CN201158458Y - A kind of flapping wing for micro-aircraft - Google Patents
A kind of flapping wing for micro-aircraft Download PDFInfo
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- CN201158458Y CN201158458Y CNU2008200281698U CN200820028169U CN201158458Y CN 201158458 Y CN201158458 Y CN 201158458Y CN U2008200281698 U CNU2008200281698 U CN U2008200281698U CN 200820028169 U CN200820028169 U CN 200820028169U CN 201158458 Y CN201158458 Y CN 201158458Y
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- flapping wing
- flapping
- wing
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Abstract
本实用新型是一种用于微型飞机的扑翼，由展向梁(3)和支撑筋(6)构成扑翼的骨架并与机身(5)连接。展向梁(3)中部被断开为两段，并在该断开处的下表面固定有可弯曲但不可拉伸的连接片(4)，在该处上表面有可伸缩的弹性材料(2)，该弹性材料(2)的两端固定在展向梁(3)的上表面。当扑翼向上扑时，展向梁承受向上的弯矩，由于在展向梁(3)的下表面固定有可弯曲但不可伸缩的连接片，扑翼全部打开，整体向上扑动；当扑翼向下扑时，展向梁(3)承受向下的弯矩，由于在展向梁的上表面固定有可伸缩的弹性材料(2)，扑翼外端则向下弯曲，克服了现有技术中存在的扑翼结构不能随着扑翼上下运动方向的不同而做调整，使得扑翼运动阻力增加不足的缺陷。
The utility model relates to a flapping wing used for a micro-aircraft. The skeleton of the flapping wing is formed by span beams (3) and supporting ribs (6) and connected with the fuselage (5). The middle part of the span-wise beam (3) is broken into two sections, and a bendable but non-stretchable connecting piece (4) is fixed on the lower surface of the break, and a stretchable elastic material (4) is fixed on the upper surface of the break ( 2), the two ends of the elastic material (2) are fixed on the upper surface of the span beam (3). When the flapping wings flutter upwards, the span beam bears the upward bending moment. Since the lower surface of the span beam (3) is fixed with a bendable but non-retractable connecting piece, the flapping wings are fully opened, and the whole flutters upward; When the wing flutters downward, the span beam (3) bears the downward bending moment. Since the stretchable elastic material (2) is fixed on the upper surface of the span beam, the outer end of the flapping wing bends downward, which overcomes the current The flapping wing structure existing in the art cannot be adjusted according to the different directions of the flapping wing's up and down movement, which results in insufficient increase in the flapping wing's movement resistance.
Description
One, technical field
The present invention relates to the minute vehicle design field, specifically is a kind of flapping wing that is used for miniplane.
Two, background technology
In the development kind of contemporary aircraft, characteristics such as minute vehicle is good, easy to carry with its stealthy performance, maneuverability have been subjected to extensive concern both domestic and external.From aerodynamic angle, the evolution rule of minute vehicle natural process circle birds and insect, promptly when the size of aircraft little to a certain degree the time, can not adopt fixing wing to obtain lift like that according to the orthodox flight device (because the size of fixed-wing is more little, aerodynamic Reynolds number is low more, pneumatic efficiency is low more), the lift of fixed wing can not be enough to overcome the weight of aircraft, so, minute vehicle need adopt the mode of the wing of fluttering, and as birds and insect, the size of aircraft is more little, and flapping wing need be fluttered soon more.From the angle and the background demand analysis angle of flight maneuver, flapping wing aircraft can be realized flare maneuver more flexibly, and therefore, flapping wing aircraft becomes an important directions of domestic and international research.
For flapping wing aircraft, what the action of fluttering up and down of flapping wing provided mainly is the thrust of aircraft, and the lift of aircraft mainly relies on the mean angle of attack and the camber of flapping wing.Adopt hard structure from the flapping wing structure of current domestic and international flapping wing aircraft, its flapping wing adds film by skeleton and forms more, and when flapping wing was fluttered up and down, flapping wing was except that the elastic deformation of structure, and not having has any adjustment because of the difference of up-and-down movement direction.But, occurring in nature birds wing is when up-and-down movement, it during the wing upward movement form of folding up, it when moving downward the form of launching, like this, during the wing upward movement, the resistance of motion that is subjected to is little (in order to distinguish the definition of conventional aircraft resistance, the above-below direction resistance that forms owing to up-and-down movement when flapping wing is fluttered is a resistance of motion, during upward movement, resistance of motion and gravity are equidirectional, are equivalent to increase gravity, to flight is disadvantageous), when wing moved downward, in fact resistance of motion had increased lift, so, resistance of motion during birds wing up-and-down movement is asymmetric, and average lift can be bigger than the wing of hard structure.Yet, in artificial aircraft, in the time of realizing the such up-and-down movement of birds wing turn up and expansion is that current manufacturing technology is beyond one's reach, even design such adaptive structure, its weight cost also is that minute vehicle is unaffordable.Just because of this, the flapping wing of mini-sized flap wings aircraft employing at present all is hard structure.
Three, summary of the invention
Can not adjust along with the difference of flapping wing up-and-down movement direction for overcoming the flapping wing structure that exists in the prior art, make the deficiency that the flapping wing resistance of motion increases to the present invention proposes a kind of flapping wing that is used for miniplane.
The present invention is the flapping wing of miniature ornithopter, comprises Zhan Xiangliang, brace rod and the covering of flapping wing, and is made of the skeleton of flapping wing to beam and brace rod exhibition; Flapping wing is connected with fuselage to beam by many exhibitions.The invention is characterized in, about being broken as with the Zhan Xiangliang of fuselage bonded assembly flapping wing two sections, and in this exhibition to the fixing flexible but non-stretchable connecting strap of a slice of the lower surface of beam, and fix a telescopic elastomeric material in this exhibition to the upper surface of beam gap, and the two ends of this elastomeric material are fixed on the upper surface of Zhan Xiangliang.When flapping wing was upwards pounced on, exhibition was subjected to moment of flexure upwards to joist support, owing to be fixed with flexible but non-telescoping connecting strap at the lower surface of Zhan Xiangliang, Zhan Xiangliang is rigidity, and flapping wing is all opened, and integral body is upwards fluttered; When flapping wing was pounced on downwards, exhibition was subjected to downward moment of flexure to joist support, owing to be fixed with telescopic elastomeric material at the upper surface of Zhan Xiangliang, the flapping wing outer end then is bent downwardly.
The mode of motion of wing when the technical solution adopted in the present invention can be imitated birds and circled in the air, when the flapping-wing aircraft flapping wing was fluttered downwards, because Zhan Xiangliang is firm, flapping wing all launched, thereby obtains favourable lift; And when the flapping wing upward movement, because the air movement resistance of outside flapping wing, flapping wing can be turned up, thereby the resistance when reducing the flapping wing upward movement reaches the effect that improves the flapping wing pneumatic efficiency.
Four, description of drawings
Accompanying drawing 1 is the structural representation of flapping wing exhibition to beam;
Accompanying drawing 2 is state of kinematic motion scheme drawings of opening up when flapping wing is fluttered downwards to beam;
Accompanying drawing 3 is state of kinematic motion scheme drawings of opening up when flapping wing is upwards fluttered to beam;
Accompanying drawing 4 is flapping wing scheme drawings;
Accompanying drawing 5 is flapping wing back views when upwards fluttering;
Accompanying drawing 6 is flapping wing back views when fluttering downwards.Wherein:
1. 3. exhibitions of attachment point 2. elastomeric materials are to beam 4. connecting straps 5. fuselages 6. brace rods 7. coverings
Five, the specific embodiment
Embodiment one
Present embodiment is a kind of mini-sized flap wings that can bend in one direction that is used for certain miniature ornithopter, comprises that three flapping wings exhibitions are to beam 3, four brace rods 6 and coverings 7.
In the present embodiment, constitute the skeleton of flapping wing by the different rectangle flapping wings exhibition of three length to beam 3 and four brace rods 6, concrete grammar is three flapping wings exhibitions to be distributed in the tangential front portion of flapping wing to the middle part to beam 3, and to be connected with fuselage 5; The flapping wing exhibition is broken as two sections to beam 3 middle parts, and this exhibition to the lower surface of beam 3 fixedly a slice leather as connecting strap 4, a slice rubber is arranged as elastomeric material 2 in this exhibition to the upper surface of beam gap, and with the two ends of this elastomeric material 2 as attachment point 1, stick on the upper surface of exhibition to beam 3; Stick on the deformation requirements of exhibition when the length of the rubber connecting strap 4 of beam upper surface and lower surface leather elastomeric material 2 should satisfy flapping wing and flutters; The exhibition of three flapping wings should be on same tangent plane, to guarantee flapping wing bending smoothly to beam 3 gaps.Four brace rods 6 distribute to beam 3 along the flapping wing exhibition, and the direction of this brace rod is tangential with flapping wing substantially; Covering 7 is overlayed on flapping wing exhibition on beam 3 and brace rod 6, and the flapping wing trailing edge do not establish Zhan Xiangliang, constitute the flexible trailing edge of flapping wing by brace rod 6 and covering 7.When flapping wing was pounced on downwards, exhibition was born moment of flexure upwards to beam 3, owing to be fixed with non-telescoping leather connecting strap 4 at the lower surface of Zhan Xiangliang, Zhan Xiangliang is rigidity, and flapping wing is all opened; When flapping wing was upwards pounced on, exhibition was born downward moment of flexure to beam 3, owing to be fixed with telescopic rubber elasticity material 2 at the upper surface of Zhan Xiangliang, the flapping wing outer end then is bent downwardly.
Embodiment two
Present embodiment is a kind of mini-sized flap wings that can bend in one direction that is used for certain miniature ornithopter, comprises flapping wing, two flapping wing exhibition Xiang Liang, three brace rods and covering.
In the present embodiment, constitute the skeleton of flapping wing by the different rectangle flapping wings exhibition Xiang Liang of two length and four brace rods, concrete grammar is two flapping wings exhibitions to be distributed in tangential front portion of flapping wing and middle part to beam, and to be connected with fuselage;
The flapping wing exhibition is broken as two sections to beam 3 middle parts, and fix a metal hinge as connecting strap 4 to the lower surface of beam 3 in this exhibition, fix a spring as elastomeric material 2 in this exhibition to the upper surface of beam gap, and as attachment point 1, be fixed on the upper surface of exhibition to beam 3 with the two ends of this elastomeric material 2; The deformation requirements of exhibition when the length of the spring of beam upper surface should satisfy flapping wing and flutters; The exhibition of two flapping wings should be on same tangent plane, to guarantee flapping wing bending smoothly to beam 3 gaps.Three brace rods 6 distribute to beam 3 along the flapping wing exhibition, and the direction of this brace rod is tangential with flapping wing substantially; Covering 7 is overlayed on flapping wing exhibition on beam 3 and brace rod 6, and the flapping wing trailing edge do not establish Zhan Xiangliang, constitute the flexible trailing edge of flapping wing by brace rod 6 and covering 7.When flapping wing was pounced on downwards, exhibition was born moment of flexure upwards to beam 3, owing to be fixed with non-telescoping metal hinge connecting strap 4 at the lower surface of Zhan Xiangliang, Zhan Xiangliang is rigidity, and flapping wing is all opened; When flapping wing was upwards pounced on, exhibition was born downward moment of flexure to beam 3, owing to be fixed with telescopic spring material 2 at the upper surface of Zhan Xiangliang, the flapping wing outer end then is bent downwardly.
Because the mode of motion of wing when technical scheme that the foregoing description adopted can be imitated birds and circled in the air, when the flapping-wing aircraft flapping wing was fluttered downwards, flapping wing all launched, thereby obtained favourable lift; And when the flapping wing upward movement, flapping wing can be turned up, thereby the resistance when reducing the flapping wing upward movement reaches the effect that improves the flapping wing pneumatic efficiency.
Claims (4)
1. flapping wing that is used for miniplane, the Zhan Xiangliang (3), many brace rods (6) and the flexible covering (7) that comprise many flapping wings, constitute the skeleton of flapping wing by Zhan Xiangliang (3) and brace rod (6), and be connected with fuselage (5) by Zhan Xiangliang (3), it is characterized in that, about the Zhan Xiangliang of flapping wing (3) is broken as two sections, and be fixed with flexible but non-telescoping connecting strap (4) in this exhibition to the lower surface of beam gap, in this exhibition to the fixing telescopic elastomeric material (2) of the upper surface of beam gap.
2. a kind of according to claim 1 flapping wing that is used for miniplane is characterized in that described flapping wing is made of the flexible trailing edge of flapping wing brace rod (6) and covering (7).
3. a kind of according to claim 1 flapping wing that is used for miniplane is characterized in that described many exhibitions should be on same tangent plane to the beam gap of beam (3).
4. a kind of according to claim 1 flapping wing that is used for miniplane is characterized in that elastomeric material (2) is fixed on the upper surface of exhibition to the beam gap by the attachment point (1) at its two ends.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNU2008200281698U CN201158458Y (en) | 2008-01-22 | 2008-01-22 | A kind of flapping wing for micro-aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNU2008200281698U CN201158458Y (en) | 2008-01-22 | 2008-01-22 | A kind of flapping wing for micro-aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN201158458Y true CN201158458Y (en) | 2008-12-03 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CNU2008200281698U Expired - Fee Related CN201158458Y (en) | 2008-01-22 | 2008-01-22 | A kind of flapping wing for micro-aircraft |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102501972A (en) * | 2011-11-20 | 2012-06-20 | 西北工业大学 | Wing of micro ornithopter |
| CN102530250A (en) * | 2010-12-20 | 2012-07-04 | 西安韦德沃德航空科技有限公司 | Ornithopter with bendable main wing |
| CN107719664A (en) * | 2016-08-11 | 2018-02-23 | 谭佑军 | Flapping-wing aircraft |
| CN115384770A (en) * | 2022-09-19 | 2022-11-25 | 上海交通大学 | Stiffness-adaptive double-layer membrane structure wing of bionic flapping wing aircraft |
-
2008
- 2008-01-22 CN CNU2008200281698U patent/CN201158458Y/en not_active Expired - Fee Related
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102530250A (en) * | 2010-12-20 | 2012-07-04 | 西安韦德沃德航空科技有限公司 | Ornithopter with bendable main wing |
| CN102501972A (en) * | 2011-11-20 | 2012-06-20 | 西北工业大学 | Wing of micro ornithopter |
| CN102501972B (en) * | 2011-11-20 | 2014-06-18 | 西北工业大学 | Wing of micro ornithopter |
| CN107719664A (en) * | 2016-08-11 | 2018-02-23 | 谭佑军 | Flapping-wing aircraft |
| CN115384770A (en) * | 2022-09-19 | 2022-11-25 | 上海交通大学 | Stiffness-adaptive double-layer membrane structure wing of bionic flapping wing 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: 20081203 Termination date: 20120122 |