CN216269880U - Aircraft nose landing gear - Google Patents
Aircraft nose landing gear Download PDFInfo
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- CN216269880U CN216269880U CN202122551715.4U CN202122551715U CN216269880U CN 216269880 U CN216269880 U CN 216269880U CN 202122551715 U CN202122551715 U CN 202122551715U CN 216269880 U CN216269880 U CN 216269880U
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- shaped frame
- landing gear
- seat
- nose landing
- aircraft nose
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Abstract
The utility model discloses an aircraft nose landing gear, wherein a support arm is arranged at the bottom of a U-shaped frame, and a tire is fixed through the support arm; the shock absorbing device is arranged at the top end inside the U-shaped frame, the shock absorbing device is obliquely arranged, the top of the supporting arm is hinged with a swing seat capable of vertically swinging, the shock absorbing device is fixed between the swing seat and the U-shaped frame, and when the ground runs and lands instantly impact, the swing seat is stressed and then swings and can absorb impact force through the shock absorbing device. The utility model can effectively improve the driving comfort level and the durability of the workpiece, has novel structure and convenient installation and disassembly, and is an ideal nose landing gear of the aircraft.
Description
Technical Field
The utility model relates to the technical field of aircrafts, in particular to an aircraft nose landing gear.
Background
It is known that when an aircraft is taxiing on the ground and taking off and landing, it is necessary to support the aircraft body on the ground by means of landing gears. Most that uses on present small aircraft is both arms undercarriage, and this kind of undercarriage passes through the supporting seat and realizes the fixed of undercarriage, and its shock absorption system is direct and the fuselage is fixed angle setting, and at the aircraft landing in-process, its atress direction on shock absorption system is invariable, and unable furthest's realization gravity and the absorption of falling to the ground impact force in the twinkling of an eye, lead to shock absorption system's part damage easily and in the twinkling of an eye in the landing, the cockpit can obviously feel the impact in the twinkling of an eye at the undercarriage position, influence the comfort level of riding.
Aiming at the defects in the prior art, as technical personnel in the industry, how to design an aircraft nose landing gear through technical improvement can realize multi-angle impact force absorption, and the technical problem to be solved by the technical personnel in the field is urgently needed to improve the ground running and the instant comfort level of landing of the flight.
Disclosure of Invention
In view of the above-mentioned drawbacks of the prior art, it is an object of the present invention to provide an aircraft nose landing gear that enables in-situ 360 degrees of rotation and is effective in absorbing transient impacts.
The aircraft nose landing gear comprises a U-shaped frame, wherein a supporting arm is vertically arranged on the side part of the U-shaped frame, and a fixing shaft is arranged at the bottom of the supporting arm and used for fixing a tire;
the top of the U-shaped frame is provided with a supporting part, and the swinging seat is hinged and fixed through the supporting part; the front end of the swing seat is provided with an upper support, the lower part of the U-shaped frame is provided with a lower support corresponding to the upper support, and a shock absorption device is arranged between the upper support and the lower support;
the top of the swing seat is provided with a bearing sleeve, and the top of the bearing sleeve is provided with a machine body fixing seat.
The swing seat is fixed with a driving sheet, and the driving sheet is provided with a plurality of fixing holes for realizing the fixation with an external driving source.
The shock absorbing device is arranged in a hollow groove in the middle of the U-shaped frame.
The upper support is arranged at the bottom of the front end of the swinging seat; the lower support is arranged on the extending seat at the rear side of the U-shaped frame.
The U-shaped frame and the supporting arm are connected through the fixing block and the reinforcing sheet to reinforce the connecting point.
The swing seat is internally provided with a hinged shaft, and the hinged shaft is connected and fixed with the swing seat.
The utility model has the following beneficial effects: according to the structure, when the tire fixing device is used, the supporting arm is arranged at the bottom of the U-shaped frame, and the tire is fixed through the supporting arm; the shock absorbing device is arranged at the top end inside the U-shaped frame, the shock absorbing device is obliquely arranged, the top of the supporting arm is hinged with a swing seat capable of vertically swinging, the shock absorbing device is fixed between the swing seat and the U-shaped frame, and when the ground runs and lands instantly impact, the swing seat is stressed and then swings and can absorb impact force through the shock absorbing device. The utility model can effectively improve the driving comfort level and the durability of the workpiece, has novel structure and convenient installation and disassembly, and is an ideal nose landing gear of the aircraft.
Drawings
The utility model is further illustrated with reference to the following figures and examples.
FIG. 1 is a schematic perspective view of the present invention;
FIG. 2 is a schematic perspective view II of the present invention;
FIG. 3 is a front view of the mounting structure of the present invention;
FIG. 4 is a perspective view of the mounting structure of the present invention;
in the figure, 1, a supporting arm, 11, a tire fixing shaft, 2, a U-shaped frame, 21, a fixing block, 22, a reinforcing sheet, 23, an extension seat, 24, a supporting seat, 25, a lower support, 3, a tire, 4, a swing seat, 41, a supporting extension section, 42, an upper support, 43, a hinge shaft, 5, a shock absorbing spring, 6, a driving sheet, 7, a bearing sleeve, 8 and a machine body fixing seat.
Detailed Description
The present invention is described in detail below, and other advantages and effects of the present invention will be easily understood by those skilled in the art from the disclosure of the present specification.
As shown in the attached drawings, the nose landing gear of the aircraft disclosed by the utility model comprises a U-shaped frame 2, wherein a single supporting arm 1 is vertically arranged on the side part of the U-shaped frame 2, and a tire fixing shaft 11 is arranged at the bottom of the supporting arm 1 and used for fixing a tire 3; after the arrangement of the structure, the tire 3 is positioned right below the U-shaped frame 2.
The top of the U-shaped frame 2 is provided with a supporting seat 24, the swinging seat 4 is hinged and fixed through the supporting seat 24, and the bottom of the swinging seat is provided with a hinge shaft 43; the bottom of the front end supporting extension section 41 of the swinging seat 4 is provided with an upper support 42, the lower part of the U-shaped frame 2 is provided with an extension seat 23 corresponding to the upper support 42, the extension seat 23 is provided with a lower support 25, a shock absorbing spring 5 is arranged between the upper support 42 and the lower support 25, and the shock absorbing spring 5 is arranged in a vacant groove in the middle of the U-shaped frame 2.
The top of swing seat 4 be provided with bearing sleeve 7, the top of bearing sleeve 7 is provided with fuselage fixing base 8 and is used for realizing and fuselage fixed. Furthermore, a driving sheet 6 is fixed on the swinging seat 4, a plurality of fixing holes are formed in the driving sheet 6 for fixing the swinging seat and an external driving source, and when the swinging seat is fixed by the external driving source, the swinging seat 4 and devices at the lower part of the swinging seat rotate under the bearing sleeve 7 so as to realize steering during ground sliding.
The structure is further improved, and the U-shaped frame 2 is connected with the supporting arm 1 through the fixing block 21 and the reinforcing sheet 22 to reinforce the connecting point.
To summarize: according to the structure, when the tire fixing device is used, the supporting arm 1 is arranged at the bottom of the U-shaped frame 2, and the tire 3 is fixed through the supporting arm 1; be provided with spring 5 of moving away to avoid possible earthquakes on U type frame 2's inside top, spring 5 of moving away to avoid possible earthquakes slope setting, but the articulated swing seat 4 that is provided with vertical wobbling in the top of support arm 1, fixed spring 5 of moving away to avoid possible earthquakes between swing seat 4 and U type frame 2, when receiving the impact in the twinkling of an eye on ground traveling and descending, can also realize the absorption of impact force through shock absorber simultaneously in the realization self swing behind the swing seat 4 atress.
The utility model can effectively improve the driving comfort level and the durability of the workpiece, has novel structure and convenient installation and disassembly, and is an ideal nose landing gear of the aircraft.
Claims (6)
1. An aircraft nose landing gear, comprising: the tire fixing device comprises a U-shaped frame, wherein a supporting arm is vertically arranged on the side part of the U-shaped frame, and a fixing shaft is arranged at the bottom of the supporting arm and used for fixing a tire;
the top of the U-shaped frame is provided with a supporting part, and the swinging seat is hinged and fixed through the supporting part; the front end of the swing seat is provided with an upper support, the lower part of the U-shaped frame is provided with a lower support corresponding to the upper support, and a shock absorption device is arranged between the upper support and the lower support;
the top of the swing seat is provided with a bearing sleeve, and the top of the bearing sleeve is provided with a machine body fixing seat.
2. The aircraft nose landing gear of claim 1, wherein: the swing seat is fixed with a driving sheet, and the driving sheet is provided with a plurality of fixing holes for realizing the fixation with an external driving source.
3. The aircraft nose landing gear of claim 1, wherein: the shock absorbing device is arranged in a hollow groove in the middle of the U-shaped frame.
4. The aircraft nose landing gear of claim 1, wherein: the upper support is arranged at the bottom of the front end of the swinging seat; the lower support is arranged on the extending seat at the rear side of the U-shaped frame.
5. The aircraft nose landing gear of claim 1, wherein: the U-shaped frame and the supporting arm are connected through the fixing block and the reinforcing sheet to reinforce the connecting point.
6. The aircraft nose landing gear of claim 1, wherein: the swing seat is internally provided with a hinged shaft, and the hinged shaft is connected and fixed with the swing seat.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202122551715.4U CN216269880U (en) | 2021-10-22 | 2021-10-22 | Aircraft nose landing gear |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202122551715.4U CN216269880U (en) | 2021-10-22 | 2021-10-22 | Aircraft nose landing gear |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN216269880U true CN216269880U (en) | 2022-04-12 |
Family
ID=81069907
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202122551715.4U Active CN216269880U (en) | 2021-10-22 | 2021-10-22 | Aircraft nose landing gear |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN216269880U (en) |
-
2021
- 2021-10-22 CN CN202122551715.4U patent/CN216269880U/en active Active
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