CN204871589U - Aircraft shock attenuation undercarriage - Google Patents
Aircraft shock attenuation undercarriage Download PDFInfo
- Publication number
- CN204871589U CN204871589U CN201520311395.7U CN201520311395U CN204871589U CN 204871589 U CN204871589 U CN 204871589U CN 201520311395 U CN201520311395 U CN 201520311395U CN 204871589 U CN204871589 U CN 204871589U
- Authority
- CN
- China
- Prior art keywords
- aircraft
- alighting gear
- utility
- model
- undercarriage
- Prior art date
- 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
Links
Abstract
The utility model relates to an aircraft shock attenuation undercarriage installs on the aircraft support, contains the cross -section and is annular undercarriage, the cover is equipped with four at least rubber circles on the undercarriage, in operation, the bottom at the support is fixed to the undercarriage, the utility model discloses an install rubber on the aircraft, play the shock attenuation effect, prevent stand stretch to the life of aircraft has been improved.
Description
Technical field
The utility model relates to aircraft field, refers in particular to a kind of aircraft damping alighting gear.
Background technology
In recent years, aircraft quietly rises, and domestic now existing many enterprises carry out development & production to electronic multi-rotor aerocraft, and in existing electronic many rotors, alighting gear is without shock absorption device, body, stand stretch is damaged when easily causing aircraft to land, decrease the service life of aircraft, for this reason, we have developed a kind of aircraft damping alighting gear, by installing rubber on board the aircraft, play damping effect, prevent stand stretch, thus improve the service life of aircraft.
Utility model content
The utility model object provides a kind of aircraft damping alighting gear to overcome the deficiencies in the prior art, by installing rubber on board the aircraft, playing damping effect, preventing stand stretch, thus improve the service life of aircraft.
For achieving the above object, the technical solution adopted in the utility model is: a kind of aircraft damping alighting gear, is arranged on aircraft parking stand, comprises the alighting gear of ring-shaped section and ring-shaped; Described alighting gear is arranged with at least four rubber rings; During work, described alighting gear is fixed on the bottom of support.
Preferably, the rubber ring on described alighting gear circumferentially distributes.
Due to the utilization of technique scheme, the utility model compared with prior art has following advantages:
Aircraft damping alighting gear described in the utility model, by installing rubber on board the aircraft, plays damping effect, prevents stand stretch, thus improve the service life of aircraft.
Accompanying drawing explanation
Below in conjunction with accompanying drawing, technical solutions of the utility model are described further:
Accompanying drawing 1 is the front view of aircraft damping alighting gear described in the utility model;
Accompanying drawing 2 is the birds-eye view of aircraft damping alighting gear described in the utility model;
Wherein: 1, alighting gear; 2, support; 3, rubber ring.
Detailed description of the invention
Below in conjunction with drawings and the specific embodiments, the utility model is described in further detail.
Accompanying drawing 1-2 is aircraft damping alighting gear described in the utility model, is arranged on aircraft parking stand 2, comprises the alighting gear 1 of ring-shaped section and ring-shaped; Described alighting gear 1 is arranged with 8 rubber rings circumferentially distributed 3; During work, described alighting gear 1 is fixed by welding in bottom the support 2 of four circle distribution.
Due to the utilization of technique scheme, the utility model compared with prior art has following advantages:
Aircraft damping alighting gear described in the utility model, by installing rubber on board the aircraft, plays damping effect, prevents stand stretch, thus improve the service life of aircraft.
Below be only embody rule example of the present utility model, protection domain of the present utility model is not constituted any limitation.The technical scheme that all employing equivalents or equivalence are replaced and formed, all drops within the utility model rights protection scope.
Claims (2)
1. an aircraft damping alighting gear, is characterized in that: be arranged on aircraft parking stand, comprises the alighting gear of ring-shaped section and ring-shaped; Described alighting gear is arranged with at least four rubber rings; During work, described alighting gear is fixed on the bottom of support.
2. aircraft damping alighting gear according to claim 1, is characterized in that: the rubber ring on described alighting gear circumferentially distributes.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520311395.7U CN204871589U (en) | 2015-05-14 | 2015-05-14 | Aircraft shock attenuation undercarriage |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520311395.7U CN204871589U (en) | 2015-05-14 | 2015-05-14 | Aircraft shock attenuation undercarriage |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN204871589U true CN204871589U (en) | 2015-12-16 |
Family
ID=54815994
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201520311395.7U Expired - Fee Related CN204871589U (en) | 2015-05-14 | 2015-05-14 | Aircraft shock attenuation undercarriage |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN204871589U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104986326A (en) * | 2015-05-14 | 2015-10-21 | 苏州绿农航空植保科技有限公司 | Vibration reduction undercarriage of aircraft |
| CN106379539A (en) * | 2016-11-09 | 2017-02-08 | 北京工业大学 | Aircraft underframe with conveying function |
| CN106516120A (en) * | 2016-11-09 | 2017-03-22 | 北京工业大学 | Aircraft underframe with function of delivering goods |
-
2015
- 2015-05-14 CN CN201520311395.7U patent/CN204871589U/en not_active Expired - Fee Related
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104986326A (en) * | 2015-05-14 | 2015-10-21 | 苏州绿农航空植保科技有限公司 | Vibration reduction undercarriage of aircraft |
| CN106379539A (en) * | 2016-11-09 | 2017-02-08 | 北京工业大学 | Aircraft underframe with conveying function |
| CN106516120A (en) * | 2016-11-09 | 2017-03-22 | 北京工业大学 | Aircraft underframe with function of delivering goods |
| CN106379539B (en) * | 2016-11-09 | 2019-09-27 | 北京工业大学 | A kind of aircraft chassis with delivery functions |
| CN106516120B (en) * | 2016-11-09 | 2020-01-17 | 北京工业大学 | Aircraft chassis with transport article function |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20151216 Termination date: 20200514 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |