CN219854500U - High-efficiency adjustable supporting device for installation of aero-engine - Google Patents
High-efficiency adjustable supporting device for installation of aero-engine Download PDFInfo
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- CN219854500U CN219854500U CN202321174448.6U CN202321174448U CN219854500U CN 219854500 U CN219854500 U CN 219854500U CN 202321174448 U CN202321174448 U CN 202321174448U CN 219854500 U CN219854500 U CN 219854500U
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- clamping plate
- threaded shaft
- seat
- supporting
- aeroengine
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- 230000008093 supporting effect Effects 0.000 title claims abstract description 80
- 238000009434 installation Methods 0.000 title claims description 62
- 230000007246 mechanism Effects 0.000 claims abstract description 12
- 238000013016 damping Methods 0.000 claims description 19
- 238000010030 laminating Methods 0.000 claims description 2
- 230000000694 effects Effects 0.000 description 7
- 235000017166 Bambusa arundinacea Nutrition 0.000 description 3
- 235000017491 Bambusa tulda Nutrition 0.000 description 3
- 241001330002 Bambuseae Species 0.000 description 3
- 235000015334 Phyllostachys viridis Nutrition 0.000 description 3
- 239000011425 bamboo Substances 0.000 description 3
- 230000003028 elevating effect Effects 0.000 description 3
- 239000000463 material Substances 0.000 description 3
- 238000005299 abrasion Methods 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 238000000465 moulding Methods 0.000 description 2
- 230000009471 action Effects 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 230000000052 comparative effect Effects 0.000 description 1
- 150000001875 compounds Chemical class 0.000 description 1
- 230000003750 conditioning effect Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000008569 process Effects 0.000 description 1
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- Vibration Prevention Devices (AREA)
Abstract
The utility model belongs to the technical field of supporting devices, in particular to a high-efficiency adjustable supporting device for mounting an aeroengine, which comprises a mounting base and a mounting mechanism arranged in the mounting base.
Description
Technical Field
The utility model relates to the technical field of supporting devices, in particular to a high-efficiency adjustable supporting device for installation of an aero-engine.
Background
Metal leadframe strips are commonly used to support electrical device packages during conventional manufacturing steps such as pin conditioning and formation, package symbolization, and electrical testing, each device package being created by encapsulating an electrical device, which may, for example, contain one or more component parts, such as integrated circuit devices, in an encapsulating material such as a block of molding compound applied during a package molding process.
However, when the existing aeroengine is installed, a certain adjusting function cannot be performed according to the length and the size of the model caliber of the aeroengine when the installed aeroengine is supported, so that the installation work cannot be performed effectively when the aeroengine is supported, and the adjusting function cannot be performed according to the installation conditions and the height of an installation staff when the aeroengine is supported, so that the installation efficiency is reduced, and therefore, the efficient adjustable supporting device for installing the aeroengine is provided for solving the problems.
Disclosure of Invention
In order to overcome the defects in the prior art, the problems that when an aeroengine is installed, the installed aeroengine cannot be supported, a certain adjusting function is carried out according to the length and the size of a model caliber of the aeroengine, so that the aeroengine with the supporting function cannot be effectively installed, and when the aeroengine with the supporting function is carried out, the adjusting function cannot be carried out according to the installation conditions and the height of an installation worker, and the installation efficiency is reduced are solved.
The technical scheme adopted for solving the technical problems is as follows: the utility model relates to a high-efficiency adjustable supporting device for installation of an aeroengine, which comprises an installation base and an installation mechanism arranged in the installation base, wherein the installation mechanism comprises an adjusting component and a fixing component;
the adjusting component comprises a supporting seat, a rotating machine, a connecting seat, a connecting block, a first threaded shaft, a clamping groove, a second threaded shaft and a bearing, wherein the supporting seat is arranged above the mounting base, the side wall of the supporting seat is fixedly connected with the rotating machine, the second threaded shaft is rotationally connected to the inside of the rotating machine, one end of the second threaded shaft is rotationally connected with the bearing, the clamping groove is formed in the surface of the supporting seat, the connecting seat is rotationally connected to the inside of the second threaded shaft, the first threaded shaft is rotationally connected to the inside of the connecting seat, and the connecting block is rotationally connected to the inside of the first threaded shaft;
the fixing assembly comprises a connecting shaft, a first clamping plate, a second clamping plate and a threaded bolt, wherein the connecting shaft is connected to the inside of the connecting block in a rotating mode, the first clamping plate and the second clamping plate are connected to the inside of the connecting shaft in a rotating mode respectively, and the threaded bolt is connected to the inside of the second clamping plate in a rotating mode.
Preferably, the four sides of installation base are provided with the removal wheel, the inside of removal wheel rotates and is connected with the screw plug, the surface laminating of first splint and second splint is connected with the rubber ring, the inside fixedly connected with pneumatic cylinder of installation base, the upper end fixedly connected with supporting seat of pneumatic cylinder, the surface of installation base is provided with buffer gear.
Preferably, the second threaded shaft and the supporting seat form a rotating structure through a bearing and a rotating machine, and the connecting seat and the supporting seat form a sliding structure through the second threaded shaft and a clamping groove.
Preferably, the connecting block and the connecting seat form a sliding structure through a first threaded shaft, and the connecting block is symmetrically installed along the horizontal direction of the connecting seat.
Preferably, the first clamping plate is in rotary connection with the connecting block through the connecting shaft, and the first clamping plate is in fixed connection with the second clamping plate through the threaded bolt.
Preferably, the supporting seat and the installation base form a lifting structure through a hydraulic cylinder, a group of rubber rings are arranged on the surfaces of the first clamping plate and the second clamping plate, and four groups of movable wheels are arranged at the lower end of the installation base.
Preferably, the buffer gear includes a support section of thick bamboo piece, damping spring and rubber slab, the four ends of installation base are provided with a support section of thick bamboo piece, the inside fixedly connected with damping spring of a support section of thick bamboo piece, damping spring's upper end fixedly connected with rubber slab.
Preferably, the connecting seat and the mounting base form an elastic structure through the supporting cylinder block, the damping spring and the rubber plate.
The utility model has the advantages that:
1. according to the utility model, by arranging the first clamping plate, the installed second threaded shaft can perform certain rotation work between the bearing and the rotating machine and the supporting seat, then the connecting seat can perform certain sliding adjustment between the clamping groove and the supporting seat through the second threaded shaft, so that the length adjustment is convenient to perform according to the installation of the aero-engine, and the installed connecting block can perform certain sliding work between the first threaded shaft and the connecting seat, so that the adjusting effect is performed according to the size of the model caliber of the aero-engine when the aero-engine is installed, and then the first clamping plate and the second clamping plate perform certain fastening effect on the aero-engine performing the supporting effect through the threaded bolt, so that the shaking caused by the supporting effect is avoided;
2. according to the utility model, by arranging the hydraulic cylinder, the installed supporting seat can perform certain lifting work between the hydraulic cylinder and the installation base, so that when the aero-engine is supported, the aero-engine is conveniently adjusted according to installation conditions and the height of installation staff, the surfaces of the first clamping plate and the second clamping plate are provided with a group of rubber rings for protecting the aero-engine with the supporting function to a certain degree, abrasion is avoided, and the supporting equipment is conveniently carried and moved through the installed moving wheels, and the supporting equipment is fixed through the screw plugs.
Drawings
In order to more clearly illustrate the embodiments of the utility model or the technical solutions of the prior art, the drawings which are used in the description of the embodiments or the prior art will be briefly described, it being obvious that the drawings in the description below are only some embodiments of the utility model, and that other drawings can be obtained from these drawings without inventive faculty for a person skilled in the art.
FIG. 1 is a schematic diagram of the overall structure of the present utility model;
FIG. 2 is a schematic diagram of a buffer mechanism according to the present utility model;
FIG. 3 is a schematic view of the internal structure of the support base of the present utility model;
fig. 4 is a schematic view of the surface structure of the connection seat according to the present utility model.
In the figure: 1. a mounting base; 2. a moving wheel; 3. a screw plug; 4. a buffer mechanism; 401. a support cylinder block; 402. a damping spring; 403. a rubber plate; 5. a hydraulic cylinder; 6. a support base; 7. a rotating machine; 8. a connecting seat; 9. a connecting block; 10. a first threaded shaft; 11. a connecting shaft; 12. a first clamping plate; 13. a second clamping plate; 14. a threaded bolt; 15. a rubber ring; 16. a clamping groove; 17. a second threaded shaft; 18. and (3) a bearing.
Detailed Description
The following description of the embodiments of the present utility model will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present utility model, but not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the utility model without making any inventive effort, are intended to be within the scope of the utility model.
Example 1
Referring to fig. 1-4, a high-efficiency adjustable supporting device for installing an aeroengine comprises an installation base 1 and an installation mechanism arranged in the installation base 1, wherein the installation mechanism comprises an adjusting component and a fixing component;
the adjusting component comprises a supporting seat 6, a rotating machine 7, a connecting seat 8, a connecting block 9, a first threaded shaft 10, a clamping groove 16, a second threaded shaft 17 and a bearing 18, wherein the supporting seat 6 is arranged above the mounting base 1, the side wall of the supporting seat 6 is fixedly connected with the rotating machine 7, the second threaded shaft 17 is rotationally connected to the inside of the rotating machine 7, one end of the second threaded shaft 17 is rotationally connected with the bearing 18, the clamping groove 16 is arranged on the surface of the supporting seat 6, the connecting seat 8 is rotationally connected to the inside of the second threaded shaft 17, the first threaded shaft 10 is rotationally connected to the inside of the connecting seat 8, and the connecting block 9 is rotationally connected to the inside of the first threaded shaft 10;
the fixed subassembly includes connecting axle 11, first splint 12, second splint 13 and threaded bolt 14, and the inside rotation of connecting block 9 is connected with connecting axle 11, and the inside of connecting axle 11 is rotated respectively and is connected with first splint 12 and second splint 13, and the inside rotation of second splint 13 is connected with threaded bolt 14.
Further, the second threaded shaft 17 and the supporting seat 6 form a rotating structure through the bearing 18 and the rotating machine 7, the connecting seat 8 and the supporting seat 6 form a sliding structure through the second threaded shaft 17 and the clamping groove 16, the installed second threaded shaft 17 can perform certain rotation work between the bearing 18 and the rotating machine 7 and the supporting seat 6, then the connecting seat 8 can perform certain sliding adjustment between the second threaded shaft 17 and the clamping groove 16 and the supporting seat 6, the length adjustment is convenient to perform when the aeroengine is installed according to the requirement of the aeroengine, and the efficient supporting function is convenient to perform when the aeroengine is installed.
Further, the connecting block 9 forms a sliding structure with the connecting seat 8 through the first threaded shaft 10, the connecting block 9 is symmetrically installed in the horizontal direction of the connecting seat 8, and the installed connecting block 9 can perform certain sliding work between the first threaded shaft 10 and the connecting seat 8 for adjusting the function according to the size of the model caliber of the engine when the aeroengine is installed.
Further, the first clamping plate 12 is in rotary connection with the connecting block 9 through the connecting shaft 11, the first clamping plate 12 and the second clamping plate 13 are in fixed connection with each other through the threaded bolt 14, the installed first clamping plate 12 can perform rotary operation between the connecting shaft 11 and the connecting block 9, and then the first clamping plate 12 and the second clamping plate 13 perform certain fastening action on the aeroengine performing supporting action through the threaded bolt 14.
Example two
Referring to fig. 1 and 4, in a first comparative example, as another embodiment of the present utility model, moving wheels 2 are disposed on four sides of a mounting base 1, a threaded plug 3 is rotatably connected to the inside of the moving wheels 2, rubber rings 15 are attached to surfaces of a first clamping plate 12 and a second clamping plate 13, a hydraulic cylinder 5 is fixedly connected to the inside of the mounting base 1, a supporting base 6 is fixedly connected to an upper end of the hydraulic cylinder 5, and a buffer mechanism 4 is disposed on the surface of the mounting base 1.
Further, the supporting seat 6 forms a lifting structure with the installation base 1 through the hydraulic cylinder 5, a group of rubber rings 15 are arranged on the surfaces of the first clamping plate 12 and the second clamping plate 13, four groups of movable wheels 2 are arranged at the lower end of the installation base 1, the installed supporting seat 6 can perform certain lifting work between the hydraulic cylinder 5 and the installation base 1, the aeroengine can be conveniently adjusted according to installation conditions and the height of an installation worker when being supported, the surfaces of the first clamping plate 12 and the second clamping plate 13 are provided with a group of rubber rings 15 for protecting the aeroengine for supporting, abrasion is avoided, and the movable wheels 2 are convenient to carry and move supporting equipment through the installation, and the aeroengine is fixed through the threaded plugs 3.
Further, the buffer mechanism 4 comprises a supporting cylinder block 401, a damping spring 402 and a rubber plate 403, the supporting cylinder block 401 is arranged at the four ends of the mounting base 1, the damping spring 402 is fixedly connected to the inside of the supporting cylinder block 401, and the rubber plate 403 is fixedly connected to the upper end of the damping spring 402.
Further, connecting seat 8 constitutes elastic structure through supporting cylinder piece 401, damping spring 402 and rubber slab 403 and installation base 1, when carrying out the lift work to the supporting seat 6 of installation, supporting seat 6 and the connecting seat 8 of installation can support cylinder piece 401, damping spring 402 and rubber slab 403 constitute elastic structure with installation base 1, guarantee when supporting seat 6 descends, through damping spring 402's effect, avoid causing the striking to installation base 1, receive the harm, and damping spring 402 coefficient of installation is less, avoids causing repeated rocking.
The working principle is that firstly, certain installation connection work is carried out on a supported aeroengine, a certain rotation work can be carried out between a bearing 18 and a rotating machine 7 and a supporting seat 6 through a second threaded shaft 17, then certain sliding adjustment can be carried out between a connecting seat 8 and the supporting seat 6 through a second threaded shaft 17 and a clamping groove 16, the length adjustment is convenient to carry out according to the installation of the aeroengine, efficient supporting effect is convenient to carry out when the aeroengine is installed, then a certain sliding work can be carried out between a first threaded shaft 10 and the connecting seat 8 through a connecting block 9 which is used for carrying out the adjusting effect according to the size of the model caliber of the engine when the aeroengine is installed, a first clamping plate 12 which is installed can carry out the rotation work between the connecting shaft 11 and the connecting block 9 through a threaded bolt 14, and then the first clamping plate 12 and a second clamping plate 13 carry out certain fastening effect on the aeroengine which carries out the supporting effect.
Finally, carry out certain elevating action to the aeroengine of support, the supporting seat 6 of installation can carry out certain elevating work through between pneumatic cylinder 5 and the installation base 1, be convenient for carry out the supporting action installation during operation to the aeroengine, be convenient for adjust the effect according to installation condition and installation staff's height, and the surface of first splint 12 and second splint 13 sets up a set of rubber ring 15, be used for carrying out certain protection to the aeroengine of supporting action, avoid causing wearing and tearing, and remove round 2 and be convenient for carry supporting equipment and remove through the installation, fix through screw plug 3, and when carrying out elevating operation to the supporting seat 6 of installation, the supporting seat 6 of installation and connecting seat 8 can support barrel 401, damping spring 402 and rubber slab 403 constitute elastic structure with installation base 1, guarantee when supporting seat 6 descends, through damping spring 402's effect, avoid causing the striking to installation base 1, receive the harm, and the damping spring 402 coefficient of installation is less, avoid causing the repeated rocking.
In the description of the present specification, the descriptions of the terms "one embodiment," "example," "specific example," and the like, 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 do not necessarily refer to the same embodiments or examples. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples.
The foregoing has shown and described the basic principles, principal features and advantages of the utility model. It will be understood by those skilled in the art that the present utility model is not limited to the embodiments described above, and that the above embodiments and descriptions are merely illustrative of the principles of the present utility model, and various changes and modifications may be made without departing from the spirit and scope of the utility model, which is defined in the appended claims.
Claims (8)
1. The utility model provides a strutting arrangement with adjustable aeroengine installs with high efficiency, includes installation base (1) and sets up at the inside installation mechanism of installation base (1), its characterized in that: the mounting mechanism comprises an adjusting component and a fixing component;
the adjusting component comprises a supporting seat (6), a rotating machine (7), a connecting seat (8), a connecting block (9), a first threaded shaft (10), a clamping groove (16), a second threaded shaft (17) and a bearing (18), wherein the supporting seat (6) is arranged above the mounting base (1), the side wall of the supporting seat (6) is fixedly connected with the rotating machine (7), the second threaded shaft (17) is rotatably connected to the inside of the rotating machine (7), the bearing (18) is rotatably connected to one end of the second threaded shaft (17), the clamping groove (16) is formed in the surface of the supporting seat (6), the connecting seat (8) is rotatably connected to the inside of the second threaded shaft (17), the first threaded shaft (10) is rotatably connected to the inside of the connecting seat (8), and the connecting block (9) is rotatably connected to the inside of the first threaded shaft (10).
The fixing assembly comprises a connecting shaft (11), a first clamping plate (12), a second clamping plate (13) and a threaded bolt (14), wherein the connecting shaft (11) is connected with the connecting block (9) in a rotating mode, the first clamping plate (12) and the second clamping plate (13) are connected with the connecting shaft (11) in a rotating mode respectively, and the threaded bolt (14) is connected with the second clamping plate (13) in the connecting shaft in a rotating mode.
2. The efficient and adjustable supporting device for installing an aeroengine according to claim 1, wherein: four sides of installation base (1) are provided with and remove round (2), the inside rotation of removal round (2) is connected with screw plug (3), the surface laminating of first splint (12) and second splint (13) is connected with rubber ring (15), the inside fixedly connected with pneumatic cylinder (5) of installation base (1), the upper end fixedly connected with supporting seat (6) of pneumatic cylinder (5), the surface of installation base (1) is provided with buffer gear (4).
3. The efficient and adjustable supporting device for installing an aeroengine according to claim 1, wherein: the second threaded shaft (17) and the supporting seat (6) form a rotating structure through the bearing (18) and the rotating machine (7), and the connecting seat (8) and the supporting seat (6) form a sliding structure through the second threaded shaft (17) and the clamping groove (16).
4. The efficient and adjustable supporting device for installing an aeroengine according to claim 1, wherein: the connecting block (9) and the connecting seat (8) form a sliding structure through a first threaded shaft (10), and the connecting block (9) is symmetrically installed in the horizontal direction of the connecting seat (8).
5. The efficient and adjustable supporting device for installing an aeroengine according to claim 1, wherein: the first clamping plate (12) is rotationally connected with the connecting block (9) through the connecting shaft (11), and the first clamping plate (12) and the second clamping plate (13) are fixedly connected with each other through the threaded bolt (14).
6. The efficient and adjustable supporting device for installing an aeroengine according to claim 2, wherein: the supporting seat (6) and the installation base (1) form a lifting structure through the hydraulic cylinder (5), a group of rubber rings (15) are arranged on the surfaces of the first clamping plate (12) and the second clamping plate (13), and four groups of movable wheels (2) are arranged at the lower end of the installation base (1).
7. The efficient and adjustable supporting device for installing an aeroengine according to claim 2, wherein: the buffer mechanism (4) comprises a supporting cylinder block (401), a damping spring (402) and a rubber plate (403), wherein the supporting cylinder block (401) is arranged at the four ends of the mounting base (1), the damping spring (402) is fixedly connected to the inside of the supporting cylinder block (401), and the rubber plate (403) is fixedly connected to the upper end of the damping spring (402).
8. The efficient and adjustable supporting device for installing an aeroengine as claimed in claim 7, wherein: the connecting seat (8) and the mounting base (1) form an elastic structure through the supporting cylinder block (401), the damping spring (402) and the rubber plate (403).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202321174448.6U CN219854500U (en) | 2023-05-16 | 2023-05-16 | High-efficiency adjustable supporting device for installation of aero-engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202321174448.6U CN219854500U (en) | 2023-05-16 | 2023-05-16 | High-efficiency adjustable supporting device for installation of aero-engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN219854500U true CN219854500U (en) | 2023-10-20 |
Family
ID=88334484
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202321174448.6U Active CN219854500U (en) | 2023-05-16 | 2023-05-16 | High-efficiency adjustable supporting device for installation of aero-engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN219854500U (en) |
-
2023
- 2023-05-16 CN CN202321174448.6U patent/CN219854500U/en active Active
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