CN201217500Y - Bionic aircraft airfoil - Google Patents
Bionic aircraft airfoil Download PDFInfo
- Publication number
- CN201217500Y CN201217500Y CNU2008200773298U CN200820077329U CN201217500Y CN 201217500 Y CN201217500 Y CN 201217500Y CN U2008200773298 U CNU2008200773298 U CN U2008200773298U CN 200820077329 U CN200820077329 U CN 200820077329U CN 201217500 Y CN201217500 Y CN 201217500Y
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- CN
- China
- Prior art keywords
- wing
- aircraft
- body frame
- main frame
- bionic
- 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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Abstract
A bionic aircraft wing belongs to the technical field of aircraft wings and structurally comprises a main frame of the wing and a wing support frame connected with the aircraft body. The utility model is characterized in that the main frame of the wing is a plate-shaped structure; resistance-reducing holes are penetrated and arranged on the upper and lower surfaces of the main frame of the wing; a vane is hinged in each resistance-reducing hole through a vane shaft; the main frame of the wing is hinged with the wing support frame through a main shaft of the wing fixed on the lateral side of the main frame of the wing; when the main frame of the wing swings upward or downward, the vanes can be automatically opened or closed to change the wind resistance of the wing; the wing support frame can adjust the angle through a control mechanism of the aircraft, so as to adjust the angle of the main frame of the wing and control the flight attitude of the aircraft; moreover, the bionic aircraft wing enables the aircraft to be quickly lifted and landed and fly smoothly, flexibly and safely.
Description
Technical field
The utility model relates to a kind of bionic Aircraft wing, and particularly a kind of bionic Aircraft wing that is applicable to small aircraft belongs to the aircraft wing technical field.
Background technology
Existing small aircraft wing is the solid shape wing, its flight lift rely on body forward high-speed cruising and produce, taking off and landing of branch's device needs long runway.
Summary of the invention
The utility model technical issues that need to address provide a kind of bionic Aircraft wing, make the action of aircraft simulation birds realize taking off, fly and landing of aircraft.
For solving the problems of the technologies described above, the technical scheme that the utility model adopted is:
The bionic Aircraft wing, structure comprises, the wing body frame reaches and aircraft body bonded assembly wing bracing frame, the wing body frame is a platy structure, run through wing body frame upper and lower surface and offer the drag reduction hole, by the sharf hinged blades, the wing body frame is hinged by the wing main shaft and the wing bracing frame that are fixed on wing body frame side in the drag reduction hole.
The further improvement of the utility model concrete structure is: the wing spindle nose is provided with star coupling; Drag reduction hole inner edge is provided with the sealing cushion blocking; Be connected by bearing between sharf and the blade; At wing body frame end face blade angle of release control stalk is set.
Because the technological advance that has adopted technique scheme, the utility model to obtain is:
On the wing body frame of the bionic Aircraft wing that the utility model provides drag reduction hole and blade are set, when the wing body frame is swung up or down, blade is opened automatically or is closed, change the wing windage, the wing bracing frame can be adjusted its angle by the control mechanism of aircraft, thereby adjusts wing body frame angle, controlling aircraft flight attitude, the bionic Aircraft wing can make aircraft hoist fast, land, have a smooth flight, flexibly, safety.
The wing spindle nose is provided with star coupling, and the star coupling outer end can connect the aircraft power part wing is driven.
Drag reduction hole inner edge is provided with the sealing cushion blocking, can improve the leak tightness of blade and wing body frame, reduces bump.Be connected by bearing between sharf and the blade, but drag-reduction energy-saving.
Wing body frame end face is provided with blade angle of release control stalk, and the controllable blade angle of release is realized blade folding automatically smoothly.
Description of drawings
Fig. 1 is a bionic Aircraft wing structure signal axonometric drawing.
Wherein: 1, wing body frame, 2, blade, 3, blade angle of release control stalk, 4, star coupling, 5, the wing bracing frame, 6, the wing main shaft, 7, sharf, 8, the drag reduction hole, 9, the sealing cushion blocking.
The specific embodiment
Below in conjunction with accompanying drawing the utility model is described in further details:
Shown in Figure 1, the utility model structure comprises, wing body frame 1 reaches and aircraft body bonded assembly wing bracing frame 5, wing body frame 1 is a platy structure, run through wing body frame 1 upper and lower surface and offer drag reduction hole 8, drag reduction hole 8 inner edges are provided with sealing cushion blocking 9, pass through sharf 7 hinged blades 2 in the drag reduction hole 8, cooperate and to cooperate by bearing between sharf 7 and the blade 2, the wing main shaft 6 of wing body frame 1 by being fixed on wing body frame 1 side is hinged with wing bracing frame 5, wing body frame 1 end face and the wing body frame blade angle of release control stalk 3 that be arranged in parallel.
Wing main shaft 6 ends are provided with star coupling 4, and star coupling 4 outer ends can connect the aircraft power part wing is driven; Also can be parallel to wing main shaft 6 revolute pair articulated linkage mechanism is set, drive wing body frame 1 by connecting rod mechanism and swing up and down at wing body frame 1 upper surface or lower surface.
The forward and reverse driving wing of aircraft power body frame 1, making wing body frame 1 is that the center swings up and down with wing main shaft 6, resemble the wing of bird, when wing body frame 1 is upwards swung, blade 2 on the wing body frame 1 is opened automatically, reduce air resistance, when wing body frame 1 during to lower swing, blade 2 auto-closings on the wing body frame 1, produce air resistance, the swing fast up and down of wing body frame 1, aircraft is hoisted fast, and wing bracing frame 5 can be adjusted angle by the control mechanism of aircraft, thereby adjusts wing body frame 1 angle, the controlling aircraft flight attitude, the size of blade 2, quantity and wing body frame 1 size shape, the position of sharf 7 and quantity all can specifically be determined according to different aircraft.
Under motorless situation, the decline rapidly of aircraft can make blade 2 auto-closings, and wing can play parachute.
Claims (5)
1, a kind of bionic Aircraft wing, its structure comprises, the wing body frame reaches and aircraft body bonded assembly wing bracing frame, it is characterized in that: the wing body frame is a platy structure, run through wing body frame upper and lower surface and offer the drag reduction hole, by the sharf hinged blades, the wing body frame is hinged by the wing main shaft and the wing bracing frame that are fixed on wing body frame side in the drag reduction hole.
2, bionic Aircraft wing according to claim 1 is characterized in that described wing spindle nose is provided with star coupling.
3, bionic Aircraft wing according to claim 1 is characterized in that described drag reduction hole inner edge is provided with the sealing cushion blocking.
4, bionic Aircraft wing according to claim 1 is characterized in that being connected by bearing between described sharf and the blade.
5, bionic Aircraft wing according to claim 1 is characterized in that described wing body frame end face is provided with blade angle of release control stalk.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNU2008200773298U CN201217500Y (en) | 2008-05-26 | 2008-05-26 | Bionic aircraft airfoil |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNU2008200773298U CN201217500Y (en) | 2008-05-26 | 2008-05-26 | Bionic aircraft airfoil |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN201217500Y true CN201217500Y (en) | 2009-04-08 |
Family
ID=40540334
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CNU2008200773298U Expired - Fee Related CN201217500Y (en) | 2008-05-26 | 2008-05-26 | Bionic aircraft airfoil |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN201217500Y (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105035290A (en) * | 2015-07-02 | 2015-11-11 | 哈尔滨工程大学 | Bionic propulsion device capable of backing up underwater |
| CN107933880A (en) * | 2017-12-06 | 2018-04-20 | 徐航 | A kind of wing structure of aircraft |
-
2008
- 2008-05-26 CN CNU2008200773298U patent/CN201217500Y/en not_active Expired - Fee Related
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105035290A (en) * | 2015-07-02 | 2015-11-11 | 哈尔滨工程大学 | Bionic propulsion device capable of backing up underwater |
| CN105035290B (en) * | 2015-07-02 | 2017-06-20 | 哈尔滨工程大学 | A kind of bionic coatings device that can be moveed backward under water |
| CN107933880A (en) * | 2017-12-06 | 2018-04-20 | 徐航 | A kind of wing structure of 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: 20090408 Termination date: 20100526 |