CN105539812A - Aircraft wing spar butting joint - Google Patents
Aircraft wing spar butting joint Download PDFInfo
- Publication number
- CN105539812A CN105539812A CN201410589054.6A CN201410589054A CN105539812A CN 105539812 A CN105539812 A CN 105539812A CN 201410589054 A CN201410589054 A CN 201410589054A CN 105539812 A CN105539812 A CN 105539812A
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- China
- Prior art keywords
- edge strip
- spar
- web
- lower edge
- wing spar
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Abstract
The present invention discloses an aircraft wing spar butting joint, which comprises an upper edge strip (1), a lower edge strip (2), a support column (3) and web plates (4), wherein the web plate (4) is positioned between the upper edge strip (1) and the lower edge strip (2), and is provided with the support column (3), and during the installation, the web plates (4) on both sides of the support column (3) are respectively connected to the wing spar web plates on the corresponding sides, the upper edge strip (1) is connected to the corresponding wing spar upper edge strip and the upper wall plate, the lower edge strip (2) is connected to the corresponding wing spar lower edge strip and the lower wall plate, and the support column is connected to the wing rib so as to achieve the wing butting. According to the present invention, the aircraft wing spar butting joint has the simple structure, and effectively solve the problems of the more number and the complex assembly relationship of the existing combined connection part.
Description
Technical field
The invention belongs to field of airplane structure, particularly a kind of wing spar abutment joint.
Background technology
Large aircraft wing spar all can be divided into some sections under normal circumstances, spar segmentation place needs to dock, and spar segmentation place also will consider the connection of the parts such as rib, wallboard, and Boeing, Air Passenger all adopt conventional compound type to connect, number of parts is many, and Standard is complicated.
Summary of the invention
The technical problem to be solved in the present invention is, design a kind of wing spar abutment joint, the entirety docking of spar segmentation can be realized, while completing spar docking, realize that spar is connected with wallboard, spar is connected with rib, avoid part too much and the complicated problem of assembling.
For the technical solution of the present invention that solves the problem provides a kind of wing spar abutment joint, comprise edge strip, lower edge strip, pillar, web, described web is between upper edge strip and lower edge strip, web there is pillar, the two ends up and down of described pillar are connected with described upper edge strip, lower edge strip respectively, the web of described pillar both sides is connected with the spar web of its respective side respectively, described upper edge strip connects with edge strip on corresponding spar and wainscot, described lower edge strip connects with edge strip under corresponding spar and lower wall panels, and described pillar is connected with rib.
Preferably, described web narrows from upper and lower side gradually to centre, and outer rim is in depression shape.
Preferably, the thickness of described upper edge strip and lower edge strip is thickening gradually from two lateral stay directions.
A kind of wing spar abutment joint structure that technical solution of the present invention provides is simple, and it is many that actv. solves existing compound type union piece quantity, the problem of assembly relation complexity.
Accompanying drawing explanation
Below in conjunction with accompanying drawing, specific embodiments of the present invention are further described in detail, wherein:
Fig. 1 is a kind of wing spar abutment joint schematic diagram;
Fig. 2 is spar docking schematic diagram.
Detailed description of the invention
The embodiment of the present invention provides a kind of wing spar abutment joint as shown in Figure 1, comprises edge strip 1, lower edge strip 2, pillar 3, web 4.The web 4 of described a kind of wing spar abutment joint, between upper edge strip 1 and lower edge strip 2, web 4 has pillar 3, and the two ends up and down of pillar 3 are connected with described upper edge strip 1, lower edge strip 2 respectively.Web 4 narrows from upper and lower side gradually to centre, and outer rim is in depression shape.The thickness of upper edge strip 1 and lower edge strip 2 is thickening gradually from two lateral stay directions.
As shown in Figure 2, described a kind of wing spar abutment joint 5 can realize the entirety docking of inner segment spar 6 and outer section of spar 7, realizes the connection of spar and wainscot 8, the connection of spar and lower wall panels 9 and spar and be connected with rib 10 while completing spar docking.
The web 4 of described pillar 3 both sides is connected with the spar web of its respective side respectively, and described upper edge strip 1 connects with edge strip on corresponding spar and wainscot, and described lower edge strip 2 connects with edge strip under corresponding spar and lower wall panels, and described pillar is connected with rib.
Claims (3)
1. a wing spar abutment joint, it is characterized in that, comprise edge strip (1), lower edge strip (2), pillar (3), web (4), described web (4) is positioned between edge strip (1) and lower edge strip (2), web (4) there is pillar (3), the two ends up and down of described pillar (3) respectively with described upper edge strip (1), lower edge strip (2) connects, the web (4) of described pillar (3) both sides is connected with the spar web of its respective side respectively, described upper edge strip (1) connects with edge strip on corresponding spar and wainscot, described lower edge strip (2) connects with edge strip under corresponding spar and lower wall panels, described pillar is connected with rib.
2. abutment joint according to claim 1, is characterized in that, described web (4) narrows from upper and lower side gradually to centre, and outer rim is in depression shape.
3. abutment joint according to claim 2, is characterized in that, the thickness of described upper edge strip (1) and lower edge strip (2) is thickening gradually from two lateral stay directions.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410589054.6A CN105539812A (en) | 2014-10-28 | 2014-10-28 | Aircraft wing spar butting joint |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410589054.6A CN105539812A (en) | 2014-10-28 | 2014-10-28 | Aircraft wing spar butting joint |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN105539812A true CN105539812A (en) | 2016-05-04 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410589054.6A Pending CN105539812A (en) | 2014-10-28 | 2014-10-28 | Aircraft wing spar butting joint |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN105539812A (en) |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107416183A (en) * | 2016-09-06 | 2017-12-01 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | A kind of spar attachment structure of aircraft wing |
| CN109305328A (en) * | 2018-11-12 | 2019-02-05 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | A kind of wing box and aircraft |
| CN109484624A (en) * | 2018-11-29 | 2019-03-19 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | A kind of technique for aircraft composite wing spar and wing root area connection structure |
| CN109520860A (en) * | 2018-12-04 | 2019-03-26 | 中国航空工业集团公司西安飞机设计研究所 | A kind of spar docking testpieces design method |
| CN110091978A (en) * | 2019-04-12 | 2019-08-06 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | A kind of stringer banjo fixing butt jointing, wing upper wall board connecting structure and aircraft |
| CN110979634A (en) * | 2019-11-20 | 2020-04-10 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | Auxiliary supporting structure, main connection area wing spar and wing |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
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| US20040056152A1 (en) * | 2002-06-24 | 2004-03-25 | Daiya Yamashita | Wing structure of airplane |
| US20090314892A1 (en) * | 2008-02-14 | 2009-12-24 | Honda Motor Co., Ltd. | Airplane wing structure |
| CN101687539A (en) * | 2007-06-25 | 2010-03-31 | 空中客车运营有限公司 | Method for coupling stiffening profile elements and structural component |
| US20120043422A1 (en) * | 2010-08-17 | 2012-02-23 | The Boeing Company | Multi-Spar Port Box Joint |
| CN103547505A (en) * | 2011-03-28 | 2014-01-29 | 空中客车营运有限公司 | Joint |
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2014
- 2014-10-28 CN CN201410589054.6A patent/CN105539812A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20040056152A1 (en) * | 2002-06-24 | 2004-03-25 | Daiya Yamashita | Wing structure of airplane |
| CN101687539A (en) * | 2007-06-25 | 2010-03-31 | 空中客车运营有限公司 | Method for coupling stiffening profile elements and structural component |
| US20090314892A1 (en) * | 2008-02-14 | 2009-12-24 | Honda Motor Co., Ltd. | Airplane wing structure |
| US20120043422A1 (en) * | 2010-08-17 | 2012-02-23 | The Boeing Company | Multi-Spar Port Box Joint |
| CN103547505A (en) * | 2011-03-28 | 2014-01-29 | 空中客车营运有限公司 | Joint |
Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107416183A (en) * | 2016-09-06 | 2017-12-01 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | A kind of spar attachment structure of aircraft wing |
| CN107416183B (en) * | 2016-09-06 | 2024-01-09 | 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 connection structure of aircraft wing |
| CN109305328A (en) * | 2018-11-12 | 2019-02-05 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | A kind of wing box and aircraft |
| CN109305328B (en) * | 2018-11-12 | 2024-01-16 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | Wing box and aircraft |
| CN109484624A (en) * | 2018-11-29 | 2019-03-19 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | A kind of technique for aircraft composite wing spar and wing root area connection structure |
| WO2020107532A1 (en) * | 2018-11-29 | 2020-06-04 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | Connection structure for connecting composite-material aircraft wing spar to wing root region |
| CN109520860A (en) * | 2018-12-04 | 2019-03-26 | 中国航空工业集团公司西安飞机设计研究所 | A kind of spar docking testpieces design method |
| CN109520860B (en) * | 2018-12-04 | 2021-07-16 | 中国航空工业集团公司西安飞机设计研究所 | Spar butt joint test piece design method |
| CN110091978A (en) * | 2019-04-12 | 2019-08-06 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | A kind of stringer banjo fixing butt jointing, wing upper wall board connecting structure and aircraft |
| CN110979634A (en) * | 2019-11-20 | 2020-04-10 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | Auxiliary supporting structure, main connection area wing spar and wing |
| CN110979634B (en) * | 2019-11-20 | 2021-08-13 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | Auxiliary supporting structure, main connection area wing spar and wing |
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| PB01 | Publication | ||
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| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20160504 |
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| WD01 | Invention patent application deemed withdrawn after publication |