CN221024241U - Self-lubricating aircraft landing gear - Google Patents
Self-lubricating aircraft landing gear Download PDFInfo
- Publication number
- CN221024241U CN221024241U CN202322904783.3U CN202322904783U CN221024241U CN 221024241 U CN221024241 U CN 221024241U CN 202322904783 U CN202322904783 U CN 202322904783U CN 221024241 U CN221024241 U CN 221024241U
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- Prior art keywords
- oil
- landing gear
- lubricating
- self
- oil storage
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- 239000003921 oil Substances 0.000 description 44
- 239000010687 lubricating oil Substances 0.000 description 18
- 238000009434 installation Methods 0.000 description 13
- 238000001125 extrusion Methods 0.000 description 6
- 230000009471 action Effects 0.000 description 4
- 238000000034 method Methods 0.000 description 4
- 230000000694 effects Effects 0.000 description 3
- 239000002184 metal Substances 0.000 description 3
- 238000002347 injection Methods 0.000 description 2
- 239000007924 injection Substances 0.000 description 2
- 230000001050 lubricating effect Effects 0.000 description 2
- 230000008569 process Effects 0.000 description 2
- 230000004075 alteration Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000008901 benefit Effects 0.000 description 1
- 230000007423 decrease Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000005484 gravity Effects 0.000 description 1
- 238000010030 laminating Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 239000000243 solution Substances 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
Classifications
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
Landscapes
- General Details Of Gearings (AREA)
Abstract
The utility model relates to the technical field of aircraft landing gears, and discloses a self-lubricating aircraft landing gear, which comprises an unmanned aerial vehicle shell, wherein mounting blocks are arranged on two sides of the unmanned aerial vehicle shell, landing gear bodies are hinged inside the mounting blocks through circular shafts, a cavity is formed in the middle of each mounting block, and the self-lubricating aircraft landing gear further comprises: the oiling component is arranged at the bottom of the unmanned aerial vehicle shell and is used for adding lubricating oil to the outer surface of the circular shaft; the oil injection assembly comprises an oil storage pipe arranged at the bottom of the unmanned aerial vehicle shell, a piston and a first spring are sleeved in the oil storage pipe, an oil transportation channel is communicated with the outer side of the oil storage pipe, an installation shaft is arranged at the bottom of the piston, an installation plate is arranged at the bottom end of the installation shaft, and the oil storage assembly further comprises a connection plate. Through the below that the piston moved to the oil delivery way, the lubricating oil that is located the piston top this moment will flow into the inside of oil delivery way and flow into the cavity and lubricate the circle axle, and then be convenient for lubricate the undercarriage body.
Description
Technical Field
The utility model relates to the technical field of aircraft landing gears, in particular to a self-lubricating aircraft landing gear.
Background
Unmanned aerial vehicle is abbreviated as unmanned aerial vehicle, and unmanned aerial vehicle's bottom can be provided with the undercarriage generally, when descending to unmanned aerial vehicle, its undercarriage can bend towards both sides and play the cushioning effect when descending to unmanned aerial vehicle, and articulate with the metal shaft generally between undercarriage and the unmanned aerial vehicle, and need use lubricating oil to scribble the surface at the metal shaft generally between undercarriage and the unmanned aerial vehicle, reduce the frictional force between metal shaft and the undercarriage, guarantee that the undercarriage can normally play the cushioning effect to unmanned aerial vehicle, and when the articulated department of undercarriage adds lubricating oil, because the undercarriage is less with the space of unmanned aerial vehicle articulated department, comparatively difficult when adding lubricating oil to it for this reason, inconvenient user operation proposes a self-lubricating aircraft undercarriage for this reason.
Disclosure of utility model
In order to overcome the defects in the prior art, the utility model provides a self-lubricating aircraft landing gear, which has the advantage of automatically lubricating the landing gear.
In order to achieve the above purpose, the present utility model provides the following technical solutions: the utility model provides a self-lubricating aircraft undercarriage, includes unmanned aerial vehicle shell, the installation piece is all installed to the both sides of unmanned aerial vehicle shell, the inside of installation piece articulates through the circle axle has the undercarriage body, the cavity has been seted up at the middle part of installation piece, still includes:
The oiling component is arranged at the bottom of the unmanned aerial vehicle shell and is used for adding lubricating oil to the outer surface of the circular shaft;
The oil injection assembly comprises an oil storage pipe arranged at the bottom of the unmanned aerial vehicle shell, a piston and a first spring are sleeved in the oil storage pipe, an oil transportation channel is communicated with the outer side of the oil storage pipe, an installation shaft is arranged at the bottom of the piston, an installation plate is arranged at the bottom end of the installation shaft, and the oil storage assembly further comprises a connection plate which is arranged at one side of the landing gear body;
The inside of oil storage pipe has cup jointed the spacing ring, circle axle and undercarriage body interference fit, oil storage pipe's top adds lubricating oil through the check valve.
As a preferable technical scheme of the utility model, a rectangular groove is formed in the outer side of the circular shaft, a fixing frame is installed on the outer side of the installation block, a second spring and a movable plate are sleeved on the outer side of the fixing frame, and a threaded rod is connected to the outer side of the fixing frame in a threaded manner.
As a preferable technical scheme of the utility model, the threaded rod is in extrusion contact with the movable plate, and the limiting block is movably clamped with the rectangular groove.
As a preferable technical scheme of the utility model, the second spring is elastically supported between the movable plate and the mounting block.
As a preferable embodiment of the present utility model, the first spring is elastically supported between the piston and the oil storage tube.
As a preferable technical scheme of the utility model, the oil delivery channel is inclined towards the position of the cavity, and the oil delivery channel is communicated with the cavity.
As a preferable technical scheme of the utility model, the limiting ring is in limiting contact with the piston, and the connecting plate is in extrusion contact with the mounting plate.
Compared with the prior art, the utility model has the following beneficial effects:
1. According to the utility model, through the cooperation between the circular shaft and the mounting block, the landing gear body moves and drives the connecting plate to rotate when the landing gear body descends and receives impact force, and meanwhile, the cooperation between the connecting plate and the mounting plate drives the mounting shaft to move downwards along the inside of the oil storage pipe, so that the piston can be driven to move to the opening position of the oil delivery channel, at the moment, lubricating oil above the piston flows into the inside of the oil delivery channel and flows into the cavity to lubricate the circular shaft due to the action of gravity, so that the landing gear body is conveniently lubricated, and meanwhile, the piston is driven to reset by the elastic force of the first spring, so that the lubricating oil is prevented from continuously flowing out.
2. According to the utility model, through the cooperation between the threaded rod and the fixing frame, the threaded rod can rotate along the outer side of the fixing frame and move left and right, and meanwhile, through the cooperation between the threaded rod and the movable plate, the movable plate can move along the outer surface of the fixing frame, so that the limiting block can be driven to be clamped with the rectangular groove, the rotation of the landing gear body can be further limited through the circular shaft, and the phenomenon that the user mistakenly touches the landing gear body to extrude lubricating oil in the oil storage pipe is prevented from flowing empty.
Drawings
FIG. 1 is a schematic diagram of the structure of the present utility model;
FIG. 2 is a schematic cross-sectional view of the front face of the present utility model;
FIG. 3 is an enlarged schematic view of the structure of FIG. 2A according to the present utility model;
FIG. 4 is a schematic cross-sectional view of a side face of the present utility model;
Fig. 5 is an enlarged schematic view of the structure of fig. 4B according to the present utility model.
In the figure: 1. unmanned aerial vehicle shell; 2. a mounting block; 3. a circular shaft; 4. a landing gear body; 5. a cavity; 6. an oil storage pipe; 7. a piston; 8. a mounting shaft; 9. a mounting plate; 10. a first spring; 11. a limiting ring; 12. an oil delivery passage; 13. a connecting plate; 14. rectangular grooves; 15. a fixing frame; 16. a second spring; 17. a movable plate; 18. a threaded rod; 19. a limiting block; 20. a one-way valve.
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.
As shown in fig. 1 to 5, the utility model provides a self-lubricating aircraft landing gear, which comprises an unmanned aerial vehicle shell 1, wherein mounting blocks 2 are mounted on two sides of the unmanned aerial vehicle shell 1, a landing gear body 4 is hinged to the inside of the mounting blocks 2 through a circular shaft 3, a cavity 5 is formed in the middle of the mounting blocks 2, and the self-lubricating aircraft landing gear further comprises:
the oiling component is arranged at the bottom of the unmanned aerial vehicle shell 1 and is used for adding lubricating oil to the outer surface of the round shaft 3;
The oil injection assembly comprises an oil storage pipe 6 arranged at the bottom of an unmanned aerial vehicle shell 1, a piston 7 and a first spring 10 are sleeved in the oil storage pipe 6, an oil transportation channel 12 is communicated with the outer side of the oil storage pipe 6, an installation shaft 8 is arranged at the bottom of the piston 7, an installation plate 9 is arranged at the bottom end of the installation shaft 8, and the oil storage assembly further comprises a connection plate 13, and the connection plate 13 is arranged at one side of a landing gear body 4;
The inside of the oil storage pipe 6 is sleeved with a limiting ring 11, the round shaft 3 is in interference fit with the landing gear body 4, and lubricating oil is added to the top of the oil storage pipe 6 through a one-way valve 20.
Through the cooperation between circle axle 3 and the installation piece 2 for landing gear body 4 will take place to move and drive connecting plate 13 and take place to rotate when the decline receives the impact force, simultaneously drive installation axle 8 through the cooperation between connecting plate 13 and the mounting panel 9 and follow the inside downwardly moving of oil storage pipe 6, thereby can drive piston 7 and remove to the below of defeated oil duct 12, the lubricating oil that is located piston 7 top at this moment will flow into the inside of defeated oil duct 12 and flow into cavity 5 and lubricate circle axle 3, and then be convenient for lubricate landing gear body 4, simultaneously will drive piston 7 through the elasticity of first spring 10 and reset, prevent that lubricating oil from continuously flowing out.
Wherein, rectangular slot 14 has been seted up in the outside of circle axle 3, and mount 15 is installed in the outside of installation piece 2, and second spring 16 and fly leaf 17 have been cup jointed in the outside of mount 15, and the outside threaded connection of mount 15 has threaded rod 18.
Through the cooperation between threaded rod 18 and the mount 15 for threaded rod 18 can rotate and control the removal along the outside of mount 15, simultaneously through the cooperation between threaded rod 18 and fly leaf 17, makes fly leaf 17 can follow the surface of mount 15 and remove, thereby can drive stopper 19 and rectangular channel 14 joint, and then can restrict the rotation of undercarriage body 4 through circle axle 3, prevent that the user from touching by mistake and cause the inside lubricating oil flow of oil storage tube 6 to the extrusion of undercarriage body 4 empty.
The threaded rod 18 is in extrusion contact with the movable plate 17, and the limiting block 19 is movably clamped with the rectangular groove 14.
Through the cooperation between threaded rod 18 and fly leaf 17 for threaded rod 18 can drive fly leaf 17 and remove along the surface of mount 15, simultaneously through the cooperation between stopper 19 and the rectangular channel 14, makes can carry out the spacing to circle axle 3 through the cooperation between stopper 19 and the rectangular channel 14.
Wherein the second spring 16 is elastically supported between the movable plate 17 and the mounting block 2.
Through the design of the second spring 16, the movable plate 17 has good elastic resetting performance, and at the moment, because the second spring 16 is in a compressed state, an elastic force is applied to the movable plate 17, so that the limiting block 19 can be driven to be separated from the rectangular groove 14, and the limiting of the circular shaft 3 is conveniently released.
Wherein the first spring 10 is elastically supported between the piston 7 and the oil reservoir tube 6.
Through the design of first spring 10 for piston 7 has good elasticity reset performance, because first spring 10 is compressed state at this moment, consequently can exert an elasticity to piston 7 to can drive piston 7 and spacing ring 11 laminating, make it play the seal effect to oil transportation way 12.
Wherein, the oil delivery way 12 inclines towards the position of the cavity 5, and the oil delivery way 12 is communicated with the cavity 5.
Through the design of oil duct 12, because oil duct 12 downward sloping for lubricating oil flows more easily when getting into the inside of oil duct 12, thereby can be through the inside interpolation lubricating oil of oil duct 12 to cavity 5, make it lubricate circle axle 3, and then more smooth when landing gear body 4 rotates.
Wherein, spacing ring 11 and piston 7 limit contact, connecting plate 13 and mounting panel 9 extrusion contact.
Through the cooperation between spacing ring 11 and piston 7 for can restrict the removal space of piston 7, be convenient for when extrudeing mounting panel 9 piston 7 can be to defeated oil duct 12 unblock, and then be convenient for store up the inside of the inside lubricating oil inflow of oil duct 12 of oil pipe 6.
The working principle and the using flow of the utility model are as follows:
When the unmanned aerial vehicle descends, through the cooperation between the round shaft 3 and the mounting block 2, the landing gear body 4 can drive the connecting plate 13 to rotate when the landing gear body descends and receives impact force, at the moment, the connecting plate 13 can squeeze the mounting plate 9 to drive the mounting shaft 8 to move downwards along the inside of the oil storage pipe 6, so that the piston 7 can be driven to move to the lower part of the oil conveying channel 12, at the moment, lubricating oil above the piston 7 can flow into the inside of the oil conveying channel 12 and enter the cavity 5 to lubricate the round shaft 3, and further lubricating of the landing gear body 4 is facilitated;
After that, the staff can rotate threaded rod 18, through the cooperation between threaded rod 18 and the mount 15 for threaded rod 18 can rotate and control the removal along the outside of mount 15, simultaneously through the cooperation between threaded rod 18 and fly leaf 17, make fly leaf 17 can follow the surface of mount 15 and remove, thereby can drive stopper 19 and rectangular channel 14 joint, and then can restrict the rotation of undercarriage body 4 through circle axle 3, prevent that the user from touching by mistake and causing the lubricating oil flow of the inside of oil storage tube 6 to undercarriage body 4 extrusion empty.
It is noted that relational terms such as first and second, and the like are used solely to distinguish one entity or action from another entity or action without necessarily requiring or implying any actual such relationship or order between such entities or actions. Moreover, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus.
Although embodiments of the present utility model have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and alterations can be made therein without departing from the principles and spirit of the utility model, the scope of which is defined in the appended claims and their equivalents.
Claims (7)
1. The utility model provides a self-lubricating aircraft undercarriage, includes unmanned aerial vehicle shell (1), installation piece (2) are all installed to the both sides of unmanned aerial vehicle shell (1), the inside of installation piece (2) articulates through circle axle (3) has undercarriage body (4), cavity (5) have been seted up at the middle part of installation piece (2), its characterized in that still includes:
The oiling component is arranged at the bottom of the unmanned aerial vehicle shell (1) and is used for adding lubricating oil to the outer surface of the round shaft (3);
the oil injection assembly comprises an oil storage pipe (6) arranged at the bottom of an unmanned aerial vehicle shell (1), a piston (7) and a first spring (10) are sleeved in the oil storage pipe (6), an oil conveying channel (12) is communicated with the outer side of the oil storage pipe (6), an installation shaft (8) is arranged at the bottom of the piston (7), an installation plate (9) is arranged at the bottom end of the installation shaft (8), and the oil storage assembly further comprises a connecting plate (13), wherein the connecting plate (13) is arranged at one side of a landing gear body (4);
The inside of oil storage pipe (6) has cup jointed spacing ring (11), circle axle (3) and undercarriage body (4) interference fit, the top of oil storage pipe (6) is through check valve (20) interpolation lubricating oil.
2. A self-lubricating aircraft landing gear according to claim 1, wherein: rectangular grooves (14) are formed in the outer side of the round shaft (3), a fixing frame (15) is installed in the outer side of the installation block (2), a second spring (16) and a movable plate (17) are sleeved on the outer side of the fixing frame (15), and a threaded rod (18) is connected with the outer side of the fixing frame (15) in a threaded mode.
3. A self-lubricating aircraft landing gear according to claim 2, wherein: the threaded rod (18) is in extrusion contact with the movable plate (17), and the limiting block (19) is movably clamped with the rectangular groove (14).
4. A self-lubricating aircraft landing gear according to claim 2, wherein: the second spring (16) is elastically supported between the movable plate (17) and the mounting block (2).
5. A self-lubricating aircraft landing gear according to claim 1, wherein: the first spring (10) is elastically supported between the piston (7) and the oil storage pipe (6).
6. A self-lubricating aircraft landing gear according to claim 1, wherein: the oil delivery channel (12) is inclined towards the position of the cavity (5), and the oil delivery channel (12) is communicated with the cavity (5).
7. A self-lubricating aircraft landing gear according to claim 1, wherein: the limiting ring (11) is in limiting contact with the piston (7), and the connecting plate (13) is in extrusion contact with the mounting plate (9).
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
CN202322904783.3U CN221024241U (en) | 2023-10-27 | 2023-10-27 | Self-lubricating aircraft landing gear |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
CN202322904783.3U CN221024241U (en) | 2023-10-27 | 2023-10-27 | Self-lubricating aircraft landing gear |
Publications (1)
Publication Number | Publication Date |
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CN221024241U true CN221024241U (en) | 2024-05-28 |
Family
ID=91171633
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
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CN202322904783.3U Active CN221024241U (en) | 2023-10-27 | 2023-10-27 | Self-lubricating aircraft landing gear |
Country Status (1)
Country | Link |
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CN (1) | CN221024241U (en) |
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2023
- 2023-10-27 CN CN202322904783.3U patent/CN221024241U/en active Active
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