CN202038452U - Automatic rotating device for wheel of aircraft landing gear - Google Patents
Automatic rotating device for wheel of aircraft landing gear Download PDFInfo
- Publication number
- CN202038452U CN202038452U CN2011201136621U CN201120113662U CN202038452U CN 202038452 U CN202038452 U CN 202038452U CN 2011201136621 U CN2011201136621 U CN 2011201136621U CN 201120113662 U CN201120113662 U CN 201120113662U CN 202038452 U CN202038452 U CN 202038452U
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- Prior art keywords
- ring plate
- wheel
- rotating disk
- end cap
- rotating device
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- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Fee Related
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- 239000000295 fuel oil Substances 0.000 abstract description 2
- 238000003466 welding Methods 0.000 abstract 1
- 230000007812 deficiency Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000009423 ventilation Methods 0.000 description 1
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Abstract
The utility model relates to an automatic rotating device for a wheel of an aircraft landing gear, which comprises a left end cover, an outer ring plate, blades, a rotating disk, an inner ring plate, a rotating shaft and a right end cover. A circle of the blades are uniformly distributed on the rotating disk; the rotating disk and the blades form a rotating impeller; the rotating shaft is installed in the middle of the rotating disk; the left end cover is installed in front of the rotating disk; the outer ring plate and the inner ring plate are welded on the left end cover and form two air inlet channels on the left side; and the right end cover is installed on the outer ring plate and the inner ring plate in a welding manner. After the automatic rotating device is installed on the wheel of the aircraft landing gear, when an aircraft lands and puts the landing gear down, the impeller is driven by the two air inlet channels to rotate due to high aircraft speed, thereby driving the wheel to rotate. Thus, the wheel has a certain speed before being in contact with the ground, so as to greatly improve the landing stability of the aircraft and the service life of the wheel. The automatic rotating device is very convenient to install and needs no fuel oil to provide the power, thereby having wide market space.
Description
Technical field
The utility model relates to a kind of wheel automatic rotating device, and especially a kind of undercarriage wheel automatic rotating device belongs to the air equipment field.
Background technology
Along with deepening constantly of reform, maritime industry develops rapidly, the aircraft quantity that China has is also more and more, but the alighting gear of aircraft still can not rotate automatically, behind the landing kiss the earth, can moment produce huge friction, have a strong impact on the service life of tire, especially on the aviation fighter plane, will bring huge discount to key in technical field herein to the manoevreability of aircraft and describe paragraph.
Summary of the invention
The purpose of this utility model provides a kind of undercarriage wheel automatic rotating device.
Problem to be solved in the utility model is the deficiency that existing undercarriage wheel can not rotate automatically.
For realizing the purpose of this utility model, the technical solution adopted in the utility model is:
The utility model undercarriage wheel automatic rotating device, comprise left end cap, outer ring plate, blade, rotating disk, inner ring plate, turning cylinder and right end cap, be evenly equipped with a circle blade on the rotating disk, rotating disk and blade constitute wheel rotor, in the middle of the rotating disk turning cylinder is installed, the place ahead of rotating disk is equipped with left end cap, is welded with outer ring plate and inner ring plate on the left end cap, outer ring plate and inner ring plate constitute two air intake passages in the left side, right end cap by welded and installed on outer ring plate and inner ring plate.
Blade is selenodont; The height of outer ring plate and inner ring plate is greater than depth of blade 2-5mm; The middle part of right end cap has a circular hole, and the wind energy of entering by ventilation inlet is come out, and the size of right end cap is the same with left end cap; Be evenly equipped with 14-17 sheet blade on the rotating disk.
The utility model has the advantages that: after this device is installed on the undercarriage wheel, when the aircraft landing drop, because the aircraft speed per hour is also very fast, rotate by two air intake passage impeller, thereby drive wheel turns, before the wheel kiss the earth, also had certain speed like this, can improve the stability of aircraft landing and the life-span of wheel greatly, cooresponding convenience is installed, does not need fuel oil that power is provided, should have the market space widely.
Description of drawings
Fig. 1 is the block diagram of the utility model undercarriage wheel automatic rotating device;
Fig. 2 is the front view of the utility model undercarriage wheel automatic rotating device;
Fig. 3 is the left view of the utility model undercarriage wheel automatic rotating device;
Fig. 4 is the scheme drawing of the utility model undercarriage wheel automatic rotating device right end cap;
Among the figure: 1, left end cap 2, outer ring plate 3, blade 4, rotating disk 5, inner ring plate 6, turning cylinder 7, right end cap.
The specific embodiment
Below in conjunction with drawings and Examples the utility model is further described.
As shown in the figure, the utility model undercarriage wheel automatic rotating device, comprise left end cap 1, outer ring plate 2, blade 3, rotating disk 4, inner ring plate 5, turning cylinder 6 and right end cap 7, be evenly equipped with a circle blade 3 on the rotating disk 4, rotating disk 4 and blade 3 constitute wheel rotor, turning cylinder 6 is installed in the middle of the rotating disk 4, the place ahead of rotating disk 4 is equipped with left end cap 1, be welded with outer ring plate 2 and inner ring plate 5 on the left end cap 1, outer ring plate 2 and inner ring plate 5 constitute two air intake passages in the left side, right end cap 7 by welded and installed on outer ring plate 2 and inner ring plate 5.
Blade 3 is selenodont; The height of outer ring plate 2 and inner ring plate 5 is greater than blade 3 height 5mm; The middle part of right end cap 7 has a circular hole, and the size of right end cap 7 is the same with left end cap 1; Be evenly equipped with 15 blades 3 on the rotating disk 4.
Turning cylinder 6 is the turning cylinder of alighting gear wheel, left end cap 1 or right end cap 7 are fixed on the support of alighting gear, after this device is installed on the undercarriage wheel, when the aircraft landing drop, because the aircraft speed per hour is also very fast, rotate by two air intake passage impeller, thereby turning cylinder 6 also and then rotates the drive wheel turns, before the wheel kiss the earth, also had certain speed like this, can improve the stability of aircraft landing and the life-span of wheel greatly.
Claims (5)
1. undercarriage wheel automatic rotating device, comprise left end cap (1), outer ring plate (2), blade (3), rotating disk (4), inner ring plate (5), turning cylinder (6) and right end cap (7), it is characterized in that: be evenly equipped with a circle blade (3) on the rotating disk (4), turning cylinder (6) is installed in the middle of the rotating disk (4), the place ahead of rotating disk (4) is equipped with left end cap (1), be welded with outer ring plate (2) and inner ring plate (5) on the left end cap (1), outer ring plate (2) and inner ring plate (5) constitute two air intake passages in the left side, right end cap (7) by welded and installed on outer ring plate (2) and inner ring plate (5).
2. undercarriage wheel automatic rotating device according to claim 1 is characterized in that: described blade (3) is selenodont.
3. undercarriage wheel automatic rotating device according to claim 1 is characterized in that: the height of described outer ring plate (2) and inner ring plate (5) is greater than blade (3) height 2-5mm.
4. undercarriage wheel automatic rotating device according to claim 1 is characterized in that: the middle part of described right end cap (7) has a circular hole, and the size of right end cap (7) is the same with left end cap (1).
5. undercarriage wheel automatic rotating device according to claim 1 is characterized in that: be evenly equipped with 14-17 sheet blade (3) on the described rotating disk (4).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011201136621U CN202038452U (en) | 2011-04-18 | 2011-04-18 | Automatic rotating device for wheel of aircraft landing gear |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011201136621U CN202038452U (en) | 2011-04-18 | 2011-04-18 | Automatic rotating device for wheel of aircraft landing gear |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN202038452U true CN202038452U (en) | 2011-11-16 |
Family
ID=44965910
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2011201136621U Expired - Fee Related CN202038452U (en) | 2011-04-18 | 2011-04-18 | Automatic rotating device for wheel of aircraft landing gear |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN202038452U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102180261A (en) * | 2011-04-18 | 2011-09-14 | 浙江海洋学院 | Autorotation device of aircraft landing gear wheel |
-
2011
- 2011-04-18 CN CN2011201136621U patent/CN202038452U/en not_active Expired - Fee Related
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102180261A (en) * | 2011-04-18 | 2011-09-14 | 浙江海洋学院 | Autorotation device of aircraft landing gear wheel |
| CN102180261B (en) * | 2011-04-18 | 2013-04-10 | 浙江海洋学院 | Autorotation device of aircraft landing gear wheel |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C17 | Cessation of patent right | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20111116 Termination date: 20120418 |