CN217100444U - Installation structure of interior trimming panel of airplane - Google Patents
Installation structure of interior trimming panel of airplane Download PDFInfo
- Publication number
- CN217100444U CN217100444U CN202122438265.8U CN202122438265U CN217100444U CN 217100444 U CN217100444 U CN 217100444U CN 202122438265 U CN202122438265 U CN 202122438265U CN 217100444 U CN217100444 U CN 217100444U
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- Prior art keywords
- groove
- joint
- connecting block
- block
- clamping
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- 238000009434 installation Methods 0.000 title claims description 13
- 238000009966 trimming Methods 0.000 title description 2
- 230000005484 gravity Effects 0.000 claims abstract description 10
- 210000002421 cell wall Anatomy 0.000 abstract description 16
- 238000000034 method Methods 0.000 abstract description 6
- 230000009286 beneficial effect Effects 0.000 abstract 1
- 238000000926 separation method Methods 0.000 description 2
- 238000003780 insertion Methods 0.000 description 1
- 230000037431 insertion Effects 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 230000000704 physical effect Effects 0.000 description 1
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Abstract
The utility model discloses a plaque mounting structure in aircraft, fixing base and plate body including mutually supporting, the spread groove has been seted up to the one end of fixing base, the joint groove has all been seted up to the top cell wall and the bottom cell wall of spread groove, the one end fixed mounting of plate body has the connecting block, a side swing joint through pivot and joint part is all passed through to the top and the bottom of connecting block both sides, joint part and joint groove joint cooperation, one side that the connecting block was kept away from to the joint part is provided with the regulation hole. The beneficial effects are that: the clamping component at the upper end of the connecting block rotates under the action of self gravity, so that the stop block is arranged at the upper end of the wedge-shaped block; when the joint part of connecting block lower extreme is installed, manual regulation rotates the stopper that ends on it to the below, and the in-process that the notch that the connecting block passes through the spread groove was pegged graft can contact with the inclined plane on the stopper that ends, and until the joint inslot, the stopper that ends rotates realizes the joint in stopper and joint groove, simple to operate is swift.
Description
Technical Field
The utility model relates to a plaque technical field in the aircraft especially relates to a plaque mounting structure in aircraft.
Background
Plaque in the aircraft, the plate body of decorating inside the aircraft as the name implies to increase the inside aesthetic property of aircraft, it all adopts special material to make, has good physical properties, carries out the in-process of installing to plaque in the aircraft, needs a plurality of staff cooperation work, just can accomplish its installation, is not convenient for operate it. And general aircraft interior plaque all fixes it through the screw at the in-process of installation, and is comparatively loaded down with trivial details during the operation.
SUMMERY OF THE UTILITY MODEL
The utility model aims at providing an installation structure of an interior trim panel of an airplane, a clamping part at the upper end of a connecting block rotates under the action of self gravity, so that a stop block is arranged at the upper end of a wedge-shaped block; when the joint part of connecting block lower extreme was installed, manual regulation rotated the stopper that ends on it to the below, and the in-process that the notch that the connecting block passed through the spread groove was pegged graft can contact with the inclined plane on the stopper that ends, and until the joint inslot, it rotates to end the stopper, realizes the joint in stopper and joint groove, installation, dismantlement convenient and fast.
The technical scheme of the utility model is realized like this:
the utility model provides an plaque mounting structure in aircraft, includes mutually supported fixing base and plate body, the spread groove has been seted up to the one end of fixing base, the joint groove has all been seted up to the top cell wall and the bottom cell wall of spread groove, the one end fixed mounting of plate body has the connecting block, a side swing joint of pivot and joint part is all passed through to the top and the bottom of connecting block both sides, joint part and joint groove joint cooperation, one side that the connecting block was kept away from to the joint part is provided with the regulation hole, the fixing base surface be provided with adjust the pole and with adjust pole matched with bar groove, adjust the pole run through in the fixing base surface extend to the spread groove with the cooperation of pegging graft of the regulation hole on the joint part to drive joint part at the spread groove internal rotation.
Further, the joint part includes the wedge, a side of wedge is connected with the connecting block rotation through the pivot, the opposite side of wedge is provided with the regulation hole, be equipped with the backstop on the wedge to only shelves the cooperation through the joint groove of backstop and spread groove top cell wall and bottom cell wall.
Furthermore, the shape of the connecting groove and the shape of the connecting block are both strip-shaped structures, and the connecting groove is matched with the connecting block in an inserting mode.
Furthermore, a fixing plate is arranged at one end, away from the plate body, of the fixing seat, and mounting holes are symmetrically formed in the fixing plate.
Further, install the focus of installing joint part in spread groove top cell wall department in its bottom through the pivot, install the focus of joint part in spread groove bottom cell wall department on its top through the pivot.
The utility model has the advantages that: the plate body is arranged on the fixed seat, the center of gravity of the clamping part is arranged at the bottom end of the groove wall at the top end of the connecting groove through the rotating shaft, and the clamping part rotates under the action of self gravity to enable the stop block to be arranged at the upper end of the wedge-shaped block; the center of gravity of the clamping part arranged at the groove wall of the bottom end of the connecting groove is arranged at the bottom end of the connecting groove through the rotating shaft, when the clamping part is arranged, the stop block on the clamping part is manually adjusted to rotate to the lower part, and then the connecting block on the plate body is inserted into the connecting groove to be matched in an inserting mode. The in-process that the connecting block passes through the notch grafting of spread groove can contact with the inclined plane on ending the stopper, and until the joint inslot, end the stopper and rotate, realize ending the joint in stopper and joint groove, simple to operate is swift.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required to be used in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to these drawings without creative efforts.
FIG. 1 is a schematic view of an aircraft interior trim panel mounting arrangement;
FIG. 2 is a schematic structural view of an installation structure of an interior trim panel of an aircraft;
FIG. 3 is a schematic view of a plate body with a clamping member in one state;
fig. 4 is a schematic view of the plate body in another state;
fig. 5 is a schematic structural view of the fixing base.
Detailed Description
The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only some embodiments of the present invention, not all embodiments.
In the description of the present invention, it is to be understood that the terms "upper", "lower", "front", "rear", "left", "right", "top", "bottom", "inner", "outer", and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, and are only for convenience of description and simplicity of description, and do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore, should not be construed as limiting the present invention.
According to the utility model discloses an embodiment provides a plaque mounting structure in aircraft.
Referring to fig. 1 to 5, the installation structure of the interior trim panel of the aircraft according to the embodiment of the present invention includes a fixing base 1 and a panel body 2 which are matched with each other, one end of the fixed seat 1 is provided with a connecting groove 3, the top groove wall and the bottom groove wall of the connecting groove 3 are both provided with a clamping groove 4, one end of the plate body 2 is fixedly provided with a connecting block 5, the top end and the bottom end of the two sides of the connecting block 5 are movably connected with one side surface of a clamping part 6 through a rotating shaft, the clamping component 6 is matched with the clamping groove 4 in a clamping way, one side of the clamping component 6, which is far away from the connecting block 5, is provided with an adjusting hole 7, the surface of the fixed seat 1 is provided with an adjusting rod 8 and a strip-shaped groove 11 matched with the adjusting rod 8, the adjusting rod 8 penetrates through the surface of the fixing seat 1 and extends into the connecting groove 3 to be matched with the adjusting hole 7 in the clamping part 6 in an inserting mode, and the clamping part 6 is driven to rotate in the connecting groove 3.
Further, joint part 6 includes wedge 61, a side of wedge 61 is rotated with connecting block 5 through the pivot and is connected, the opposite side of wedge 61 is provided with adjustment hole 7, be equipped with on the wedge 61 and end the dog 62 to end the cooperation through the dog 62 and the joint groove 4 of 3 top cell walls of spread groove and bottom cell wall.
Further, the shape of connecting groove 3 and the shape of connecting block 5 are bar structures, connecting groove 3 and connecting block 5 are in inserting fit.
Furthermore, a fixing plate 9 is arranged at one end, away from the plate body 2, of the fixing seat 1, and mounting holes 10 are symmetrically formed in the fixing plate 9.
Further, install the focus of installing joint part 6 in 3 top cell walls of spread groove through the pivot in its bottom, install the focus of installing joint part 6 in 3 bottom cell walls of spread groove through the pivot on its top.
During specific implementation, the plate body 2 is arranged on the fixed seat 1, the center of gravity of the clamping part 6 at the groove wall at the top end of the connecting groove 3 is arranged at the bottom end of the connecting groove through the rotating shaft, and the clamping part 6 rotates under the action of self gravity, so that the stop block 62 is arranged at the upper end of the wedge-shaped block 61; install the centre of gravity of joint part 6 in the bottom cell wall department of spread groove 3 through the pivot at its bottom, when the installation, manual regulation rotates the stopper 62 on it to the below, inserts the cooperation of pegging graft in the spread groove 3 with connecting block 5 on the plate body 2 again. In the process that the connecting block 5 is inserted through the notch of the connecting groove 3, the connecting block can be contacted with the inclined surface on the stop block 62 until the clamping groove 4, and the stop block 62 rotates to realize the clamping connection of the stop block 62 and the clamping groove 4.
As shown in fig. 1 and 4, when the plate body 2 is detached from the fixing base 1, the adjusting rod 8 is inserted through the insertion hole of the fixing base 1, so that the adjusting rod 8 is inserted into the adjusting hole 7 of the wedge block 61 and is engaged with the adjusting hole, and the wedge block 61 is driven to rotate. Install at 3 top cell walls of spread groove department joint part 6 through adjusting pole 8 rotation earlier, make it rotate and realize ending stopper 62 and 4 separations in joint groove, rotate through adjusting pole 8 again and install at 3 bottom cell walls of spread groove department joint part 6, make it rotate and realize ending stopper 62 and the 3 bottom cell walls of spread groove on joint groove 4 separations, at last with plate body 2 follow fixing base 1 extract can, adjust pole 8 can be along the 11 roll-offs in bar groove.
The above, only be the concrete implementation of the preferred embodiment of the present invention, but the protection scope of the present invention is not limited thereto, and any person skilled in the art is in the technical scope of the present invention, according to the technical solution of the present invention and the utility model, the concept of which is equivalent to replace or change, should be covered within the protection scope of the present invention.
Claims (5)
1. The installation structure of the aircraft interior trim panel is characterized by comprising a fixing seat (1) and a panel body (2) which are matched with each other, wherein a connecting groove (3) is formed in one end of the fixing seat (1), clamping grooves (4) are formed in the top groove wall and the bottom groove wall of the connecting groove (3), a connecting block (5) is fixedly installed at one end of the panel body (2), the top end and the bottom end of the two sides of the connecting block (5) are movably connected with one side face of a clamping part (6) through rotating shafts, the clamping part (6) is in clamping fit with the clamping grooves (4), an adjusting hole (7) is formed in one side, away from the connecting block (5), of the clamping part (6), the surface of the fixing seat (1) is provided with an adjusting rod (8) and a strip-shaped groove (11) matched with the adjusting rod (8), the adjusting rod (8) penetrates through the surface of the fixing seat (1) and extends into the connecting groove (3) to be in inserting fit with the adjusting hole (7) on the clamping part (6), and drives the clamping part (6) to rotate in the connecting groove (3).
2. The aircraft interior trim panel mounting structure of claim 1, wherein the clamping component (6) comprises a wedge-shaped block (61), one side of the wedge-shaped block (61) is rotatably connected with the connecting block (5) through a rotating shaft, the other side of the wedge-shaped block (61) is provided with an adjusting hole (7), the wedge-shaped block (61) is provided with a stop block (62), and the stop block (62) is matched with the clamping groove (4) of the top groove wall and the bottom groove wall of the connecting groove (3) in a stop manner.
3. The mounting structure of the aircraft interior trim panel according to claim 1, wherein the shape of the connecting groove (3) and the shape of the connecting block (5) are both strip-shaped structures, and the connecting groove (3) is in plug fit with the connecting block (5).
4. The installation structure of the interior trim panel of the aircraft according to claim 1, wherein a fixing plate (9) is disposed at one end of the fixing seat (1) far away from the panel body (2), and the fixing plate (9) is symmetrically provided with installation holes (10).
5. An installation structure of an aircraft interior trim panel according to claim 1, characterized in that the center of gravity of the catching member (6) installed at the groove wall of the top end of the connecting groove (3) is at the bottom end thereof by a rotating shaft, and the center of gravity of the catching member (6) installed at the groove wall of the bottom end of the connecting groove (3) is at the top end thereof by a rotating shaft.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202122438265.8U CN217100444U (en) | 2021-10-11 | 2021-10-11 | Installation structure of interior trimming panel of airplane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202122438265.8U CN217100444U (en) | 2021-10-11 | 2021-10-11 | Installation structure of interior trimming panel of airplane |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN217100444U true CN217100444U (en) | 2022-08-02 |
Family
ID=82575977
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202122438265.8U Active CN217100444U (en) | 2021-10-11 | 2021-10-11 | Installation structure of interior trimming panel of airplane |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN217100444U (en) |
-
2021
- 2021-10-11 CN CN202122438265.8U patent/CN217100444U/en active Active
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CP03 | Change of name, title or address | ||
| CP03 | Change of name, title or address |
Address after: Room 303, Building 1, No. 3 Diamond Road, Anhui Xinwu Economic Development Zone, Wanzhou District, Wuhu City, Anhui Province, 241100 Patentee after: Anhui Hongmeng Machinery Technology Co.,Ltd. Address before: 230000 workshop A4 of gongtou, Huashan Industrial Park, Chaohu Economic Development Zone, Hefei, Anhui Province Patentee before: HEFEI LIANHE AIRPLANE TECHNOLOGY Co.,Ltd. |