CN216038434U - Aircraft part overhauls lift platform - Google Patents
Aircraft part overhauls lift platform Download PDFInfo
- Publication number
- CN216038434U CN216038434U CN202122462775.9U CN202122462775U CN216038434U CN 216038434 U CN216038434 U CN 216038434U CN 202122462775 U CN202122462775 U CN 202122462775U CN 216038434 U CN216038434 U CN 216038434U
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- Prior art keywords
- lifting
- sliding
- lifting platform
- platform
- supporting table
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- 230000000087 stabilizing effect Effects 0.000 claims abstract description 9
- 239000000758 substrate Substances 0.000 claims abstract description 6
- 230000000149 penetrating effect Effects 0.000 claims description 2
- 230000003028 elevating effect Effects 0.000 abstract description 11
- 238000012423 maintenance Methods 0.000 abstract description 11
- 230000001681 protective effect Effects 0.000 abstract description 2
- 230000000712 assembly Effects 0.000 abstract 1
- 238000000429 assembly Methods 0.000 abstract 1
- 239000003921 oil Substances 0.000 description 8
- 239000010687 lubricating oil Substances 0.000 description 6
- 238000000034 method Methods 0.000 description 5
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000007689 inspection Methods 0.000 description 1
- 210000001503 joint Anatomy 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000000926 separation method Methods 0.000 description 1
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Abstract
The utility model discloses an aircraft part maintenance lifting platform which comprises a substrate, wherein a supporting table is arranged at the top end of the substrate, a lifting table is arranged above the supporting table, a protective pad covers the top end of the lifting table, a mounting plate is connected to the bottom of the supporting table in an inscribed mode, electric push rods are symmetrically mounted at the bottom end of the mounting plate, the output end of each electric push rod is connected with a lifting assembly, the lifting table can be driven by the lifting assemblies to lift along the driving direction of the electric push rods, rod grooves are formed in four corners of the top end of the supporting table, stabilizing rods in sliding fit with the rod grooves are arranged in four corners of the bottom end of the lifting table, and one end, far away from the lifting table, of each stabilizing rod extends into the supporting table and is connected with the sliding assembly. Has the advantages that: the top through the brace table is provided with the elevating platform, and when the aircraft part overhauls, the elevating platform will support fast and overhaul the part, overhauls the department and forms the support protection to the part, security when improving the maintenance.
Description
Technical Field
The utility model relates to the technical field of aircraft part maintenance, in particular to an aircraft part maintenance lifting platform.
Background
At present, in the aircraft maintenance process, some key parts need to be disassembled so as to be convenient for further maintenance, and because the parts have large weight, the parts need to be accepted and supported at the bottoms of the parts in the disassembly process so as to prevent the parts from falling off and damaging in the disassembly process.
Among the prior art, when dismantling aircraft spare part, have lift platform and come the dismantlement of supplementary aircraft, but the use convenience among the current elevating system is not high, is unfavorable for playing the protection to spare part when dismantling.
SUMMERY OF THE UTILITY MODEL
The utility model aims to provide an aircraft part maintenance lifting platform, wherein a lifting platform is arranged at the top of a support platform, and when an aircraft part is maintained, the lifting platform can be quickly abutted against a part maintenance part to support and protect the part maintenance part, so that the maintenance safety is improved.
The technical scheme of the utility model is realized as follows:
the utility model provides an aircraft parts overhauls lift platform, includes the base plate, the top of base plate is provided with a supporting bench, the supporting bench top is provided with the elevating platform, the top of elevating platform covers there is the protection pad, the supporting bench bottom inscription has the mounting panel, electric putter is installed to the bottom symmetry of mounting panel, electric putter's output is connected with lifting unit to accessible lifting unit drives the elevating platform and goes up and down along electric putter's direction of drive, the rod groove has all been seted up in supporting bench top four corners, elevating platform bottom four corners be provided with rod groove sliding fit's firm pole, the one end that the elevating platform was kept away from to firm pole extends to inside the supporting bench to be connected with sliding unit.
Furthermore, the lifting component is detachably matched with the bottom end of the lifting platform.
Furthermore, the lifting assembly comprises a lifting plate connected with the output end of the electric push rod in a penetrating mode through the mounting plate, the lifting plate is fixedly connected with a moving block through a screw, the moving block is arranged on a sliding rail in a sliding mode, the sliding rail is mounted on the L-shaped support through a screw, and the L-shaped support is fixedly mounted on the surface of the mounting plate.
Furthermore, the top of lifter plate is connected through the supporting roof, supporting roof and elevating platform detachable cooperation.
Furthermore, the sliding assembly comprises a guide cylinder fixedly mounted on the side wall of the support table, a sliding block is arranged in the guide cylinder in a sliding mode, and the top end of the sliding block is fixedly connected with the bottom end of the stabilizing rod.
Furthermore, guide blocks are arranged on two sides of the sliding block along the height direction of the sliding block, and guide grooves matched with the guide blocks are formed in the inner wall of the guide cylinder.
Furthermore, an oil groove is formed in the side face of the guide block along the sliding direction of the sliding block, a plurality of balls are arranged in the oil groove, and the balls are in sliding butt joint with the guide groove.
Furthermore, the bottom of guide cylinder is provided with the elasticity post, the cover is equipped with the spring on the elasticity post.
The utility model has the beneficial effects that: the lifting plate connected with the output end of the lifting plate can be driven to lift along the sliding rail in the vertical direction through the electric push rod, the lifting plate can be in contact with and separated from the lifting platform through the supporting top plate on the top end of the lifting plate in the lifting process, the lifting platform can be adjusted to a proper position when the lifting plate is detached as required, the lifting plate is in contact with the bottom of an airplane part, and the sliding assembly is matched to play a role in protecting the detachment of the part. Through the sliding assembly who sets up, the oil groove has been seted up in the side slip direction of guide block, injects lubricating oil back in the spout, and partial lubricating oil can be stored in the oil groove, and has sufficient lubricating oil between the contact surface of guide block and guide way, has reduced the friction between guide block and the guide way, improve equipment's life.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings needed 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 it is obvious for those skilled in the art to obtain other drawings without creative efforts.
FIG. 1 is a schematic view of an aircraft parts inspection lift platform;
FIG. 2 is a schematic structural view of the sliding assembly;
fig. 3 is a top view of the slider.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the 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, are merely for convenience in describing the present invention and simplifying the 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 thus, should not be construed as limiting the present invention.
According to an embodiment of the utility model, an aircraft component overhaul lifting platform is provided.
Referring to fig. 1-3, the aircraft part maintenance lifting platform according to the embodiment of the utility model comprises a substrate 1, a supporting table 2 is arranged at the top end of the substrate 1, a lifting table 3 is arranged above the supporting table 2, a protective pad 4 covers the top end of the lifting table 3, a mounting plate 5 is connected in the bottom of the supporting table 2, electric push rods 6 are symmetrically arranged at the bottom end of the mounting plate 5, the output end of the electric push rod 6 is connected with a lifting assembly 7, the lifting table 3 can be driven by the lifting assembly 7 to lift along the driving direction of the electric push rod 6, rod grooves 8 are formed in four corners of the top end of the supporting table 2, stabilizing rods 9 in sliding fit with the rod grooves 8 are arranged in four corners of the bottom end of the lifting table 3, and one end, far away from the lifting table 3, of each stabilizing rod 9 extends into the supporting table 2 and is connected with a sliding assembly 10.
Further, the lifting component 7 is detachably matched with the bottom end of the lifting platform 3.
Further, the lifting assembly 7 comprises a lifting plate 71, an output end of the electric push rod 6 penetrates through the mounting plate 5 to be connected, a moving block 72 is fixedly connected to the lifting plate 71 through a screw, the moving block 72 is slidably arranged on a sliding rail 73, the sliding rail 73 is mounted on an L-shaped bracket 74 through a screw, and the L-shaped bracket 74 is fixedly mounted on the surface of the mounting plate 5.
Further, the top end of the lifting plate 71 is connected through a supporting top plate 75, and the supporting top plate 75 is detachably engaged with the lifting table 3.
Further, the sliding assembly 10 includes a guide cylinder 101 fixedly mounted on the side wall of the support table 2, a sliding block 102 is slidably disposed in the guide cylinder 101, and the top end of the sliding block 102 is fixedly connected to the bottom end of the stabilizing rod 9.
Further, guide blocks 103 are arranged on two sides of the sliding block 102 along the height direction thereof, and a guide groove 104 matched with the guide blocks 103 is arranged on the inner wall of the guide cylinder 101.
Further, an oil groove 105 is formed in the side surface of the guide block 103 along the sliding direction of the sliding block 102, a plurality of balls 106 are arranged in the oil groove 105, and the balls 106 are in sliding abutting joint with the guide groove 104.
Furthermore, the bottom of the guide cylinder 101 is provided with an elastic column 107, and the elastic column 107 is sleeved with a spring 108.
During the concrete implementation, can drive the lifter plate 71 that its output is connected through electric putter 6 and realize going up and down in vertical direction along slide rail 73, lifter plate 71 is at the in-process that goes up and down, and contact and separation can be realized with elevating platform 3 to the supporting roof 75 on its top, can adjust elevating platform 3 to the suitable position when dismantling as required, with the bottom contact of aircraft spare part to cooperation sliding assembly 10 plays the guard action to the dismantlement of spare part. In addition, the sliding assembly 10 can also be used for independently abutting and supporting the disassembled parts.
Through the sliding assembly 10 who sets up, oil groove 105 has been seted up in the side slip direction of guide block 103, injects lubricating oil back into spout 105, and partial lubricating oil can be stored in oil groove 105, and has sufficient lubricating oil between the contact surface of guide block 103 and guide way 104, has reduced the friction between guide block 103 and the guide way 104, improve equipment's life.
The above description is only for the preferred embodiment of the present invention, but the scope of the present invention is not limited thereto, and any person skilled in the art should be considered to be within the technical scope of the present invention, and equivalent alternatives or modifications according to the technical solution of the present invention and the inventive concept thereof should be covered by the scope of the present invention.
Claims (8)
1. The aircraft part overhauling lifting platform is characterized by comprising a substrate (1), wherein a supporting table (2) is arranged at the top end of the substrate (1), a lifting platform (3) is arranged above the supporting table (2), a protection pad (4) covers the top end of the lifting platform (3), a mounting plate (5) is connected to the bottom of the supporting table (2) in an inscribed mode, electric push rods (6) are symmetrically installed at the bottom end of the mounting plate (5), the output end of each electric push rod (6) is connected with a lifting assembly (7), the lifting platform (3) can be driven to lift along the driving direction of each electric push rod (6) through the lifting assembly (7), rod grooves (8) are formed in four corners of the top end of the supporting table (2), stabilizing rods (9) are arranged in four corners of the bottom end of the lifting platform (3) in a sliding fit mode with the rod grooves (8), one ends, far away from the lifting platform (3), of the stabilizing rods (9), extend to the inside the supporting table (2), and is connected with the sliding component (10).
2. An aircraft component service lift platform according to claim 1, wherein the lift assembly (7) is detachably engaged with the bottom end of the lift table (3).
3. The aircraft part overhauling lifting platform as claimed in claim 2, wherein the lifting assembly (7) comprises a lifting plate (71) connected with the output end of the electric push rod (6) by penetrating through the mounting plate (5), the lifting plate (71) is fixedly connected with a moving block (72) through a screw, the moving block (72) is slidably arranged on a sliding rail (73), the sliding rail (73) is mounted on an L-shaped bracket (74) through a screw, and the L-shaped bracket (74) is fixedly mounted on the surface of the mounting plate (5).
4. An aircraft component service lift platform according to claim 3, characterized in that the top ends of the lift plates (71) are connected by a supporting roof (75), the supporting roof (75) being detachably fitted to the lift table (3).
5. The aircraft part overhauling lifting platform according to claim 1, wherein the sliding assembly (10) comprises a guide cylinder (101) fixedly installed on the side wall of the supporting platform (2), a sliding block (102) is arranged in the guide cylinder (101) in a sliding manner, and the top end of the sliding block (102) is fixedly connected with the bottom end of the stabilizing rod (9).
6. The aircraft part overhauling lifting platform as claimed in claim 5, wherein guide blocks (103) are arranged on two sides of the sliding block (102) along the height direction of the sliding block, and a guide groove (104) matched with the guide blocks (103) is formed in the inner wall of the guide cylinder (101).
7. The aircraft part overhauling lifting platform as claimed in claim 6, wherein an oil groove (105) is formed in the side surface of the guide block (103) along the sliding direction of the sliding block (102), a plurality of balls (106) are arranged in the oil groove (105), and the balls (106) are in sliding abutting joint with the guide groove (104).
8. An aircraft component service lift platform according to any of claims 5 to 7, wherein the bottom of the guide cylinder (101) is provided with a resilient post (107), and the resilient post (107) is sleeved with a spring (108).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202122462775.9U CN216038434U (en) | 2021-10-13 | 2021-10-13 | Aircraft part overhauls lift platform |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202122462775.9U CN216038434U (en) | 2021-10-13 | 2021-10-13 | Aircraft part overhauls lift platform |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN216038434U true CN216038434U (en) | 2022-03-15 |
Family
ID=80548616
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202122462775.9U Active CN216038434U (en) | 2021-10-13 | 2021-10-13 | Aircraft part overhauls lift platform |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN216038434U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116553424A (en) * | 2023-05-11 | 2023-08-08 | 射阳兴凯飞航空设备有限公司 | Lifting platform and method for intelligent aircraft part overhaul |
-
2021
- 2021-10-13 CN CN202122462775.9U patent/CN216038434U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116553424A (en) * | 2023-05-11 | 2023-08-08 | 射阳兴凯飞航空设备有限公司 | Lifting platform and method for intelligent aircraft part overhaul |
| CN116553424B (en) * | 2023-05-11 | 2023-12-19 | 射阳兴凯飞航空设备有限公司 | Lifting platform and method for intelligent aircraft part overhaul |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| 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. |
|
| CP03 | Change of name, title or address |