CN203486136U - Variable cross-section spring steel plate type landing gear - Google Patents
Variable cross-section spring steel plate type landing gear Download PDFInfo
- Publication number
- CN203486136U CN203486136U CN201320432266.4U CN201320432266U CN203486136U CN 203486136 U CN203486136 U CN 203486136U CN 201320432266 U CN201320432266 U CN 201320432266U CN 203486136 U CN203486136 U CN 203486136U
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- Prior art keywords
- steel plate
- spring steel
- wheel
- landing gear
- plate type
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- Expired - Fee Related
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- 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
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Abstract
The utility model discloses a variable cross-section spring steel plate type landing gear which consists of a spring steel plate (1), an axle (2), a brake device (3), a brake mounting base (4), a wheel (5) and a tire (6), wherein the spring steel plate (1) is mounted on one side of the axle (2) through a group of bolts; the brake device (3) is arranged on the axle (2) through the brake mounting base (4); the wheel (5) is arranged on the other side of the axle (2); the tire (6) is arranged on the wheel (5). The variable cross-section spring steel plate type landing gear has the advantages that the structure is simple, not only are requirements on bearing strength and transmission force of functions and reasonable structures of a light type aircraft landing gear met, but also the capability that the landing gear absorbs the collision energy generated when the aircraft lands and slides is greatly improved, so that the load that a machine structure bears is reduced, and the weight of the aircraft is reduced.
Description
Technical field
The utility model patent relates to the take-off and landing device field of aviette device, is specifically related to a kind of tapered spring steel plate type take-off and landing device.
Background technology
At present, take-off and landing device is mainly used in parking, sliding and run, take off and land of aircraft.The take-off and landing device of existing lightweight aircraft is framework type take-off and landing device, mainly mounting pipe, brake gear, brake mount pad, wheel and tire, consists of, and its weak point is that damping performance is very poor, and occupant's comfort level is very low; Simultaneously due to take-off and landing device in aircraft lands process absorbs and consume energy seldom, the load increase that housing construction will be born, the significantly increase that thereupon brings housing construction weight.
Summary of the invention
Take-off and landing device is mainly used in parking, sliding and run, take off and land of aircraft.The take-off and landing device of existing lightweight aircraft is framework type take-off and landing device, mainly mounting pipe, brake gear, brake mount pad, wheel and tire, consists of, and its weak point is that damping performance is very poor, and occupant's comfort level is very low; Simultaneously due to take-off and landing device in aircraft lands process absorbs and consume energy seldom, the load increase that housing construction will be born, the significantly increase that thereupon brings housing construction weight.The purpose of this utility model is exactly for the above-mentioned deficiency of existing lightweight aircraft take-off and landing device, and a kind of tapered spring steel plate type take-off and landing device is provided.
The utility model is comprised of spring plate, wheel axle, brake gear, brake mount pad and wheel and tire, spring plate is arranged on a side of wheel axle by one group of bolt, brake gear is arranged on wheel axle by brake mount pad, wheel is arranged on the opposite side of wheel axle, and tire is loaded on wheel.
Spring plate width is 70-80 millimeter by 150-160 millimeter even variation, and thickness is 10-12 millimeter by 16-18 millimeter even variation.
The angle of spring plate and horizontal surface is 8-12 °.
Tire and horizontal surface vertical angle are 4-6 °.
The utility model advantage is: simple in structure, the function of lightweight aircraft take-off and landing device and load, power transmission requirement rational in infrastructure have not only been met, and the ability of Impact energy when having increased substantially take-off and landing device and absorbing aircraft lands and sliding race, thereby reduced the load that housing construction will bear, reduced the weight of aircraft.
accompanying drawing explanation
Fig. 1 is the utility model structural representation.
Fig. 2 is the plan structure schematic diagram of Fig. 1.
The specific embodiment
As shown in Figure 1, the utility model is comprised of spring plate 1, wheel axle 2, brake gear 3, brake mount pad 4 and wheel 5 and tire 6, spring plate 1 is arranged on a side of wheel axle 2 by one group of bolt, brake gear 3 is arranged on wheel axle 2 by brake mount pad 4, wheel 5 is arranged on the opposite side of wheel axle 2, and tire 6 is loaded on wheel 5.
The angle α of spring plate 1 and horizontal surface
1for 8-12 °.
Tire 6 and horizontal surface vertical angle α
2for 4-6 °.
Claims (4)
1.
a kind of tapered spring steel plate type take-off and landing deviceit is characterized in that it is comprised of spring plate (1), wheel axle (2), brake gear (3), brake mount pad (4) and wheel (5) and tire (6), spring plate (1) is arranged on a side of wheel axle (2) by one group of bolt, brake gear (3) is arranged on wheel axle (2) by brake mount pad (4), wheel (5) is arranged on the opposite side of wheel axle (2), and tire (6) is loaded on wheel (5).
2. a kind of tapered spring steel plate type take-off and landing device according to claim 1, is characterized in that spring plate (1) width is 70-80 millimeter by 150-160 millimeter even variation, and thickness is 10-12 millimeter by 16-18 millimeter even variation.
3. a kind of tapered spring steel plate type take-off and landing device according to claim 1, is characterized in that the angle (α of spring plate (1) and horizontal surface
1) be 8-12 °.
4. a kind of tapered spring steel plate type take-off and landing device according to claim 1, is characterized in that tire (6) and horizontal surface vertical angle (α
2) be 4-6 °.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320432266.4U CN203486136U (en) | 2013-07-20 | 2013-07-20 | Variable cross-section spring steel plate type landing gear |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320432266.4U CN203486136U (en) | 2013-07-20 | 2013-07-20 | Variable cross-section spring steel plate type landing gear |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203486136U true CN203486136U (en) | 2014-03-19 |
Family
ID=50256982
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201320432266.4U Expired - Fee Related CN203486136U (en) | 2013-07-20 | 2013-07-20 | Variable cross-section spring steel plate type landing gear |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN203486136U (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107244412A (en) * | 2017-06-12 | 2017-10-13 | 西北工业大学 | A kind of undercarriage plate spring structure for being used to lift UAV Landing shock-absorbing capacity |
| CN108557057A (en) * | 2018-06-11 | 2018-09-21 | 通航国际（西安）飞机技术有限公司 | A kind of aircraft main landing gear |
| CN111645853A (en) * | 2020-06-08 | 2020-09-11 | 中航飞机起落架有限责任公司 | Aircraft undercarriage |
| CN114408168A (en) * | 2021-12-30 | 2022-04-29 | 中国特种飞行器研究所 | Light low-resistance composite plate spring type landing gear |
-
2013
- 2013-07-20 CN CN201320432266.4U patent/CN203486136U/en not_active Expired - Fee Related
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107244412A (en) * | 2017-06-12 | 2017-10-13 | 西北工业大学 | A kind of undercarriage plate spring structure for being used to lift UAV Landing shock-absorbing capacity |
| CN107244412B (en) * | 2017-06-12 | 2019-06-04 | 西北工业大学 | It is a kind of for promoting the undercarriage plate spring structure of UAV Landing cushion performance |
| CN108557057A (en) * | 2018-06-11 | 2018-09-21 | 通航国际（西安）飞机技术有限公司 | A kind of aircraft main landing gear |
| CN111645853A (en) * | 2020-06-08 | 2020-09-11 | 中航飞机起落架有限责任公司 | Aircraft undercarriage |
| CN114408168A (en) * | 2021-12-30 | 2022-04-29 | 中国特种飞行器研究所 | Light low-resistance composite plate spring type landing gear |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20140319 Termination date: 20190720 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |