CN201925288U - Metal/composite material pin type connecting structure - Google Patents
Metal/composite material pin type connecting structure Download PDFInfo
- Publication number
- CN201925288U CN201925288U CN201020677140XU CN201020677140U CN201925288U CN 201925288 U CN201925288 U CN 201925288U CN 201020677140X U CN201020677140X U CN 201020677140XU CN 201020677140 U CN201020677140 U CN 201020677140U CN 201925288 U CN201925288 U CN 201925288U
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- China
- Prior art keywords
- metal
- composite material
- fiber
- glue
- layer
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- Expired - Fee Related
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- 239000002131 composite material Substances 0.000 title claims abstract description 48
- 239000007769 metal material Substances 0.000 title claims abstract description 14
- 239000002184 metal Substances 0.000 claims abstract description 35
- 239000000835 fiber Substances 0.000 claims abstract description 28
- 239000003292 glue Substances 0.000 abstract 8
- 238000000034 method Methods 0.000 description 4
- 238000002048 anodisation reaction Methods 0.000 description 2
- 239000004744 fabric Substances 0.000 description 2
- 238000009413 insulation Methods 0.000 description 2
- 239000000203 mixture Substances 0.000 description 2
- 238000006396 nitration reaction Methods 0.000 description 2
- 239000011347 resin Substances 0.000 description 2
- 229920005989 resin Polymers 0.000 description 2
- 238000010079 rubber tapping Methods 0.000 description 2
- 239000000853 adhesive Substances 0.000 description 1
- 230000001070 adhesive effect Effects 0.000 description 1
- 230000032683 aging Effects 0.000 description 1
- 230000002929 anti-fatigue Effects 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 239000004568 cement Substances 0.000 description 1
- 238000009826 distribution Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000007613 environmental effect Effects 0.000 description 1
- 230000003116 impacting effect Effects 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000000465 moulding Methods 0.000 description 1
- 238000010008 shearing Methods 0.000 description 1
- 238000007711 solidification Methods 0.000 description 1
- 230000008023 solidification Effects 0.000 description 1
- 238000004804 winding Methods 0.000 description 1
Images
Abstract
The utility model relates to a metal/composite material pin type connecting structure, consisting of a metal piece, metal convex pins, a composite material skin, skin fiber and a glue layer. Metal convex pins are arranged on the surface of the metal piece, and the skin fiber is coiled on the metal convex pins and is in glue joint with the metal piece through the glue layer. In the metal/composite material pin type connecting structure, convex pins on the surface of a glue joint area of the metal piece are inserted into a composite material fiber layer so that the glue joint contacting area between metal and the composite material is increased. In addition, the metal convex pins pull the composite material fiber so that the glue layer between the metal and the composite material, the glue layer between fiber of the same layer and the glue layer between a fiber layer and a fiber layer can bear external force load together, and the join strength can be greatly improved.
Description
Technical field
The utility model relates to composite structure, particularly a kind of metal/composite material nail type linkage structure.
Background technique
At present both at home and abroad composite material in the application in Aeronautics and Astronautics field more and more widely, advantage such as that composite material has is in light weight, specific strength is high, specific modulus is big, designability is strong, anti-fatigue performance is good, decay resistance is superior, on lightweight, miniaturization and the high performance of various weaponrys, played the effect that can not be substituted, but composite material does not satisfy the maneuvering load requirement at fuselage, place, the crucial force part of body, this situation is used metalwork carrying mostly instead, carries out being connected of metal and composite material again.
Composite material with mainly contain splicing, mechanical connection, splicing and modes such as mechanical mixing is connected being connected of metal, wherein adhesive technology is simple, is convenient to the parts global formation, but splicing connection allowable load is little, and be subjected to the restriction of Environmental Conditions temperature, and have the shortcoming of interface glue-line ageing failure; Mechanical connection intensity height, but can interrupt composite fiber in the operation, influence the overall performance of member; Adopt splicing to be connected and can effectively improve metal/composite material join strength, have the advantage of the two with mechanical mixing, but the phenomenon that also exists composite fiber to interrupt simultaneously.
The model utility content
The purpose of this utility model is, just at the prior art situation, and design provides a kind of novel nail type linkage structure, have and glued joint the advantage that is connected with mechanical mixing, simultaneously owing to do not interrupt composite fiber, its bearing capacity obtains bigger raising, can solve the connectivity problem of the crucial stressed place of aircraft metal/composite material.
The particular content of the technical solution of the utility model is: a kind of metal/composite material nail type linkage structure, it is made up of metalwork, the protruding nail of metal, composite material skin, covering fiber, glue-line, the metalwork surface is provided with the protruding nail of metal, and the covering fiber in the composite material skin glueds joint by glue-line and metalwork around the protruding nail of metal.
Advantage of the present utility model is, adopts metalwork to glued joint district's protruding nail of surface metal and inserts the composite fiber floor, makes the splicing area of contact of metal and composite material increase, and the fiber of original position is walked around the protruding nail of metal, keeps its continuity.When metal and composite material joint are stressed, the protruding nail of metal is by pullling composite fiber, make metal between composite material glue-line, with between layer fiber and the fiber between glue-line, layer of fibers and the layer of fibers glue-line bear external force load, can improve join strength greatly.
Description of drawings
Fig. 1 is metal of the present utility model/composite material nail type linkage structure schematic representation.
Fig. 2 is the protruding nail 2 Fiber Distribution figure of place of metal of the present utility model.
Fig. 3 is that nail type of the present utility model connects glue-line schematic representation between metalwork and the composite material.
Among the figure: 1-metalwork, the protruding nail of 2-metal, 3-composite material skin, 4-covering fiber, 5-glue-line.
Embodiment
The utility model is described in further detail below in conjunction with accompanying drawing, referring to Fig. 1-Fig. 3, a kind of metal/composite material nail type linkage structure, it is made up of metalwork 1, the protruding nail 2 of metal, composite material skin 3, covering fiber 4, glue-line 5, metalwork 1 surface is provided with the protruding nail 2 of metal, and the covering fiber 4 in the composite material skin 3 glueds joint by glue-line 5 and metalwork 1 around the protruding nail 2 of metal.
Carry out testpieces design and production according to this material with novel technological scheme, embodiment is as follows: process the protruding nail 2 of metal on the splicing face of metalwork 1 and composite material skin 3, the metalwork 1 that appearance has a protruding nail 2 of metal glueds joint in preceding 5 hours and carries out the nitration mixture anodization, then composite material weave cloth covering fiber 4 prepregs in the composite material skin 3 are twined and be laid on the protruding nail 2 district's cement planes of metal, the most laggard solidification of hot-press tank moulding, 175 ± 5 ℃ of heating-up temperatures, solidify insulation 7 hours, 60 ℃ of tapping temperatures.
Metalwork 1 stays 30mm to glued joint width with composite material skin 3, and the high 3mm of protruding nail is designed to positive four sides taper, and basal area is 1.2mm * 1.2mm, and the spacing of arranging of protruding nail is 3.5mm * 3.5mm, composite material skin 3 weld thickness 5mm.
Its method step is:
1, makes the metalwork 1 that has the protruding nail 2 of metal, make the protruding nail 2 of metal be distributed in the surface of metalwork 1;
2, glued joint in preceding 5 hours at metalwork 1 and make the nitration mixture anodization;
3, application of resin NY9200GB glue-line 5 on the protruding nail of the metal of metalwork 12 zones;
4,4 windings of the weave cloth prepreg resin NY9200GB covering fiber in the composite material skin 3 are laid on the protruding nail of metal 2 zones of metalwork 1;
5, the most laggard hot-press tank solidifies insulation 7 hours, 60 ℃ of solidifyings of tapping temperature by 175 ± 5 ℃ of heating-up temperatures.
Respectively produce some testpieces according to common bonding mode and nail type Placement, get the typical shaft of metal/composite material connection and carry out the join strength test to shearing load:
Test data as can be known, the nail type connects than reticulate pattern join strength and improves 40.1%, improves 220.5% than common connection, can be used in being connected of metalwork and composite element under the big load-up condition.
Glued joint the surface at metalwork and directly process the protruding nail of metal, contrast is gluedd joint and the mechanical mixing Placement, the nail type connects does not need extra link, does not improve join strength by the impacting force between metalwork and the composite material, does not destroy the continuity of composite fiber.
Claims (1)
1. metal/composite material nail type linkage structure, it is characterized in that, it is made up of metalwork [1], the protruding nail of metal [2], composite material skin [3], covering fiber [4], glue-line [5], metalwork [1] surface is provided with the protruding nail of metal [2], and the covering fiber [4] in the composite material skin [3] glueds joint by glue-line [5] and metalwork [1] around the protruding nail of metal [2].
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201020677140XU CN201925288U (en) | 2010-12-23 | 2010-12-23 | Metal/composite material pin type connecting structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201020677140XU CN201925288U (en) | 2010-12-23 | 2010-12-23 | Metal/composite material pin type connecting structure |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN201925288U true CN201925288U (en) | 2011-08-10 |
Family
ID=44429139
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201020677140XU Expired - Fee Related CN201925288U (en) | 2010-12-23 | 2010-12-23 | Metal/composite material pin type connecting structure |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN201925288U (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103711764A (en) * | 2012-09-29 | 2014-04-09 | 北京汽车研究总院有限公司 | Connecting structure and connecting method of composite-material connecting piece and metal connecting piece |
| 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 |
| CN107323022A (en) * | 2017-07-24 | 2017-11-07 | 北京汽车集团有限公司 | Splicing attachment structure of composite and metal material and preparation method thereof |
| 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 |
-
2010
- 2010-12-23 CN CN201020677140XU patent/CN201925288U/en not_active Expired - Fee Related
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103711764A (en) * | 2012-09-29 | 2014-04-09 | 北京汽车研究总院有限公司 | Connecting structure and connecting method of composite-material connecting piece and metal connecting piece |
| 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 |
| CN107323022A (en) * | 2017-07-24 | 2017-11-07 | 北京汽车集团有限公司 | Splicing attachment structure of composite and metal material and preparation method thereof |
| 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 |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| ASS | Succession or assignment of patent right |
Owner name: JIANGXI HONGDU TECHNOLOGY CO., LTD. Free format text: FORMER OWNER: HONGDU AVIATION INDUSTRY GROUP CO., TD., JIANGXI PROV. Effective date: 20140814 |
|
| C41 | Transfer of patent application or patent right or utility model | ||
| COR | Change of bibliographic data |
Free format text: CORRECT: ADDRESS; FROM: 330000 NANCHANG, JIANGXI PROVINCE TO: 330096 NANCHANG, JIANGXI PROVINCE |
|
| TR01 | Transfer of patent right |
Effective date of registration: 20140814 Address after: 330096, Nanchang hi tech Zone, Jiangxi Province, No. 59, No. 3, building 3, high tech and low carbon innovation and Pioneering Park Patentee after: Jiangxi Hongdu Technology Co., Ltd. Address before: 330000 Jiangxi city of Nanchang province Qingyunpu new bridge Patentee before: Hongdu Aviation Industry Group Co., td., Jiangxi Prov. |
|
| EE01 | Entry into force of recordation of patent licensing contract |
Assignee: Jiangxi Hongdu Technology Co., Ltd. Assignor: Hongdu Aviation Industry Group Co., td., Jiangxi Prov. Contract record no.: 2014360000160 Denomination of utility model: Metal/composite material pin type connecting structure Granted publication date: 20110810 License type: Exclusive License Record date: 20140709 |
|
| LICC | Enforcement, change and cancellation of record of contracts on the licence for exploitation of a patent or utility model | ||
| EC01 | Cancellation of recordation of patent licensing contract |
Assignee: Jiangxi Hongdu Technology Co., Ltd. Assignor: Hongdu Aviation Industry Group Co., td., Jiangxi Prov. Contract record no.: 2014360000160 Date of cancellation: 20141202 |
|
| LICC | Enforcement, change and cancellation of record of contracts on the licence for exploitation of a patent or utility model | ||
| C41 | Transfer of patent application or patent right or utility model | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20151229 Address after: 330000 Jiangxi city in Nanchang Province, the new bridge box 460 box 5001 Patentee after: Hongdu Aviation Industry Group Co., td., Jiangxi Prov. Address before: 330096, Nanchang hi tech Zone, Jiangxi Province, No. 59, No. 3, building 3, high tech and low carbon innovation and Pioneering Park Patentee before: Jiangxi Hongdu Technology Co., Ltd. |
|
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20110810 Termination date: 20161223 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |