CN203902838U - Thrust generating device comprising rotary flapping wing - Google Patents
Thrust generating device comprising rotary flapping wing Download PDFInfo
- Publication number
- CN203902838U CN203902838U CN201420282406.9U CN201420282406U CN203902838U CN 203902838 U CN203902838 U CN 203902838U CN 201420282406 U CN201420282406 U CN 201420282406U CN 203902838 U CN203902838 U CN 203902838U
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- flapping wing
- wing
- main shaft
- pivoted arm
- guides
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- 238000013459 approach Methods 0.000 claims description 6
- 238000000034 method Methods 0.000 description 3
- 230000000694 effects Effects 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 230000007547 defect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000005096 rolling process Methods 0.000 description 1
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Abstract
The utility model relates to a thrust generating device comprising a rotary flapping wing, which belongs to the technical field of aircrafts. The thrust generating device is composed of a main shaft, a rocking arm, a flapping wing, a wing shaft, a guide bar and a guider, wherein the main shaft, the rocking arm and the wing shaft form a crank structure, the flapping wing is fixedly connected to one end of the guide bar, and the other end of the guide bar penetrates through the guider. Under the driving of an engine, the flapping wing is driven to circumferentially rotate by the wing shaft, so as to flutter air to generate thrust; the efficiency is high, the thrust direction can be conveniently adjusted, and the thrust generating device comprising the rotary flapping wing is applied to thrust and lift devices of the aircrafts.
Description
Technical field
A rotary flapping wing thrust generating apparatus, belongs to vehicle technology field, relates in particular to a kind of flapping wing aircraft thrust generating apparatus.
Background technology
Traditional flapping wing aircraft is to drive flapping wing by crankshaft-connecting rod mechanism, and flapping wing is fluttered up and down and produced lift, and its efficiency is lower, is inconvenient to adjust lift direction, and the strength at repeated alternation of flapping wing material is had relatively high expectations; Existing fin aerofoil profile of rolling the wing adopts symmetrical airfoil more, and resistance is large, and 1ift-drag ratio is little, and efficiency is lower.
Summary of the invention
The object of the invention is to overcome the above-mentioned defect of conventional aircraft, invent the rotatable similar flapping wing thrust generating apparatus that rolls the wing that a kind of efficiency is higher.
A rotary flapping wing thrust generating apparatus, is comprised of main shaft, pivoted arm, flapping wing, wing axle, pilot bar and guides.One end of main shaft is connected with flapping wing aircraft fuselage by antifriction-bearing box, one end of pivoted arm is connected with the other end of main shaft is vertical, vertical being connected in one end of the other end of pivoted arm and wing axle, wing axle, pivoted arm and main shaft form crank structure in same plane, the other end of wing axle is connected with flapping wing by bearing and through the hole that approaches leading edge parallel with flapping wing leading edge, flapping wing can be around wing axle flexible rotating, but wing axle can not be made axial linear movement; The end face of the close pivoted arm of flapping wing is that the root end face of flapping wing is vertical with the leading edge of flapping wing, one end of pilot bar and flapping wing are fixed on the intersection point place of this end face string of a musical instrument and trailing edge, pilot bar is on the extended line of this end face string of a musical instrument outside trailing edge and vertical with wing axle, and the other end of pilot bar is through guides; Guides is combined by linear bearing and oscillating bearing, and linear bearing is fixedly bumped in oscillating bearing, and guides is connected by the shell of its oscillating bearing and the fuselage of flapping wing aircraft; Pilot bar inserts in the linear bearing of guides, and pilot bar can do reciprocating linear motion flexibly in linear bearing, and along with linear bearing together can be around the oscillating bearing center of guides switch; One end that the length of pilot bar should enough be guaranteed pilot bar in whole motion process is all the time in guides and do not come off; Guides approaches the rotation round of wing axle and installs, but guides is greater than the maximum chord length sum of arm length and flapping wing to the distance between main shaft, so that flapping wing rotates smoothly.
The form of pivoted arm has two kinds: the first is a flat rod member; The second is comprised of round bar and suit symmetrical airfoil blade thereon, and the angle of attack of blade can regulate as conventional helicopters tail-rotor, can produce horizontal aerodynamic force, in order to the direction of change of flight device.
For reducing the resistance of air, improve 1ift-drag ratio, improve the efficiency of fluttering, the aerofoil profile of flapping wing adopts flat pattern or epirelief concave shape under epirelief, and this point is that cycloid propeller and half traditional rotation mechanism flapping wing are nonsensical for traditional wing that rolls.
The principle of work of this kind of rotary flapping wing thrust generating apparatus is: the power of driving engine passes to main shaft after slowing down, main shaft rotates and drives pivoted arm rotation, pivoted arm drives the rotation of wing axle, under the traction of wing axle, flapping wing rotation is fluttered, control due to pilot bar and guides, during flapping wing rotation, its angle of attack revolves at a cycle of operations the interior meeting of turning around regular variation occurs, and meets flapping wing, is conducive to produce thrust.Because guides approaches the rotation round of wing axle, in one-period, the effect of flutterring generation under flapping wing much larger than on flutter, the efficiency that produces lift is higher.Change the size that rotating speed can change thrust, when rotating speed is constant, by changing guides, to the distance between main shaft, also can change the size of thrust; The direction of thrust is to realize by changing the orientation of the relative main shaft of guides.Because flapping wing is made circular-rotation, less demanding to the strength at repeated alternation of material.
Accompanying drawing explanation
Fig. 1 is that the master of a kind of rotary flapping wing thrust of the present invention generating apparatus looks schematic diagram; Fig. 2 is the birds-eye view of Fig. 1.
In figure, 1-main shaft, 2-pivoted arm, 3-flapping wing, 4-wing axle, 5-pilot bar, 6-guides, 61-linear bearing, 62-oscillating bearing; In Fig. 1: the large broken circle with arrow represents rotational trajectory and the rotation direction of wing axle 4.
The specific embodiment
Now by reference to the accompanying drawings 1 and accompanying drawing 2 for example the present invention is illustrated: a kind of rotary flapping wing thrust generating apparatus, is comprised of main shaft 1, pivoted arm 2, flapping wing 3, wing axle 4, pilot bar 5 and guides 6.One end of main shaft 1 is connected with flapping wing aircraft fuselage by antifriction-bearing box, vertical being connected of the other end of one end of pivoted arm 2 and main shaft 1, vertical being connected in one end of the other end of pivoted arm 2 and wing axle 4, wing axle 4, pivoted arm 2 and main shaft 1 form crank structure in same plane, the other end of wing axle 4 is connected with flapping wing 3 by bearing and through the hole that approaches leading edge parallel with flapping wing 3 leading edges, flapping wing 3 can be around wing axle 4 flexible rotatings, but wing axle 4 can not be made axial linear movement; The end face of the close pivoted arm 2 of flapping wing 3 is that the root end face of flapping wing 3 is vertical with the leading edge of flapping wing 3, one end of pilot bar 5 and flapping wing 3 are fixed on the intersection point place of the flapping wing 3 root end face strings of a musical instrument and flapping wing 3 trailing edges, pilot bar 5 is on the extended line of this end face string of a musical instrument outside trailing edge and vertical with wing axle 4, and the other end of pilot bar 5 is through guides 6; Guides 6 is combined by linear bearing 61 and oscillating bearing 62, and linear bearing 61 is fixedly bumped in oscillating bearing 62, and guides 6 is connected by the shell of its oscillating bearing 62 and the fuselage of flapping wing aircraft; Pilot bar 5 inserts in the linear bearing 61 of guidess 6, and pilot bar 5 can be at the interior flexible moving linearly of linear bearing 61, and along with linear bearing 61 together can be around the oscillating bearing 62 center switches of guides 6; One end that the length of pilot bar 5 should enough be guaranteed pilot bar 5 in whole motion process is all the time in guides 6 and do not come off; Guides 6 approaches the rotation round of wing axle 4 and installs, but guides 6 is greater than the maximum chord length sum of pivoted arm 2 length and flapping wing 3 to the distance between main shaft 1, so that flapping wing 3 rotates smoothly.
The form of pivoted arm 2 has two kinds: the first is a flat rod member; The second is comprised of round bar and suit symmetrical airfoil blade thereon, and the angle of attack of blade can regulate as conventional helicopters tail-rotor, can produce horizontal power, in order to the direction of change of flight device.
The power of driving engine passes to main shaft 1 after slowing down, main shaft 1 rotates and drives pivoted arm 2 rotations, pivoted arm 2 drives 4 rotations of wing axle, under the traction of wing axle 4, flapping wing 3 rotations are fluttered, control due to pilot bar 5 and guides 6, during flapping wing 3 rotation, its angle of attack revolves at a cycle of operations the interior meeting of turning around regular variation occurs, and meets flapping wing, is conducive to produce thrust.When flapping wing 3 rotates a circle, the concrete change procedure of its angle of attack is: suppose that guides exceeds main shaft, and the large broken circle of crossing the horizontal surface of guides and the rotational trajectory circumference of wing axle 4 and being in Fig. 1 is tangent, and the reference position of supposing flapping wing 3 rotations is the position of flapping wing 3 the most close guidess 6, now the angle of attack of flapping wing 3 is negative 90 °, rotation traction along with wing axle 4, flapping wing 3 upward movements, the absolute value of the angle of attack is reduced to rapidly 0 °, now pilot bar 5 exceeds main shaft 1 and is horizontal, and rear wing axle 4 continues rotation, flapping wing is flutterred for 3 times, the angle of attack of flapping wing 3 becomes 90 ° more slowly from 0 °, now flapping wing 3 is away from guides 6, continuation traction along with wing axle 4, the angle of attack of flapping wing 3 becomes 0 ° more slowly from 90 °, now the rotational trajectory circumference of pilot bar 5 and wing axle 4 is tangential on the below of main shaft 1, continuation rotation along with wing axle 4, the angle of attack of flapping wing 3 becomes rapidly negative 90 ° by 0 °, now get back to reference position, complete a swing circle.Due to the rotation round of guides 5 near wing axle 4, in one-period, the effect that flapping wing is flutterred generation for 3 times much larger than on flutter, the efficiency that produces lift is higher.Change the size that rotating speed can change thrust, the faster thrust of rotating speed is larger; When rotating speed is constant, by changing guides 6, to the distance between main shaft 1, also can change the size of thrust, guides 6 from main shaft 1 more close to thrust larger; The direction of thrust is to realize by changing the orientation of guides 6 relative main shafts 1, if guides 6 in the dead aft of main shaft 1, guides 6 is from moving with high position with main shaft 1, the direction of thrust can be toward moving forward.Because flapping wing 3 is made circular-rotation, less demanding to the strength at repeated alternation of material.This apparatus structure is simple, and efficiency is higher, and the direction of more convenient adjustment thrust.
This is invented a kind of rotary flapping wing thrust generating apparatus use and on aircraft, makes thrust and lift unit.Be particularly useful for the slower aircraft of cruising speed.
Claims (5)
1. a rotary flapping wing thrust generating apparatus, is characterized in that: main shaft (1), pivoted arm (2), flapping wing (3), wing axle (4), pilot bar (5) and guides (6), consist of; One end of main shaft (1) is connected with flapping wing aircraft fuselage by antifriction-bearing box, vertical being connected of the other end of one end of pivoted arm (2) and main shaft (1), vertical being connected in one end of the other end of pivoted arm (2) and wing axle (4), wing axle (4), pivoted arm (2) and main shaft (1) are in same plane, and the other end of wing axle (4) is connected with flapping wing (3) by bearing and through the hole that approaches leading edge parallel with flapping wing (3) leading edge; The root end face of flapping wing (3) is vertical with leading edge, one end of pilot bar (5) and flapping wing (3) are fixed on the intersection point place of flapping wing (3) the root end face string of a musical instrument and flapping wing (3) trailing edge, pilot bar (5) is on the extended line of this end face string of a musical instrument outside trailing edge and vertical with wing axle (4), and the other end of pilot bar (5) is through guides (6).
2. a kind of rotary flapping wing thrust generating apparatus according to claim 1, is characterized in that: guides (6) is combined by linear bearing (61) and oscillating bearing (6).
3. a kind of rotary flapping wing thrust generating apparatus according to claim 1, is characterized in that: the aerofoil profile of flapping wing (3) adopts flat pattern or epirelief concave shape under epirelief.
4. a kind of rotary flapping wing thrust generating apparatus according to claim 1, is characterized in that: pivoted arm (2) is a flat rod member.
5. a kind of rotary flapping wing thrust generating apparatus according to claim 1, is characterized in that: pivoted arm (2) is comprised of round bar and suit symmetrical airfoil blade thereon.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420282406.9U CN203902838U (en) | 2014-05-30 | 2014-05-30 | Thrust generating device comprising rotary flapping wing |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420282406.9U CN203902838U (en) | 2014-05-30 | 2014-05-30 | Thrust generating device comprising rotary flapping wing |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203902838U true CN203902838U (en) | 2014-10-29 |
Family
ID=51777125
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201420282406.9U Withdrawn - After Issue CN203902838U (en) | 2014-05-30 | 2014-05-30 | Thrust generating device comprising rotary flapping wing |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN203902838U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103991546A (en) * | 2014-05-30 | 2014-08-20 | 佛山市神风航空科技有限公司 | Push force generation device of rotary flapping wing |
| CN105235903A (en) * | 2015-11-03 | 2016-01-13 | 安徽工业大学 | Bionic swing wing aircraft |
-
2014
- 2014-05-30 CN CN201420282406.9U patent/CN203902838U/en not_active Withdrawn - After Issue
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103991546A (en) * | 2014-05-30 | 2014-08-20 | 佛山市神风航空科技有限公司 | Push force generation device of rotary flapping wing |
| CN105235903A (en) * | 2015-11-03 | 2016-01-13 | 安徽工业大学 | Bionic swing wing aircraft |
| CN105235903B (en) * | 2015-11-03 | 2017-03-22 | 安徽工业大学 | Bionic swing wing aircraft |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| AV01 | Patent right actively abandoned |
Granted publication date: 20141029 Effective date of abandoning: 20151223 |
|
| C25 | Abandonment of patent right or utility model to avoid double patenting |