CN204310044U - A kind of rotating vanes class flapping wing aircraft - Google Patents
A kind of rotating vanes class flapping wing aircraft Download PDFInfo
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- CN204310044U CN204310044U CN201420788830.0U CN201420788830U CN204310044U CN 204310044 U CN204310044 U CN 204310044U CN 201420788830 U CN201420788830 U CN 201420788830U CN 204310044 U CN204310044 U CN 204310044U
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- fin
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- heart gear
- flapping wing
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Abstract
A kind of rotating vanes class flapping wing aircraft, belongs to technical field of aerospace, forms primarily of fuselage, tail undercarriage, anticlockwise class flapping wing device, right rotation class flapping wing device and alighting gear.Control system, automatic navigation autonomous flight instrument and command and control system is furnished with in fuselage.Anticlockwise class flapping wing device and right rotation class flapping wing device structure, parameter are all identical with principle of work and be symmetrically arranged on the overhanging left socle in the left and right sides of fuselage and right support.Tail undercarriage is driven by small machine.Right rotation class flapping wing device comprises driving engine, main shaft, pivoted arm, center fixed gear wheel, the first nearly heart gear, the first heart gear far away, the first fin, the second nearly heart gear, the second heart gear far away and the second fin; The transmitting ratio of all gears meshing is 1: 1; Flutter under first fin and the second fin hocket and on flutter, produce thrust forward and lift upwards.This aircraft is used for taking photo by plane, Agriculture, forestry And Animal Husbandry operation and military requirement.
Description
Technical field
A kind of rotating vanes class flapping wing aircraft, belongs to technical field of aerospace, particularly relates to a kind flapping wing aircraft.
Background technology
The wing of tradition flapping wing aircraft is fluttered by arc track, portion of air powertrain components is created in the horizontal direction of transverse direction during wing flapping motion, the component of this horizontal direction does not all have positive effect to moving ahead and going up to the air of flapping wing aircraft, is a kind of loss of power.Wing is fluttered up and down, there is steering procedure, and continuity of movement is poor; Flapping wing lift generating device flapping wing sheet being resetted by flapping wing lift system that the patent No. a kind of structure disclosed in the Chinese patent of ZL200910073435.8 is more complicated, although the more traditional flapping wing of efficiency is high, but flutter under fin in process, midway location fin is only had to be horizontal, other time fin and horizontal surface all there is an angle, more leave midway location angle larger, the lift produced is the component of the vertical direction of fin application force, the component of horizontal direction has become loss, and the efficiency producing lift is also limited.
Summary of the invention
The object of the invention is the above-mentioned deficiency overcoming existing flapping wing aircraft, invent the rotating vanes class flapping wing aircraft that a kind of efficiency is higher.
A kind of rotating vanes class flapping wing aircraft, forms primarily of fuselage, tail undercarriage, anticlockwise class flapping wing device, right rotation class flapping wing device and alighting gear.Control system, automatic navigation autonomous flight instrument and command and control system is furnished with in fuselage, the mode that this aircraft adopts automatic navigation autonomous flight pattern and remote control distributor pattern to combine is flown, plane-hop adopts remote control mode flight, and long-distance flight adopts automatic navigation autonomous flight mode flight.Anticlockwise class flapping wing device and right rotation class flapping wing device structure, parameter are all identical with principle of work and be symmetrically arranged on the overhanging left socle in the left and right sides of fuselage and right support, are used for producing lift and thrust.Tail undercarriage is driven by small machine, tail undercarriage plane of rotation can tilt to the left or to the right, also can tilt forward or backward, can produce upwards under the manipulation of control system, to upper left side, to upper right side, forward upward or pulling force rearwardly and upwardly, to realize pitching and the yawed flight attitude of this aircraft.The steering wheel of small machine, operating system, automatic navigation autonomous flight instrument and telecommand equipment adopt lithium battery power supply.Bikini wheel undercarriage after alighting gear adopts.
The concrete structure of right rotation class flapping wing device is: it comprises driving engine, main shaft, pivoted arm, center fixed gear wheel, the first nearly heart gear, the first heart gear far away, the first fin, the second nearly heart gear, the second heart gear far away and the second fin.First nearly heart gear, the first heart gear far away and the first fin and the second nearly heart gear, the second heart gear far away and the second fin two overlap component one_to_one corresponding, and the identical and symmetry of corresponding element structure is arranged on the both sides of center fixed gear wheel.Center fixed gear wheel is fixedly installed in the right support end stretching out right side of fuselage.Main shaft vertical equity is arranged, the rear end of main shaft and pivoted arm are fixed on the center of pivoted arm, the stage casing of main shaft is connected in the centre hole of center fixed gear wheel by bearing and center fixed gear wheel, flexible rotating in the centre hole of main shaft Neng center fixed gear wheel, the front end of main shaft is connected with the output shaft of driving engine.Point-blank, rotational plane and the center fixed gear wheel of the second heart gear far away, the second nearly heart gear, the first nearly heart gear and the first heart gear far away are in same horizontal vertical plane for second heart gear far away, the second nearly heart gear, center fixed gear wheel, the first nearly heart gear and the first heart gear row far away; The rotating shaft of the second heart gear far away is arranged on one end of pivoted arm by bearing, the rotating shaft of the first heart gear far away is arranged on the other end of pivoted arm by bearing; The rotating shaft of the second nearly heart gear is arranged on the centre of a section near the second heart gear far away of pivoted arm by bearing, the rotating shaft of the first nearly heart gear is arranged on the centre of a section near the first heart gear far away of pivoted arm by bearing; Second heart gear far away and the second nearly heart gears meshing, the second nearly heart gear engages with center fixed gear wheel, center fixed gear wheel and the first nearly heart gears meshing, and the first nearly heart gear and the first heart gears meshing far away, the transmitting ratio of all gears meshing is 1: 1.First fin and the second fin are nonrigid rectangular tab, and aerofoil profile is flat pattern under epirelief concave shape or epirelief, specifically certain elasticity.The rear end of the rotating shaft of the first heart gear far away and the first fin are fixed on the front end midway location of the first fin; The rear end of the rotating shaft of the second heart gear far away and the second fin are fixed on the front end midway location of the second fin.When pivoted arm is in horizontal stationary state, the first fin and the second fin are in same level.The section of pivoted arm is aerofoil profile, can produce pulling force forward when pivoted arm rotates.
From the tail end of this aircraft toward front end, the principle of work of right rotation class flapping wing device is: reference position is that the first fin is in extreme higher position, and the second fin is in extreme lower position, and two fins are all in horizontality.Under the control of control system, start the engine, under the driving of power, main shaft rotates clockwise, drive pivoted arm rotates clockwise, because center fixed gear wheel is fixing, and the transmitting ratio of center fixed gear wheel and the first heart gear far away and the second heart gear far away is the anticlockwise direction rotation under the drive of the first heart gear far away and the second heart gear far away respectively while revolving round the sun around main shaft of the 1: 1, first fin and the second fin.First fin runs to lowest part is from highest point and flutters process: flutter under the leading edge maintenance horizontality of the first fin, the displacement of flutterring under the identical chord positions of spanwise first fin is identical, realizes flat flutterring downwards; Because the first fin is nonrigid, have certain elasticity, under flutter midway the first fin trailing edge want delayed first fin leading edge some.Because the aerofoil profile of the first fin is flat pattern under epirelief concave shape or epirelief, under the first fin, flutter the larger lift upwards of generation and less thrust forward.Meanwhile, the second fin runs to highest point from lowest part to carry out flutterring process: the leading edge of the second fin keeps horizontality to flutter, identical along the displacement that the identical chord positions of spanwise second fin is flutterred, and realizes upwards flat flutterring.Because the second fin is nonrigid, have certain elasticity, the second fin being flutterred its trailing edge of midway also can its leading edge delayed.Because the aerofoil profile of the second fin is flat pattern under epirelief concave shape or epirelief, compared with the lower bat of the first fin, the degree of the delayed leading edge of trailing edge of the second fin is larger.Second fin flutterred the larger thrust forward of generation and less lift upwards or do not produce lift, the size producing lift is relevant with the speed that this aircraft moves ahead.First fin and the second fin complete down flutter and on flutter process after, along with the continuation clickwise of main shaft, following first fin is flutterred, flutters under the second fin.Like this, main shaft rotates continuously, flutter under the first fin and the second fin hocket and on flutter, produce thrust forward and lift upwards, maintain this aircraft flight.
The principle of work of anticlockwise class flapping wing device is identical with the principle of work of right rotation class flapping wing device, due to and the symmetrical installation identical with right rotation class flapping wing device structure of anticlockwise class flapping wing device.Main shaft anticlockwise direction rotating band under the driving of the driving engine of anticlockwise class flapping wing device of anticlockwise class flapping wing device moves the pivoted arm anticlockwise direction rotation of anticlockwise class flapping wing device.The fin of anticlockwise class flapping wing device is flutterred at present in the left side of the main shaft of anticlockwise class flapping wing device, flutters on when the right side of the main shaft of anticlockwise class flapping wing device.
Namely all fins laterally can not produce horizontal component of force in spanwise in the process of fluttering up and down, and efficiency is higher.This aircraft adopts two driving engine individual drive, mobility strong.
Accompanying drawing explanation
Fig. 1 is the schematic rear view of a kind of rotating vanes class of the present invention flapping wing aircraft; Fig. 2 is the schematic top plan view of Fig. 1; Fig. 3 is the enlarged diagram of the right rotation class flapping wing device in Fig. 1; Fig. 4 is the enlarged diagram of the right rotation class flapping wing device in Fig. 2; Fig. 5 is the motion process diagrammatic rear view of right rotation class flapping wing device.
In figure, 1-fuselage, 11-left socle, 12-right support; 2-tail undercarriage, 21-small machine; 3-anticlockwise class flapping wing device; 4-right rotation class flapping wing device; 5-alighting gear.
Belong to the assembly of anticlockwise class flapping wing device 3: 30-driving engine, 31-main shaft, 32-pivoted arm frame, 33-center fixed gear wheel, the nearly heart gear of 34-first, 35-first heart gear far away, 36 first fins, the leading edge of 361-first fin, the trailing edge of 362-first fin, the nearly heart gear of 37-second, 38-second heart gear far away, 39-second fin, the leading edge of 391-second fin, the trailing edge of 392-second fin.
Belong to the assembly of right rotation class flapping wing device 4: 40-driving engine, 41-main shaft, 42-pivoted arm frame, 43-center fixed gear wheel, the nearly heart gear of 44-first, 45-first heart gear far away, 46 first fins, the leading edge of 461-first fin, the trailing edge of 462-first fin, the nearly heart gear of 47-second, 48-second heart gear far away, 49-second fin, the leading edge of 491-second fin, the trailing edge of 492-second fin.
Detailed description of the invention
Now 1 ~ 5 couple of the present invention is illustrated by reference to the accompanying drawings: a kind of rotating vanes class flapping wing aircraft, forms primarily of fuselage 1, tail undercarriage 2, anticlockwise class flapping wing device 3, right rotation class flapping wing device 4 and alighting gear 5.Control system, automatic navigation autonomous flight instrument and command and control system is furnished with in fuselage 1, the mode that this aircraft adopts automatic navigation autonomous flight pattern and remote control distributor pattern to combine is flown, plane-hop adopts remote control mode flight, and long-distance flight adopts automatic navigation autonomous flight mode flight.Anticlockwise class flapping wing device 3 and right rotation class flapping wing device 4 structure, parameter are all identical with principle of work and be symmetrically arranged on the overhanging left socle 11 in the left and right sides of fuselage 1 and right support 12, are used for producing lift and thrust.Tail undercarriage 2 is driven by small machine 21, tail undercarriage 2 plane of rotation can tilt to the left or to the right, also can tilt forward or backward, can produce upwards under the manipulation of control system, to upper left side, to upper right side, forward upward or pulling force rearwardly and upwardly, to realize pitching and the yawed flight attitude of this aircraft.The steering wheel of small machine 21, operating system, automatic navigation autonomous flight instrument and telecommand equipment adopt lithium battery power supply.Alighting gear 5 adopts rear bikini wheel undercarriage.
The concrete structure of right rotation class flapping wing device 4 is: it comprises driving engine 40, main shaft 41, pivoted arm 42, the nearly heart gear of center fixed gear wheel 43, first 44, first heart gear 45, first fin 46, second far away nearly heart gear 47, second heart gear 48 far away and the second fin 49.First nearly heart gear 44, first heart gear far away 45 and the first fin 46 and the second nearly heart gear 47, second heart gear 48 far away and the second fin 49 liang overlap component one_to_one corresponding, and the identical and symmetry of corresponding element structure is arranged on the both sides of center fixed gear wheel 43.Center fixed gear wheel 43 is fixedly installed in right support 12 end stretching out right side of fuselage 1.Main shaft 41 vertical equity is arranged, the rear end of main shaft 41 and pivoted arm 42 are fixed on the center of pivoted arm 42, the stage casing of main shaft 41 is connected in the centre hole of center fixed gear wheel 43 by bearing and center fixed gear wheel 43, flexible rotating in the centre hole of main shaft 41 Neng center fixed gear wheel 43, the front end of main shaft 41 is connected with the output shaft of driving engine 40.The nearly heart gear 47 of second heart gear 48, second far away, the nearly heart gear of center fixed gear wheel 43, first 44 and the first heart gear 45 5 far away are arranged point-blank, and rotational plane and the center fixed gear wheel 43 of the nearly heart gear 44 of the nearly heart gear of the second heart gear 48, second far away 47, first and the first heart gear 45 far away are in same horizontal vertical plane; The rotating shaft of the second heart gear 48 far away is arranged on one end of pivoted arm 42 by bearing, the rotating shaft of the first heart gear 45 far away is arranged on the other end of pivoted arm 42 by bearing; The rotating shaft of the second nearly heart gear 47 is arranged on the centre of a section near the second heart gear 48 far away of pivoted arm 42 by bearing, the rotating shaft of the first nearly heart gear 44 is arranged on the centre of a section near the first heart gear 45 far away of pivoted arm 42 by bearing; Second heart gear 48 far away engages with the second nearly heart gear 47, second nearly heart gear 47 engages with center fixed gear wheel 43, center fixed gear wheel 43 engages with the first nearly heart gear 44, and the first nearly heart gear 44 engages with the first heart gear 45 far away, and the transmitting ratio of all gears meshing is 1: 1.First fin 46 and the second fin 49 are nonrigid rectangular tab, and aerofoil profile is flat pattern under epirelief concave shape or epirelief, specifically certain elasticity.The rear end of the rotating shaft of the first heart gear 45 far away and the first fin 46 are fixed on the front end midway location of the first fin 46; The rear end of the rotating shaft of the second heart gear 48 far away and the second fin 49 are fixed on the front end midway location of the second fin 49.When pivoted arm 42 is in horizontal stationary state, the first fin 46 and the second fin 49 are in same level.The section of pivoted arm 42 is aerofoil profile, can produce pulling force forward when pivoted arm 42 rotates.
From the tail end of this aircraft toward front end, the principle of work of right rotation class flapping wing device 4 is: reference position is that the first fin 46 is in extreme higher position, and the second fin 49 is in extreme lower position, and two fins are all in horizontality.Under the control of control system, start the engine 40, under the driving of power, main shaft 41 rotates clockwise, pivoted arm 42 is driven to rotate clockwise, because center fixed gear wheel 43 is fixing, and the transmitting ratio of center fixed gear wheel 43 and the first heart gear 45 far away and the second heart gear 48 far away is the anticlockwise direction rotation under the drive of the first heart gear 45 far away and the second heart gear 48 far away respectively while revolving round the sun around main shaft 41 of the 1: 1, first fin 46 and the second fin 49.First fin 46 runs to lowest part is from highest point and flutters process: flutter under the leading edge 461 of the first fin 46 keeps horizontality, the displacement of flutterring under the identical chord positions of spanwise first fin 46 is identical, realizes flat flutterring downwards; Because the first fin 46 is nonrigid, have certain elasticity, under flutter midway the first fin trailing edge 462 want delayed first fin leading edge 461 some.Because the aerofoil profile of the first fin 46 is flat patterns under epirelief concave shape or epirelief, the first fin 46 times flutters the larger lift upwards of generation and less thrust forward.Meanwhile, the second fin 49 runs to highest point from lowest part to carry out flutterring process: the leading edge 491 of the second fin keeps horizontality to flutter, identical along the displacement that the identical chord positions of spanwise second fin 49 is flutterred, and realizes upwards flat flutterring.Because the second fin 49 is nonrigid, have certain elasticity, the second fin 49 being flutterred its trailing edge 492 of midway also can its leading edge 491 delayed.Because the aerofoil profile of the second fin 49 is flat patterns under epirelief concave shape or epirelief, compared with the lower bat of the first fin 46, the degree of the delayed leading edge of trailing edge 492 491 of the second fin 49 is larger.Second fin 49 flutterred the larger thrust forward of generation and less lift upwards or do not produce lift, the size producing lift is relevant with the speed that this aircraft moves ahead.First fin 46 and the second fin 49 complete down flutter and on flutter process after, along with the continuation clickwise of main shaft 41, following first fin 46 is flutterred, the second fin 49 times is flutterred.Like this, main shaft 41 rotates continuously, flutter under the first fin 46 and the second fin 49 hocket and on flutter, produce thrust forward and lift upwards, maintain this aircraft flight.
The principle of work of anticlockwise class flapping wing device 3 is identical with the principle of work of right rotation class flapping wing device 4, due to anticlockwise class flapping wing device 3 and symmetrical installation identical with right rotation class flapping wing device 4 structure.Main shaft 31 anticlockwise direction rotating band under the driving of the driving engine 30 of anticlockwise class flapping wing device 3 of anticlockwise class flapping wing device 3 moves the pivoted arm 32 anticlockwise direction rotation of anticlockwise class flapping wing device 3.The fin of anticlockwise class flapping wing device 3 is flutterred at present in the left side of the main shaft 31 of anticlockwise class flapping wing device 3, flutters on when the right side of the main shaft 31 of anticlockwise class flapping wing device 3.
Namely all fins laterally can not produce horizontal component of force in spanwise in the process of fluttering up and down, and efficiency is higher.This aircraft adopts two driving engine individual drive, mobility strong.
Two driving engines are identical, all adopt combustion engine or motor, lithium battery power supply during employing motor.
Four fins of anticlockwise class flapping wing device 3 and right rotation class flapping wing device 4 be locked in same level height and four fins all keep the angle of attack between 4 ° to 8 ° time, be conducive to this aircraft and glide.
This aircraft can be used for taking photo by plane, the disaster relief, Agriculture, forestry And Animal Husbandry operation and some military requirements.
Claims (6)
1. a rotating vanes class flapping wing aircraft, is characterized in that: form primarily of fuselage (1), tail undercarriage (2), anticlockwise class flapping wing device (3), right rotation class flapping wing device (4) and alighting gear (5); Control system, automatic navigation autonomous flight instrument and command and control system is furnished with in fuselage (1); Anticlockwise class flapping wing device (3) is all identical with right rotation class flapping wing device (4) structure, parameter and principle of work and be symmetrically arranged on the overhanging left socle (11) in the left and right sides of fuselage (1) and right support (12); Tail undercarriage (2) is driven by small machine (21), and tail undercarriage (2) plane of rotation can tilt to the left or to the right, also can tilt forward or backward;
The concrete structure of right rotation class flapping wing device (4) is: it comprises driving engine (40), main shaft (41), pivoted arm (42), center fixed gear wheel (43), the first nearly heart gear (44), the first heart gear (45) far away, the first fin (46), the second nearly heart gear (47), the second heart gear (48) far away and the second fin (49); First nearly heart gear (44), the first heart gear (45) far away and the first fin (46) and the second near heart gear (47), the second heart gear (48) far away and the second fin (49) two overlap component one_to_one corresponding, and the identical and symmetry of the element structure of correspondence is arranged on the both sides of center fixed gear wheel (43); Center fixed gear wheel (43) is fixedly installed in right support (12) end stretching out right side of fuselage (1); Main shaft (41) vertical equity is arranged, the rear end of main shaft (41) and pivoted arm (42) are fixed on the center of pivoted arm (42), the stage casing of main shaft (41) is connected in the centre hole of center fixed gear wheel (43) by bearing and center fixed gear wheel (43), flexible rotating in the centre hole at main shaft (41) Neng center fixed gear wheel (43), the front end of main shaft (41) is connected with the output shaft of driving engine (40); Second heart gear (48) far away, the second nearly heart gear (47), center fixed gear wheel (43), the first nearly heart gear (44) and the first heart gear (45) five far away are arranged point-blank, and rotational plane and the center fixed gear wheel (43) of the second heart gear (48) far away, the second nearly heart gear (47), the first nearly heart gear (44) and the first heart gear (45) far away are in same horizontal vertical plane; The rotating shaft of the second heart gear (48) far away is arranged on one end of pivoted arm (42) by bearing, the rotating shaft of the first heart gear (45) far away is arranged on the other end of pivoted arm (42) by bearing; The rotating shaft of the second nearly heart gear (47) is arranged on the centre of a section near the second heart gear (48) far away of pivoted arm (42) by bearing, the rotating shaft of the first nearly heart gear (44) is arranged on the centre of a section near the first heart gear (45) far away of pivoted arm (42) by bearing; Second heart gear (48) far away is engaged with the second nearly heart gear (47), second nearly heart gear (47) is engaged with center fixed gear wheel (43), center fixed gear wheel (43) engages with the first nearly heart gear (44), first nearly heart gear (44) is engaged with the first heart gear (45) far away, and the transmitting ratio of all gears meshing is 1: 1; First fin (46) and the second fin (49) are nonrigid rectangular tab, and aerofoil profile is flat pattern under epirelief concave shape or epirelief, specifically certain elasticity; The rear end of the rotating shaft of the first heart gear (45) far away and the first fin (46) are fixed on the front end midway location of the first fin (46); The rear end of the rotating shaft of the second heart gear (48) far away and the second fin (49) are fixed on the front end midway location of the second fin (49); When pivoted arm (42) is in horizontal stationary state, the first fin (46) and the second fin (49) are in same level.
2. a kind of rotating vanes class flapping wing aircraft according to claim 1, is characterized in that: the steering wheel of small machine (21), operating system, automatic navigation autonomous flight instrument and telecommand equipment adopt lithium battery power supply.
3. a kind of rotating vanes class flapping wing aircraft according to claim 1, is characterized in that: bikini wheel undercarriage after alighting gear (5) adopts.
4. a kind of rotating vanes class flapping wing aircraft according to claim 1, is characterized in that: the section of pivoted arm (42) is aerofoil profile.
5. a kind of rotating vanes class flapping wing aircraft according to claim 1, is characterized in that: two driving engines adopt combustion engine or motor, lithium battery power supply during employing motor.
6. a kind of rotating vanes class flapping wing aircraft according to claim 1, is characterized in that: four fins of anticlockwise class flapping wing device (3) and right rotation class flapping wing device (4) can be locked in same level height and four fins all can keep between one 4 ° to 8 ° the angle of attack.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420788830.0U CN204310044U (en) | 2014-12-15 | 2014-12-15 | A kind of rotating vanes class flapping wing aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420788830.0U CN204310044U (en) | 2014-12-15 | 2014-12-15 | A kind of rotating vanes class flapping wing aircraft |
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| Publication Number | Publication Date |
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| CN204310044U true CN204310044U (en) | 2015-05-06 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201420788830.0U Withdrawn - After Issue CN204310044U (en) | 2014-12-15 | 2014-12-15 | A kind of rotating vanes class flapping wing aircraft |
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| CN (1) | CN204310044U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104443384A (en) * | 2014-12-15 | 2015-03-25 | 佛山市神风航空科技有限公司 | Rotary wing blade type flapping wing air vehicle |
| CN105197223A (en) * | 2015-10-30 | 2015-12-30 | 王志成 | Convenient-to-glide aircraft provided with moving vane |
| CN107972864A (en) * | 2017-12-06 | 2018-05-01 | 佛山市神风航空科技有限公司 | A kind of lift unit |
-
2014
- 2014-12-15 CN CN201420788830.0U patent/CN204310044U/en not_active Withdrawn - After Issue
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104443384A (en) * | 2014-12-15 | 2015-03-25 | 佛山市神风航空科技有限公司 | Rotary wing blade type flapping wing air vehicle |
| CN105197223A (en) * | 2015-10-30 | 2015-12-30 | 王志成 | Convenient-to-glide aircraft provided with moving vane |
| CN107972864A (en) * | 2017-12-06 | 2018-05-01 | 佛山市神风航空科技有限公司 | A kind of lift unit |
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