CN204297047U - A kind of interior trim flange bridging arrangement - Google Patents
A kind of interior trim flange bridging arrangement Download PDFInfo
- Publication number
- CN204297047U CN204297047U CN201420696848.8U CN201420696848U CN204297047U CN 204297047 U CN204297047 U CN 204297047U CN 201420696848 U CN201420696848 U CN 201420696848U CN 204297047 U CN204297047 U CN 204297047U
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- trim panel
- panel
- trim
- turnup structure
- honeycomb core
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Abstract
The utility model relates to a kind of for aircraft interior trim flange bridging arrangement.A kind of interior trim flange bridging arrangement is provided, comprise: the first trim panel 1 and the second trim panel 2, described first trim panel 1 and the second trim panel 2 are all by exterior skin 3, honeycomb core 4 and inside panel 5 form, honeycomb core 4 edge carries out sharping process, honeycomb core 4 is not laid at the first trim panel 1 and the second trim panel 2 edge, only fitted by exterior skin 3 and inside panel 5 and form turnup structure, wherein, the turnup structure of the first trim panel 1 is zigzag, the turnup structure of the second trim panel 2 is L shape, the turnup structure of the second trim panel 2 is overlapped on outside the turnup structure of the first trim panel 1, all there is the knuckle of large cambered surface at first trim panel 1 and the second trim panel 2 flange place.
Description
Technical field
The utility model relates to a kind of for aircraft interior trim flange bridging arrangement.
Background technology
At present, the docking connected mode that conventional airplane trim panel adopts easily produces jump, and trim panel edge is mostly right angle, affects the aesthetic property of whole structure.Existing docking mode lacks adjustment surplus in addition, and alignment error is large, not easily regulates.
Utility model content
Utility model object
A kind of interior trim flange bridging arrangement is provided, effectively can reduces the error of installing and producing in jump and installation process.
Technical scheme
A kind of interior trim flange bridging arrangement, comprising:
First trim panel 1 and the second trim panel 2,
Described first trim panel 1 and the second trim panel 2 are all made up of exterior skin 3, honeycomb core 4 and inside panel 5, honeycomb core 4 edge carries out sharping process, honeycomb core 4 is not laid at the first trim panel 1 and the second trim panel 2 edge, only fitted by exterior skin 3 and inside panel 5 and form turnup structure, wherein, the turnup structure of the first trim panel 1 is zigzag, the turnup structure of the second trim panel 2 is L shape, the turnup structure of the second trim panel 2 is overlapped on outside the turnup structure of the first trim panel 1, and all there is the knuckle of large cambered surface at the first trim panel 1 and the second trim panel 2 flange place.
Beneficial effect
The utility model devises a kind of flange bridging arrangement of aircraft trim panel, its structure is relatively simple, and all there is the knuckle of large cambered surface at flange place, and installation effect is attractive in appearance, flange lap-joint has certain regulatory function, effectively can reduce the error of installing and producing in jump and installation process.
Accompanying drawing explanation
Fig. 1 trim panel flange bridging arrangement schematic diagram.
Fig. 2 trim panel flange bridging arrangement sectional view.
Detailed description of the invention
Trim panel flange bridging arrangement as shown in Figure 1 and Figure 2 comprises: the first trim panel 1 and the second trim panel 2; Described first trim panel 1 and the second trim panel 2 are all made up of exterior skin 3, honeycomb core 4 and inside panel 5, honeycomb core 4 edge carries out sharping process, honeycomb core 4 is not laid at the first trim panel 1 and the second trim panel 2 edge, only fitted by exterior skin 3 and inside panel 5 and form turnup structure, wherein, the turnup structure of the first trim panel 1 is zigzag, the turnup structure of the second trim panel 2 is L shape, the turnup structure of the second trim panel 2 is overlapped on outside the turnup structure of the first trim panel 1, and all there is the knuckle of large cambered surface at the first trim panel 1 and the second trim panel 2 flange place.
The utility model flange lap-joint has certain regulatory function, and the first trim panel 1 and the second trim panel 2 horizontal direction can produce relative displacement, effectively can reduce the error of installing and producing in jump and installation process.
Above-mentioned embodiment is only for illustrating technical conceive of the present utility model and feature; object is person skilled in the art can be understood content of the present utility model and be implemented; protection domain of the present utility model can not be limited with this; all equivalences done according to the utility model Spirit Essence change or modify, and all should be encompassed in protection domain of the present utility model.
Claims (1)
1. an interior trim flange bridging arrangement, is characterized in that, comprising:
First trim panel (1) and the second trim panel (2),
Described first trim panel (1) and the second trim panel (2) are all by exterior skin (3), honeycomb core (4) and inside panel (5) composition, honeycomb core (4) edge carries out sharping process, honeycomb core (4) is not laid at the first trim panel (1) and the second trim panel (2) edge, only fitted by exterior skin (3) and inside panel (5) and form turnup structure, wherein, the turnup structure of the first trim panel (1) is zigzag, the turnup structure of the second trim panel (2) is L shape, the turnup structure of the second trim panel (2) is overlapped on outside the turnup structure of the first trim panel (1), all there is the knuckle of large cambered surface at first trim panel (1) and the second trim panel (2) flange place.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420696848.8U CN204297047U (en) | 2014-11-19 | 2014-11-19 | A kind of interior trim flange bridging arrangement |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420696848.8U CN204297047U (en) | 2014-11-19 | 2014-11-19 | A kind of interior trim flange bridging arrangement |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN204297047U true CN204297047U (en) | 2015-04-29 |
Family
ID=53102610
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201420696848.8U Active CN204297047U (en) | 2014-11-19 | 2014-11-19 | A kind of interior trim flange bridging arrangement |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN204297047U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104843168A (en) * | 2015-05-05 | 2015-08-19 | 江苏逸帆航空科技有限公司 | Rapid-disassembly rapid-assembly structure for aircraft interior decoration |
| CN110145678A (en) * | 2019-05-13 | 2019-08-20 | 湖北三江航天红阳机电有限公司 | A kind of compound shell pieces of large scale complexity honeycomb sandwich construction and integral forming method |
| WO2021109894A1 (en) * | 2019-12-03 | 2021-06-10 | 向杰 | Honeycomb array multi-rotor composite part, rack and air vehicle |
-
2014
- 2014-11-19 CN CN201420696848.8U patent/CN204297047U/en active Active
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104843168A (en) * | 2015-05-05 | 2015-08-19 | 江苏逸帆航空科技有限公司 | Rapid-disassembly rapid-assembly structure for aircraft interior decoration |
| CN110145678A (en) * | 2019-05-13 | 2019-08-20 | 湖北三江航天红阳机电有限公司 | A kind of compound shell pieces of large scale complexity honeycomb sandwich construction and integral forming method |
| CN110145678B (en) * | 2019-05-13 | 2022-06-17 | 湖北三江航天红阳机电有限公司 | Large-size complex honeycomb sandwich structure composite shell sheet and integral forming method |
| WO2021109894A1 (en) * | 2019-12-03 | 2021-06-10 | 向杰 | Honeycomb array multi-rotor composite part, rack and air vehicle |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant |