CN104477388B - A kind of four fins are flat claps flapping wing aircraft - Google Patents

A kind of four fins are flat claps flapping wing aircraft Download PDF

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Publication number
CN104477388B
CN104477388B CN201410769872.4A CN201410769872A CN104477388B CN 104477388 B CN104477388 B CN 104477388B CN 201410769872 A CN201410769872 A CN 201410769872A CN 104477388 B CN104477388 B CN 104477388B
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swing device
bat swing
fin
fuselage
synchronous wheel
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CN104477388A (en
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王志成
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Jiangsu Jiuzhou Electronic Technology Co., Ltd
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Foshan Shenfeng Aviation Technology Co Ltd
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Abstract

A kind of four fins are flat claps flapping wing aircraft, belongs to technical field of aerospace, comprises fuselage, vertical fin, left back bat swing device, right back bat swing device, left front bat swing device, right front bat swing device and landing gear. Control system, airborne equipment and power unit it is furnished with in fuselage. It is configured with automatic navigation autonomous driving device or remote-control equipment. Left back bat swing device, right back bat swing device, the left front bat swing device left and right sides that be between two symmetrically arranged in fuselage identical with right front bat swing device structure and parameter. Vertical fin is made up of fixed fin and yaw rudder. Fixed synchronous wheel in left back bat swing device is 1: 1 with the transmitting ratio of dynamic synchronous wheel. The rear front position of the left and right sides of fuselage is provided with left back breach, right back breach, left front breach and right front breach respectively. Four fins can not laterally produce horizontal component in the process of flapping motion, and efficiency is higher. This aircraft is used for taking photo by plane, geographical measurements, traffic duty, agricultural operation, military investigate and rescue and relief work multiple-task.

Description

A kind of four fins are flat claps flapping wing aircraft
Technical field
A kind of four fins are flat claps flapping wing aircraft, belongs to technical field of aerospace, particularly relates to a kind of flapping wing aircraft.
Background technology
The wing of tradition flapping wing aircraft is fluttered by arc track, portion of air power component is created in the horizontal direction of transverse direction and wing length direction during wing flapping motion, moving ahead and going up to the air of aircraft is not all had positive effect by the component of this horizontal direction, is a kind of loss of power; Tradition flapping wing aircraft is mostly two panels wing, and flight underaction, maneuvering ability is not strong.
Summary of the invention
It is an object of the invention to overcome the above-mentioned deficiency of existing flapping wing aircraft, invent the four fins flat bat flapping wing aircraft of the higher maneuverability of a kind of efficiency.
A kind of four fins are flat claps flapping wing aircraft, comprises fuselage, vertical fin, left back bat swing device, right back bat swing device, left front bat swing device, right front bat swing device and landing gear. Being furnished with control system, airborne equipment and power unit in fuselage, this aircraft flight attitude is handled by control system, and airborne equipment comprises various flight instrumentation instrument and capture apparatus, and employing lithium cell is that control system, airborne equipment and all motors are powered. It is configured with automatic navigation autonomous driving device or remote-control equipment, adopts automatic navigation autonomous driving mode or remote control mode flight. Left back bat swing device, right back bat swing device, the left front bat swing device left and right sides that be between two symmetrically arranged in fuselage identical with right front bat swing device structure and parameter. Vertical fin is made up of moving part and the yaw rudder of the fixed part of front section and fixed fin and rear section. Yaw rudder is deflection under the manipulation of control system, and this aircraft can be made to go off course to the left or to the right. Landing gear adopts wheeled landing gear. In order to compact construction and facilitate left back bat swing device, right back bat swing device, left front bat swing device and right front bat swing device to flutter up and down flexibly, it is provided with left back breach, right back breach, left front breach and right front breach respectively in the rear front position of the left and right sides of fuselage.
The structure of left back bat swing device is: comprise motor, main shaft, swing arm, wing axle, fin, fixed synchronous wheel, synchronous band and dynamic synchronous wheel. Fin is non-rigid, and fin leading edge is perfectly round abundant, and airfoil point is thin, relatively hard near the part of leading edge, softer near the part of trailing edge. Fin planeform is rectangular, and the aerofoil profile of fin adopts flat type aerofoil profile under epirelief concave shape or epirelief. Fin is horizontally disposed, and the rear end of wing axle is vertically fixed on the leading edge medium position of fin, and wing axle is horizontally disposed and and main axis parallel. Main shaft vertical equity is arranged, the front section of main shaft is connected with fuselage by bearing after the centre hole of fixed synchronous wheel, and the front end of main shaft is connected with the output shaft of motor, and the rear end of main shaft is connected with fuselage by bearing. Fixed synchronous wheel is fixed in the left back breach of fuselage by termination and the fuselage of surely synchronous wheel, and fixed synchronous wheel and main shaft are with high coaxial. One end of swing arm is vertical with the stage casing of main shaft to be fixed in the left back breach of fuselage, and the other end of swing arm is by the bearing stage casing that be connected in wing axle vertical with wing axle. Dynamic synchronous wheel is connected in the front end of wing axle, and dynamic synchronous wheel is connected by being synchronously with fixed synchronous wheel, and fixed synchronous wheel is 1: 1 with the transmitting ratio of dynamic synchronous wheel. Synchronous band plane of movement is vertical with main shaft. Motor is fixedly mounted in the frame of fuselage, control system can to the rotating speed of motor, turn to and angle range controls.
From the tail end of this invention aircraft toward front end, the principle of work of left back bat swing device is: under flutter process: assume that zero position is that fin is in higher position, under the control of control system, start motor to rotate counterclockwise, under the driving of motor, spindle axis counterclockwise rotation, drive swing arm rotates counterclockwise, fixed synchronous wheel maintains static, owing to the transmitting ratio of surely synchronous wheel with dynamic synchronous wheel is 1: 1, synchronous band drives the clockwise rotation of dynamic synchronous wheel, the leading edge of fin is kept to be horizontal lower bat, the displaced phase clapped under the identical chord positions of spanwise fin is same, realize flat bat downwards. owing to fin is non-rigid, have certain soft degree and elasticity, when clapping under fin the trailing edge of fin want delayed fin leading edge some. owing to the aerofoil profile of fin is flat type under epirelief concave shape or epirelief, claps under fin and produce bigger lift upwards and less thrust forward. on the process of flutterring be: be in relatively lower position from fin, control system control motor reversal, under the driving of motor, main shaft rotates clockwise, and drives swing arm to rotate clockwise, fixed synchronous wheel maintains static, owing to the transmitting ratio of surely synchronous wheel with dynamic synchronous wheel is 1: 1, synchronous band drives the counterclockwise rotation of dynamic synchronous wheel, keeps the leading edge of fin to be horizontal bat, the displaced phase clapped along the identical chord positions of spanwise fin is same, it is achieved upwards flat bat. owing to fin is non-rigid, having certain soft degree and elasticity, when fin is clapped, the trailing edge of fin also can the leading edge of delayed fin. owing to the aerofoil profile of fin is flat type under epirelief concave shape or epirelief, compared with lower bat, the degree of the leading edge of the delayed fin of the trailing edge of fin is larger. upper bat fin produces bigger thrust forward and less lift upwards or does not produce lift, and the size that upper bat process produces lift is relevant with the speed flown before this aircraft, and the lift that the front speed flown produces more soon is more big. the speed that fin is flapped and angle scope are the rotating speeds by controlling motor, turn to and carry out regulating with corner, and the scope flapped is adjustable between 0 �� to 180 ��. if on flutter and swing arm gone to directly over main shaft, be in vertical position, under flutter and swing arm gone to immediately below main shaft, be in vertical position, then the scope fluttered is 180 ��.
The principle of work of left front bat swing device is identical with the principle of work of left back bat swing device, and the direction fluttered is identical.
The principle of work of right back bat swing device is identical with the principle of work of left back bat swing device, and the direction fluttered is symmetrical. From the tail end of this invention aircraft toward front end, the main shaft of right back bat swing device rotates clockwise, and claps under its fin; The spindle axis counterclockwise rotation of right back bat swing device, its fin is clapped.
The principle of work of right front bat swing device is identical with the principle of work of right back bat swing device, and the direction fluttered is identical.
The fin of left back bat swing device, right back bat swing device, left front bat swing device and right front bat swing device all can not laterally produce horizontal component in the process of flapping motion, and efficiency is higher.
The power that synchronous V belt translation mode in left back bat swing device, right back bat swing device, left front bat swing device and right front bat swing device is replaced with this invention aircraft of chain drive mode simultaneously can be larger, and loading capacity can be strong.
Left back bat swing device, right back bat swing device, left front bat swing device and right front bat swing device be separately control independently, their motor all adopts servomotor, controlling more convenient, especially convenient their angle scope of fluttering of control and speed of fluttering, make this aircraft flight maneuverability more.
Accompanying drawing explanation
Fig. 1 is that a kind of four fins of the present invention equal the schematic rear view clapping flapping wing aircraft, in this figure, left back bat swing device, right back bat swing device, left front bat swing device and right front bat swing device are all in down in the process of flutterring, and their fin is all in lower bat, down, trailing edge is upward for the leading edge of four fins; Fig. 2 is the schematic top plan view of Fig. 1; Fig. 3 is the left view schematic diagram of Fig. 1; Fig. 4 is that a kind of four fins of the present invention are put down and clapped the left back bat swing device of flapping wing aircraft, right back bat swing device, left front bat swing device and right front bat swing device and be all in schematic rear view when flutterring process, in figure, their fin is all in bat process, upward, trailing edge is down for the leading edge of four fins.
In figure, 1-fuselage, the left back breach of 11-, the right back breach of 12-, the left front breach of 13-, the right front breach of 14-; 2-vertical fin, 21-fixed fin, 22-yaw rudder; The left back bat swing device of 3-; The right back bat swing device of 4-; The left front bat swing device of 5-; The right front bat swing device of 6-; 7-landing gear.
Having of the integral part belonging to left back bat swing device 3 indicated in the drawings: 31-motor, 32-main shaft, 33-swing arm, 34-wing axle, 35-fin, the leading edge of 351-fin, the trailing edge of 352-fin, 36-synchronously takes turns surely, the termination that 361-synchronously takes turns surely, 37-is synchronously with, the dynamic synchronous wheel of 38-.
In Fig. 1 and Fig. 4, the longest motion track that when the 341 left back bat swing devices 3 of expression are fluttered, its wing axle 34 is possible.
Embodiment
Now 1 ~ 4 the present invention is specifically illustrated by reference to the accompanying drawings: a kind of four fins are flat claps flapping wing aircraft, comprises fuselage 1, vertical fin 2, left back bat swing device 3, right back bat swing device 4, left front bat swing device 5, right front bat swing device 6 and landing gear 7. Being furnished with control system, airborne equipment and power unit in fuselage 1, this aircraft flight attitude is handled by control system, and airborne equipment comprises various flight instrumentation instrument and capture apparatus, and employing lithium cell is that control system, airborne equipment and all motors are powered. It is configured with automatic navigation autonomous driving device or remote-control equipment, adopts automatic navigation autonomous driving mode or remote control mode flight. Left back bat swing device 3, right back bat swing device 4, left front bat swing device 5 left and right sides that be between two symmetrically arranged in fuselage 1 identical with right front bat swing device 6 structure and parameter. Vertical fin 2 is made up of moving part and the yaw rudder 22 of the fixed part of front section and fixed fin 21 and rear section. Yaw rudder 22 is deflection under the manipulation of control system, and this aircraft can be made to go off course to the left or to the right. Landing gear 7 adopts wheeled landing gear. In order to compact construction and facilitate left back bat swing device 3, right back bat swing device 4, left front bat swing device 5 and right front bat swing device 6 to flutter up and down flexibly, it is provided with left back breach 11, right back breach 12, left front breach 13 and right front breach 14 respectively in the rear front position of the left and right sides of fuselage 1.
The structure of left back bat swing device 3 is: comprise motor 31, main shaft 32, swing arm 33, wing axle 34, fin 35, fixed synchronous wheel 36, synchronous band 37 and dynamic synchronous wheel 38. Fin 35 is non-rigid, and fin 35 leading edge is perfectly round abundant, and airfoil point is thin, relatively hard near the part of leading edge, softer near the part of trailing edge. Fin 35 planeform is rectangular, and the aerofoil profile of fin 35 adopts flat type under epirelief concave shape or epirelief. Fin 35 is horizontally disposed, and the rear end of wing axle 34 is vertically fixed on the leading edge medium position of fin 35, and wing axle 34 is horizontally disposed and parallel with main shaft 32. Main shaft 32 vertical equity is arranged, the front section of main shaft 32 is connected with fuselage 1 by bearing after the centre hole of fixed synchronous wheel 36, the front end of main shaft 32 is connected with the output shaft of motor 31, if motor 31 adopts high speed motor, then motor 31 is connected with main shaft 32 after slowing down again, and the rear end of main shaft 32 is connected with fuselage 1 by bearing. Fixed synchronous wheel 36 is fixed in the left back breach 11 of fuselage 1 by the termination 361 of surely synchronous wheel with fuselage 1, and fixed synchronous wheel 36 and main shaft 32 are with high coaxial. One end of swing arm 33 is vertical with the stage casing of main shaft 32 to be fixed in the left back breach 11 of fuselage 1, and the other end of swing arm 33 is by the bearing stage casing that be connected in wing axle 34 vertical with wing axle 34. Dynamic synchronous wheel 38 is connected in the front end of wing axle 34, and dynamic synchronous wheel 38 is connected by synchronous band 37 with fixed synchronous wheel 36, and fixed synchronous wheel 36 is 1: 1 with the transmitting ratio of dynamic synchronous wheel 38. Synchronous band 37 plane of movement are vertical with main shaft 32. Motor 31 is fixedly mounted in the frame of fuselage 1, control system can to the rotating speed of motor 31, turn to and angle range controls.
From the tail end of this invention aircraft toward front end, the principle of work of left back bat swing device 3 is: under flutter process: assume that zero position is that fin 35 is in higher position, under the control of control system, start motor 31 to rotate counterclockwise, under the driving of motor 31, main shaft 32 rotates counterclockwise, swing arm 33 is driven to rotate counterclockwise, fixed synchronous wheel 36 maintains static, it is 1: 1 owing to surely synchronously taking turns 36 with the dynamic synchronous transmitting ratio taking turns 38, synchronous band 37 drive dynamic synchronous wheel 38 clockwise rotations, the leading edge 351 of fin is kept to be horizontal lower bat, the displaced phase clapped under the identical chord positions of spanwise fin 35 is same, realize flat bat downwards. owing to fin 35 is non-rigid, have certain soft degree and elasticity, when fin 35 times is clapped the trailing edge 352 of fin want delayed fin leading edge 351 some. owing to the aerofoil profile of fin 35 is flat type under epirelief concave shape or epirelief, fin is clapped for 35 times and is produced bigger lift upwards and less thrust forward. on the process of flutterring be: be in relatively lower position from fin 35, control system control motor 31 reverses, under the driving of motor 31, main shaft 32 rotates clockwise, and drives swing arm 33 to rotate clockwise, fixed synchronous wheel 36 maintains static, being 1: 1 owing to surely synchronously taking turns 36 with the transmitting ratio of dynamic synchronous wheel 38, the drive of synchronous band 37 is dynamic synchronously takes turns 38 counterclockwise rotations, and the leading edge 351 of maintenance fin is horizontal bat, the displaced phase clapped along the identical chord positions of spanwise fin 35 is same, it is achieved upwards flat bat. owing to fin 35 is non-rigid, having certain soft degree and elasticity, when fin 35 is clapped, the trailing edge 352 of fin also can the leading edge 351 of delayed fin. owing to the aerofoil profile of fin 35 is flat type under epirelief concave shape or epirelief, compared with lower bat, the degree of the leading edge 351 of the delayed fin of trailing edge 352 of fin is larger. upper bat fin 35 produces bigger thrust forward and less lift upwards or does not produce lift, and the size that upper bat process produces lift is relevant with the speed flown before this aircraft, and the lift that the front speed flown produces more soon is more big. the speed that fin 35 is flapped and angle scope are the rotating speeds by controlling motor 31, turn to and carry out regulating with corner, and the scope flapped is between 0 �� to 180 ��. if on flutter and swing arm 33 gone to directly over main shaft 32, be in vertical position, under flutter and swing arm 33 gone to immediately below main shaft 32, be in vertical position, then the scope fluttered is 180 ��.
The principle of work of left front bat swing device 5 is identical with the principle of work of left back bat swing device 3, and the direction fluttered is identical.
The principle of work of right back bat swing device 4 is identical with the principle of work of left back bat swing device 3, and the direction fluttered is symmetrical. From the tail end of this invention aircraft toward front end, the main shaft of right back bat swing device 4 rotates clockwise, and claps under its fin; The spindle axis counterclockwise rotation of right back bat swing device 4, its fin is clapped.
The principle of work of right front bat swing device 6 is identical with the principle of work of right back bat swing device 4, and the direction fluttered is identical.
The fin of left back bat swing device 3, right back bat swing device 4, left front bat swing device 5 and right front bat swing device 6 all can not laterally produce horizontal component in the process of flapping motion, and efficiency is higher.
When load is heavier, the synchronous V belt translation mode in left back bat swing device 3, right back bat swing device 4, left front bat swing device 5 and right front bat swing device 6 is replaced with chain drive mode simultaneously, and transmitting ratio is constant.
The independent separately control of left back bat swing device 3, right back bat swing device 4, left front bat swing device 5 and right front bat swing device 6, their motor all adopts servomotor, controlling more convenient, especially convenient their angle scope of fluttering of control and speed of fluttering, make this aircraft flight maneuverability more.
It is furnished with pick up camera and information processing system in fuselage 1, can take photo by plane, the image information of shooting can be sent to uphole equipment. Machine can realize remote control flight with this aircraft of remote-control equipment of ground configurations match.
This aircraft adopts hand to throw mode and takes off or adopt the runway mode of sliding to take off; Left back bat swing device 3, right back bat swing device 4, left front bat swing device 5 and right front bat swing device 6 these four clap flap frequency and the angle scope of flapping of swing device by control system regulating and controlling, realize aerodynamic size and direction that their four fins of regulating and controlling produce, in conjunction with the control to vertical fin 2, thus fly before realizing, pitching, the different flight attitude such as turning; Four fins of left back bat swing device 3, right back bat swing device 4, left front bat swing device 5 and right front bat swing device 6 are locked in the level attitude with the high center of gravity crossing aircraft or higher than the level attitude crossing aircraft center of gravity, facilitate this aircraft to glide or landing.
A kind of four fins of the present invention are flat claps that flapping wing aircraft can be used for taking photo by plane, geographical measurements, traffic duty, agricultural operation, military investigate and the multiple-task such as rescue and relief work.

Claims (11)

1. a fin flat bat flapping wing aircraft, it is characterised in that: it comprises fuselage (1), vertical fin (2), left back bat swing device (3), right back bat swing device (4), left front bat swing device (5), right front bat swing device (6) and landing gear (7); Fuselage is furnished with control system, airborne equipment and power unit in (1); It is configured with automatic navigation autonomous driving device or remote-control equipment; Left back bat swing device (3), right back bat swing device (4), left front bat swing device (5) left and right sides that be between two symmetrically arranged in fuselage (1) identical with right front bat swing device (6) structure and parameter; Vertical fin (2) is made up of moving part and the yaw rudder (22) of the fixed part of front section and fixed fin (21) and rear section; The rear front position of the left and right sides of fuselage (1) is provided with left back breach (11), right back breach (12), left front breach (13) and right front breach (14) respectively; Left back bat swing device (3) comprises motor (31), main shaft (32), swing arm (33), wing axle (34), fin (35), fixed synchronous wheel (36), synchronous band (37) and dynamic synchronous wheel (38); Fin (35) is non-rigid, and fin (35) leading edge is perfectly round abundant, and fin (35) trailing edge point is thin, relatively hard near the part of leading edge, softer near the part of trailing edge; Fin (35) is horizontally disposed, and the rear end of wing axle (34) is vertically fixed on the leading edge medium position of fin (35), and wing axle (34) is horizontally disposed and parallel with main shaft (32); Main shaft (32) vertical equity is arranged, the front section of main shaft (32) is connected with fuselage (1) by bearing after the centre hole of fixed synchronous wheel (36), the front end of main shaft (32) is connected with the output shaft of motor (31), and the rear end of main shaft (32) is connected with fuselage (1) by bearing; Fixed synchronous wheel (36) is fixed in the left back breach (11) of fuselage (1) by the termination (361) of fixed synchronous wheel with fuselage (1), and fixed synchronous wheel (36) and main shaft (32) are with high coaxial; One end of swing arm (33) is vertical with the stage casing of main shaft (32) to be fixed in the left back breach (11) of fuselage (1), and the other end of swing arm (33) is by the bearing stage casing that be connected in wing axle (34) vertical with wing axle (34); Dynamic synchronous wheel (38) is connected in the front end of wing axle (34), and dynamic synchronous wheel (38) is connected by synchronous band (37) with fixed synchronous wheel (36), and fixed synchronous wheel (36) is 1: 1 with the transmitting ratio of dynamic synchronous wheel (38); Synchronous band (37) plane of movement is vertical with main shaft (32); Motor (31) is fixedly mounted in the frame of fuselage (1), control system can to the rotating speed of motor (31), turn to and control with angle range; Left back bat swing device (3), right back bat swing device (4), left front bat swing device (5) are identical with the principle of work of right front bat swing device (6).
2. a kind of four fins according to claim 1 are flat claps flapping wing aircraft, it is characterized in that: the fin planeform of left back bat swing device (3), right back bat swing device (4), left front bat swing device (5) and right front bat swing device (6) is rectangular, aerofoil profile adopts flat type under epirelief concave shape or epirelief.
3. a kind of four fins according to claim 1 are flat claps flapping wing aircraft, it is characterised in that: the independent separately control of left back bat swing device (3), right back bat swing device (4), left front bat swing device (5) and right front bat swing device (6).
4. a kind of four fins according to claim 1 are flat claps flapping wing aircraft, it is characterised in that: the motor of left back bat swing device (3), right back bat swing device (4), left front bat swing device (5) and right front bat swing device (6) all adopts servomotor.
5. a kind of four fins according to claim 1 are flat claps flapping wing aircraft, it is characterised in that: fuselage is furnished with pick up camera and information processing system in (1), the image information of shooting can be sent to uphole equipment.
6. a kind of four fins according to claim 1 are flat claps flapping wing aircraft, it is characterised in that: with the remote-control equipment of ground configurations match on machine.
7. a kind of four fins according to claim 1 are flat claps flapping wing aircraft, it is characterised in that: the scope that fin (35) is flapped is between 0 �� to 180 ��.
8. a kind of four fins according to claim 1 are flat claps flapping wing aircraft, it is characterised in that: landing gear (7) adopts wheeled landing gear.
9. a kind of four fins according to claim 1 are flat claps flapping wing aircraft, it is characterised in that: when motor adopts high speed motor, motor by slowing down after be connected with corresponding main shaft again.
10. a kind of four fins according to claim 1 are flat claps flapping wing aircraft, it is characterized in that: synchronous V belt translation in left back bat swing device (3), right back bat swing device (4), left front bat swing device (5) and right front bat swing device (6) or adopt chain drive, transmitting ratio is constant.
11. one four fins according to claim 1 or 9 or 10 are flat claps flapping wing aircraft, it is characterised in that: this aircraft adopts hand to throw mode and takes off or adopt the runway mode of sliding to take off.
CN201410769872.4A 2014-12-15 2014-12-15 A kind of four fins are flat claps flapping wing aircraft Active CN104477388B (en)

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CN110844066B (en) * 2019-11-26 2021-01-26 中国科学院合肥物质科学研究院 Flapping wing aircraft with tandem double-pair-wing structure and control method thereof

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DE3435125A1 (en) * 1984-09-25 1986-04-03 Ludwig 7500 Karlsruhe Naake Springing system for flapping gliders
DE3537365C2 (en) * 1985-10-19 1989-01-19 Ernst 7000 Stuttgart De Dausch
CN1513726A (en) * 2003-08-11 2004-07-21 施仲伟 Couple distance moving arc type feathering aricraft
CN1629038A (en) * 2004-10-02 2005-06-22 高晓燕 Aircraft with flapping wings
CN104002971B (en) * 2014-05-30 2016-01-20 佛山市神风航空科技有限公司 A kind of four rotary flapping wing flying platforms
CN204297083U (en) * 2014-12-15 2015-04-29 佛山市神风航空科技有限公司 A kind of four fins are flat claps flapping wing aircraft

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Effective date of registration: 20191219

Address after: 225236 Airport Industrial Zone, dinggou Town, Jiangdu District, Yangzhou City, Jiangsu Province

Patentee after: Jiangsu Jiuzhou Electronic Technology Co., Ltd

Address before: Foshan City, Guangdong province 528500 city streets Gaoming District No. 78 Jiangwan Road, room 402 Fu Wan

Patentee before: Shenfeng science and technology of aviation Co., Ltd of Foshan City