CN219655055U - Anti-falling bolt mechanism - Google Patents
Anti-falling bolt mechanism Download PDFInfo
- Publication number
- CN219655055U CN219655055U CN202320942698.3U CN202320942698U CN219655055U CN 219655055 U CN219655055 U CN 219655055U CN 202320942698 U CN202320942698 U CN 202320942698U CN 219655055 U CN219655055 U CN 219655055U
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- CN
- China
- Prior art keywords
- bolt
- seat bottom
- bottom beam
- installation
- backout
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- 238000009434 installation Methods 0.000 claims abstract description 33
- 125000006850 spacer group Chemical group 0.000 claims description 3
- 230000000149 penetrating effect Effects 0.000 claims 2
- 238000012423 maintenance Methods 0.000 abstract description 3
- 230000002265 prevention Effects 0.000 abstract description 3
- 238000004519 manufacturing process Methods 0.000 abstract description 2
- 239000000463 material Substances 0.000 description 3
- 229910000838 Al alloy Inorganic materials 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 2
- 229910003460 diamond Inorganic materials 0.000 description 2
- 239000010432 diamond Substances 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 239000004677 Nylon Substances 0.000 description 1
- 238000011900 installation process Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 229920001778 nylon Polymers 0.000 description 1
- 239000010935 stainless steel Substances 0.000 description 1
- 229910001220 stainless steel Inorganic materials 0.000 description 1
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Abstract
The utility model provides an anti-falling bolt mechanism, and relates to the technical field of design, manufacture and assembly of aircraft seats. The anti-disengagement bolt mechanism includes: the anti-falling device and the installation bolt are used for locally enlarging the bolt head and the bolt rod of the installation bolt, the installation bolt penetrates through the anti-falling device to be connected with the aircraft preset nut, and the anti-falling device controls the fastening degree of the installation bolt through the tight jacking screw on the cushion column. The utility model has the advantages of simple assembly, convenient operation, high reliability and no need of special tool equipment for assembly and maintenance. The diameters of the bolt head and the bolt rod are locally increased, so that the fastening force of the bolt is ensured not to be lower than the design value. The tight top position of the tight top screw is adjusted, so that the installation bolt can freely rotate and cannot fall out of the mechanism, and the purpose of loss prevention is achieved.
Description
Technical Field
The utility model relates to the technical field of design, manufacture and assembly of aircraft seats, in particular to an anti-falling bolt mechanism.
Background
Some airline seats are portable, quick-disconnect seats. Can be placed in a trunk at ordinary times, and can be assembled on the reserved hole site of the aircraft floor in a short time if needed. In order to prevent the installation bolts from being lost, the tethered bolts can be used, but the tethered ropes have certain obstruction to the disassembly and assembly of the bolts, the time for assembling and disassembling the bolts can be shortened, and the fixing strength of the bolts can be influenced to a certain extent.
Disclosure of Invention
The utility model aims to provide an anti-disengagement bolt mechanism, which improves the fixing reliability of a mounting bolt 1 and shortens the dismounting and mounting time, and comprises: the anti-falling device and the installation bolt 1, the bolt head and the bolt rod of the installation bolt 1 are partially enlarged, the installation bolt 1 passes through the anti-falling device to be connected with the aircraft preset nut 8, and the anti-falling device controls the fastening degree of the installation bolt 1 through the tight top screw 4 on the cushion column 3.
Preferably, the anti-falling device is detachably inserted into the seat bottom beam end 12, one end of the anti-falling device is integrally connected with the seat bottom beam end blanking cover 6, and the other end of the anti-falling device is provided with a first through hole 11 communicated with the aircraft preset nut 8.
Preferably, the cushion column 3 is a hollow sleeve and is embedded into the first through hole 11, a threaded hole 9 is formed in the pipe wall of the cushion column 3, the threaded hole 9 is communicated with the second through hole 10, and a tightening screw 4 is arranged in the threaded hole 9.
Preferably, the bolt rod between the bolt head of the mounting bolt 1 and the threaded hole 9 is enlarged and is attached to the inner wall of the cushion column 3, and the bolt rod at the junction of the seat bottom beam 5 and the aircraft floor 7 is enlarged and is attached to the seat bottom beam 5.
Preferably, a spacer 2 is also provided between the mounting bolt 1 and the seat bottom beam 5.
Preferably, the seat bottom beam 5 is integrally connected to the seat, and the seat bottom beam 5 projects toward the aircraft floor 7.
Preferably, the aircraft floor 7 is pre-grooved and the seat bottom beams 5 are embedded in the grooves.
The beneficial effects of the utility model are as follows: the anti-falling bolt mechanism related by the utility model has the advantages of simple assembly, convenient operation, high reliability and no need of special tool equipment for assembly and maintenance. The diameters of the bolt head and the bolt rod are locally increased, so that the fastening force of the bolt is ensured not to be lower than the design value. The tight top position of the tight top screw is adjusted, so that the installation bolt can freely rotate and cannot fall out of the mechanism, and the purpose of loss prevention is achieved.
Drawings
FIG. 1 is a schematic cross-sectional view of an anti-removal bolt mechanism:
FIG. 2 is a schematic cross-sectional view of a mat post installation:
Detailed Description
The present utility model will be described in further detail with reference to the accompanying drawings, in order to make the objects, technical solutions and advantages of the present utility model more apparent. It should be understood that the detailed description is presented by way of example only and is not intended to limit the utility model.
As shown in fig. 1 and 2, the present embodiment provides an anti-disengagement bolt mechanism, including: the anti-falling device and the installation bolt 1, the bolt head and the bolt rod of the installation bolt 1 are partially enlarged, and in the use process, the installation bolt 1 firstly passes through the anti-falling device and is connected with the aircraft preset nut 8 through threads, and the tightening degree of the installation bolt 1 is controlled through the tightening of the tightening top screw 4 arranged on the cushion column 3. The installation bolt 1 passes through the gasket 2, the anti-falling device, the seat bottom beam 5, the aircraft floor 7 and the aircraft preset nut 8 are connected, and the seat can be detachably installed at the aircraft preset position after the installation bolt 1 is screwed.
In one embodiment, the anti-falling device is in a hollow column shape, is detachably inserted into the seat bottom beam end 12, one end of the anti-falling device is integrally connected with the seat bottom beam end blanking cover 6, the other end of the anti-falling device is provided with a first through hole 11 communicated with the aircraft preset nut 8, and the seat bottom beam end blanking cover 6 is left outside and is attached to the seat bottom beam end 12 during installation. The anti-falling device of integral connection reduces the part setting, prevents that the part from losing, conveniently takes simultaneously when the installation.
In one embodiment, the pad column 3 is a hollow sleeve, and is embedded into the first through hole 11, 2 cross sections of the pad column 3 are parallel to the first through hole 11, the inner wall of the pad column 3 is smooth and circular, and the outer wall is six diamond. The pipe wall of the cushion column 3 is provided with a threaded hole 9, the end plug 6 of the seat bottom beam is provided with a second through hole 10, the threaded hole 9 is communicated with the second through hole 10, a tightening screw 4 is arranged in the threaded hole 9, in the use process, the tightening screw 4 is arranged in the threaded hole 9 in advance and does not enter the inner wall surface of the cushion column 3, after the installation bolt 1 is arranged, the tightening screw 4 is rotated from the outside through the second through hole 10, so that the tightening screw enters the inner wall surface of the cushion column 3 and finally contacts the installation bolt 1, and therefore the tightening degree of the installation bolt 1 is controlled to prevent the tightening screw from falling off.
The smooth inner wall of the cushion column 3 is convenient for the installation bolt 1 to pass through without resistance, and the friction force is increased by the outer wall of the six-diamond cushion column 3, so that the cushion column 3 can not rotate when the installation bolt 1 rotates.
In one embodiment, the bolt head of the installation bolt 1 is enlarged to facilitate screwing the installation bolt 1, and the bolt rod between the bolt head and the threaded hole 9 is partially enlarged, and is attached to the inner wall of the pad column 3 in the installation process to stabilize the installation bolt 1, so that the installation is facilitated. The bolt rod at the junction of the seat bottom beam 5 and the airplane floor 7 is enlarged, and the enlarged part is preferably an annular bulge and is attached to the seat bottom beam 5 so as to stabilize the mounting bolt 1 and facilitate the mounting.
In one embodiment, a spacer 2 is also provided between the mounting bolt 1 and the seat bottom beam 5 to reduce wear of the seat bottom beam 5 by the mounting bolt 1.
In one embodiment, the seat bottom beam 5 is integrally connected with the seat, the seat bottom beam 5 protrudes towards the aircraft floor 7, the protruding length is consistent with the size of the aircraft pre-groove, the seat bottom beam is preferably circular, and the center of the circle is hollow and columnar and used for passing through the installation bolt 1. The number of installation parts is reduced through the integrated connection design, and the circular design is more convenient to butt-joint and install.
In one embodiment, the aircraft floor 7 is pre-grooved and the seat bottom beams 5 are embedded in the grooves.
In one embodiment, the mounting bolts 1 are made of high strength stainless steel, the gaskets 2 are navigation mark standard pieces, the tightening top screws 4 are navigation mark standard pieces, the cushion columns 3 are made of super hard aluminum alloy, the seat bottom beams 5 are made of hard aluminum alloy pipe materials, and the seat bottom beam end heads 6 are made of nylon.
By adopting the technical scheme disclosed by the utility model, the following beneficial effects are obtained:
the anti-falling bolt mechanism related by the utility model has the advantages of simple assembly, convenient operation, high reliability and no need of special tool equipment for assembly and maintenance. The diameters of the bolt head and the bolt rod are locally increased, so that the fastening force of the bolt is ensured not to be lower than the design value. The tight top position of the tight top screw 4 is adjusted, so that the installation bolt can freely rotate and can not fall out of the mechanism, and the purpose of loss prevention is realized.
In the description of the present specification, the descriptions of the terms "one embodiment," "an implementation," "an example," "a particular example," or "some examples," etc., mean that a particular feature, structure, material, or characteristic described in connection with the embodiment or example is included in at least one embodiment or example of the present utility model. In this specification, schematic representations of the above terms are not necessarily directed to the same embodiment or example. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples. Further, one skilled in the art can engage and combine the different embodiments or examples described in this specification.
While embodiments of the present utility model have been shown and described above, it will be understood that the above embodiments are illustrative and not to be construed as limiting the utility model, and that variations, modifications, alternatives and variations may be made to the above embodiments by one of ordinary skill in the art within the scope of the utility model.
Claims (7)
1. An anti-backout bolt mechanism, comprising: the anti-falling device is connected with an aircraft preset nut (8) by penetrating through the anti-falling device, and the tightening degree of the installation bolt (1) is controlled by a tightening top screw (4) on a cushion column (3).
2. An anti-backout bolt mechanism according to claim 1, wherein the anti-backout means is detachably inserted into a seat bottom beam end (12), one end of which is integrally connected with a seat bottom beam end blanking cover (6), and the other end of which is provided with a first through hole (11) penetrating the aircraft pre-set nut (8).
3. An anti-falling bolt mechanism according to claim 2, wherein the pad column (3) is a hollow sleeve, the pad column is embedded into the first through hole (11), a threaded hole (9) is formed in the pipe wall of the pad column (3), the threaded hole (9) is communicated with the second through hole (10), and a tightening screw (4) is arranged in the threaded hole (9).
4. An anti-backout bolt mechanism according to claim 3, wherein the bolt shaft between the bolt head of the mounting bolt (1) and the threaded hole (9) is enlarged and is attached to the inner wall of the cushion column (3), and the bolt shaft at the junction of the seat bottom beam (5) and the aircraft floor (7) is enlarged and is attached to the seat bottom beam (5).
5. An anti-backout bolt mechanism according to claim 4, wherein a spacer (2) is further provided between the mounting bolt (1) and the seat bottom beam (5).
6. An anti-backout bolt mechanism according to claim 4, wherein the seat bottom beam (5) is integrally connected to the seat, the seat bottom beam (5) protruding in the direction of the aircraft floor (7).
7. An anti-backout bolt mechanism according to claim 4, wherein the aircraft floor (7) is pre-grooved and the seat bottom beams (5) are embedded in grooves.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202320942698.3U CN219655055U (en) | 2023-04-24 | 2023-04-24 | Anti-falling bolt mechanism |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202320942698.3U CN219655055U (en) | 2023-04-24 | 2023-04-24 | Anti-falling bolt mechanism |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN219655055U true CN219655055U (en) | 2023-09-08 |
Family
ID=87860453
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202320942698.3U Active CN219655055U (en) | 2023-04-24 | 2023-04-24 | Anti-falling bolt mechanism |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN219655055U (en) |
-
2023
- 2023-04-24 CN CN202320942698.3U patent/CN219655055U/en active Active
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| Date | Code | Title | Description |
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| GR01 | Patent grant | ||
| GR01 | Patent grant |