CN205168870U - Aircraft wing body connection structure - Google Patents
Aircraft wing body connection structure Download PDFInfo
- Publication number
- CN205168870U CN205168870U CN201520888974.8U CN201520888974U CN205168870U CN 205168870 U CN205168870 U CN 205168870U CN 201520888974 U CN201520888974 U CN 201520888974U CN 205168870 U CN205168870 U CN 205168870U
- Authority
- CN
- China
- Prior art keywords
- wing
- girder
- fuselage
- back plate
- connection structure
- 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.)
- Withdrawn - After Issue
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Abstract
The utility model discloses an aircraft wing body connection structure, a serial communication port, fuselage and wing including interconnect, the wing is equipped with: the flat preceding girder of vertical bar shape wing of putting to and flat put girder behind the vertical bar shape wing, the fuselage is equipped with: a flat center adjustment centre steelframe roof beam that is used for connecting girder before the wing to and be used for connecting the outer coupling assembling of girder behind the wing. The utility model discloses aircraft wing body connection structure, it is rational in infrastructure, simple to operate.
Description
Technical field
The utility model 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.
Utility model content
The purpose of this utility model is to provide a kind of aircraft wing body connection structure, and it is rational in infrastructure, easy for installation.
For achieving the above object, the technical solution of the utility model 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 utility model and beneficial effect are: provide a kind of aircraft wing body connection structure, it is rational in infrastructure, easy for installation.
The utility model aircraft wing body connection structure, 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 utility model.
Detailed description of the invention
Below in conjunction with drawings and Examples, detailed description of the invention of the present utility model is further described.Following examples only for clearly the technical solution of the utility model being described, and can not limit protection domain of the present utility model with this.
The technical scheme that the utility model is specifically implemented 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 preferred implementation of the present utility model; should be understood that; for those skilled in the art; under the prerequisite not departing from the utility model know-why; can also make some improvements and modifications, these improvements and modifications also should be considered as protection domain of the present utility model.
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 |
|---|---|---|---|
| CN201520888974.8U CN205168870U (en) | 2015-11-10 | 2015-11-10 | Aircraft wing body connection structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520888974.8U CN205168870U (en) | 2015-11-10 | 2015-11-10 | Aircraft wing body connection structure |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205168870U true CN205168870U (en) | 2016-04-20 |
Family
ID=55732887
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201520888974.8U Withdrawn - After Issue CN205168870U (en) | 2015-11-10 | 2015-11-10 | Aircraft wing body connection structure |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN205168870U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105253289A (en) * | 2015-11-10 | 2016-01-20 | 康福斯（苏州）航空工业有限公司 | Wing and body connecting structure of airplane |
-
2015
- 2015-11-10 CN CN201520888974.8U patent/CN205168870U/en not_active Withdrawn - After Issue
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105253289A (en) * | 2015-11-10 | 2016-01-20 | 康福斯（苏州）航空工业有限公司 | Wing and body connecting structure of airplane |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| AV01 | Patent right actively abandoned |
Granted publication date: 20160420 Effective date of abandoning: 20171003 |
|
| AV01 | Patent right actively abandoned |