CN105314087A - Connection structure between central wing and fuselage - Google Patents
Connection structure between central wing and fuselage Download PDFInfo
- Publication number
- CN105314087A CN105314087A CN201410263599.8A CN201410263599A CN105314087A CN 105314087 A CN105314087 A CN 105314087A CN 201410263599 A CN201410263599 A CN 201410263599A CN 105314087 A CN105314087 A CN 105314087A
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- China
- Prior art keywords
- wing
- connection structure
- section
- fuselage
- bolt
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- 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.)
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- Connection Of Plates (AREA)
- Pressure Vessels And Lids Thereof (AREA)
- Filling Or Discharging Of Gas Storage Vessels (AREA)
Abstract
The invention belongs to the technical field of aviation and particularly provides a connection structure between a central wing and a fuselage. In the connection structure a sectional bolt (1) is matched with a suspended nut (7) respectively through an aerofoil girder (2), a wing lower panel (3), an adjustment pad plate (4), a fuselage reinforcing frame (5) and a tapered washer (6). The structure solves a sealing problem in sealing zones, greatly improves assembly technology and meanwhile improves fatigue life and safety of high-stress part connection structures.
Description
Technical field
The present invention is used for technical field of aerospace.Specifically, for central wing and fuselage docking structure.
Background technology
Certain type machine central wing is integral tank, is connected herein not only will ensures that structure oil is close but also for crucial force part with fuselage.Improve structural fatigue performance and manufacturability for meeting sealing structure simultaneously.Need proposition a kind of for there being the connecting device of the crucial force part of seal request for this reason.
Summary of the invention
(1) goal of the invention:
Instant invention overcomes deficiency of the prior art, provide one and can ensure sealing element seal request, wing body connection structure fatigue property can be improved again, improve the bolted manufacturability of interference simultaneously.
(2) technical scheme:
In order to solve the problems of the technologies described above, the present invention is achieved by the following technical solutions: a kind of central wing and body connection structure, and this connection structure adopts that segmentation bolt 1 is each passed through wing crossbeam 2, wing lower wall panels 3, adjustment backing plate 4, fuselage reinforcing frame 5, cone washer 6 coordinate with Tension Nut 7; Wherein segmentation bolt 1 is made up of bolt cap 101, interference section 102, transition phase 103, gap section 104, relief groove 105, MJ thread segment 106, traction section 107.Interference section 102 and wing crossbeam 2, wing lower wall panels 3 interference fit ensure that central wing integral tank seals, transition phase 103 to gap section 104 and fuselage reinforcing frame 5 free-running fit, MJ thread segment and Tension Nut 7 fit through cone washer 6 and are pressed in fuselage reinforcing frame 5, and traction section 107 plays technique draw and cuts away after assembling terminates in fitting process.
(3) beneficial effect
Compared with prior art, the invention has the beneficial effects as follows: first, solve the seal request of sealing area; Secondly, interference bolts assemblies manufacturability is substantially improved; Improve fatigue life and the safety of heavily stressed position connection structure simultaneously.
Accompanying drawing explanation
Fig. 1 is this connection structure schematic diagram; Fig. 2 is segmentation bolt 1 schematic diagram, and Fig. 3 is relief groove and knuckle schematic diagram, and Fig. 4 is pressure-bearing flange bolt head and regular bolt head, and Fig. 5 is Tension Nut and cone washer connection diagram, and Fig. 6 is that nut receives crush-cutting mouth schematic diagram.
Detailed description of the invention
Below in conjunction with accompanying drawing and detailed description of the invention, the present invention is described in further detail.
Traditional wing and body connection structure are made up of bolt, safety washer, self lock nut, are a kind of typical connection structures.Special being in one of the segmentation bolt fastening structure that the present invention adopts is that position is special, in central wing integral tank, must ensure that oil is close and construction space is narrow and small; Two is crucial force parts, this place, needs special shape could meet intensity, rigidity, the fatigue life requirements of the docking of wing body, so have employed special shape bolt, nut and packing ring.
A kind of central wing and body connection structure, this connection structure adopts that segmentation bolt 1 is each passed through wing crossbeam 2, wing lower wall panels 3, adjustment backing plate 4, fuselage reinforcing frame 5, cone washer 6 coordinate with Tension Nut 7; Wherein segmentation bolt 1 is made up of bolt cap 101, interference section 102, transition phase 103, gap section 104, relief groove 105, MJ thread segment 106, traction section 107.Interference section 102 and wing crossbeam 2, wing lower wall panels 3 interference fit ensure that central wing integral tank seals, by transition phase 103 excessively to gap section 104 with fuselage reinforcing frame 5 free-running fit to reduce technology difficulty, MJ thread segment and Tension Nut 7 fit through cone washer 6 and are pressed in fuselage reinforcing frame 5 and improve Anti-Fatigue performance, and traction section 107 plays technique draw and cuts away after assembling terminates in fitting process.
In use, interference section ensures leak tightness, does not have seal request mating area to adopt gap section, as shown in Figure 2.Design gaps section can effectively reduce pressing-in force during bolts assemblies, as narrow and small in bolt join domain cannot for the press-fit equipments such as compression machine construction space is provided when, increasing traction section, during for assembling, providing pressing-in force.Traction section is cut away after assembling terminates.
Adopt MJ screw thread, relief groove in conjunction with large scale knuckle (shown in Fig. 3), effectively improve bolt fatigue property.
Special bolt head (as shown in Figure 4) increases bolt cap and attaching parts contact surface ensures that larger predetermincd tension does not fail, and effectively improves bolted strength at repeated alternation.
Adopt cone washer to be combined with Tension Nut (shown in Fig. 5), improve screw thread loading and reduce or avoid bolt to be subject to additional bending stress, improving bolt fatigue life.
Tension Nut design receipts crush-cutting mouth (shown in Fig. 6) reaches locking object in addition.
Claims (1)
1. a central wing and body connection structure, it is characterized in that, this connection structure adopts that segmentation bolt (1) is each passed through wing crossbeam (2), wing lower wall panels (3), adjustment backing plate (4), fuselage reinforcing frame (5), cone washer (6) coordinate with Tension Nut (7); Wherein segmentation bolt (1) is made up of bolt cap (101), interference section (102), transition phase (103), gap section (104), relief groove (105), MJ thread segment (106), traction section (107); Interference section (102) and wing crossbeam (2), wing lower wall panels (3) interference fit ensure that central wing integral tank seals, transition phase (103) is to gap section (104) and fuselage reinforcing frame (5) free-running fit, MJ thread segment and Tension Nut (7) fit through cone washer (6) and are pressed in fuselage reinforcing frame (5), and traction section (107) plays technique draw and cuts away after assembling terminates in fitting process.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410263599.8A CN105314087A (en) | 2014-06-13 | 2014-06-13 | Connection structure between central wing and fuselage |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410263599.8A CN105314087A (en) | 2014-06-13 | 2014-06-13 | Connection structure between central wing and fuselage |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN105314087A true CN105314087A (en) | 2016-02-10 |
Family
ID=55242597
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410263599.8A Pending CN105314087A (en) | 2014-06-13 | 2014-06-13 | Connection structure between central wing and fuselage |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN105314087A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109110103A (en) * | 2018-09-12 | 2019-01-01 | 淮北创之社信息科技有限公司 | A kind of aircraft cabin siding docking structure |
| CN111824388A (en) * | 2019-04-18 | 2020-10-27 | 成都飞机工业（集团）有限责任公司 | Fixed wing unmanned aerial vehicle tail boom hangs |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5018920A (en) * | 1989-01-23 | 1991-05-28 | Mcdonnell Douglas Corporation | Interference fit bolt and sleeve |
| RU2456204C2 (en) * | 2007-04-26 | 2012-07-20 | Эйрбас Оперейшнс Гмбх | Aircraft wing-fuselage section |
| CN202783772U (en) * | 2012-03-09 | 2013-03-13 | 陕西飞机工业（集团）有限公司 | Butt-joint structure of airplane wing body |
| CN103252893A (en) * | 2012-02-20 | 2013-08-21 | 空中客车西班牙运营有限责任公司 | Riveting device for aircraft fuselages |
| CN203230706U (en) * | 2013-04-20 | 2013-10-09 | 湖北博士隆科技有限公司 | Snap type efficient locking bolt |
| CN203641229U (en) * | 2013-12-12 | 2014-06-11 | 陕西飞机工业（集团）有限公司 | Bearing sealing bolt |
-
2014
- 2014-06-13 CN CN201410263599.8A patent/CN105314087A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5018920A (en) * | 1989-01-23 | 1991-05-28 | Mcdonnell Douglas Corporation | Interference fit bolt and sleeve |
| RU2456204C2 (en) * | 2007-04-26 | 2012-07-20 | Эйрбас Оперейшнс Гмбх | Aircraft wing-fuselage section |
| CN103252893A (en) * | 2012-02-20 | 2013-08-21 | 空中客车西班牙运营有限责任公司 | Riveting device for aircraft fuselages |
| CN202783772U (en) * | 2012-03-09 | 2013-03-13 | 陕西飞机工业（集团）有限公司 | Butt-joint structure of airplane wing body |
| CN203230706U (en) * | 2013-04-20 | 2013-10-09 | 湖北博士隆科技有限公司 | Snap type efficient locking bolt |
| CN203641229U (en) * | 2013-12-12 | 2014-06-11 | 陕西飞机工业（集团）有限公司 | Bearing sealing bolt |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109110103A (en) * | 2018-09-12 | 2019-01-01 | 淮北创之社信息科技有限公司 | A kind of aircraft cabin siding docking structure |
| CN111824388A (en) * | 2019-04-18 | 2020-10-27 | 成都飞机工业（集团）有限责任公司 | Fixed wing unmanned aerial vehicle tail boom hangs |
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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 | ||
| RJ01 | Rejection of invention patent application after publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20160210 |