CN202147840U - Wing with adjustable radian - Google Patents
Wing with adjustable radian Download PDFInfo
- Publication number
- CN202147840U CN202147840U CN201120173320U CN201120173320U CN202147840U CN 202147840 U CN202147840 U CN 202147840U CN 201120173320 U CN201120173320 U CN 201120173320U CN 201120173320 U CN201120173320 U CN 201120173320U CN 202147840 U CN202147840 U CN 202147840U
- Authority
- CN
- China
- Prior art keywords
- wing
- rear end
- keel
- hydraulic mandril
- aircraft
- 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
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- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
Abstract
A wing with an adjustable radian comprises a front end wing, a keel, a hydraulic mandril, a control device and a rear end wing, wherein the front and the rear end wings are the main body piece of the wing; the upper surface of the whole main body piece is an arc surface; the lower surface of the whole main body piece is a flat surface; the control device is arranged below the joint of the front and the rear end wings; the hydraulic mandril is arranged in the center of the joint of the front and the rear end wings; the keel is arranged above the joint of the front and the rear end wings; the upper end of the keel is flush with the upper surfaces of the front and the rear end wings; the hydraulic mandril is arranged below the keel; overall, the keel is the main body support piece of the hydraulic mandril; and the control device is arranged below the hydraulic mandril. The utility model has the advantages of simple integral structure, convenience in operation and use and high reliability. As the wing adopts the adjustable-radian structural style, the flexibility of an aircraft is improved; the flying cost of the aircraft is reduced; and the reliability of the aircraft is improved.
Description
Technical field
The utility model relates to aircraft wing, relates in particular to the adjustable wing of radian.
Background technology
Aircraft relies on wing to obtain lift; And lifting force of wings is utilized bernoulli principle and obtain; Therefore, the wing profile of aircraft generally adopts under the epirelief flat structure, this wing in air during motion windstream different through the speed of aerofoil upper and lower surfaces; And thereby produce difference of pressure, just lift is provided for aircraft.The wing wing-shaped structure of prior art is complicated, and productive costs is higher, and the overall radian of wing adopts uncontrollable structure, has influenced the lift demand under the different needs condition, has therefore also just strengthened the flight cost of aircraft.
The utility model content
The purpose of the utility model is, overcomes the weak point of prior art, provides a kind of radian adjustable wing, adopts the adjustable version of wing radian, and the alerting ability of aircraft is provided, and reduces the flight expense of aircraft, improves the reliability of aircraft.
The adjustable wing of the described radian of the utility model includes the front end wing, keel, hydraulic mandril, control setup and the rear end wing and forms.The front end wing and the rear end wing are the main components of the utility model, and it is the radian face that integral body is presented the plane, and lower plane is the structure of flat face; In the position that the front end wing is connected with the rear end wing; Be arranged with control setup, be provided with hydraulic mandril between two parties, be provided with keel.The last plane of the upper end of keel and the front end wing and the rear end wing maintains an equal level, and is provided with hydraulic mandril below the keel, says that on the whole keel are body supports parts of hydraulic mandril, below the hydraulic mandril, is provided with control setup.
The adjustable wing of the described radian of the utility model, integral structure is simple, and is easy for operation, good stability, reliability is high.The utility model adopts the adjustable version of wing radian, and the alerting ability of aircraft is provided, and reduces the flight expense of aircraft, improves the reliability of aircraft.
Description of drawings
Accompanying drawing 1 is the overall structure scheme drawing of the adjustable wing of the said radian of the utility model; Accompanying drawing 2 is structural representations of overlooking state.1-front end wing, 2-keel, 3-hydraulic mandril, 4-control setup, 5-rear end wing.
The specific embodiment
Existing with reference to accompanying drawing 1, explain as follows in conjunction with embodiment: the adjustable wing of the described radian of the utility model includes the front end wing 1, keel 2, hydraulic mandril 3, control setup 4 and the rear end wing 5 and forms.The front end wing 1 is main components of the utility model with the rear end wing 5, and it is the radian face that integral body is presented the plane, and lower plane is the structure of flat face; In the position that the front end wing 1 is connected with the rear end wing 5; Being arranged with control setup 4, be provided with hydraulic mandril 3 between two parties, be provided with keel 2.The last plane of the upper end of keel 2 and the front end wing 1 and the rear end wing 5 is fair, is provided with hydraulic mandril 3 below the keel 2, says that on the whole keel 2 are body supports parts of hydraulic mandril 3, below the hydraulic mandril 3, is provided with control setup 4.The adjustable wing of the described radian of the utility model, integral structure is simple, and is easy for operation, good stability, reliability is high.The utility model adopts the adjustable version of wing radian, and the alerting ability of aircraft is provided, and reduces the flight expense of aircraft, improves the reliability of aircraft.
Claims (1)
1. the adjustable wing of radian; The front end wing (1) and the rear end wing (5) are main components, and it is the radian face that integral body is presented the plane, and lower plane is the structure of flat face; It is characterized in that the position that is connected with the rear end wing (5) at the front end wing (1); Be arranged with control setup (4), be provided with hydraulic mandril (3) between two parties, be provided with keel (2); The last plane of the upper end of keel (2) and the front end wing (1) and the rear end wing (5) maintains an equal level.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201120173320U CN202147840U (en) | 2011-05-27 | 2011-05-27 | Wing with adjustable radian |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201120173320U CN202147840U (en) | 2011-05-27 | 2011-05-27 | Wing with adjustable radian |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN202147840U true CN202147840U (en) | 2012-02-22 |
Family
ID=45588908
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201120173320U Expired - Fee Related CN202147840U (en) | 2011-05-27 | 2011-05-27 | Wing with adjustable radian |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN202147840U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105346705A (en) * | 2015-12-11 | 2016-02-24 | 刘文浩 | Self-adaptive wing with variable wing surface curvature and control manner of aircraft thereof |
| CN110539876A (en) * | 2019-09-03 | 2019-12-06 | 中国航空工业集团公司西安飞机设计研究所 | Variable airfoil wing and aircraft |
-
2011
- 2011-05-27 CN CN201120173320U patent/CN202147840U/en not_active Expired - Fee Related
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105346705A (en) * | 2015-12-11 | 2016-02-24 | 刘文浩 | Self-adaptive wing with variable wing surface curvature and control manner of aircraft thereof |
| CN110539876A (en) * | 2019-09-03 | 2019-12-06 | 中国航空工业集团公司西安飞机设计研究所 | Variable airfoil wing and aircraft |
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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: 20120222 Termination date: 20120527 |