CN109592002A - A kind of technique for aircraft composite siding interconnection method - Google Patents
A kind of technique for aircraft composite siding interconnection method Download PDFInfo
- Publication number
- CN109592002A CN109592002A CN201811306361.3A CN201811306361A CN109592002A CN 109592002 A CN109592002 A CN 109592002A CN 201811306361 A CN201811306361 A CN 201811306361A CN 109592002 A CN109592002 A CN 109592002A
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- CN
- China
- Prior art keywords
- siding
- wedge
- rib
- edge strip
- docking area
- 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.)
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Connection Of Plates (AREA)
- Finishing Walls (AREA)
Abstract
A kind of technique for aircraft composite siding interconnection method, contain the first adjacent siding, second siding and to rib, contain the first wedge-shaped docking area in the inside of first siding, contain the second wedge-shaped docking area in the inside of second siding, described is respectively corresponding wedge structure to the edge strip of rib web two sides, the wedge-shaped docking area of edge strip corresponding first on the left of web, the wedge-shaped docking area of edge strip corresponding second on the right side of web, rib will be placed between the first siding and the second siding, the left side edge strip and the first wedge-shaped docking area lamination of rib are fixed, the right side edge strip and the second wedge-shaped docking area lamination of rib are fixed.
Description
Technical field
This application involves airplane design technical field, specifically a kind of technique for aircraft composite siding interconnection method is suitable for
Technique for aircraft composite central wing is docked with outer wing.
Background technique
The siding of existing aircraft central wing and outer wing mostly uses composite material to make greatly, and in the siding of central wing and outer wing
When docking, in order to guarantee that the intensity of docking, the prior art are that docking band plate and docking costal margin item is used to reinforce admittedly on the outside of siding
It is fixed, and aircraft configuration is not allow for the prominent shape of structural member in design, the prominent theoretical shape of the docking band plate of the prior art is right
Tape splicing plate has apparent influence to aircraft configuration.
Summary of the invention
When the purpose of the present invention is docked mainly for technique for aircraft composite outer wing and central wing, when shape requirement is relatively high,
The structure for being not allow for prominent shape exists, and provides a kind of efficiently feasible technique for aircraft composite siding interconnection method.
A kind of technique for aircraft composite siding interconnection method, it is special containing the first adjacent siding, the second siding and to rib
Sign is that the first wedge-shaped docking area is contained in the inside of first siding, and the second wedge shape docking is contained in the inside of the second siding
Area, the edge strip to rib web two sides are respectively corresponding wedge structure, and corresponding first wedge shape of edge strip is right on the left of web
Area is met, the wedge-shaped docking area of edge strip corresponding second, will be placed in rib between the first siding and the second siding, to rib on the right side of web
Edge strip is fixed with the first wedge-shaped docking area lamination on the left of web, solid to edge strip on the right side of rib web and the second wedge-shaped docking area lamination
It is fixed.
The beneficial effects of the present application are as follows: the docking area that siding is docked in two sides is wedge shape, the corresponding web edge to rib
Item is also wedge shape, and the wedge-shaped docking area lamination of web edge strip and two side wall panels to rib is fixed, to the platform at rib web center
Rank protrusion is embedded between two side wall panels, and smooth transition, improves the aeroperformance of aircraft configuration on the outside of the siding after making docking.
Attached drawing is described in further detail the application with reference to embodiments.
Detailed description of the invention
Fig. 1 is the signal of technique for aircraft composite siding interconnection method.
Fig. 2 is the second wedge-shaped docking area signal of the second siding.
Fig. 3 is the section structure signal for docking costal margin item.
Explanation: 1 first siding, 2 second sidings, 3 docking costal margin items, 4 first wedge-shaped docking areas, 5 second wedges is numbered in figure
Edge strip, 7 webs right side edge strip, 8 steps, 9 central wings docking band plate, 10 outer wings dock band plate on the left of shape docking area, 6 webs.
Specific embodiment
Referring to attached drawing, the technique for aircraft composite siding interconnection method of the application, with the central wing siding and outer wing of certain aircraft
For siding, the first siding 1 is central wing siding, the second siding 2 is outer wing siding, is that a titanium alloy machine adds part to rib 3,
The first wedge-shaped docking area 4 is contained in the inside of first siding 1, and the second wedge-shaped docking area 5 is contained in the inside of the second siding 2,
Described is respectively corresponding wedge structure to the edge strip of 3 web two sides of rib, the corresponding first wedge shape docking of edge strip 6 on the left of web
Area 4, the wedge-shaped docking area 5 of web right side edge strip 7 corresponding second, will be placed in rib 3 between first siding 1 and the second siding 2, right
Edge strip 6 is fixed with the first 4 lamination of wedge-shaped docking area on the left of the web of rib 3, right to edge strip 7 on the right side of rib web and the second wedge shape
5 lamination of area is connect to fix.
In order to make to be fitted close between rib and adjacent siding, there is the platform of protrusion at the center to 3 web edge strip of rib
Rank 8, the height of 8 side of step is suitable with the first wedge-shaped 4 end thickness of docking area, the height and second of 8 other side of step
Wedge-shaped 5 end thickness of docking area is suitable.When docking, the step at the center to rib web edge strip is embedded in the first siding and
Between two sidings, fixation is superimposed with the first wedge-shaped docking area 4 to edge strip on the left of rib web；To edge strip on the right side of rib web and the
The two wedge-shaped superpositions of docking area 5 are fixed.
In order to guarantee dock intensity, the stringer of the central wing siding in the first siding 1 namely embodiment with to rib
Rib by central wing dock band plate 9 be connected and fixed, the stringer of the outer wing siding in the second siding 1 namely embodiment with
Band plate 10 is docked by outer wing to the rib of rib to be connected and fixed.
In implementation, composite material outer wing is splayed with central wing siding in root, forms the first wedge-shaped docking area and the second wedge
Shape docking area, wedge-shaped docking area can directly be formed into also curable post-processing in paving, and wedge-shaped docking area design is by load
It is carefully analyzed with stress.
It is that titanium alloy machine adds part to rib web edge strip, splays to be formed and composite material outer wing and center at the edge strip of two sides
The size of splaying of wing wedge shape docking area cooperation.
Claims (2)
1. a kind of technique for aircraft composite siding interconnection method, containing the first adjacent siding, the second siding and to rib, feature
It is, the first wedge-shaped docking area is contained in the inside of first siding, and the second wedge-shaped docking area is contained in the inside of the second siding,
Described is respectively corresponding wedge structure to the edge strip of rib web two sides, the corresponding first wedge shape docking of edge strip on the left of web
Area, the wedge-shaped docking area of web right side edge strip corresponding second, will be placed in rib between the first siding and the second siding, to rib abdomen
Edge strip is fixed with the first wedge-shaped docking area lamination on the left of plate, solid to edge strip on the right side of rib web and the second wedge-shaped docking area lamination
It is fixed.
2. technique for aircraft composite siding interconnection method as described in claim 1, which is characterized in that at the center of docking costal margin item
There is the step of protrusion, the height of the step side is suitable with the first wedge-shaped docking area end thickness, the height of the step other side
It is suitable with the second wedge-shaped docking area end thickness.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811306361.3A CN109592002B (en) | 2018-11-02 | 2018-11-02 | Butt joint method for composite material wall plates of airplane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811306361.3A CN109592002B (en) | 2018-11-02 | 2018-11-02 | Butt joint method for composite material wall plates of airplane |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN109592002A true CN109592002A (en) | 2019-04-09 |
| CN109592002B CN109592002B (en) | 2022-03-15 |
Family
ID=65957414
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811306361.3A Active CN109592002B (en) | 2018-11-02 | 2018-11-02 | Butt joint method for composite material wall plates of airplane |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109592002B (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110027696A (en) * | 2019-04-30 | 2019-07-19 | 中国商用飞机有限责任公司 | The docking structure of aircraft lower wall panels |
| CN113911314A (en) * | 2021-11-16 | 2022-01-11 | 中国商用飞机有限责任公司 | Keel beam edge strip connecting structure and mounting method thereof |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103803054A (en) * | 2012-11-13 | 2014-05-21 | 波音公司 | Joint for composite wings |
| WO2014081356A1 (en) * | 2012-11-20 | 2014-05-30 | Saab Ab | An airframe leading edge |
| CN104229119A (en) * | 2013-06-07 | 2014-12-24 | 波音公司 | Lower joints between outboard wing boxes and center wing sections of aircraft wing assemblies |
| CN204297046U (en) * | 2014-11-17 | 2015-04-29 | 中国航空工业集团公司西安飞机设计研究所 | A kind of technique for aircraft composite wallboard root docking structure |
| 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 |
-
2018
- 2018-11-02 CN CN201811306361.3A patent/CN109592002B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103803054A (en) * | 2012-11-13 | 2014-05-21 | 波音公司 | Joint for composite wings |
| WO2014081356A1 (en) * | 2012-11-20 | 2014-05-30 | Saab Ab | An airframe leading edge |
| CN104229119A (en) * | 2013-06-07 | 2014-12-24 | 波音公司 | Lower joints between outboard wing boxes and center wing sections of aircraft wing assemblies |
| CN204297046U (en) * | 2014-11-17 | 2015-04-29 | 中国航空工业集团公司西安飞机设计研究所 | A kind of technique for aircraft composite wallboard root docking structure |
| 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 |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110027696A (en) * | 2019-04-30 | 2019-07-19 | 中国商用飞机有限责任公司 | The docking structure of aircraft lower wall panels |
| CN113911314A (en) * | 2021-11-16 | 2022-01-11 | 中国商用飞机有限责任公司 | Keel beam edge strip connecting structure and mounting method thereof |
| CN113911314B (en) * | 2021-11-16 | 2024-04-16 | 中国商用飞机有限责任公司 | Keel beam edge strip connection structure and installation method thereof |
Also Published As
| Publication number | Publication date |
|---|---|
| CN109592002B (en) | 2022-03-15 |
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