CN105253289B - Aircraft wing body attachment structure - Google Patents
Aircraft wing body attachment structure Download PDFInfo
- Publication number
- CN105253289B CN105253289B CN201510758449.9A CN201510758449A CN105253289B CN 105253289 B CN105253289 B CN 105253289B CN 201510758449 A CN201510758449 A CN 201510758449A CN 105253289 B CN105253289 B CN 105253289B
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- CN
- China
- Prior art keywords
- wing
- girder
- fuselage
- support plate
- steel beam
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Fee Related
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Abstract
The invention discloses a kind of aircraft wing body attachment structure, it is characterised in that fuselage and wing including interconnection；The wing is provided with：Girder after girder before horizontal vertical bar shaped wing, and horizontal vertical bar shaped wing；The fuselage is provided with：The central truss-steel beam of horizontal for connecting girder before wing, and for connecting the outer connection component of girder after wing.Aircraft wing body attachment structure of the present invention, it is rational in infrastructure, it is easy for installation.
Description
Technical field
The present invention relates to aircraft wing body attachment structure.
Background technology
Aircraft wing body attachment structure is to influence the key factor of aircaft configuration performance, and existing aircraft wing body attachment structure compares
Auxiliary, it has not been convenient to install.
The content of the invention
It is an object of the invention to provide a kind of aircraft wing body attachment structure, its is rational in infrastructure, easy for installation.
To achieve the above object, the technical scheme is that designing a kind of aircraft wing body attachment structure, it is characterised in that
Fuselage and wing including interconnection；
The wing is provided with：Girder after girder before horizontal vertical bar shaped wing, and horizontal vertical bar shaped wing；
The fuselage is provided with：The central truss-steel beam of horizontal for connecting girder before wing, and it is main after wing for connecting
The outer connection component of beam；
The central truss-steel beam runs through fuselage perpendicular to fuselage length direction；The central truss-steel beam, is located at machine at it
End on the outside of body, which is provided with, is used for the inserting groove of girder before grafting wing, and the inserting groove is parallel to each other for two on central truss-steel beam
Be vertically arranged clamping plate composition；
The inserting groove of the central truss-steel beam of girder insertion before the wing, and fixed by fastener with central truss-steel beam；Institute
State the mounting hole for being respectively provided with before clamping plate, wing on girder and installing fastener；
Girder after the wing, in the end that it is connected with fuselage, provided with the company of being vertically arranged for being connected with outer connection component
Connect ring；
The outer connection component is located at fuselage outer side, and it is made up of a pair of symmetrically arranged outer connectors；The outer connection
Part includes：The substrate being fixed on fuselage, and it is vertically arranged support plate by what substrate stretched out；
Above-mentioned a pair of symmetrically arranged outer connectors, their support plate is parallel to each other；The connection of girder after above-mentioned wing
Ring is placed between the support plate of the external connection part, and is fixed by the support plate of fastener and the external connection part；This externally connects
The support plate of fitting is provided with the mounting hole for being used for installing fastener.
It is preferred that, the fastener includes the pin and nut cooperated.
It is preferred that, the fixation of girder and inserting groove before the wing, pin runs through the mounting hole of girder and clamping plate before wing.
It is preferred that, the fixation of the connection ring and support plate, pin is through the centre bore of connection ring and the mounting hole of support plate.
The advantages of the present invention are：A kind of aircraft wing body attachment structure is provided, its is rational in infrastructure, installation side
Just.
Girder can be fixed conveniently with central truss-steel beam before aircraft wing body attachment structure of the present invention, wing, girder after wing
Can also conveniently it be fixed with outer connection component.
Brief description of the drawings
Fig. 1 is the schematic diagram of the present invention.
Embodiment
With reference to the accompanying drawings and examples, the embodiment to the present invention is further described.Following examples are only
For clearly illustrating technical scheme, and it can not be limited the scope of the invention with this.
The technical scheme that the present invention is embodied is：
As shown in figure 1, a kind of body attachment structure of the aircraft wing 2, it is characterised in that fuselage 1 and wing including interconnection
2；
The wing 2 is provided with：Girder 22 after girder 21 before horizontal vertical bar shaped wing, and horizontal vertical bar shaped wing；
The fuselage 1 is provided with：The central truss-steel beam 11 of horizontal for connecting girder 21 before wing, and for connecting wing
The outer connection component 12 of girder 22 afterwards；
The central truss-steel beam 11 runs through fuselage 1 perpendicular to the length direction of fuselage 1；The central truss-steel beam 11, at it
Being provided with positioned at the end in the outside of fuselage 1 is used for the inserting groove 110 of girder 21 before grafting wing, and the inserting groove 110 is by central steelframe
Two clamping plates 111 that are vertically arranged being parallel to each other are constituted on beam 11；
Girder 21 inserts the inserting groove 110 of central truss-steel beam 11 before the wing, and passes through fastener and central truss-steel beam
11 fix；The mounting hole for installing fastener is respectively provided with before the clamping plate 111, wing on girder 21；
Girder 22 after the wing, in the end that it is connected with fuselage 1, provided with perpendicular for what is be connected with outer connection component 12
Put connection ring 220；
The outer connection component 12 is located at the outside of fuselage 1, and it is made up of a pair of symmetrically arranged outer connectors；The outer company
Fitting includes：The substrate 121 being fixed on fuselage 1, and it is vertically arranged support plate 122 by what substrate 121 stretched out；
Above-mentioned a pair of symmetrically arranged outer connectors, their support plate 122 is parallel to each other；Girder 22 after above-mentioned wing
Connection ring 220 is placed between the support plate 122 of the external connection part, and passes through fastener and the support plate 122 of the external connection part
It is fixed；The support plate 122 of the external connection part is provided with the mounting hole for being used for installing fastener.
The fastener includes the pin 31,32 and nut 41,42 cooperated.
The fixation of girder 21 and inserting groove 110 before the wing, pin 31 runs through the installation of girder 21 and clamping plate 111 before wing
Hole.
The fixation of the connection ring 220 and support plate 122, centre bore and support plate 122 of the pin 32 through connection ring 220
Mounting hole.
Described above is only the preferred embodiment of the present invention, it is noted that for the ordinary skill people of the art
For member, without departing from the technical principles of the invention, some improvements and modifications can also be made, these improvements and modifications
Also it should be regarded as protection scope of the present invention.
Claims (4)
1. aircraft wing body attachment structure, it is characterised in that fuselage and wing including interconnection；
The wing is provided with：Girder after girder before horizontal vertical bar shaped wing, and horizontal vertical bar shaped wing；
The fuselage is provided with：The central truss-steel beam of horizontal for connecting girder before wing, and for connecting girder after wing
Outer connection component；
The central truss-steel beam runs through fuselage perpendicular to fuselage length direction；The central truss-steel beam, is located at outside fuselage at it
The end of side, which is provided with, is used for the inserting groove of girder before grafting wing, the inserting groove on central truss-steel beam two be parallel to each other it is perpendicular
Put clamping plate composition；
The inserting groove of the central truss-steel beam of girder insertion before the wing, and fixed by fastener with central truss-steel beam；The folder
The mounting hole for installing fastener is respectively provided with before plate, wing on girder；
Girder after the wing, in the end that it is connected with fuselage, provided with for outer connection component is connected is vertically arranged connection ring；
The outer connection component is located at fuselage outer side, and it is made up of a pair of symmetrically arranged outer connectors；The outer connector bag
Include：The substrate being fixed on fuselage, and it is vertically arranged support plate by what substrate stretched out；
Above-mentioned a pair of symmetrically arranged outer connectors, their support plate is parallel to each other；The connection ring of girder is put after above-mentioned wing
Fixed between the support plate of the external connection part, and by the support plate of fastener and the external connection part；The external connection part
Support plate be provided with and be used to the mounting hole of fastener be installed.
2. aircraft wing body attachment structure according to claim 1, it is characterised in that the fastener includes what is cooperated
Pin and nut.
3. aircraft wing body attachment structure according to claim 2, it is characterised in that girder and inserting groove before the wing
Steady pin runs through the mounting hole of girder and clamping plate before wing.
4. aircraft wing body attachment structure according to claim 3, it is characterised in that the fixation of the connection ring and support plate
Pin is through the centre bore of connection ring and the mounting hole of support plate.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510758449.9A CN105253289B (en) | 2015-11-10 | 2015-11-10 | Aircraft wing body attachment structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510758449.9A CN105253289B (en) | 2015-11-10 | 2015-11-10 | Aircraft wing body attachment structure |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN105253289A CN105253289A (en) | 2016-01-20 |
| CN105253289B true CN105253289B (en) | 2017-10-03 |
Family
ID=55093326
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510758449.9A Expired - Fee Related CN105253289B (en) | 2015-11-10 | 2015-11-10 | Aircraft wing body attachment structure |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN105253289B (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107215451A (en) * | 2017-06-16 | 2017-09-29 | 中电科芜湖通用航空产业技术研究院有限公司 | A kind of wing attachment structure of general-purpose aircraft |
Family Cites Families (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE102007063159A1 (en) * | 2007-12-30 | 2010-07-08 | Airbus Deutschland Gmbh | Wing-fuselage structural component for connecting two wings and a fuselage section on an aircraft |
| US8746616B2 (en) * | 2011-10-19 | 2014-06-10 | The Boeing Company | Mid-wing multi-deck airplane |
| FR2991287B1 (en) * | 2012-06-05 | 2015-02-27 | Airbus Operations Sas | AIRCRAFT AIRCRAFT WITHOUT CENTRAL HOUSING |
| CN102730182B (en) * | 2012-06-20 | 2014-10-01 | 中国航天时代电子公司 | Unmanned aerial vehicle wing and body connection apparatus |
| CN103895856A (en) * | 2014-04-24 | 2014-07-02 | 哈尔滨工业大学 | Composite-material I beam connecting device of aerofoils and aeroplane body |
| CN205168870U (en) * | 2015-11-10 | 2016-04-20 | 康福斯（苏州）航空工业有限公司 | Aircraft wing body connection structure |
-
2015
- 2015-11-10 CN CN201510758449.9A patent/CN105253289B/en not_active Expired - Fee Related
Also Published As
| Publication number | Publication date |
|---|---|
| CN105253289A (en) | 2016-01-20 |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20171003 Termination date: 20181110 |
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| CF01 | Termination of patent right due to non-payment of annual fee |