012-08-15 | 波音公司 | Methods and apparatus for mechanically joining metal components and composite components |
| WO2013051809A2 (en) * | 2011-10-07 | 2013-04-11 | 한국항공우주연구원 | Z-pin patch and method for manufacturing or coupling a composite laminated structure using same |
| CN102622472A (en) * | 2012-02-27 | 2012-08-01 | 西北工业大学 | Method for analyzing load and stress distribution and stress levels of composite mechanical connection pins |
Non-Patent Citations (2)
| Title |
|---|
| 冒颖等: "复合材料多钉连接数值计算方法研究", 《科学技术与工程》 * |
| 张俊琪等: "《第17届全国复合材料学术会议（复合材料力学分论坛）论文集》", 31 December 2012 * |
Cited By (20)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105172317A (en) * | 2015-09-25 | 2015-12-23 | 刘龙权 | Solidified composite and enhancing method of repairing structure and connecting structure of solidified composite |
| WO2017063885A1 (en) * | 2015-10-13 | 2017-04-20 | Bayerische Motoren Werke Aktiengesellschaft | Method for joining components and component composite |
| CN107735581A (en) * | 2015-10-13 | 2018-02-23 | 宝马股份公司 | Method and component composition structure for connecting elements |
| CN105622127A (en) * | 2015-12-29 | 2016-06-01 | 北京航空航天大学 | Connecting method for high-temperature composite component and metal component for aircraft engine |
| CN105622127B (en) * | 2015-12-29 | 2018-01-30 | 北京航空航天大学 | The connection method of aero-engine high-temperature composite material component and hardware |
| CN106378986A (en) * | 2016-08-29 | 2017-02-08 | 江西昌兴航空装备股份有限公司 | Metal matrix composite material and its preparation method |
| CN106515137A (en) * | 2016-09-28 | 2017-03-22 | 中航复合材料有限责任公司 | Composite material sandwich board and manufacturing method thereof |
| CN106696118B (en) * | 2016-12-14 | 2019-02-15 | 中国航空工业集团公司基础技术研究院 | A kind of Z-direction Enhancement Method suitable for dry state fiber preform body |
| CN106696118A (en) * | 2016-12-14 | 2017-05-24 | 中国航空工业集团公司基础技术研究院 | Z-direction enhancing method suitable for dry-state fiber preform |
| CN106827560A (en) * | 2017-01-20 | 2017-06-13 | 上海交通大学 | A kind of manufacture method of composite and metal connecting structure |
| CN106938509A (en) * | 2017-05-18 | 2017-07-11 | 大连日瑞铸模有限公司 | A kind of compound resin metal die and preparation method thereof |
| CN109210049A (en) * | 2017-07-07 | 2019-01-15 | 戴弗根特技术有限公司 | The system and method that node is connected for implementing node in mechanized component |
| CN109210049B (en) * | 2017-07-07 | 2022-08-16 | 戴弗根特技术有限公司 | System and method for implementing node-to-node connections in a mechanized assembly |
| CN110315784A (en) * | 2019-06-25 | 2019-10-11 | 浙江众泰汽车制造有限公司 | Carbon fibre reinforced composite part and metalwork connection method, connection structure and automobile |
| WO2021138751A1 (en) * | 2020-01-10 | 2021-07-15 | 杭州友凯船艇有限公司 | Reinforcement for periphery of connecting hole of fiber composite material and preparation solution therefor |
| CN111734718A (en) * | 2020-07-30 | 2020-10-02 | 西南交通大学 | A continuous fiber reinforced composite material connection structure and preparation method thereof |
| CN112709735A (en) * | 2020-12-29 | 2021-04-27 | 中国航空工业集团公司西安飞机设计研究所 | Composite material-metal integrated fusion joint |
| CN116538174A (en) * | 2023-04-04 | 2023-08-04 | 中国科学院工程热物理研究所 | Connection structure of metal and composite fiber material and processing method |
| CN116384163A (en) * | 2023-06-05 | 2023-07-04 | 中国航发四川燃气涡轮研究院 | Design method of ceramic matrix composite complex component for aero-engine |
| CN116384163B (en) * | 2023-06-05 | 2023-09-05 | 中国航发四川燃气涡轮研究院 | Design method of ceramic matrix composite complex component for aero-engine |
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