CN105620753A - Airplane interior trim fixing method - Google Patents
Airplane interior trim fixing method Download PDFInfo
- Publication number
- CN105620753A CN105620753A CN201410589055.0A CN201410589055A CN105620753A CN 105620753 A CN105620753 A CN 105620753A CN 201410589055 A CN201410589055 A CN 201410589055A CN 105620753 A CN105620753 A CN 105620753A
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- CN
- China
- Prior art keywords
- interior trim
- support
- fixing
- airplane
- fixed
- 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.)
- Pending
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- Connection Of Plates (AREA)
- Vehicle Interior And Exterior Ornaments, Soundproofing, And Insulation (AREA)
Abstract
The invention belongs to the technical field of airplane interior trim fixing and particularly relates to an airplane interior trim fixing method. The method is characterized by mainly including the steps that the angle of one edge of an n-shaped fixing support (1) is adjusted, so that the edge is attached and fixed to a corresponding interior trim plate (5) on an airplane in a support fixing region (2) through screws and the like; a secondary connecting plane (3) forming a fixed angle with the horizontal plane or a certain plane of the airplane is designed on the fixing support (1); and the secondary connecting plane (3) and a second fixing support (4) are connected, so that the second fixing support (4) is connected to an airplane body structure of the airplane. By the adoption of the airplane interior trim fixing method, when installed, an interior trim can be used as a tool for space positioning, the interior trim molded face is guaranteed, and therefore the positioning process is simplified. Meanwhile, the support fixing regions at the two ends of the fixing support are connected with the two adjacent interior trim plates, and it is guaranteed that the joints of the interior trim plates are aligned.
Description
Technical field
The invention belongs to aircraft interior trim technique for fixing field, particularly to a kind of aircraft interior trim fixing means.
Background technology
When existing aircraft interior trim is installed, it is necessary to connect trim panel and structural framing with support. Due to the complexity of trim panel profile and surrounding structure, support Design is complicated, location difficulty. When trim panel divides fast block to install, it is difficult to ensure that alignment at seam crossing, affects whole structure.
Summary of the invention
It is an object of the present invention to provide a kind of aircraft interior trim fixing means easy and simple to handle.
The technical scheme is that, comprise the steps:
Step one, the angle according to the Adjusting Shape fixed support 1 of interior trim to be fixed, it is ensured that support fixed area 2 is fixing with interior trim laminating, and ensure support 1 has a secondary connect plane 3;
Step 2: the secondary on support 1 connects fixes secondary fixed support 4 in plane 3;
Step 3: the angle according to airframe Yu interior trim to be fixed, adjusts the shape of secondary fixed support 4, is fixed on fuselage by secondary fixed support 4.
The invention has the beneficial effects as follows, a kind of aircraft interior trim fixing means is connected with aircraft fuselage structure by secondary fixed support. Utilize secondary to connect plane and the aircaft configuration plane of reference or machine coordinate is parallel or angled entirely and the shape of fixed support itself, frock can be served as when interior trim is installed and carry out space orientation and ensure interior trim profile, thus simplifying positioning process. Meanwhile, by the support fixed area at fixed support two ends is attached with two pieces of adjacent trim panels respectively, it is ensured that the alignment of trim panel seam crossing.
Accompanying drawing explanation
Fig. 1 is the fixing schematic diagram of the present invention;
In figure, 1 is fixed support, and 2 is support fixed area, connects plane 3 two times, and 4 is secondary fixed support, and 5 is trim panel.
Detailed description of the invention
Fixed support is a few font sheet metal components, while angle can be changed thus be affixed in support fixed area with trim panel plane or curved surface of high curvature and pass through to be spirally connected, riveted joint or other connected modes are attached fixing, a few font tops of fixed support 1 are that secondary connects plane 3, this secondary connects plane 3 can be parallel or angled with the aircaft configuration plane of reference or full machine coordinate, connect at secondary and plane is attached fixing by riveted joint or other connected modes with secondary fixed support 4, Position Design L-shaped according to trim panel 5 and aircraft fuselage structure or the secondary fixed support of other shapes, thus secondary fixed support is fixed on airframe.
Claims (1)
1. an aircraft interior trim fixing means, is characterized by: comprise the steps:
Step one, the angle according to the Adjusting Shape fixed support (1) of interior trim to be fixed, it is ensured that support fixed area (2) is fixing with interior trim laminating, and ensure support (1) has a secondary connect plane (3);
Step 2: the secondary on support (1) connects the upper fixing secondary fixed support (4) of plane (3);
Step 3: the angle according to airframe Yu interior trim to be fixed, adjusts the shape of secondary fixed support (4), is fixed on fuselage by secondary fixed support (4).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410589055.0A CN105620753A (en) | 2014-10-28 | 2014-10-28 | Airplane interior trim fixing method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410589055.0A CN105620753A (en) | 2014-10-28 | 2014-10-28 | Airplane interior trim fixing method |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN105620753A true CN105620753A (en) | 2016-06-01 |
Family
ID=56036182
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410589055.0A Pending CN105620753A (en) | 2014-10-28 | 2014-10-28 | Airplane interior trim fixing method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN105620753A (en) |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0437870A1 (en) * | 1989-12-27 | 1991-07-24 | The Boeing Company | Universal cabin sidewall panel for aircraft |
| US20050211838A1 (en) * | 2004-03-29 | 2005-09-29 | The Boeing Company | Foam composite insulation for aircraft |
| CN203111508U (en) * | 2013-02-01 | 2013-08-07 | 中国航空工业集团公司西安飞机设计研究所 | Plug-in type interior trimming panel connecting structure |
| CN203594657U (en) * | 2013-12-12 | 2014-05-14 | 湖北航宇嘉泰飞机设备有限公司 | Mounting mechanism for interior trim sidewall panel of aircraft |
| CN103963976A (en) * | 2013-02-01 | 2014-08-06 | 中国航空工业集团公司西安飞机设计研究所 | Aircraft interior trim part connecting structure |
-
2014
- 2014-10-28 CN CN201410589055.0A patent/CN105620753A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0437870A1 (en) * | 1989-12-27 | 1991-07-24 | The Boeing Company | Universal cabin sidewall panel for aircraft |
| US20050211838A1 (en) * | 2004-03-29 | 2005-09-29 | The Boeing Company | Foam composite insulation for aircraft |
| CN203111508U (en) * | 2013-02-01 | 2013-08-07 | 中国航空工业集团公司西安飞机设计研究所 | Plug-in type interior trimming panel connecting structure |
| CN103963976A (en) * | 2013-02-01 | 2014-08-06 | 中国航空工业集团公司西安飞机设计研究所 | Aircraft interior trim part connecting structure |
| CN203594657U (en) * | 2013-12-12 | 2014-05-14 | 湖北航宇嘉泰飞机设备有限公司 | Mounting mechanism for interior trim sidewall panel of aircraft |
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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 | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20160601 |
|
| WD01 | Invention patent application deemed withdrawn after publication |