CN204297084U - A kind of single-shot rotary flat claps class flapping wing aircraft - Google Patents
A kind of single-shot rotary flat claps class flapping wing aircraft Download PDFInfo
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- CN204297084U CN204297084U CN201420789018.XU CN201420789018U CN204297084U CN 204297084 U CN204297084 U CN 204297084U CN 201420789018 U CN201420789018 U CN 201420789018U CN 204297084 U CN204297084 U CN 204297084U
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Abstract
A kind of single-shot rotary flat bat class flapping wing aircraft, belongs to technical field of aerospace, comprises fuselage, empennage, anticlockwise flat bat swing device, right rotation flat bat swing device, engine installation and alighting gear.Control system, airborne equipment and mains connection set is furnished with in fuselage.Anticlockwise flat bat swing device is put down with right rotation and clapped swing device structure, parameter is identical with principle of work is arranged symmetrically with.Empennage is used for control and faces upward and to bow and turning flight attitude.Power driven anticlockwise is flat claps swing device and the synchronized contrarotation of right rotation flat bat swing device.The flat swing device of clapping of right rotation comprises main shaft, pivoted arm, wing axle, fin, central synchronous wheel, Timing Belt and wing synchronizing wheel.The transmitting ratio of central synchronous wheel and wing synchronizing wheel is 1: 1.The fixed installation of central synchronous wheel.The leading edge of fin is horizontal all the time.Fin can not produce component in spanwise in the process of flapping motion, and efficiency is higher.This aircraft is used for taking photo by plane, geographical measurements, agrisilviculture, militaryly to investigate and the task such as rescue and relief work.
Description
Technical field
A kind of single-shot rotary flat claps 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.
Summary of the invention
The object of the invention is the above-mentioned deficiency overcoming existing flapping wing aircraft, invent the higher single-shot rotary flat of a kind of efficiency and clap class flapping wing aircraft.
One single-shot rotary flat claps class flapping wing aircraft, comprises fuselage, empennage, anticlockwise flat bat swing device, right rotation flat bat swing device, engine installation and alighting gear.Control system, airborne equipment and mains connection set is furnished with in fuselage, this aircraft flight attitude is handled by control system, airborne equipment comprises various flight instrumentation instrument and capture apparatus, and employing lithium cell is the feeding electric motors of control system, airborne equipment and engine installation.Be configured with automatic navigation autonomous driving device or telecommand equipment, adopt automatic navigation autonomous driving mode or remote control mode flight.Anticlockwise is put down bat swing device and is put down the bat identical left and right sides being symmetrically arranged in fuselage of swing device structure and parameter with right rotation.Empennage comprises fin blade, horizontal switch steering wheel and longitudinal switch steering wheel.Longitudinal switch steering wheel carries out longitudinal switch control to fin blade under the control of control system, fin blade can be made to deflect up or down, the effect of lifting rudder.During manipulation moves ahead, the fin blade of this aircraft upward deflects and this aircraft can be made to come back, and realizes facing upward; The downward bias change of team makes this aircraft bow, and realizes nutation.Horizontal switch steering wheel carries out horizontal switch control to fin blade under the control of control system, fin blade can be made to tilt to the left or to the right, with longitudinal switch steering wheel with the use of the course that can change this aircraft.Bikini wheel undercarriage after alighting gear adopts.
Engine installation comprises the identical left chain gearing of driving engine, gear cluster, structure and right chain gearing.Driving engine adopts motor.Motor and gear cluster are arranged in fuselage, and left chain gearing is arranged on the left socle on the left of fuselage, and right chain gearing is arranged on the right support on the right side of fuselage.Pass to respectively by left chain gearing and right chain gearing after the power of motor is distributed by gear cluster that anticlockwise is flat claps swing device and right rotation is flat claps swing device, anticlockwise put down clap swing device and right rotation put down the rotating speed clapping swing device identical turn to contrary.The flat swing device of clapping of anticlockwise is all identical with principle of work with the flat swing device structure of clapping of right rotation, and they are arranged symmetrically in the left and right sides of fuselage.Anticlockwise is put down bat swing device and is arranged on left socle by the central synchronous wheel of itself, and anticlockwise is put down the front end of main shaft of clapping swing device and is connected with the flower wheel of the left chain gearing of engine installation; Right rotation is put down bat swing device and is arranged on right support by the central synchronous wheel of itself, and right rotation is put down the front end of main shaft of clapping swing device and is connected with the flower wheel of the right chain gearing of engine installation.
The concrete structure clapping swing device is put down in right rotation: the flat swing device of clapping of right rotation comprises main shaft, pivoted arm, wing axle, fin, central synchronous wheel, Timing Belt and wing synchronizing wheel.The transmitting ratio of central synchronous wheel and wing synchronizing wheel is 1: 1.Central synchronous wheel is fixedly mounted on the rear side of right support.Main shaft vertical equity is arranged, the leading portion of main shaft is taken turns by bearing and central synchronous and is connected in centre hole that central synchronous takes turns, main shaft can in this centre hole flexible rotating, main shaft is also the rotating shaft of the flower wheel of the right chain gearing of engine installation, the rear end of main shaft is vertical with pivoted arm to be connected, and the other end of pivoted arm is connected with wing axle is vertical by bearing.Main shaft, pivoted arm and wing axle three are in same plane.Front end and the wing synchronizing wheel of wing axle are connected, and the rear end of wing axle and fin are fixed on the front center position of fin, and wing axle is vertical with the front of fin, and wing axle and fin are in same plane.Wing synchronizing wheel is taken turns with central synchronous and is connected by Timing Belt.Pivoted arm is parallel with the rotational plane of Timing Belt.Fin is nonrigid, and aspect is rectangular; The aerofoil profile of fin adopts flat pattern under epirelief concave shape or epirelief; The leading edge of fin is much thicker than the trailing edge of fin, and the part near the leading edge of fin is comparatively hard, and the part near the trailing edge of fin is softer, and flexible.During assembling right rotation flat bat swing device, the reference position of its fin is made to be in horizontality, so, because central synchronous wheel is fixing, and central synchronous wheel is 1: 1 with the transmitting ratio of wing synchronizing wheel, pivoted arm is when main axis, and fin is can reversing sense rotation under the drive of wing synchronizing wheel while main shaft revolution, and when pivoted arm turns to any position, the leading edge of fin all can be horizontal.
From the tail end of this aircraft toward front end, right rotation is put down and is clapped the principle of work of swing device and be: under flutter process: reference position is that fin is in extreme higher position, under the control of control system, starter motor, under the driving of engine installation, main shaft rotates clockwise, drive pivoted arm rotates clockwise, because central synchronous wheel is fixing, and central synchronous wheel is 1: 1 with the transmitting ratio of wing synchronizing wheel, fin is in anticlockwise direction rotation under the drive of wing synchronizing wheel while main shaft revolution, clap under the leading edge maintenance level attitude of fin, the displacement of clapping under the identical chord positions of spanwise fin is identical, realize flat bat downwards.Because fin is nonrigid, have certain flexibility and elasticity, under fin clap midway fin trailing edge want delayed fin leading edge some.Because the aerofoil profile of fin is flat pattern under epirelief concave shape or epirelief, claps under fin and produce larger lift upwards and less thrust forward.Under the process of flutterring be complete on the right side of longitudinal vertical guide crossing main shaft.On flutter process: from fin is in extreme lower position, along with being rotated further of motor, under the driving of engine installation, main shaft continues to rotate clockwise, pivoted arm is driven to continue to rotate clockwise, because central synchronous wheel is fixing, and central synchronous wheel is 1: 1 with the transmitting ratio of wing synchronizing wheel, fin is continuing anticlockwise direction rotation while main shaft revolution under the drive of wing synchronizing wheel, the leading edge of fin keeps level attitude arsis, displacement along spanwise fin identical chord positions arsis is identical, realizes upwards flat bat.Because fin is nonrigid, have certain flexibility and elasticity, the trailing edge of fin arsis midway fin also can the leading edge of delayed fin.Because the aerofoil profile of fin is flat pattern under epirelief concave shape or epirelief, compared with lower bat, the degree of the leading edge of the delayed fin of trailing edge of fin is larger.Arsis fin produces larger thrust forward and less lift upwards or does not produce lift.The size producing lift is relevant with the speed that this aircraft moves ahead.On the process of flutterring be complete in the left side of longitudinal vertical guide crossing main shaft.It is undertaken regulating by the rotating speed of control motor that fin rotates the speed of flapping.
Principle of work and the right rotation of clapping swing device are put down in anticlockwise, and to equal the principle of work of clapping swing device identical, anticlockwise is flat clap swing device and right rotation flat clap swing device synchronously flutter be same flutter at present or simultaneously on flutter.From the tail end of this aircraft toward front end, the hand of rotation that the main shaft clapping swing device is put down in anticlockwise is anticlockwise direction.
Motor rotates continuously, and engine installation continuous drive anticlockwise flat bat swing device and the rotation of right rotation flat bat swing device synchronous backward, produce enough lift and thrust maintains this aircraft flight.Namely fin laterally can not produce horizontal component of force in spanwise in the process of flapping motion, and efficiency is higher.
Accompanying drawing explanation
Fig. 1 is the schematic rear view that a kind of single-shot rotary flat of the present invention claps class flapping wing aircraft, and in this figure, anticlockwise flat bat swing device and the flat swing device of clapping of right rotation are in down in the process of flutterring, and two fins are all in lower bat, and down, trailing edge upward for their leading edge; Fig. 2 is the schematic top plan view of Fig. 1; Fig. 3 is that anticlockwise that a kind of single-shot rotary flat of the present invention claps class flapping wing aircraft is put down and clapped swing device and right rotation and put down and clap swing device and be in schematic rear view when flutterring process, and in figure, two fins are all in arsis process, and upward, trailing edge down for their leading edge; Fig. 4 is that the schematic diagram clapping swing device is put down in the right rotation be exaggerated in Fig. 1; Fig. 5 is that the schematic diagram clapping swing device is put down in the right rotation be exaggerated in Fig. 2; Fig. 6 is that the schematic rear view of clapping swing device rotary course is equalled in the right rotation be exaggerated, and in figure, dotted line represents that the diverse location residing for swing device is clapped in right rotation.
In figure, 1-fuselage, 11-left socle, 12-right support; 2-empennage, 21-fin blade, the horizontal switch steering wheel of 22-, the longitudinal switch steering wheel of 23-; 3-anticlockwise is flat claps swing device; 4-right rotation is flat claps swing device, 41-main shaft, 42-pivoted arm, 43-wing axle, 44-fin, the leading edge of 441-fin, the trailing edge of 442-fin, and 45-central synchronous is taken turns, 46-Timing Belt, 47-wing synchronizing wheel; 5-engine installation, 51-motor, 52-gear cluster, the left chain gearing of 53-, the right chain gearing of 54-; 6-alighting gear.
Detailed description of the invention
Now 1 ~ 6 couple of the present invention is illustrated by reference to the accompanying drawings: a kind of single-shot rotary flat claps class flapping wing aircraft, comprises fuselage 1, empennage 2, anticlockwise flat bat swing device 3, right rotation flat bat swing device 4, engine installation 5 and alighting gear 6.Control system, airborne equipment and mains connection set is furnished with in fuselage 1, this aircraft flight attitude is handled by control system, airborne equipment comprises various flight instrumentation instrument and capture apparatus, and employing lithium cell is that the motor 51 of control system, airborne equipment and engine installation 5 is powered.Be configured with automatic navigation autonomous driving device or telecommand equipment, adopt automatic navigation autonomous driving mode or remote control mode flight.Anticlockwise is put down bat swing device 3 and is put down the bat identical left and right sides being symmetrically arranged in fuselage 1 of swing device 4 structure and parameter with right rotation.Empennage 2 comprises fin blade 21, horizontal switch steering wheel 22 and longitudinal switch steering wheel 23.Longitudinal switch steering wheel 23 carries out longitudinal switch control to fin blade 21 under the control of control system, fin blade 21 can be made to deflect up or down, the effect of lifting rudder.During manipulation moves ahead, the fin blade 21 of this aircraft upward deflects and this aircraft can be made to come back, and realizes facing upward; The downward bias change of team makes this aircraft bow, and realizes nutation.Horizontal switch steering wheel 22 carries out horizontal switch control to fin blade 21 under the control of control system, fin blade 21 can be made to tilt to the left or to the right, with longitudinal switch steering wheel 23 with the use of the course that can change this aircraft.Alighting gear 6 adopts rear bikini wheel undercarriage.
Engine installation 5 comprises the identical left chain gearing 53 of driving engine, gear cluster 52, structure and right chain gearing 54, and driving engine adopts motor.Motor 51 and gear cluster 52 are arranged in fuselage 1, and left chain gearing 53 is arranged on the left socle 11 on the left of fuselage 1, and right chain gearing 54 is arranged on the right support 12 on the right side of fuselage 1.Pass to respectively by left chain gearing 53 and right chain gearing 54 after the power of motor 51 is distributed by gear cluster 52 that anticlockwise is flat claps swing device 3 and right rotation is flat claps swing device 4, anticlockwise put down clap swing device 3 and right rotation put down the rotating speed clapping swing device 4 identical turn to contrary.The flat swing device 3 of clapping of anticlockwise is all identical with principle of work with flat swing device 4 structure of clapping of right rotation, and they are arranged symmetrically in the left and right sides of fuselage 1.Anticlockwise is put down bat swing device 3 and is arranged on left socle 11 by the central synchronous wheel of itself, and anticlockwise is put down the front end of main shaft of clapping swing device 3 and is connected with the flower wheel of the left chain gearing 53 of engine installation 5; Right rotation is put down bat swing device 4 and is arranged on right support 12 by the central synchronous wheel 45 of itself, and right rotation is put down the front end of main shaft 41 of clapping swing device 4 and is connected with the flower wheel of the right chain gearing 54 of engine installation 5.
The concrete structure clapping swing device 4 is put down in right rotation: the flat swing device 4 of clapping of right rotation comprises main shaft 41, pivoted arm 42, wing axle 43, fin 44, central synchronous wheel 45, Timing Belt 46 and wing synchronizing wheel 47.The transmitting ratio of central synchronous wheel 45 and wing synchronizing wheel 47 is 1: 1.Central synchronous wheel 45 is fixedly mounted on the rear side of right support 12.Main shaft 41 vertical equity is arranged, the leading portion of main shaft 41 is taken turns 45 by bearing and central synchronous and is connected in central synchronous and takes turns in the centre hole of 45, main shaft 41 can in this centre hole flexible rotating, main shaft 41 is also the rotating shaft of the flower wheel of the right chain gearing 54 of engine installation 5, the rear end of main shaft 41 is vertical with pivoted arm 42 to be connected, and the other end of pivoted arm 42 is connected with wing axle 43 is vertical by bearing.Main shaft 41, pivoted arm 42 and wing axle 43 three are in same plane.Front end and the wing synchronizing wheel 47 of wing axle 43 are connected, and the rear end of wing axle 43 and fin 44 are fixed on the front center position of fin 44, and wing axle 43 is vertical with the front of fin 44, and wing axle 43 and fin 44 are in same plane.Wing synchronizing wheel 47 and central synchronous are taken turns 45 and are connected by Timing Belt 46.Pivoted arm 42 is parallel with the rotational plane of Timing Belt 46.Fin 44 is nonrigid, and aspect is rectangular; The aerofoil profile of fin 44 adopts flat pattern under epirelief concave shape or epirelief; The leading edge 441 of fin is much thicker than the trailing edge 442 of fin, and the part near the leading edge 441 of fin is comparatively hard, and the part near the trailing edge 442 of fin is softer, and flexible.During assembling right rotation flat bat swing device 4, the reference position of its fin 44 is made to be in horizontality, so, because central synchronous wheel 45 is fixing, and central synchronous wheel 45 is 1: 1 with the transmitting ratio of wing synchronizing wheel 47, pivoted arm 42 is when main shaft 41 rotates, and fin 44 can reversing sense rotation under the drive of wing synchronizing wheel 47 while revolving round the sun around main shaft 41, and when pivoted arm 42 turns to any position, the leading edge of fin 44 all can be horizontal.
From the tail end of this aircraft toward front end, right rotation is put down and is clapped the principle of work of swing device 4 and be: under flutter process: reference position is that fin 44 is in extreme higher position, under the control of control system, starter motor 51, under the driving of engine installation 5, main shaft 41 rotates clockwise, pivoted arm 42 is driven to rotate clockwise, because central synchronous wheel 45 is fixing, and central synchronous wheel 45 is 1: 1 with the transmitting ratio of wing synchronizing wheel 47, fin 44 anticlockwise direction rotation under the drive of wing synchronizing wheel 47 while revolving round the sun around main shaft 41, clap under the leading edge 441 of fin keeps level attitude, the displacement of clapping under the identical chord positions of spanwise fin 44 is identical, realize flat bat downwards.Because fin 44 is nonrigid, have certain flexibility and elasticity, the trailing edge 442 that fin 44 times claps midway fins want delayed fin leading edge 441 some.Because the aerofoil profile of fin 44 is flat patterns under epirelief concave shape or epirelief, fin is clapped for 44 times and is produced larger lift upwards and less thrust forward.Under the process of flutterring be complete on the right side of longitudinal vertical guide crossing main shaft 41.On flutter process: from fin 44 is in extreme lower position, along with being rotated further of motor 51, under the driving of engine installation 5, main shaft 41 continues to rotate clockwise, pivoted arm 42 is driven to continue to rotate clockwise, because central synchronous wheel 45 is fixing, and central synchronous wheel 45 is 1: 1 with the transmitting ratio of wing synchronizing wheel 47, fin 44 continues anticlockwise direction rotation while revolving round the sun around main shaft 41 under the drive of wing synchronizing wheel 47, the leading edge 441 of fin keeps level attitude arsis, displacement along spanwise fin 44 identical chord positions arsis is identical, realize upwards flat bat.Because fin 44 is nonrigid, have certain flexibility and elasticity, the trailing edge 442 of fin 44 arsis midway fin also can the leading edge 441 of delayed fin.Because the aerofoil profile of fin 44 is flat patterns under epirelief concave shape or epirelief, compared with lower bat, the degree of the leading edge 441 of the delayed fin of trailing edge 442 of fin is larger.Arsis fin 44 produces larger thrust forward and less lift upwards or does not produce lift.The size producing lift is relevant with the speed that this aircraft moves ahead, and the lift that front line speed produces sooner is larger.On the process of flutterring be complete in the left side of longitudinal vertical guide crossing main shaft 41.It is undertaken regulating by the rotating speed of control motor 51 that fin 44 rotates the speed of flapping.
Principle of work and the right rotation of clapping swing device 3 are put down in anticlockwise, and to equal the principle of work of clapping swing device 4 identical, anticlockwise is flat clap swing device 3 and right rotation flat clap swing device 4 synchronously flutter be same flutter at present or simultaneously on flutter.From the tail end of this aircraft toward front end, the hand of rotation that the main shaft clapping swing device 3 is put down in anticlockwise is anticlockwise direction.
Motor 51 rotates continuously, and engine installation 5 continuous drive anticlockwise flat bat swing device 3 and the rotation of right rotation flat bat swing device 4 synchronous backward, produce enough lift and thrust maintains this aircraft flight.Namely two fins laterally can not produce horizontal component of force in spanwise in the process of flapping motion, and this aircraft efficiency is higher.
The light material that the fuselage 1 of this aircraft adopts the hardness such as aluminum alloy or titanium alloy high makes.The covering of fin adopts carbon fibre material.Be furnished with pick up camera and information handling system in fuselage 1, can take photo by plane, the image information of shooting can be sent to wayside equipment.With the telecommand equipment of ground configurations match on machine, this aircraft can realize remote control distributor.
This aircraft adopts hand mode of throwing take off or adopt the runway mode of sliding to take off; Two fins are locked in the sustained height of the center of gravity higher than this aircraft, facilitate this aircraft to glide or landing.
A kind of single-shot rotary flat of the present invention claps that class flapping wing aircraft can be used for taking photo by plane, geographical measurements, traffic duty, agrisilviculture, militaryly to investigate and the multiple-task such as rescue and relief work.
Claims (7)
1. a single-shot rotary flat claps class flapping wing aircraft, comprise fuselage (1), empennage (2), anticlockwise flat bat swing device (3), right rotation flat bat swing device (4), engine installation (5) and alighting gear (6), fuselage is furnished with control system, airborne equipment and mains connection set in (1), it is characterized in that: fuselage is configured with automatic navigation autonomous driving device or telecommand equipment in (1); The flat swing device (3) of clapping of anticlockwise claps swing device (4) structure, the parameter left and right sides that be symmetrically arranged in fuselage (1) all identical with principle of work with right rotation is flat; Empennage (2) comprises fin blade (21), horizontal switch steering wheel (22) and longitudinal switch steering wheel (23); Engine installation (5) comprises the identical left chain gearing (53) of driving engine, gear cluster (52), structure and right chain gearing (54), and driving engine adopts motor; Motor (51) and gear cluster (52) are arranged in fuselage (1), and left chain gearing (53) is arranged on the left socle (11) in fuselage (1) left side, and right chain gearing (54) is arranged on the right support (12) on fuselage (1) right side; Pass to respectively by left chain gearing (53) and right chain gearing (54) after the power of motor (51) is distributed by gear cluster (52) that anticlockwise is flat claps swing device (3) and right rotation is flat claps swing device (4), anticlockwise is flat claps swing device (3) and right rotation and puts down that the rotating speed of bat swing device (4) is identical to be turned on the contrary; The flat swing device (3) of clapping of anticlockwise is arranged on left socle (11) by the central synchronous wheel of itself, and the flat front end of main shaft of clapping swing device (3) of anticlockwise is connected with the flower wheel of the left chain gearing (53) of engine installation (5); The flat swing device (4) of clapping of right rotation is arranged on right support (12) by central synchronous wheel (45) of itself, and the flat front end of main shaft (41) of clapping swing device (4) of right rotation is connected with the flower wheel of the right chain gearing (54) of engine installation (5);
The flat concrete structure clapping swing device (4) of right rotation is: the flat swing device (4) of clapping of right rotation comprises main shaft (41), pivoted arm (42), wing axle (43), fin (44), central synchronous wheel (45), Timing Belt (46) and wing synchronizing wheel (47); The transmitting ratio of central synchronous wheel (45) and wing synchronizing wheel (47) is 1: 1; Central synchronous wheel (45) is fixedly mounted on the rear side of right support (12); Main shaft (41) vertical equity is arranged, the leading portion of main shaft (41) is taken turns (45) by bearing and central synchronous and is connected in central synchronous and takes turns in the centre hole of (45), main shaft (41) can in this centre hole flexible rotating, main shaft (41) is also the rotating shaft of the flower wheel of the right chain gearing (54) of engine installation (5), the rear end of main shaft (41) is vertical with pivoted arm (42) to be connected, and the other end of pivoted arm (42) is connected with wing axle (43) is vertical by bearing; Main shaft (41), pivoted arm (42) and wing axle (43) three are in same plane; Front end and the wing synchronizing wheel (47) of wing axle (43) are connected, the rear end of wing axle (43) and fin (44) are fixed on the front center position of fin (44), wing axle (43) is vertical with the front of fin (44), and wing axle (43) and fin (44) are in same plane; Wing synchronizing wheel (47) is taken turns (45) and is connected by Timing Belt (46) with central synchronous; Pivoted arm (42) is parallel with the rotational plane of Timing Belt (46); Fin (44) is nonrigid; The leading edge (441) of fin is much thicker than the trailing edge (442) of fin, and the part near the leading edge (441) of fin is comparatively hard, and the part near the trailing edge (442) of fin is softer, and flexible; The reference position of fin (44) is in horizontality.
2. a kind of single-shot rotary flat according to claim 1 claps class flapping wing aircraft, it is characterized in that: employing lithium cell is motor (51) power supply of control system, airborne equipment and engine installation (5).
3. a kind of single-shot rotary flat according to claim 1 claps class flapping wing aircraft, it is characterized in that: bikini wheel undercarriage after alighting gear (6) adopts.
4. a kind of single-shot rotary flat according to claim 1 claps class flapping wing aircraft, it is characterized in that: fuselage (1) adopts the light material that hardness is high to make; The covering of all fins adopts carbon fibre material.
5. a kind of single-shot rotary flat according to claim 1 claps class flapping wing aircraft, it is characterized in that: fin (44) aspect is rectangular, and aerofoil profile adopts flat pattern under epirelief concave shape or epirelief.
6. a kind of single-shot rotary flat according to claim 1 claps class flapping wing aircraft, it is characterized in that: fuselage is furnished with pick up camera and information handling system in (1), the image information of shooting can be sent to wayside equipment.
7. a kind of single-shot rotary flat according to claim 1 claps class flapping wing aircraft, it is characterized in that: two fins can be locked in the sustained height position of the center of gravity higher than this aircraft.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420789018.XU CN204297084U (en) | 2014-12-15 | 2014-12-15 | A kind of single-shot rotary flat claps class flapping wing aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420789018.XU CN204297084U (en) | 2014-12-15 | 2014-12-15 | A kind of single-shot rotary flat claps class flapping wing aircraft |
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| Publication Number | Publication Date |
|---|---|
| CN204297084U true CN204297084U (en) | 2015-04-29 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201420789018.XU Withdrawn - After Issue CN204297084U (en) | 2014-12-15 | 2014-12-15 | A kind of single-shot rotary flat claps class flapping wing aircraft |
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| CN (1) | CN204297084U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104494826A (en) * | 2014-12-15 | 2015-04-08 | 佛山市神风航空科技有限公司 | Single-engine rotary horizontal flapping wing air vehicle |
| CN105197223A (en) * | 2015-10-30 | 2015-12-30 | 王志成 | Convenient-to-glide aircraft provided with moving vane |
-
2014
- 2014-12-15 CN CN201420789018.XU patent/CN204297084U/en not_active Withdrawn - After Issue
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104494826A (en) * | 2014-12-15 | 2015-04-08 | 佛山市神风航空科技有限公司 | Single-engine rotary horizontal flapping wing air vehicle |
| CN104494826B (en) * | 2014-12-15 | 2016-06-15 | 佛山市神风航空科技有限公司 | A kind of single-shot rotary flat claps class flapping wing aircraft |
| CN105197223A (en) * | 2015-10-30 | 2015-12-30 | 王志成 | Convenient-to-glide aircraft provided with moving vane |
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Granted publication date: 20150429 Effective date of abandoning: 20160615 |
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| C25 | Abandonment of patent right or utility model to avoid double patenting |