CN104986326A - Vibration reduction undercarriage of aircraft - Google Patents
Vibration reduction undercarriage of aircraft Download PDFInfo
- Publication number
- CN104986326A CN104986326A CN201510246113.4A CN201510246113A CN104986326A CN 104986326 A CN104986326 A CN 104986326A CN 201510246113 A CN201510246113 A CN 201510246113A CN 104986326 A CN104986326 A CN 104986326A
- Authority
- CN
- China
- Prior art keywords
- aircraft
- alighting gear
- undercarriage
- vibration reduction
- present
- 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.)
- Pending
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Abstract
The invention relates to a vibration reduction undercarriage of an aircraft. The vibration reduction undercarriage is installed on an aircraft support. The vibration reduction undercarriage comprises an undercarriage body with the annular section. The undercarriage body is sleeved with at least four rubber rings. During working, the undercarriage body is fixed to the bottom of the support. According to the vibration reduction undercarriage of the aircraft, rubber is installed on the aircraft so that the vibration reduction effect is achieved and the deformation of a rack is avoided, and therefore the service life of the aircraft is prolonged.
Description
Technical field
The present invention relates to aircraft field, refer 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.
Summary of the invention
The present invention seeks to provide 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 used in the present invention 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 present invention compared with prior art has following advantages:
Aircraft damping alighting gear of the present invention, 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 solution of the present invention is described further:
Accompanying drawing 1 is the front view of aircraft damping alighting gear of the present invention;
Accompanying drawing 2 is the birds-eye view of aircraft damping alighting gear of the present invention;
Wherein: 1, alighting gear; 2, support; 3, rubber ring.
Detailed description of the invention
Below in conjunction with drawings and the specific embodiments, the present invention is described in further detail.
Accompanying drawing 1-2 is aircraft damping alighting gear of the present invention, 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 present invention compared with prior art has following advantages:
Aircraft damping alighting gear of the present invention, 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 invention, protection scope of the present invention is not constituted any limitation.The technical scheme that all employing equivalents or equivalence are replaced and formed, all drops within rights protection scope of the present invention.
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 |
|---|---|---|---|
| CN201510246113.4A CN104986326A (en) | 2015-05-14 | 2015-05-14 | Vibration reduction undercarriage of aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510246113.4A CN104986326A (en) | 2015-05-14 | 2015-05-14 | Vibration reduction undercarriage of aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN104986326A true CN104986326A (en) | 2015-10-21 |
Family
ID=54298259
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510246113.4A Pending CN104986326A (en) | 2015-05-14 | 2015-05-14 | Vibration reduction undercarriage of aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN104986326A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117734991A (en) * | 2024-02-21 | 2024-03-22 | 福建创享蓝途科技发展有限公司 | Foldable unmanned aerial vehicle buffering support and unmanned aerial vehicle thereof |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5224669A (en) * | 1991-05-06 | 1993-07-06 | Aerospatiale Societe Nationale Industrielle | Landing gear for an aerodyne, with arches in composite material |
| CN101417707A (en) * | 2008-01-08 | 2009-04-29 | 上海大学 | Attitude-variable flying robot |
| FR2992289A1 (en) * | 2012-06-26 | 2013-12-27 | Eurocopter France | Landing gear for aircraft, has supporting unit including bearing and elevation portions, and footboards extending from elevated portion to be fixed to rear and front cross elements for connecting front cross element to rear cross element |
| CN203727649U (en) * | 2014-03-13 | 2014-07-23 | 中国科学院沈阳自动化研究所 | Drug-applying unmanned helicopter |
| CN104443416A (en) * | 2014-12-29 | 2015-03-25 | 马鞍山市赛迪智能科技有限公司 | Unmanned aerial vehicle in-the-air illuminating system |
| CN204871589U (en) * | 2015-05-14 | 2015-12-16 | 苏州绿农航空植保科技有限公司 | Aircraft shock attenuation undercarriage |
-
2015
- 2015-05-14 CN CN201510246113.4A patent/CN104986326A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5224669A (en) * | 1991-05-06 | 1993-07-06 | Aerospatiale Societe Nationale Industrielle | Landing gear for an aerodyne, with arches in composite material |
| CN101417707A (en) * | 2008-01-08 | 2009-04-29 | 上海大学 | Attitude-variable flying robot |
| FR2992289A1 (en) * | 2012-06-26 | 2013-12-27 | Eurocopter France | Landing gear for aircraft, has supporting unit including bearing and elevation portions, and footboards extending from elevated portion to be fixed to rear and front cross elements for connecting front cross element to rear cross element |
| CN203727649U (en) * | 2014-03-13 | 2014-07-23 | 中国科学院沈阳自动化研究所 | Drug-applying unmanned helicopter |
| CN104443416A (en) * | 2014-12-29 | 2015-03-25 | 马鞍山市赛迪智能科技有限公司 | Unmanned aerial vehicle in-the-air illuminating system |
| CN204871589U (en) * | 2015-05-14 | 2015-12-16 | 苏州绿农航空植保科技有限公司 | Aircraft shock attenuation undercarriage |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117734991A (en) * | 2024-02-21 | 2024-03-22 | 福建创享蓝途科技发展有限公司 | Foldable unmanned aerial vehicle buffering support and unmanned aerial vehicle thereof |
| CN117734991B (en) * | 2024-02-21 | 2024-05-03 | 福建创享蓝途科技发展有限公司 | Foldable unmanned aerial vehicle buffering support and unmanned aerial vehicle thereof |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20151021 |