CN108454851A - A kind of sector wing flapping-wing aircraft - Google Patents
A kind of sector wing flapping-wing aircraft Download PDFInfo
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- CN108454851A CN108454851A CN201810382689.7A CN201810382689A CN108454851A CN 108454851 A CN108454851 A CN 108454851A CN 201810382689 A CN201810382689 A CN 201810382689A CN 108454851 A CN108454851 A CN 108454851A
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- 210000003462 vein Anatomy 0.000 claims description 28
- 230000033001 locomotion Effects 0.000 claims description 21
- 230000009467 reduction Effects 0.000 claims description 18
- 239000004744 fabric Substances 0.000 claims description 11
- 230000008859 change Effects 0.000 claims description 4
- 239000007787 solid Substances 0.000 claims description 3
- 230000003796 beauty Effects 0.000 abstract 1
- 238000010586 diagram Methods 0.000 description 11
- 238000000034 method Methods 0.000 description 6
- 230000008569 process Effects 0.000 description 6
- 230000007246 mechanism Effects 0.000 description 5
- 230000000694 effects Effects 0.000 description 3
- 230000002045 lasting effect Effects 0.000 description 3
- 238000005452 bending Methods 0.000 description 2
- 230000005540 biological transmission Effects 0.000 description 2
- 230000008602 contraction Effects 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 238000004377 microelectronic Methods 0.000 description 2
- 238000002360 preparation method Methods 0.000 description 2
- 230000009471 action Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000007664 blowing Methods 0.000 description 1
- 238000005265 energy consumption Methods 0.000 description 1
- 238000002474 experimental method Methods 0.000 description 1
- 238000007667 floating Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 230000035800 maturation Effects 0.000 description 1
- 230000008450 motivation Effects 0.000 description 1
- 239000011664 nicotinic acid Substances 0.000 description 1
- 238000003860 storage Methods 0.000 description 1
- 230000001360 synchronised effect Effects 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C33/00—Ornithopters
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C33/00—Ornithopters
- B64C33/02—Wings; Actuating mechanisms therefor
- B64C33/025—Wings; Actuating mechanisms therefor the entire wing moving either up or down
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
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Abstract
A kind of sector wing flapping-wing aircraft, it includes fuselage（3）And flapping wing（11）, it is characterized in that the flapping wing（11）In sector structure, which is fully deployed when being flutterred under to obtain maximum lift, is gradually tapered up during upper flutter to reduce air drag.The fan-shaped wing of the present invention has more bio-imitability, richer beauty more close to the live flying of birds than two sections of wings of tradition.The configuration of the present invention is simple, it is easily fabricated.
Description
Technical field
The present invention relates to a kind of Flight Vehicle Design, especially a kind of flapping wing type Flight Vehicle Design, specifically a kind of fan
Shape wing flapping-wing aircraft designs.
Background technology
High bionical in order to accomplish, we first pass through the variation of wing during the bird flying flapping wing of high-speed camera record
Study pinion flight.A flapping wing period for bird, which is roughly divided into down, flutters, is bent, above carrying, flattening four-stage.
(1) stage is flutterred under：Wing since peak under flutter to minimum point, wing is held substantially flat.Because of wing at this time
Wing is flattened to maximum area state, and air acts on it upward face power maximum, is provided so this stage is entire flapping flight
The lift most important stage.
(2) it is bent the stage：In minimum point wing, there are one dwells, and wing outer end is folded down into an arch (camber
Greatly).This stage does not generate lift directly, but the useful lift generated for the entire flapping wing period is vital.It is curved
The angle of the bending in bent stage is bigger, and the efficiency of entire flapping flight is higher.
(3) stage is above carried：Wing is above carried since minimum point to peak, and wing keeps folding to overarch.This stage is
The inverse process of first stage, it is therefore an objective to make the lasting flapping wing that wing is restored to next cycle prepare, inevitably receive
The downward active force of air.This process is short compared with being taken for the first stage, but since the effect wing of second stage has become high folding
Repeatedly flexuosity, relative atmospheric moving areas significantly reduce, and (can be approximately considered) in the state of identical pressure, by air
Down force be much smaller than the first stage, the useful lift for keeping the entire flapping wing period total is upward.
(4) stage is flattened：In peak, wing flattens rapidly, and the duration is very short, then repeats to start the first stage.
This process is the inverse process of second stage, in order to so that wing is obtained product of blowing on one's face under bigger, improve lift coefficient.This is opened
Show us, opening, the form of folding that can be according to Chinese tradition folding fan, to imitate the flapping wing process of bird's wing wing.And it originally sets
The characteristics of counting, substantially conforming to birds flapping wing, that is, comply fully with the action and effect of flapping wing period four-stage, has very high imitate
Natural disposition.
Imitative birds flapping wing aircraft is divided into two major classes according to research direction, first, common mechanically flutters, second is that base
In fluttering for MEMS micro-electronic mechanical skills.Two this two major classes research directions have the disadvantage of itself：Common mechanical flapping wing
Machine research cost is relatively low, technology maturation, can easily embody the performance of flapping flight, can become a big research side
To, but due to its energy consumption is big and structure is complex, so flapping wing aircraft itself lightweight cannot be made, in certain technical indicator
On do not reach requirement.And the flapping-wing aircraft based on MEMS micro-electronic mechanical skills can make body lightweight, reach truly
Bionical effect, but be also required to good experiment condition simultaneously so that many researchers hang back.
The structure of mechanical flapping-wing aircraft can be attributed to two kinds substantially, crank and rocker mechanism, five-bar mechanism.Crank connecting link machine
Structure flutter be not it is full symmetric flutter, structure is relatively simple.Five-bar mechanism can reach ideal state of fluttering, and need
Five connecting rods and Double-gear cooperation, mechanical power loss is larger in the process, and structure is complex.
Imitative birds flapping wing aircraft is divided according to aerofoil profile：
One, page flapping wing is combined.
The reciprocating motion of negative direction is synchronized to generate lasting lift using 2 groups of flapping wings, is moved back and forth by increasing
Stroke reduce motion frequency, to overcome the technical bottleneck for needing high frequency to flutter during traditional flapping wing promotes, to being solution
The problem that high frequency must be utilized to flutter its wings up and down in certainly traditional flapping wing propulsion mode provides reference.
The straight reciprocating motion direction for combining the upper and lower flapping wing of page flapping wing by change under floating state, to change
The state of its opening and closing generates negative lift so that the flapping wing for generating positive lift force increases in the projected area of the direction of motion
The projected area of flapping wing reduces, to generate lasting positive lift force.For the flapping wing model of different motion frequency, total life system
Several average value is 3.536~3.810.(2) when the reciprocating speed of driving mechanism is 1.0m/s, both wings are carried out with identical speed
The lift generated when reciprocating motion is not much different.In different movement travels, the lift coefficient of page flapping wing is combined at any time
Variation tendency it is consistent, i.e., as reciprocating frequence increases, ratio shared by the time of 1 period intra vane opening and closing increases
Add, the average value of total life coefficient increases.
Two, two-part flexibility flap flapping wing.
This flapping wing is actually fluttered closer to bird flex-wing.Compared to the non-collapsible wing, the folding movement of folding wings reduces
The negative lift for above flutterring the stage, increases down the lift for flutterring the intermediate stage, which results in folding wings and non-collapsible wing aerodynamic characteristic
Difference, average lift coefficient can be effectively improved.
In conclusion traditional flapping-wing aircraft generally uses the blocky wing (the single hop wing or the multistage wing) structure (such as Fig. 1), this machine
The characteristics of wing is to manufacture and design simple, the easy determination of movement locus.But its shortcomings that, is also more apparent：It is simple upper and lower to flutter
The significant change of flapping wing area is not caused, flapping wing is inefficient, is difficult to obtain larger liter under conditions of the identical span
Power.
Invention content
The purpose of the present invention is problem low for efficiency existing for existing Bionic ornithopter, that loss is big, design is a kind of
Fan-shaped wing flapping-wing aircraft with complete bionical performance.
The technical scheme is that：
A kind of sector wing flapping-wing aircraft, it includes fuselage 3 and flapping wing 11, it is characterized in that the flapping wing 11 is in sector structure,
The sector structure is fully deployed when being flutterred under to obtain maximum lift, is gradually tapered up during upper flutter to reduce air resistance
Power.
The flapping wing 11 is mainly made of driving lever 7, fixed link 9, vein 5 and elastical cloth 6, and fixed link 9 is solid with fuselage 3
Fixed to be connected, one end of each vein 5 is journaled into same fixing axle 17, and the power end of driving lever 7 stretches out the first flexural pivot head simultaneously
12 are connected with the output end of crank 13, and crank 13 is connected with the output end of reduction box 14, the input shaft and engine of reduction box 14
15 output shaft is connected, and driving lever 7 is hinged by another the second flexural pivot head 16 and fuselage and the second flexural pivot head 16 simultaneously
The centre of sphere is fixed on fuselage 3 near the position of fixing axle 17, and elastical cloth 6 is covered on driving lever 7 and vein 5 and relatively solid
Fixed, to make between driving lever 7 and vein 5, the angle between vein and vein changes with the movement of driving lever 7.
The axis of the reduction box and engine is with fuselage axis in about 120 ° of arrangements.
Movement locus of the first flexural pivot head 12 of the end that the driving lever 7 is connected with bent axle 13 in fuselage is one
It is in 60 ° of roundlet with fuselage, since driving lever 7 is fulcrum with the second flexural pivot head 16, the endpoint far from fuselage side
Movement locus will be great circle that one and fuselage are in 60 °.
The angle of the vein 5 is no more than 35 degree.
Beneficial effects of the present invention：
1, the design of flapping-wing aircraft wing of the invention is adopted in the principle that traditional two-period form flexible folding wing increases lift
With the higher fan-shaped wing of bio-imitability, while it can also further increase lift.The traditional two-period form bulk wing such as Fig. 1, L1To lean on
The wing section of nearly fuselage, L2It is useful lift of the part far from fuselage to acquisition bigger, it is necessary to increase Ll2, reduction L1,
Such that the bending stress that L1 sections of wings are received is excessive, it is unfavorable for selecting, being durable for flapping flight and material.And novel sector
The wing flutters the stage and is much smaller than the blocky wing by resistance and is achieved in that total useful lift more in the case of the identical span upper
Greatly, it is easier to realize high-lift flapping flight.
2, the fan-shaped wing of the invention deform during flapping wing is easy, compared to combining mechanical resistance that page wing is subject to more
It is small, improve mechanical efficiency.And the fan-shaped wing can utmostly be folded in storage or transport, space occupancy is reduced,
More there are economy, portability.
3, the fan-shaped wing of the invention has more bio-imitability more close to the live flying of birds than two sections of wings of tradition, richer
It is beautiful.
The configuration of the present invention is simple, it is easily fabricated.
Description of the drawings
Fig. 1 is the structural schematic diagram of existing two sections flexible flap flapping-wing aircrafts.
Fig. 2 is the drive mechanism schematic diagram (isometric view) of the present invention.
Fig. 3 is the vertical view of Fig. 2.
Fig. 4 is the fan-shaped flapping wing schematic diagram of the present invention.
Fig. 5 is the fan-shaped flapping wing work starting point status diagram of the present invention.
Fig. 6 is status diagram of the fan-shaped flapping wing of the present invention when maximum is fluttered downwards windward.
Fig. 7 be the present invention fan-shaped flapping motion to minimum point when status diagram.
Fig. 8 be the present invention fan-shaped flapping wing vein between angle reduce, elastical cloth shrink, wing contraction state schematic diagram it
One.
Fig. 9 be the present invention fan-shaped flapping wing vein between angle reduce, elastical cloth shrink, wing contraction state schematic diagram it
Two.
Status diagram when Figure 10 is front face area very little after the fan-shaped flapping wing of the present invention is shunk.
Figure 11 is that the fan-shaped flapping wing of the present invention stretches status diagram one of of preparation when fluttering next time again.
Figure 12 is the two of the status diagram that the fan-shaped flapping wing of the present invention is stretched again when preparing to flutter next time.
In figure：1 is tail, and 2 be head, and 3 be fuselage, and 4 be the hinged O points of each branch vein, and 5 be vein, and 6 be elastical cloth, 7
It is the P points on driving lever top for driving lever, 8,9 be parallel with fuselage, hinged fixed link, and 10 are and the hinged rod rear end of fuselage
Q points.
Specific implementation mode
The present invention is further illustrated with reference to the accompanying drawings and examples.
As shown in figs. 2-12.
A kind of sector wing flapping-wing aircraft, it includes fuselage 3 and flapping wing 11, and the flapping wing 11 is in sector structure, sector knot
Structure is fully deployed when being flutterred under to obtain maximum lift, is gradually tapered up during upper flutter to reduce air drag.Described
Flapping wing 11 is mainly made of driving lever 7, fixed link 9, vein 5 and elastical cloth 6, and fixed link 9 is fixedly linked with fuselage 3, each vein 5
One end be journaled into same fixing axle 17, the output end phase of the first flexural pivot head 12 and crank 13 of the power end of driving lever 7
Even, crank 13 is connected with the output end of reduction box 14, and the input shaft of reduction box 14 is connected with the output shaft of engine 15, driving lever
12 simultaneously the centre of sphere hinged by another the second flexural pivot head 16 and fuselage 3 and the second flexural pivot head 16 be fixed on fuselage 3 and lean on
Near the position of nearly fixing axle 17.Elastical cloth 6 is covered on driving lever 7 and vein 5 and is relatively fixed, to make driving lever 7 with
Between vein 5, the angle between vein and vein changes with the movement of driving lever 7.The reduction box and engine
Axis and fuselage axis in about 120 ° of arrangements.One end that the crank 13 is connected with driving lever 7 passes through the first flexural pivot head 12
Spherical surface is hinged, and driving lever 12 is hinged simultaneously by another the second flexural pivot head 16 and fuselage 3 and the centre of sphere of the second flexural pivot head 16
It is fixed on fuselage 3.Movement locus of the first flexural pivot head 12 of the end that the driving lever 7 is connected with bent axle 13 in fuselage
It is in 60 ° of roundlet for one and fuselage, since driving lever 7 is fulcrum with the second flexural pivot head 16, far from fuselage side
The movement locus of endpoint will be great circle that one and fuselage are in 60 °.The angle of the vein 5 is no more than 35 degree.Such as Fig. 2,3 institutes
Show.It should be noted that since fuselage is symmetrical, therefore Fig. 2,3 parts only draw left side) engine and reduction box in flapping wing
It keeps opposing stationary, omits fixing device herein.The output shaft of fuselage intrinsic motivation is connected with reduction box, is specific in reduction box
Train of reduction gears.The reduction of speed that act as of reduction box increases torque.The axis of reduction box and engine is with fuselage axis in about
120 ° (119.2 degree are actually about in Fig. 3).After deceleration, the output shaft of reduction box is rotated in the form of crank, crank and driving lever
The flexural pivot head shoot face at end is hinged, another flexural pivot head and fuselage spherical surface of driving lever are hinged.In this way, crank rotates a circle, actively
Movement locus of the flexural pivot head of boom end in fuselage is one and the roundlet that fuselage is in 60 °, with another flexural pivot of driving lever
Head is fulcrum, and the movement locus of endpoint of the driving lever far from fuselage side will be one and fuselage is in 60 ° of great circle.This great circle rail
Mark is similar to the track of Fig. 6-Figure 11.By this transmission device, engine is realized --- the power of driving lever transmits.
The present invention operation principle be：
The fan-shaped wing is exactly as its name suggests to have certain radian, and the varicose that can stretch as fan.
Fig. 4 is that the basic framework of high imitative fan-shaped wing (is not added with covering, and because wing about fuselage axisymmetrical only draws a left side
Side wing).Wherein, barIt is hinged and connected with side-of-body, andIt is the direction (course) that head is directed toward by tail portion.
Flight path axis system is taken, within the flapping wing period, when the fan type wing is overturnIt can be rotated around X-axis (tail direction head).It is
Driving lever is driven by the transmission device in fuselage.In this way, being flutterred the preparation stage under (such as Fig. 5), Q points are located at body upper most
Eminence, the angle between vein reach maximum value, and elasticity is arranged exhibits to maximum area,It is downward in the plane of fuselage head around O points
Rotation, keeps maximum front face area to flutter downwards (such as Fig. 6) in this way, until (such as Fig. 7 obtains maximum lift to flapping wing minimum point；
Second stage,ToIt draws close, the angle between each vein reduces, and elastical cloth is shunk, and wing shrinks (such as Fig. 8,9)；
Phase III,It is rotated up, due to front face area very little, so the resistance being subject to also very little (such as Figure 10)；Fourth stage,It goes toDirection is maximum, and the angle between each vein increases, and elastical cloth stretches, and reaches the starting point (such as Figure 11,12) of first stage,
Repeat next flapping wing period.
Part that the present invention does not relate to is the same as those in the prior art or can be realized by using the prior art.
Claims (5)
1. a kind of sector wing flapping-wing aircraft, it includes fuselage（3）And flapping wing（11）, it is characterized in that the flapping wing（11）It is tied in sector
Structure, the sector structure are fully deployed to obtain maximum lift when being flutterred under, are gradually tapered up during upper flutter to reduce air
Resistance.
2. sector wing flapping-wing aircraft according to claim 1, it is characterized in that the flapping wing（11）Mainly by driving lever（7）、
Fixed link（9）, vein（5）And elastical cloth（6）Composition, fixed link（9）With fuselage（3）It is fixedly linked, each vein（5）One end it is equal
It is journaled into same fixing axle（17）On, driving lever（7）Power end pass through the first flexural pivot（12）With crank（13）Output end phase
Even, crank（13）With reduction box（14）Output end be connected, reduction box（14）Input shaft and engine（15）Output shaft phase
Even, driving lever（7）Pass through the second flexural pivot head simultaneously（16）And fuselage（3）Spherical surface is hinged and the second flexural pivot head（16）The centre of sphere it is solid
It is scheduled on fuselage（3）On；Elastical cloth（6）It is covered in driving lever（7）And vein（5）It goes up and is relatively fixed, to make driving lever（7）With
Vein（5）Between, the angle between vein and vein is with driving lever（7）Movement and change.
3. sector wing flapping-wing aircraft according to claim 2, it is characterized in that the axis and machine of the reduction box and engine
Body axis are in about 120 ° of arrangements.
4. sector wing flapping-wing aircraft according to claim 2, it is characterized in that the driving lever（7）With bent axle（13）Connected
First flexural pivot head of end（12）Movement locus in fuselage is one and the roundlet that fuselage is in 60 °, due to driving lever（7）With
Second flexural pivot head（16）For fulcrum, therefore, the movement locus of the endpoint far from fuselage side will be one and fuselage is in 60 °
Great circle.
5. sector wing flapping-wing aircraft according to claim 2, it is characterized in that the vein（5）Angle be no more than 35 degree.
Priority Applications (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810382689.7A CN108454851A (en) | 2018-04-26 | 2018-04-26 | A kind of sector wing flapping-wing aircraft |
| CN201910077933.3A CN109592030B (en) | 2018-04-26 | 2019-01-28 | Fan-shaped wing ornithopter |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810382689.7A CN108454851A (en) | 2018-04-26 | 2018-04-26 | A kind of sector wing flapping-wing aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN108454851A true CN108454851A (en) | 2018-08-28 |
Family
ID=63236073
Family Applications (2)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810382689.7A Pending CN108454851A (en) | 2018-04-26 | 2018-04-26 | A kind of sector wing flapping-wing aircraft |
| CN201910077933.3A Active CN109592030B (en) | 2018-04-26 | 2019-01-28 | Fan-shaped wing ornithopter |
Family Applications After (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910077933.3A Active CN109592030B (en) | 2018-04-26 | 2019-01-28 | Fan-shaped wing ornithopter |
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| Country | Link |
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| CN (2) | CN108454851A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112173067A (en) * | 2020-09-11 | 2021-01-05 | 北京凌空天行科技有限责任公司 | Space flight vehicle |
Family Cites Families (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB227234A (en) * | 1923-11-01 | 1925-01-15 | Ern Westgate Walter | Improvements in a flying machine |
| GB270240A (en) * | 1926-04-30 | 1927-09-01 | Karl Cerny | Flying machine with flapping wings |
| CN2581325Y (en) * | 2002-09-04 | 2003-10-22 | 赖金群 | Ornithopter |
| CN2858482Y (en) * | 2005-09-13 | 2007-01-17 | 江民泽 | Endless-track circulating flapping-wing |
| CN201183610Y (en) * | 2007-09-10 | 2009-01-21 | 黄光富 | Ornithopter |
| KR101495863B1 (en) * | 2014-01-27 | 2015-02-26 | 한국과학기술원 | Gliding robot system with single actuator |
| US10017248B2 (en) * | 2014-04-28 | 2018-07-10 | University Of Maryland, College Park | Flapping wing aerial vehicles |
| CN208198826U (en) * | 2018-04-26 | 2018-12-07 | 南京航空航天大学 | A kind of sector wing flapping-wing aircraft |
-
2018
- 2018-04-26 CN CN201810382689.7A patent/CN108454851A/en active Pending
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2019
- 2019-01-28 CN CN201910077933.3A patent/CN109592030B/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112173067A (en) * | 2020-09-11 | 2021-01-05 | 北京凌空天行科技有限责任公司 | Space flight vehicle |
Also Published As
| Publication number | Publication date |
|---|---|
| CN109592030A (en) | 2019-04-09 |
| CN109592030B (en) | 2024-03-29 |
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