CN203864999U - Tapered rotating flapping wing thrust generating device - Google Patents
Tapered rotating flapping wing thrust generating device Download PDFInfo
- Publication number
- CN203864999U CN203864999U CN201420282418.1U CN201420282418U CN203864999U CN 203864999 U CN203864999 U CN 203864999U CN 201420282418 U CN201420282418 U CN 201420282418U CN 203864999 U CN203864999 U CN 203864999U
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- wing
- fin
- pivoted arm
- guides
- axis positioner
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Abstract
The utility model discloses a tapered rotating flapping wing thrust generating device, and belongs to the technical field of air vehicles. The device comprises a main shaft, a rotating arm, a wing panel, a wing shaft, a wing shaft positioning device, a guide rod and a guider, wherein the rotating arm is vertically and fixedly connected with the main shaft; the wing shaft and the rotating arm are mutually connected and form an acute angle; the wing shaft is fixed by penetrating through the wing shaft positioning device; the wing shaft is connected with the wing panel; the guide rod is movably connected with the wing panel through a hinge pin at the opening end of the U-shaped fork of the guide rod; the round rod of the guide rod penetrates through the guider. The wing panel performs tapered rotating under the driving of an engine, so as to flap air to produce thrust, and the tapered rotating flapping wing thrust generating device is high in efficiency, convenient to adjust the thrust direction, and serves as a thrust device of the air vehicle.
Description
Technical field
A taper rotary flapping wing thrust generating apparatus, belongs to vehicle technology field, relates in particular to a kind of thruster for aircraft.
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 thrust, and its efficiency is lower, is inconvenient to adjust thrust direction, and the strength at repeated alternation of flapping wing material is had relatively high expectations.
Summary of the invention
The object of the invention is to overcome the above-mentioned defect of traditional flapping wing aircraft thruster, invent a kind of for the higher taper rotary flapping wing thrust generating apparatus of the efficiency of aircraft.
A taper rotary flapping wing thrust generating apparatus, is comprised of main shaft, pivoted arm, fin, wing axle, wing axis positioner, pilot bar and guides.One end of main shaft is connected with aircraft fuselage by antifriction-bearing box, and one end of pivoted arm is connected with the other end of main shaft is vertical, and one end of the other end of pivoted arm and wing axle is connected, and the angle of wing axle and pivoted arm is acute angle, and wing axle, pivoted arm and main shaft are in same plane; The other end of wing axle is connected in the leading edge place of fin by antifriction-bearing box and fin, wing axle is parallel with fin leading edge, and fin can be around wing axle flexible rotating; The end face of the close pivoted arm of fin is that the root end face of fin is vertical with the leading edge of fin.Wing axis positioner is between fin and pivoted arm, and wing axle is through wing axis positioner being entangled by wing axis positioner, and wing axle can be around wing axis positioner center switch, but can not move axially.Pilot bar is comprised of round bar, U-shaped fork and bearing pin, the closed end of one end of round bar and U-shaped fork is connected, round bar and U-shaped fork draw a straight line, the root that the bearing pin vertical with round bar that the open end that pilot bar is pitched by its U-shaped is installed and fin work are connected in fin close wing axle place, the plane of bearing pin vertically passing fin leading edge and trailing edge, the clearance of U-shaped fork thickness direction enough guarantees that the fin clipping can do neatly the swing of fin in-plane in U-shaped fork.Guides is fixedly bumped in oscillating bearing by linear bearing and forms; Guides is connected by the shell of its oscillating bearing and the fuselage of aircraft.The other end of round bar is through the linear bearing of guides, and round bar can do reciprocating linear motion neatly in linear bearing, round bar can be around the center of guides flexible switch.The U-shaped fork that forms pilot bar has enough length, to guarantee that the whole rotation process of fin can not be stuck; Round bar has enough length to guarantee that round bar is not deviate from guides in the whole rotation process of fin; Guides is installed near wing axis positioner as far as possible, but should guarantee that fin and U-shaped fork can not touch guides in the whole rotation process of fin; Main shaft and wing axis positioner are respectively in the both sides of pivoted arm plane of rotation, and wing axis positioner is on the extended line of main shaft, and guides and wing axis positioner are in the same side of pivoted arm plane of rotation; Guides is greater than wing axis positioner to the distance of pivoted arm plane of rotation to the distance of pivoted arm plane of rotation.
For reducing the resistance of air, improve 1ift-drag ratio, improve the efficiency of fluttering, the aerofoil profile of fin adopts flat pattern or epirelief concave shape under epirelief.
The principle of work of this kind of taper 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 wing axle to rotate, traction lower panel at wing axle rotates, due to the restriction of pilot bar and guides, guides all the time in the plane in crossing fin leading edge and trailing edge or near, during fin rotation, its angle of attack revolves to turn around at a cycle of operations and interior regular variation can occur, meet flapping wing, be conducive to produce thrust.Because guides approaches wing axis positioner, install, in one-period, the effect of flutterring generation under fin much larger than on flutter, the efficiency that produces lift is higher.Change the size that rotating speed can change thrust, the direction of thrust is to realize by changing the relative height of guides and main shaft.Because the angle of wing axle and pivoted arm is acute angle, and be subject to the restriction of wing axis positioner, in the left and right sides of wing axis positioner, the rotational trajectory of wing axle is taper, only needs shorter pivoted arm, and the scope of fluttering of fin is larger, efficiency is high, and this is simple and compact for structure, lightweight construction; Because fin is done tapered circumference rotation, rotating speed is higher, can produce larger thrust, and less demanding to the strength at repeated alternation of material.
Accompanying drawing explanation
Fig. 1 is the schematic diagram of a kind of taper rotary flapping wing of the present invention thrust generating apparatus.
In figure, 1-main shaft, 2-pivoted arm, 3-wing axis positioner, 4-wing axle, 5-fin, 6-pilot bar, 61-round bar, 62-U shape fork, 63-bearing pin, 7-guides, 71-linear bearing, 72-oscillating bearing; The hand of rotation of the arc representation main shaft 1 of main shaft 1 place's band arrow.
The specific embodiment
Now 1 for example the present invention is illustrated by reference to the accompanying drawings: a kind of taper rotary flapping wing thrust generating apparatus, is comprised of main shaft 1, pivoted arm 2, fin 5, wing axle 4, wing axis positioner 3, pilot bar 6 and guides 7.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, one end of the other end of pivoted arm 2 and wing axle 4 is connected, the angle α of wing axle 4 and pivoted arm 2 is between 30 ° ~ 60 °, and wing axle 4, pivoted arm 2 and main shaft 1 are in same plane; The other end of wing axle 1 is connected in the leading edge place of fin 5 by antifriction-bearing box and fin 5, wing axle 4 is parallel with fin 5 leading edges, and fin 5 can be around wing axle 4 flexible rotatings; The end face of the close pivoted arm 2 of fin 5 is that the root end face of fin 5 is vertical with the leading edge of fin 5.Wing axis positioner 3 is a swivel bearing (swivel bearing), wing axis positioner 3 is between fin 5 and pivoted arm 2, wing axle 4 passes wing axis positioner 3 and is entangled by wing axis positioner 3, wing axle 4 can be around wing axis positioner 3 center switches, the maximum taper of switch is greater than 120 °, but can not move axially.Pilot bar 6 is comprised of round bar 61, U-shaped fork 62 and bearing pin 63; The closed end of one end of round bar 61 and U-shaped fork 62 is connected, round bar 61 draws a straight line with U-shaped fork 62, the bearing pin vertical with round bar 61 63 that pilot bar 6 is installed by the open end of its U-shaped fork 62 and fin 5 root that is connected in fin 5 alive is also near wing axle 4 places, the plane of bearing pin 63 vertically passing fin 5 leading edges and trailing edge, the clearance that U-shaped is pitched 62 thickness directions enough guarantees that the fin 5 clipping can pitch the swing of making neatly fin 5 in-planes in 62 at U-shaped.Guides 7 is fixedly bumped in oscillating bearing 72 by linear bearing 71 and forms; Guides 7 is connected by the shell of its oscillating bearing 72 and the fuselage of flapping wing aircraft.The other end of round bar 61 is through the linear bearing 71 of guides 7, and round bar 61 can do reciprocating linear motion neatly in linear bearing 71, round bar 61 can be around the center of guides 7 flexible switch.The U-shaped fork 62 that forms pilot bar 6 has enough length, to guarantee that the whole rotation process of fin 5 can not be stuck; Round bar 61 has enough length to guarantee that round bar 61 is not deviate from guides 7 in the whole rotation process of fin 5; Guides 7 is installed near wing axis positioner 3 as far as possible, but should guarantee that fin 5 and U-shaped fork 62 can not touch guides 7 in the whole rotation process of fin 5; Main shaft 1 and wing axis positioner 3 are respectively in the both sides of pivoted arm 2 plane of rotations, and wing axis positioner 3 is on the extended line of main shaft 1, and guides 7 and wing axis positioner 3 are in the same side of pivoted arm 2 plane of rotations; Guides 7 to the distance of pivoted arm 2 plane of rotations in wing axis positioner 3 between 1.3 times ~ 2.5 times of the distance of pivoted arm 2 plane of rotations.
For reducing the resistance of air, improve 1ift-drag ratio, improve the efficiency of fluttering, the aerofoil profile of fin 5 adopts flat pattern or epirelief concave shape under epirelief.
The principle of work of this kind of taper rotary flapping wing thrust generating apparatus is: 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 wing axle 4 to rotate, traction lower panel 5 at wing axle 4 rotates, restriction due to pilot bar 6 and guides 7, guides 7 all the time in the plane in crossing fin 5 leading edges and trailing edge or near, during fin 5 rotation, its angle of attack revolves at a cycle of operations the interior meeting of turning around regular variation occurs, meet flapping wing, be conducive to produce thrust.When fin 5 rotates a circle, the concrete change procedure of its angle of attack is: suppose that guides 7 and main shaft 1 are in same level, now guides 7 is zero with the relative height of main shaft 1, the reference position of supposing fin 5 rotations is the position of fin 5 the most close guidess 7, now the angle of attack of fin 5 is negative 90 °, rotation traction along with wing axle 4, fin 5 upward movements, the absolute value of the angle of attack is reduced to rapidly 0 °, now pilot bar 6 cross main shaft 1 horizontal surface above tangent with the rotating cone of wing axle 4, and rear wing axle 4 continues rotation, the angle of attack of fin 5 becomes 90 ° more slowly from 0 °, pilot bar 6 levels now, fin 5 is away from guides 7, continuation traction along with wing axle 4, fin 5 moves downward, the angle of attack becomes 0 ° more slowly from 90 °, now pilot bar 6 cross main shaft 1 horizontal surface below tangent with the rotating cone of wing axle 4, continuation rotation along with wing axle 4, the angle of attack of fin 5 becomes rapidly negative 90 ° by 0 °, now get back to reference position, complete a swing circle.Because guides 7 approaches wing axis positioner 3, install, in one-period, the effect that fin is flutterred generation for 5 times much larger than on flutter, the efficiency that produces lift is higher.Change the size that rotating speed can change thrust, the direction of thrust is to realize with the relative height of main shaft 1 by changing guides 7.Because wing axle 4 is acute angle with the angle of pivoted arm 2, and be subject to the restriction of wing axis positioner 3, in the left and right sides of wing axis positioner 3, the rotational trajectory of wing axle 4 is taper, only needs shorter pivoted arm 2, and the scope of fluttering of fin 5 is larger, efficiency is high, and this is simple and compact for structure, lightweight construction; Because fin 5 is done tapered circumference rotation, rotating speed is higher, can produce larger thrust, and less demanding to the strength at repeated alternation of material.
Use in couples this contrive equipment can produce larger thrust on aircraft.
Claims (5)
1. a taper rotary flapping wing thrust generating apparatus, is characterized in that: main shaft (1), pivoted arm (2), wing axis positioner (3), wing axle (4), fin (5), pilot bar (6) and guides (7), consist of; One end of pivoted arm (2) is connected with vertical being connected of main shaft (1), the other end of pivoted arm (2) and wing axle (4), and wing axle (4) is acute angle with the angle of pivoted arm (2), and wing axle (4), pivoted arm (2) and main shaft (1) are in same plane; Wing axle (1) is connected in fin (5) leading edge place by antifriction-bearing box and fin (5), and wing axle (4) is parallel with fin (5) leading edge; Wing axis positioner (3) is between fin (5) and pivoted arm (2), and wing axle (4) passes wing axis positioner (3) and entangled by wing axis positioner (3); Pilot bar (6) is comprised of round bar (61), U-shaped fork (62) and bearing pin (63), the closed end of one end of round bar (61) and U-shaped fork (62) is connected, the bearing pin (63) vertical with round bar (61) that pilot bar (6) is installed by the open end of its U-shaped fork (62) lived and is connected in the root of fin (5) and near wing axle (4), locates the plane of bearing pin (63) vertically passing fin (5) leading edge and trailing edge with fin (5); Guides (7) is fixedly bumped in oscillating bearing (72) by linear bearing (71) and forms; The other end of round bar (61) is through the linear bearing (71) of guides (7); Main shaft (1) and wing axis positioner (3) are respectively in the both sides of pivoted arm (2) plane of rotation, and guides (7) and wing axis positioner (3) are in the same side of pivoted arm (2) plane of rotation; Guides (7) is greater than wing axis positioner (3) to the distance of pivoted arm (2) plane of rotation to the distance of pivoted arm (2) plane of rotation.
2. a kind of taper rotary flapping wing thrust generating apparatus according to claim 1, is characterized in that: the angle (α) of wing axle (4) and pivoted arm (2) is between 30 ° ~ 60 °.
3. a kind of taper rotary flapping wing thrust generating apparatus according to claim 1, is characterized in that: the aerofoil profile of fin (5) adopts flat pattern or epirelief concave shape under epirelief.
4. a kind of taper rotary flapping wing thrust generating apparatus according to claim 1, is characterized in that: wing axis positioner (3) is a swivel bearing.
5. a kind of taper rotary flapping wing thrust generating apparatus according to claim 1, is characterized in that: guides (7) to the distance of pivoted arm (2) plane of rotation in wing axis positioner (3) between 1.3 times ~ 2.5 times of the distance of pivoted arm (2) plane of rotation.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420282418.1U CN203864999U (en) | 2014-05-30 | 2014-05-30 | Tapered rotating flapping wing thrust generating device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420282418.1U CN203864999U (en) | 2014-05-30 | 2014-05-30 | Tapered rotating flapping wing thrust generating device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203864999U true CN203864999U (en) | 2014-10-08 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201420282418.1U Withdrawn - After Issue CN203864999U (en) | 2014-05-30 | 2014-05-30 | Tapered rotating flapping wing thrust generating device |
Country Status (1)
| Country | Link |
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| CN (1) | CN203864999U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103991545A (en) * | 2014-05-30 | 2014-08-20 | 佛山市神风航空科技有限公司 | Conical rotary flapping wing thrust generation device |
| CN104494828A (en) * | 2014-12-15 | 2015-04-08 | 佛山市神风航空科技有限公司 | Panel type flapping wing lifting device with electromagnetic brake |
-
2014
- 2014-05-30 CN CN201420282418.1U patent/CN203864999U/en not_active Withdrawn - After Issue
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103991545A (en) * | 2014-05-30 | 2014-08-20 | 佛山市神风航空科技有限公司 | Conical rotary flapping wing thrust generation device |
| CN103991545B (en) * | 2014-05-30 | 2016-01-06 | 佛山市神风航空科技有限公司 | A kind of taper rotary flapping wing thrust generating apparatus |
| CN104494828A (en) * | 2014-12-15 | 2015-04-08 | 佛山市神风航空科技有限公司 | Panel type flapping wing lifting device with electromagnetic brake |
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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: 20141008 Effective date of abandoning: 20160106 |
|
| C25 | Abandonment of patent right or utility model to avoid double patenting |