CN104176228B - A kind of composite fuselage, Wing Joint - Google Patents
A kind of composite fuselage, Wing Joint Download PDFInfo
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- CN104176228B CN104176228B CN201410066981.XA CN201410066981A CN104176228B CN 104176228 B CN104176228 B CN 104176228B CN 201410066981 A CN201410066981 A CN 201410066981A CN 104176228 B CN104176228 B CN 104176228B
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Abstract
The present invention relates to air equipment technical field, more particularly to a kind of composite fuselage, Wing Joint.Composite fuselage, Wing Joint, including upper cantilever, lower cantalever, left cantilever and right cantilever, wherein, the upper cantilever, lower cantalever, left cantilever and right cantilever are formed by multilayer materials cloth stacking.The joint that the application is provided is stacked by multilayer materials cloth and is made fuselage, Wing Joint, when metal joint can be avoided to be connected with composite wing or fuselage, because joint is connected unsteady problem with fuselage, wing caused by the factors such as galvanic corrosion, thermal expansion, and on the premise of attachment structure intensity is met, with lightweight, the characteristics of low cost of manufacture.
Description
Technical field
The present invention relates to air equipment technical field, more particularly to a kind of composite fuselage, Wing Joint.
Background technology
Modern times in the world, all propose higher wanting in terms of seaworthiness clause or economic benefit to Ci vil Aircraft Design
Ask.Its economy, security, comfortableness turn into the target that global civil aircraft manufacturer praises highly the most.And come in terms of another
Say, new material, new technology are greatly developed also as Ci vil Aircraft Design provides more wide stage.Especially contemporary composite
Application,, not in the cutting out property of metal, density is light, is widely used in civil aircraft structures the advantages of anticorrosive for it.The country is multiple
The application of condensation material, especially the application paces in terms of Ci vil Aircraft Design are slower than other giant manufacturers in the world and more protect
Keep.
Wing connection is most important link in airplane design.During cross jointing is also Large Civil Aircraft fuselage
Centre wing box and the principal mode of wing connection.Its material is mostly metal, joint assembling form be mostly fastener connection or
Welding.The connection of this metal joint is more expensive to manufacture, allowance control is difficult, weight weight the shortcomings of.
Regarding to the issue above, it would be desirable to when one kind can avoid metal joint and composite wing or fuselage from connecting,
Due to some problems that the factors such as galvanic corrosion, thermal expansion cause, structure is also caused on the premise of intensity is met, with weight
Gently, the joint design of low cost of manufacture.
The content of the invention
It is an object of the invention to propose a kind of composite fuselage, Wing Joint, with structural strength higher, and matter
Amount is light, low cost of manufacture, and stronger with the stability that wing and fuselage are connected.
It is that, up to this purpose, the present invention uses following technical scheme：
A kind of composite fuselage, Wing Joint, including upper cantilever, lower cantalever, left cantilever and right cantilever, wherein, it is described
Upper cantilever, lower cantalever, left cantilever and right cantilever are formed by multilayer materials cloth stacking.
Used as above-mentioned composite fuselage, a kind of preferred scheme of Wing Joint, every layer of composite material cloth includes first
Part and Part II, the Part I and Part II are vertically arranged.
Used as above-mentioned composite fuselage, a kind of preferred scheme of Wing Joint, the multilayer materials cloth included
Area is crossed, the transition region is ramp type structure.
Used as above-mentioned composite fuselage, a kind of preferred scheme of Wing Joint, the transition region passes through multi-layer composite materials
Layer is lost in material cloth stacking process or increases layer and be made.
Used as above-mentioned composite fuselage, a kind of preferred scheme of Wing Joint, the interval between two adjacent transitions is big
In 2.5mm.
Used as above-mentioned composite fuselage, a kind of preferred scheme of Wing Joint, the laying positioned at transition region two ends is differed
Two-layer.
Used as above-mentioned composite fuselage, a kind of preferred scheme of Wing Joint, the composite material cloth is control of two-dimensional braided
Cloth, the control of two-dimensional braided cloth includes warp and parallel, and the warp of at least described control of two-dimensional braided cloth is combined by carbon fiber/epoxy resin
Material is made.
Used as above-mentioned composite fuselage, a kind of preferred scheme of Wing Joint, the multilayer materials cloth passes through glue
Knot agent cementation solidifying.
Used as above-mentioned composite fuselage, a kind of preferred scheme of Wing Joint, the joint includes four kinds towards difference
The composite material cloth in direction, respectively the first composite material cloth, the second composite material cloth, triplex material cloth and the 4th are combined
Material cloth；
The Part II of first composite material cloth and the Part II of the second composite material cloth constitute upper cantilever, described
The Part I of the second composite material cloth and the Part I of triplex material cloth constitute right cantilever, the triplex material
The Part II of the Part II of cloth and the 4th composite material cloth constitutes lower cantalever, the Part I of the 4th composite material cloth
Left cantilever is constituted with the Part I of the first composite material cloth.
As above-mentioned composite fuselage, a kind of preferred scheme of Wing Joint, when the joint is connected with metal structure
When, side glass fibre or titanium are equipped with the joint face of joint.
Beneficial effects of the present invention are：This application provides a kind of composite fuselage, Wing Joint, it passes through multilayer and answers
Condensation material cloth stacking is made fuselage, Wing Joint, when metal joint can be avoided to be connected with composite wing or fuselage, due to
Joint is connected unsteady problem with fuselage, wing caused by the factors such as galvanic corrosion, thermal expansion, and is meeting attachment structure
On the premise of intensity, with lightweight, the characteristics of low cost of manufacture.
Brief description of the drawings
Fig. 1 is composite fuselage, the structural representation of Wing Joint that the specific embodiment of the invention is provided；
Fig. 2 is the structural representation of the multilayer materials cloth with transition region that the specific embodiment of the invention is provided.
Wherein：
1：Upper cantilever；2：Lower cantalever；3：Left cantilever；4：Right cantilever；5：Transition region；6：First composite material cloth；7：Second
Composite material cloth；8：Triplex material cloth；9：4th composite material cloth.
Specific embodiment
Further illustrate technical scheme below in conjunction with the accompanying drawings and by specific embodiment.
As shown in figure 1, in this embodiment, this application provides a kind of composite fuselage, Wing Joint, it includes
Upper cantilever 1, lower cantalever 2, left cantilever 3 and right cantilever 4, above-mentioned upper cantilever 1, lower cantalever 2, left cantilever 3 and right cantilever 4 are answered by multilayer
Condensation material cloth stacking is formed.
Specifically, the cross-shaped configuration that joint is made up of upper cantilever 1, lower cantalever 2, left cantilever 3 and right cantilever 4, plays
The effect of connection fuselage and wing.Wherein, upper cantilever 1 is connected with fuselage frame or fuselage, lower cantalever 2 and airfoil root floor phase
Even, left cantilever 3 is connected with the wainscot of fuselage center wing box, and right cantilever 4 is connected with the wainscot of wing.In this embodiment
Joint is formed using multilayer materials cloth stacking, can improve the stability of fuselage and wing connection.
In this embodiment, every layer of composite material cloth includes Part I and Part II, Part I and second
Part is vertically arranged, specifically, Part I is horizontally disposed, Part II is vertically arranged.
As shown in Fig. 2 in order to joint install or structure on the need for, multilayer materials cloth include transition region, the transition
Area 5 is ramp type structure.Transition region 5 is made by losing layer in multilayer materials cloth stacking process or increasing layer.And two is adjacent
Interval between transition region is more than 2.5mm.
The laying that laying positioned at the two ends of transition region 5 differs two-layer, i.e. transition region is successively decreased 2 layers every time.
Used as preferred, there is complete laying the laminate surface part of transition region 5, and loses layer or increase layer and all should
It should be uniform arrangement.
Composite material cloth is control of two-dimensional braided cloth, and control of two-dimensional braided cloth includes warp and parallel, at least warp of control of two-dimensional braided cloth
It is made up of carbon fiber/epoxy resin composite material.Because the warp of control of two-dimensional braided cloth is main Impact direction, parallel does not possess
Structural behaviour, parallel is used only to keep the position of warp, therefore, the warp of control of two-dimensional braided cloth is by carbon fiber/epoxy resin
Composite is made, parallel it is not necessary to be made up of carbon fiber/epoxy resin composite material.
In order to improve the structural strength of joint, the cross facet of the horizontally and vertically plate of cruciform joint has radially continuous fiber
Pass through.
Multilayer materials cloth carries out fastener connection by cementing agent cementation solidifying after solidification, if joint and metal knot
Structure is connected, and layer of glass or titanium are laid in its connection surface.And the edge of structure need to carry out encapsulation process.
In this embodiment, joint includes four kinds of composite material cloths towards different directions, respectively the first composite wood
Material cloth 6, the second composite material cloth 7, triplex material cloth 8 and the 4th composite material cloth 9.The second of first composite material cloth 6
The Part II of part and the second composite material cloth 7 constitutes upper cantilever 1, and the Part I of the second composite material cloth 7 and the 3rd answer
The Part I of condensation material cloth 8 constitutes right cantilever 4, and the of the Part II of triplex material cloth 8 and the 4th composite material cloth 9
Two parts constitute a Part I composition left side for lower cantalever 2, the Part I of the 4th composite material cloth 9 and the first composite material cloth 6
Cantilever 3.
Know-why of the invention is described above in association with specific embodiment.These descriptions are intended merely to explain of the invention
Principle, and can not by any way be construed to limiting the scope of the invention.Based on explanation herein, the technology of this area
Personnel associate other specific embodiments of the invention by would not require any inventive effort, these modes fall within
Within protection scope of the present invention.
Claims (7)
1. a kind of composite fuselage, Wing Joint, including upper cantilever, lower cantalever, left cantilever and right cantilever, it is characterised in that
The upper cantilever, lower cantalever, left cantilever and right cantilever are formed by multilayer materials cloth stacking；
The multilayer materials cloth includes transition region, and there is complete laying the transition region layer clamp surface part；
Interval between two adjacent transitions is more than 2.5mm；
The composite material cloth is control of two-dimensional braided cloth, and the control of two-dimensional braided cloth includes warp and parallel, at least described control of two-dimensional braided
The warp of cloth is made up of carbon fiber/epoxy resin composite material；
When the joint is connected with metal structure, side glass fibre or titanium are equipped with the joint face of joint.
2. composite fuselage according to claim 1, Wing Joint, it is characterised in that every layer of composite material cloth is wrapped
Part I and Part II are included, the Part I and Part II are vertically arranged.
3. composite fuselage according to claim 1, Wing Joint, it is characterised in that the transition region is ramp type
Structure.
4. composite fuselage according to claim 3, Wing Joint, it is characterised in that the transition region passes through multilayer
Layer is lost in composite material cloth stacking process or increases layer and be made.
5. composite fuselage according to claim 3, Wing Joint, it is characterised in that positioned at the paving at transition region two ends
Layer difference two-layer.
6. composite fuselage according to claim 1, Wing Joint, it is characterised in that the multilayer materials cloth
By cementing agent cementation solidifying.
7. composite fuselage according to claim 2, Wing Joint, it is characterised in that the joint includes four kinds of courts
To the composite material cloth of different directions, respectively the first composite material cloth, the second composite material cloth, triplex material cloth and
Four composite material cloths；
The Part II of first composite material cloth and the Part II of the second composite material cloth constitute upper cantilever, described second
The Part I of composite material cloth and the Part I of triplex material cloth constitute right cantilever, the triplex material cloth
The Part II of Part II and the 4th composite material cloth constitutes lower cantalever, the Part I of the 4th composite material cloth and the
The Part I of one composite material cloth constitutes left cantilever.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410066981.XA CN104176228B (en) | 2014-02-26 | 2014-02-26 | A kind of composite fuselage, Wing Joint |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410066981.XA CN104176228B (en) | 2014-02-26 | 2014-02-26 | A kind of composite fuselage, Wing Joint |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN104176228A CN104176228A (en) | 2014-12-03 |
| CN104176228B true CN104176228B (en) | 2017-07-11 |
Family
ID=51957648
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410066981.XA Active CN104176228B (en) | 2014-02-26 | 2014-02-26 | A kind of composite fuselage, Wing Joint |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN104176228B (en) |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105290739B (en) * | 2015-11-24 | 2018-09-07 | 中国航空工业集团公司北京航空制造工程研究所 | The laying increasing material manufacturing method of abnormally-structured titanium alloy member based on diffusion connection |
| CN106314759A (en) * | 2016-09-06 | 2017-01-11 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | Spar connecting structure of aircraft wing |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1171356A (en) * | 1996-07-18 | 1998-01-28 | 西科尔斯基飞机公司 | Optimized composite flexbeam for helicopter tail rotors |
| CN101323370A (en) * | 2008-06-24 | 2008-12-17 | 北京航空航天大学 | Joint of body and wing of large-sized civil aeroplane |
| CN101522520A (en) * | 2006-10-03 | 2009-09-02 | 空中客车英国有限公司 | Fitting |
| CN102300772A (en) * | 2008-11-27 | 2011-12-28 | 空中客车西班牙运营有限责任公司 | Front Trimming Fitting And Related Assembly |
Family Cites Families (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2873347B1 (en) * | 2004-07-22 | 2006-11-17 | Airbus France Sas | DEVICE FOR LAUNCHING ELEMENTS OF COMPOSITE STRUCTURE WITH METALLIC STRUCTURE ELEMENTS |
| ES2372849B1 (en) * | 2010-03-25 | 2012-12-13 | Airbus Operations, S.L. | STRUCTURE OF UNION OF TORSION DRAWERS IN AN AIRCRAFT THROUGH A TRIFORM HARDWARE OF NON-METAL COMPOSITE MATERIALS. |
| CN103448918B (en) * | 2013-08-08 | 2016-08-10 | 上海卫星工程研究所 | With loaded cylinder canister fabric continuous print composite end frame and loaded cylinder |
-
2014
- 2014-02-26 CN CN201410066981.XA patent/CN104176228B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1171356A (en) * | 1996-07-18 | 1998-01-28 | 西科尔斯基飞机公司 | Optimized composite flexbeam for helicopter tail rotors |
| CN101522520A (en) * | 2006-10-03 | 2009-09-02 | 空中客车英国有限公司 | Fitting |
| CN101323370A (en) * | 2008-06-24 | 2008-12-17 | 北京航空航天大学 | Joint of body and wing of large-sized civil aeroplane |
| CN102300772A (en) * | 2008-11-27 | 2011-12-28 | 空中客车西班牙运营有限责任公司 | Front Trimming Fitting And Related Assembly |
Also Published As
| Publication number | Publication date |
|---|---|
| CN104176228A (en) | 2014-12-03 |
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