CN105253289A - Wing and body connecting structure of airplane - Google Patents
Wing and body connecting structure of airplane Download PDFInfo
- Publication number
- CN105253289A CN105253289A CN201510758449.9A CN201510758449A CN105253289A CN 105253289 A CN105253289 A CN 105253289A CN 201510758449 A CN201510758449 A CN 201510758449A CN 105253289 A CN105253289 A CN 105253289A
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- wing
- girder
- fuselage
- back plate
- steel beam
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Abstract
The invention discloses a wing and body connecting structure of an airplane. The wing and body connecting structure of the airplane is characterized in that an airplane body and a wing which are connected with each other are included; the wing is provided with a horizontally arranged straight-bar-shaped wing front main beam and a horizontally arranged straight-bar-shaped wing back main beam; the airplane body is provided with a horizontally arranged central steel frame beam used for connecting the wing front main beam and an outer connecting assembly used for connecting the wing back main beam. The wing and body connecting structure of the airplane is reasonable in structure and convenient to install.
Description
Technical field
The present invention relates to aircraft wing body connection structure.
Background technology
Aircraft wing body connection structure is the key factor affecting aircaft configuration performance, and existing aircraft wing body connection structure is more auxiliary, is inconvenient to install.
Summary of the invention
The object of the present invention is to provide a kind of aircraft wing body connection structure, it is rational in infrastructure, easy for installation.
For achieving the above object, technical scheme of the present invention is a kind of aircraft wing body connection structure of design, it is characterized in that, comprises interconnective fuselage and wing;
Described wing is provided with: girder before horizontal vertical bar shaped wing, and girder after horizontal vertical bar shaped wing;
Described fuselage is provided with: for connecting the horizontal central authorities truss-steel beam of girder before wing, and for connecting the outer coupling assembling of girder after wing;
Described central truss-steel beam perpendicular to fuselage length direction, and runs through fuselage; Described central truss-steel beam, is provided with the inserting groove of girder before for grafting wing in the end that it is positioned at fuselage outer side, this inserting groove is made up of two perpendicular clamping plate of putting be parallel to each other on central truss-steel beam;
Before described wing, girder inserts the inserting groove of central truss-steel beam, and is fixed by fastener and central truss-steel beam; Before described clamping plate, wing, girder is respectively equipped with the mounting hole for mounting fastener;
Girder after described wing, in the end that it is connected with fuselage, is provided with and perpendicularly puts coupling link for what be connected with outer coupling assembling;
Described outer coupling assembling is positioned at fuselage outer side, and it is made up of a pair symmetrically arranged outer connector; Described outer connector comprises: be fixed on the substrate on fuselage, and puts back plate by outward extending the erecting of substrate;
Above-mentioned a pair symmetrically arranged outer connector, their back plate is parallel to each other; After above-mentioned wing, the coupling link of girder is placed in this between the back plate of outer connector, and is fixed the back plate of outer connector by fastener and this; This is provided with the mounting hole for mounting fastener to the back plate of outer connector.
Preferably, described fastener comprises the pin and nut that cooperatively interact.
Preferably, before described wing, girder and inserting groove is fixing, and pin runs through the mounting hole of girder and clamping plate before wing.
Preferably, described coupling link and back plate fixing, pin runs through the centre hole of coupling link and the mounting hole of back plate.
Advantage of the present invention and beneficial effect are: provide a kind of aircraft wing body connection structure, it is rational in infrastructure, easy for installation.
Aircraft wing body connection structure of the present invention, before wing, girder and central truss-steel beam can conveniently be fixed, and after wing, girder and outer coupling assembling also can conveniently be fixed.
Accompanying drawing explanation
Fig. 1 is schematic diagram of the present invention.
Detailed description of the invention
Below in conjunction with drawings and Examples, the specific embodiment of the present invention is further described.Following examples only for technical scheme of the present invention is clearly described, and can not limit the scope of the invention with this.
The technical scheme that the present invention specifically implements is:
As shown in Figure 1, a kind of aircraft wing 2 body connection structure, is characterized in that, comprise interconnective fuselage 1 and wing 2;
Described wing 2 is provided with: girder 21 before horizontal vertical bar shaped wing, and girder 22 after horizontal vertical bar shaped wing;
Described fuselage 1 is provided with: for connecting the horizontal central authorities truss-steel beam 11 of girder 21 before wing, and for connecting the outer coupling assembling 12 of girder 22 after wing;
Described central truss-steel beam 11 perpendicular to fuselage 1 length direction, and runs through fuselage 1; Described central truss-steel beam 11, is provided with the inserting groove 110 of girder 21 before for grafting wing in its end be positioned at outside fuselage 1, this inserting groove 110 is made up of two perpendicular clamping plate 111 of putting be parallel to each other on central truss-steel beam 11;
Before described wing, girder 21 inserts the inserting groove 110 of central truss-steel beam 11, and is fixed by fastener and central truss-steel beam 11; Before described clamping plate 111, wing, girder 21 is respectively equipped with the mounting hole for mounting fastener;
Girder 22 after described wing, in the end that it is connected with fuselage 1, is provided with and perpendicularly puts coupling link 220 for what be connected with outer coupling assembling 12;
Described outer coupling assembling 12 is positioned at outside fuselage 1, and it is made up of a pair symmetrically arranged outer connector; Described outer connector comprises: be fixed on the substrate 121 on fuselage 1, and puts back plate 122 by outward extending the erecting of substrate 121;
Above-mentioned a pair symmetrically arranged outer connector, their back plate 122 is parallel to each other; After above-mentioned wing, the coupling link 220 of girder 22 is placed in this between the back plate 122 of outer connector, and is fixed the back plate 122 of outer connector by fastener and this; This is provided with the mounting hole for mounting fastener to the back plate 122 of outer connector.
Described fastener comprises the pin 31,32 and nut 41,42 that cooperatively interact.
Before described wing, girder 21 and inserting groove 110 is fixing, and pin 31 runs through the mounting hole of girder 21 and clamping plate 111 before wing.
Described coupling link 220 is fixing with back plate 122, and pin 32 runs through the centre hole of coupling link 220 and the mounting hole of back plate 122.
The above is only the preferred embodiment of the present invention; it should be pointed out that for those skilled in the art, under the prerequisite not departing from the technology of the present invention principle; can also make some improvements and modifications, these improvements and modifications also should be considered as protection scope of the present invention.
Claims (4)
1. aircraft wing body connection structure, is characterized in that, comprises interconnective fuselage and wing;
Described wing is provided with: girder before horizontal vertical bar shaped wing, and girder after horizontal vertical bar shaped wing;
Described fuselage is provided with: for connecting the horizontal central authorities truss-steel beam of girder before wing, and for connecting the outer coupling assembling of girder after wing;
Described central truss-steel beam perpendicular to fuselage length direction, and runs through fuselage; Described central truss-steel beam, is provided with the inserting groove of girder before for grafting wing in the end that it is positioned at fuselage outer side, this inserting groove is made up of two perpendicular clamping plate of putting be parallel to each other on central truss-steel beam;
Before described wing, girder inserts the inserting groove of central truss-steel beam, and is fixed by fastener and central truss-steel beam; Before described clamping plate, wing, girder is respectively equipped with the mounting hole for mounting fastener;
Girder after described wing, in the end that it is connected with fuselage, is provided with and perpendicularly puts coupling link for what be connected with outer coupling assembling;
Described outer coupling assembling is positioned at fuselage outer side, and it is made up of a pair symmetrically arranged outer connector; Described outer connector comprises: be fixed on the substrate on fuselage, and puts back plate by outward extending the erecting of substrate;
Above-mentioned a pair symmetrically arranged outer connector, their back plate is parallel to each other; After above-mentioned wing, the coupling link of girder is placed in this between the back plate of outer connector, and is fixed the back plate of outer connector by fastener and this; This is provided with the mounting hole for mounting fastener to the back plate of outer connector.
2. aircraft wing body connection structure according to claim 1, is characterized in that, described fastener comprises the pin and nut that cooperatively interact.
3. aircraft wing body connection structure according to claim 2, is characterized in that, before described wing, girder and inserting groove is fixing, and pin runs through the mounting hole of girder and clamping plate before wing.
4. aircraft wing body connection structure according to claim 3, is characterized in that, described coupling link and back plate fixing, and pin runs through the centre hole of coupling link and the mounting hole of back 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 true CN105253289A (en) | 2016-01-20 |
| CN105253289B 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) |
Cited By (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 |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101909989A (en) * | 2007-12-30 | 2010-12-08 | 空中客车营运有限公司 | Wing-fuselage structural component for the connection of two airfoils and a fuselage section on an aircraft |
| CN102730182A (en) * | 2012-06-20 | 2012-10-17 | 中国航天时代电子公司 | Unmanned aerial vehicle wing and body connection apparatus |
| GB2495846A (en) * | 2011-10-19 | 2013-04-24 | Boeing Co | Twin-deck aircraft with mid-mounted wing |
| FR2991287A1 (en) * | 2012-06-05 | 2013-12-06 | Airbus Operations Sas | Transport aircraft e.g. military transport aircraft, has mast strut carrying out structural connection between longerons leveled with aerofoil fastener zone and large frame of zone of fuselage, and fitting arranged integral to frame |
| 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
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101909989A (en) * | 2007-12-30 | 2010-12-08 | 空中客车营运有限公司 | Wing-fuselage structural component for the connection of two airfoils and a fuselage section on an aircraft |
| GB2495846A (en) * | 2011-10-19 | 2013-04-24 | Boeing Co | Twin-deck aircraft with mid-mounted wing |
| FR2991287A1 (en) * | 2012-06-05 | 2013-12-06 | Airbus Operations Sas | Transport aircraft e.g. military transport aircraft, has mast strut carrying out structural connection between longerons leveled with aerofoil fastener zone and large frame of zone of fuselage, and fitting arranged integral to frame |
| CN102730182A (en) * | 2012-06-20 | 2012-10-17 | 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 |
Cited By (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 |
Also Published As
| Publication number | Publication date |
|---|---|
| CN105253289B (en) | 2017-10-03 |
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| 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 |