CN2918218Y - Foldaway two-section-type wings for ornithopter - Google Patents
Foldaway two-section-type wings for ornithopter Download PDFInfo
- Publication number
- CN2918218Y CN2918218Y CN 200520142064 CN200520142064U CN2918218Y CN 2918218 Y CN2918218 Y CN 2918218Y CN 200520142064 CN200520142064 CN 200520142064 CN 200520142064 U CN200520142064 U CN 200520142064U CN 2918218 Y CN2918218 Y CN 2918218Y
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- CN
- China
- Prior art keywords
- wing
- skeleton
- segment
- fuselage
- flapping
- 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
The utility model relates to a two-segment ornithopter wing, comprising an inner wing segment and an outer wing segment which can be folded symmetrically. A transmission crankshaft is connected with a pull rod, the pull rod traverses the top of the inner wing segment skeleton in the fuselage, and outward is connected with the vertex of an extend segment, which is a segment of the outer wing segment over the junction of the inner and outer wing segment, in the way, the pull rod is driven by the circular motion of the transmission crankshaft, the outer wing segment skeleton is pulled by the pull rod and in the lever motion with the fulcrum which is a junction of the inner and outer wing segment, the inner wing segment skeleton is also in the lever motion synchronously with the fulcrum which is the junction of the inner wing segment and the fuselage, making the flutter of wing look like the motion state of the bird wing very much.
Description
Technical field
The utility model belongs to all purpose aircraft field, relates to a kind of wing structure of flapping-wing aircraft.
Background technology
The research of flapping-wing aircraft all is the straight wing of using as the hard wing of insect at present, though this wing is simple in structure, easy to use, load capacity is poor.For complete machine, the work efficiency ratio, flight stability is bad.
Summary of the invention
In order to change the shortcoming of flapping-wing aircraft work efficiency than low and load capacity difference, the utility model provides a kind of flapping-wing aircraft wing of real wing as bird, and this wing can be as the fluttering of bird, on when lifting, outer wing is sagging; Under when pouncing on, outer wing launches.
During scheme that the straight-winged problem that solves the utility model adopts, wing is divided into two sections, is interior wing panel and outer panel, but interior outer panel doubling.Be connected with interior wing panel skeleton with interior wing panel in the middle of the outer panel skeleton, outer panel skeleton extension summit links to each other with pull bar fuselage outer dead centre.Interior wing panel skeleton intermediate point is connected with fuselage.The summit of wing panel frame machine body inner segment in the pull bar intermediate point connects in fuselage, pull bar fuselage inner vertex is connected to driving crank.
The beneficial effects of the utility model are, make flapping-wing aircraft more as the flight of bird, and the interior outer panel that can roll over can make when lifting on the wing resistance littler, produces bigger lift downwards when brandishing.Can make flapping-wing aircraft can carry more load like this, and work efficiency is than bigger.
Description of drawings
The utility model is described in further detail below in conjunction with accompanying drawing:
Fig. 1 is the left side wing skeleton, and bent axle is in the view of vertex position;
Fig. 2 is the left side wing skeleton, and bent axle is in the view of left-most position;
Fig. 3 is the left side wing skeleton, and bent axle is in the view of lowest position;
Fig. 4 is the left side wing skeleton, and bent axle is in the view of right-most position.
1. outer panel skeletons among the figure, 2. interior outer panel skeleton point of connection, 3. the inside extension of outer panel skeleton, 4. interior wing panel skeleton, the point of connection of 5. interior wing panel skeleton and fuselage, 6. pull bar, 7. the point of connection of pull bar and outer panel skeleton extension, 8. pull bar and interior wing panel skeleton one section point of connection in fuselage, 9. bent axle, the 10. point of connection of pull bar and bent axle.
The specific embodiment
Among the figure, pull bar 6 one ends are connected on the point of connection 10 of bent axle 9, and pull bar 6 outwards at first passes and interior wing panel skeleton point of connection 8 of one section in fuselage, and the pull bar other end connects the point of connection 7 with outer panel skeleton extension 3.Like this, when pull bar 6 was made circular movement with bent axle 9, wing panel skeleton 4 was that fulcrum is done lever motion with the point of connection 5 of interior wing panel skeleton and fuselage in will driving; Simultaneously pull bar can spur the inside extension of outer panel 3, is fulcrum with the point of connection 2 of inside and outside wing skeleton, makes whole outer panel do lever motion.The wing that so just makes whole flapping-wing aircraft has been fluttered as the wing of bird.
Claims (4)
1, a kind of two sectional type flapping-wing aircraft wing of rolling over is characterized in that: outer wing was two sections in wing was divided into, but interior outer panel doubling.
2, flapping-wing aircraft wing according to claim 1 is characterized in that: be connected with interior wing panel skeleton in the middle of the outer panel skeleton, outer panel skeleton extension summit links to each other with pull bar fuselage outer dead centre.
3, flapping-wing aircraft wing according to claim 1 is characterized in that: interior wing panel skeleton intermediate point is connected with fuselage.
4, flapping-wing aircraft wing according to claim 1 is characterized in that: the summit of wing panel frame machine body inner segment in the pull bar intermediate point connects in fuselage, pull bar fuselage inner vertex is connected to driving crank.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 200520142064 CN2918218Y (en) | 2005-11-30 | 2005-11-30 | Foldaway two-section-type wings for ornithopter |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 200520142064 CN2918218Y (en) | 2005-11-30 | 2005-11-30 | Foldaway two-section-type wings for ornithopter |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN2918218Y true CN2918218Y (en) | 2007-07-04 |
Family
ID=38216028
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 200520142064 Expired - Fee Related CN2918218Y (en) | 2005-11-30 | 2005-11-30 | Foldaway two-section-type wings for ornithopter |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN2918218Y (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101633409B (en) * | 2009-08-08 | 2012-05-30 | 杨绍河 | Bidirectional synchronous automatic turning flapping-wings |
| CN104677199A (en) * | 2015-01-21 | 2015-06-03 | 浙江理工大学 | Single-drive synchronous unfolding mechanism provided with multiple folding control planes |
| WO2016179726A1 (en) * | 2015-05-14 | 2016-11-17 | 许允夫 | Wings and transmission mechanism of ornithopter |
| CN110550206A (en) * | 2019-09-10 | 2019-12-10 | 南宁蜂虎科技有限公司 | ornithopter steering control method, device and system |
| CN113232856A (en) * | 2021-06-17 | 2021-08-10 | 东莞理工学院 | Passive deformation flapping wing structure |
-
2005
- 2005-11-30 CN CN 200520142064 patent/CN2918218Y/en not_active Expired - Fee Related
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101633409B (en) * | 2009-08-08 | 2012-05-30 | 杨绍河 | Bidirectional synchronous automatic turning flapping-wings |
| CN104677199A (en) * | 2015-01-21 | 2015-06-03 | 浙江理工大学 | Single-drive synchronous unfolding mechanism provided with multiple folding control planes |
| WO2016179726A1 (en) * | 2015-05-14 | 2016-11-17 | 许允夫 | Wings and transmission mechanism of ornithopter |
| CN110550206A (en) * | 2019-09-10 | 2019-12-10 | 南宁蜂虎科技有限公司 | ornithopter steering control method, device and system |
| CN110550206B (en) * | 2019-09-10 | 2020-11-06 | 南宁蜂虎科技有限公司 | Ornithopter steering control method, device and system |
| CN113232856A (en) * | 2021-06-17 | 2021-08-10 | 东莞理工学院 | Passive deformation flapping wing structure |
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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: 20070704 Termination date: 20121130 |