CN109163006A - A kind of link mechanism of composite material and metal bonding - Google Patents
A kind of link mechanism of composite material and metal bonding Download PDFInfo
- Publication number
- CN109163006A CN109163006A CN201811332440.1A CN201811332440A CN109163006A CN 109163006 A CN109163006 A CN 109163006A CN 201811332440 A CN201811332440 A CN 201811332440A CN 109163006 A CN109163006 A CN 109163006A
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- China
- Prior art keywords
- metal
- composite material
- connecting rod
- barrel
- joints
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
- F16C7/00—Connecting-rods or like links pivoted at both ends; Construction of connecting-rod heads
- F16C7/02—Constructions of connecting-rods with constant length
- F16C7/026—Constructions of connecting-rods with constant length made of fibre reinforced resin
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- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Mutual Connection Of Rods And Tubes (AREA)
Abstract
针对现有复合材料连杆的筒身和金属接头之间的耐久性差的问题，本发明提供一种复合材料与金属结合的连杆结构，属于飞机减重技术领域。本发明包括两个金属接头和复合材料筒身，两个金属接头分别与复合材料筒身的两端连接；每个金属接头包括两个金属耳片和一个金属连接结构，两个金属耳片设置在金属连接结构的首端，两个金属耳片和金属连接结构为一体结构；复合材料筒身为内外双筒结构；两个金属接头的金属连接结构的末端分别与复合材料筒身内筒的两个端部连接；沿着连杆的轴向方向，利用复合材料将两个金属接头的金属连接结构和复合材料筒身的内筒的缠绕在一起，并在内筒和金属连接结构的外表面形成复合材料筒身的外筒。
Aiming at the problem of poor durability between the cylinder body and the metal joint of the existing composite material connecting rod, the invention provides a connecting rod structure combined with a composite material and a metal, which belongs to the technical field of aircraft weight reduction. The invention includes two metal joints and a composite material barrel, the two metal joints are respectively connected with two ends of the composite material barrel; each metal joint includes two metal ear pieces and a metal connection structure, and the two metal ear pieces are arranged At the head end of the metal connection structure, the two metal lugs and the metal connection structure are integrated; the composite material barrel is an inner and outer double-barrel structure; the ends of the metal connection structures of the two metal joints are respectively connected with the two ends of the inner barrel of the composite material barrel. The two ends are connected; along the axial direction of the connecting rod, the metal connection structure of the two metal joints and the inner cylinder of the composite material cylinder are wound together by composite materials, and the outer surface of the inner cylinder and the metal connection structure is wound together. The outer barrel that forms the composite barrel.
Description
Technical field
The present invention relates to a kind of aircrafts to hang box force transferring structure, in particular to a kind of composite material connecting rod belongs to aircraft and subtracts
Weight technical field.
Background technique
The development of aircraft mainly using low cost, high carrying capacity as target, will reach this target and be to solve first
Structural weight reduction problem hangs box section lower link, is the important force-transmitting part for hanging box section, for connecting hanging box section bottom and machine
Wing lower aerofoil transmits motor power.Conventional airplane, including B737, B777, C919 aircraft are all made of metal material, but with
The progress of composite technology, compared to conventional steel link mechanism, if hanging connecting rod is mutually tied using metal with composite material
It closes, can be with loss of weight 50%~60%, potential economic benefit is huge.Therefore, developing composite material connecting rod is to realize aircraft loss of weight mesh
One of key technology.
The existing link mechanism using composite material, weight reduces 35% compared with the similar component of steel, but right
For designer, how to guarantee that the design of composite structure meets fiber properties and ensures component safety when in use
It is reliably a huge challenge.Compared with metal structure, behavior of the composite material under load condition is more complicated, so cannot
Simply metal structure is substituted with fiber compound structure.
Connecting rod is as the critical component in aircraft, and Development Techniques directly determine its performance, and its performance has aircraft
Very big influence, if connecting rod is primarily subjected to tensile load and compressive load during the work time, the reliability during being on active service
Seem most important, especially the durability between composite cylinder and metal joint.
Summary of the invention
For the problem of the durability difference between the stack shell and metal joint of existing composite material connecting rod, the present invention provides one
The link mechanism of kind composite material and metal bonding.
The link mechanism of a kind of composite material and metal bonding of the invention, including two metal joints 1 and composite material
Stack shell 2, two metal joints 1 are connect with the both ends of composite material stack shell 2 respectively；
Each metal joint 1 includes two metal auricle 1-1 and metal connecting structure a 1-2, two metal auricle 1-1
The head end of metal connecting structure 1-2 is set, and two metal auricle 1-1 and metal connecting structure 1-2 are structure as a whole；
The composite material stack shell 2 is inside and outside double-barrel structure；
The end of the metal connecting structure 1-2 of two metal joints 1 two with 2 inner cylinder 2-1 of composite material stack shell respectively
End connection；
Along the axial direction of connecting rod, using composite material by the metal connecting structure 1-2 of two metal joints 1 and compound
The inner cylinder 2-1's of material stack shell 2 is intertwined, and forms composite wood in the outer surface of inner cylinder 2-1 and metal connecting structure 1-2
The outer cylinder 2-2 of barrel body 2.
Preferably, a groove 1-3 is arranged in the end metal connecting structure 1-2 between two metal auricle 1-1.
Preferably, the laying angle of the composite material stack shell is ± 10 °.
Preferably, the end of the metal connecting structure 1-2 and the end of 2 inner cylinder 2-1 of composite material stack shell use wedge
The bonding mode of shape connects.
Beneficial effects of the present invention, the structure that the present invention be combined with each other using composite material and metal, mitigate significantly
The weight of structural body, improves structure efficiency, main loss of weight of the invention is on composite material barrel body structure, due to connecting rod master
Pulling force and pressure are born, the coil structure of composite material stack shell and metal joint that the present invention is arranged can effectively transmit drawing
Power enables composite material outer cylinder to bear pulling force well, and composite material inner cylinder is then arranged by outer cylinder package in two metals
Among connector, inner cylinder is allowed effectively to bear pressure, increases the durability between the stack shell of connecting rod and metal joint.The present invention
For composite material and the connecting rod unitary design of metal bonding and load bearing organization plan, structure can be made full use of in this way
Material reduces the quality of structure.
Detailed description of the invention
Fig. 1 is the structure principle chart for not twining the metal joint of composite material；
Fig. 2 is the overall structure diagram of connecting rod of the invention；
Fig. 3 is the structural schematic diagram of metal joint 1 of the invention；
Fig. 4 is the part of the front structure diagram of metal joint 1 in Fig. 2；
Fig. 5 is the axial cross-sectional views of the metal joint 1 in Fig. 2.
Specific embodiment
Following will be combined with the drawings in the embodiments of the present invention, and technical solution in the embodiment of the present invention carries out clear, complete
Site preparation description, it is clear that described embodiments are only a part of the embodiments of the present invention, instead of all the embodiments.It is based on
Embodiment in the present invention, those of ordinary skill in the art without creative labor it is obtained it is all its
His embodiment, shall fall within the protection scope of the present invention.
It should be noted that in the absence of conflict, the feature in embodiment and embodiment in the present invention can phase
Mutually combination.
The present invention will be further explained below with reference to the attached drawings and specific examples, but not as the limitation of the invention.
The link mechanism of a kind of composite material and metal bonding of the invention, including two metal joints 1 and composite material
Stack shell 2, two metal joints 1 are connect with the both ends of composite material stack shell 2 respectively；
Each metal joint 1 includes two metal auricle 1-1 and metal connecting structure a 1-2, two metal auricle 1-1
The head end of metal connecting structure 1-2 is set, and two metal auricle 1-1 and metal connecting structure 1-2 are structure as a whole；
The composite material stack shell 2 is inside and outside double-barrel structure；
The end of the metal connecting structure 1-2 of two metal joints 1 two with 2 inner cylinder 2-1 of composite material stack shell respectively
End connection；
Along the axial direction of connecting rod, using composite material by the metal connecting structure 1-2 of two metal joints 1 and compound
The inner cylinder 2-1's of material stack shell 2 is intertwined, and forms composite wood in the outer surface of inner cylinder 2-1 and metal connecting structure 1-2
The outer cylinder 2-2 of barrel body 2.
Present embodiment winds outer cylinder 2-2, and there are two types of modes:
The first forms outer cylinder original shape, further along connecting rod first in the outer surface wound composite of inner cylinder 2-1
Outer cylinder original shape and the metal connecting structure 1-2 of two metal joints 1 are intertwined by axial direction using composite material,
The composite material wound twice is formed together outer cylinder 2-2；
Second, do not wind outer cylinder original shape, directed along connecting rod axial direction by the metal of two metal joints 1
Connection structure 1-2 and inner cylinder 2-1 are intertwined, the composite material of winding while fixing two metal joints 1 and inner cylinder,
And outer cylinder 2-2 is formed, because of the limitation of metal connecting structure 1-2, outer cylinder is unsuitable blocked up in this case；
In preferred embodiment, a groove 1- is arranged in the end metal connecting structure 1-2 between two metal auricle 1-1
3, when Filament Wound Composite, across the groove of one end metal connecting structure 1-2, using 2 inner cylinder 2-1 of composite material stack shell and another
The groove of one end metal connecting structure 1-2 repeats to wind, and realizes the coil structure of composite material stack shell and metal joint, described
Groove is for placing composite material.
The schematic illustration of the link mechanism of present embodiment is as shown in Figures 1 to 5, when connecting rod under tension, metal
Auricle 1-1 by pulling force by the end effect of composite material stack shell 2 and metal connecting structure 1-2 in outer cylinder, when connecting rod is pressed
When power, pressure is acted on inner cylinder by composite material stack shell 2 and metal connecting structure 1-2 by metal auricle 1-1, makes pulling force and pressure
Power can be good at transmitting.
The design method of present embodiment connecting rod:
For composite material connecting rod, since size limits, composite material stack shell very thin thickness, therefore composite material connecting rod
Structure design it is particularly important.Winding pattern design and ply stacking-sequence of the composite cylinder during winding process design past
Toward prior to technological design, design and craft is caused to disconnect.The result of optimum design of laminate layup is often unable to satisfy fiber in technique
Stable requirement causes the target of optimization design cannot achieve, and needs to redesign, and carries out a large amount of test technology and grope.
By the calculating of butt joint winding path, the boundary condition of theoretical optimization design can be determined, trial and error test is greatly reduced
Quantity, while reducing cost, available feasible optimal case.
Winding layer of the composite material connecting rod at fiber and metal joint is attached in connector due to continuous fiber winding
Fiber accumulations phenomenon will be closely generated, this fiber accumulations will lead to joint thickness and discontinuous nonlinear change occur, and connector is attached
The design size and composite material of nearly composite wood material heap height limitation connector during the winding process fiber slip, it is aerial phenomena such as.
In addition, the near joints thickness distribution under various winding patterns and winding layer distribution how is accurately predicted, to composite joint
The accuracy of finite element modeling also influences greatly.Therefore, by the accurate prediction to winding thickness, while every kind of line style is being connect
Head place track distribution accurately calculated after, available every kind of line style within the scope of each unit thickness accumulation situation with
Then winding angle exact value substitutes into finite element unit point by point again, can carry out more accurate FEM calculation.
On the basis of the above work, by combination Abaqus and iterative calculation program and winding pattern table, design is not
With winding pattern, and then with strain uniformly for design object, to it is various permission line styles under deformations carry out calculate and it is excellent
Choosing reaches the strength and stiffness optimization design of composite material stack shell, and then completes the design of entire connecting rod.
In preferred embodiment, the laying angle of the composite material stack shell is ± 10 °.
In preferred embodiment, the end of the metal connecting structure 1-2 and the end of 2 inner cylinder 2-1 of composite material stack shell are adopted
It is connected with the bonding mode of wedge shape.
The present invention uses the composite material barrel body structure of the inside and outside bitubular, substantially increases the energy that structure bears compressive load
Power, while carbon fibre composite stack shell 2 being connect with metal joint 1 with wedge shape and canoe, it improves structure and bears to draw
The ability of load is stretched, to meet link mechanism requirement.
Although describing the present invention herein with reference to specific embodiment, it should be understood that, these realities
Apply the example that example is only principles and applications.It should therefore be understood that can be carried out to exemplary embodiment
Many modifications, and can be designed that other arrangements, without departing from spirit of the invention as defined in the appended claims
And range.It should be understood that different appurtenances can be combined by being different from mode described in original claim
Benefit requires and feature described herein.It will also be appreciated that the feature in conjunction with described in separate embodiments can be used
In other described embodiments.
Claims (4)
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811332440.1A CN109163006A (en) | 2018-11-09 | 2018-11-09 | A kind of link mechanism of composite material and metal bonding |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811332440.1A CN109163006A (en) | 2018-11-09 | 2018-11-09 | A kind of link mechanism of composite material and metal bonding |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN109163006A true CN109163006A (en) | 2019-01-08 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811332440.1A Pending CN109163006A (en) | 2018-11-09 | 2018-11-09 | A kind of link mechanism of composite material and metal bonding |
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| CN (1) | CN109163006A (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110937119A (en) * | 2019-12-24 | 2020-03-31 | 肇庆市海特复合材料技术研究院 | An integrated all-composite connecting rod structure |
| CN110966284A (en) * | 2019-12-18 | 2020-04-07 | 肇庆市海特复合材料技术研究院 | Composite material connecting joint and preparation method thereof |
| CN111997987A (en) * | 2020-07-20 | 2020-11-27 | 西安方元明科技股份有限公司 | Helicopter missile-tail-prevention transmission shaft and manufacturing method thereof |
| CN112498654A (en) * | 2020-10-12 | 2021-03-16 | 深圳烯创先进材料研究院有限公司 | Composite material hanging rod piece structure |
Citations (5)
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| US6116113A (en) * | 1997-08-13 | 2000-09-12 | Maclean-Fogg Company | Composite link |
| CN102369363A (en) * | 2008-12-24 | 2012-03-07 | 梅西耶-布加蒂-道提公司 | Method for making a metal connecting rod reinforced with long fibres |
| CN103615461A (en) * | 2013-11-22 | 2014-03-05 | 中联重科股份有限公司 | Connecting rod, engineering machine and manufacturing method of connecting rod |
| CN104879646A (en) * | 2015-05-08 | 2015-09-02 | 上海云逸民用航空科技有限公司 | Composite material rod member |
| CN207064407U (en) * | 2017-04-12 | 2018-03-02 | 北京先进复材产品设计有限公司 | A kind of composite material connecting rod attachment structure of big carrying |
-
2018
- 2018-11-09 CN CN201811332440.1A patent/CN109163006A/en active Pending
Patent Citations (5)
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| US6116113A (en) * | 1997-08-13 | 2000-09-12 | Maclean-Fogg Company | Composite link |
| CN102369363A (en) * | 2008-12-24 | 2012-03-07 | 梅西耶-布加蒂-道提公司 | Method for making a metal connecting rod reinforced with long fibres |
| CN103615461A (en) * | 2013-11-22 | 2014-03-05 | 中联重科股份有限公司 | Connecting rod, engineering machine and manufacturing method of connecting rod |
| CN104879646A (en) * | 2015-05-08 | 2015-09-02 | 上海云逸民用航空科技有限公司 | Composite material rod member |
| CN207064407U (en) * | 2017-04-12 | 2018-03-02 | 北京先进复材产品设计有限公司 | A kind of composite material connecting rod attachment structure of big carrying |
Non-Patent Citations (2)
| Title |
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| 张东兴: "《聚合物基符合材料科学与工程》", 31 July 2018 * |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110966284A (en) * | 2019-12-18 | 2020-04-07 | 肇庆市海特复合材料技术研究院 | Composite material connecting joint and preparation method thereof |
| CN110937119A (en) * | 2019-12-24 | 2020-03-31 | 肇庆市海特复合材料技术研究院 | An integrated all-composite connecting rod structure |
| CN111997987A (en) * | 2020-07-20 | 2020-11-27 | 西安方元明科技股份有限公司 | Helicopter missile-tail-prevention transmission shaft and manufacturing method thereof |
| CN112498654A (en) * | 2020-10-12 | 2021-03-16 | 深圳烯创先进材料研究院有限公司 | Composite material hanging rod piece structure |
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Application publication date: 20190108 |
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| RJ01 | Rejection of invention patent application after publication |