CN204297096U - A kind of small-sized four wing flutter aircraft - Google Patents
A kind of small-sized four wing flutter aircraft Download PDFInfo
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- CN204297096U CN204297096U CN201420789412.3U CN201420789412U CN204297096U CN 204297096 U CN204297096 U CN 204297096U CN 201420789412 U CN201420789412 U CN 201420789412U CN 204297096 U CN204297096 U CN 204297096U
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- guide rod
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Abstract
A kind of small-sized four wing flutter aircraft, belong to technical field of aerospace, comprise fuselage, empennage, left flutter device, right flutter device and undercarriage.Control system, airborne equipment and power-supply device is furnished with in fuselage.Be configured with self-navigation autonomous driving device or remote control equipment.The left flutter device left and right sides that be symmetrically arranged in fuselage all identical with right flutter apparatus structure, parameter and operation principle.Left flutter device comprises motor, rotating disk, slide block, translation guide rod, front setting guide rod, rear setting guide rod, front fin, rear fin, front upper linear bearing, front lower linear bearing, rear upper linear bearing and rear lower linear bearing.Four fins upper and lower translation under the driving of independent two motors controlled vibrates and produces lift and thrust, and laterally can not produce horizontal component in the process of flapping motion, efficiency is higher.This aircraft is used for taking photo by plane, geographical measurements, traffic duty, agrisilviculture, militaryly to investigate and the multiple-task such as rescue and relief work.
Description
Technical field
A kind of small-sized four wing flutter aircraft, belong to technical field of aerospace, particularly relate to a kind of flutter 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 and wing length 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 aircraft, is a kind of loss of power; Tradition flapping wing aircraft is mostly two panels wing, and flight underaction, mobility is not strong.
Summary of the invention
The object of the invention is the above-mentioned deficiency overcoming existing flapping wing aircraft, invent small-sized four wing flutter aircraft of the higher maneuverability of a kind of efficiency.
A kind of small-sized four wing flutter aircraft, comprise fuselage, empennage, left flutter device, right flutter device and undercarriage.Be furnished with control system, airborne equipment and power-supply device in fuselage, this aircraft flight attitude is manipulated by control system, and airborne equipment comprises various flight instrumentation instrument and capture apparatus, and employing lithium battery is control system, airborne equipment and all feeding electric motors.Be configured with self-navigation autonomous driving device or remote control equipment, adopt self-navigation autonomous driving mode or remote control mode flight.The left flutter device left and right sides that be symmetrically arranged in fuselage all identical with the structure and parameter of right flutter device.Empennage is made up of tailplane and vertical tail.The effect of the upper and lower switch lifting rudder of tailplane energy.Tailplane deflects up and down under the manipulation of control system, thus controls this aircraft landing or pitching flying attitude.Vertical tail is made up of the standing part of leading portion and the movable part of fixed fin and back segment and rudder.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.Undercarriage adopts wheel undercarriage.
The structure of left flutter device is: comprise motor, rotating disk, slide block, translation guide rod, front setting guide rod, rear setting guide rod, front fin, rear fin, front upper linear bearing, front lower linear bearing, rear upper linear bearing and rear lower linear bearing.Front fin is identical with rear fin, and they are nonrigid, and leading edge is perfectly round abundant, trailing edge is tapering, and the part near leading edge is comparatively hard, and the part near trailing edge is softer, flat shape is at right angles trapezoidal, and aerofoil profile adopts flat pattern aerofoil profile under epirelief concave shape or epirelief, and they are all horizontally disposed.Front upper linear bearing, front lower linear bearing, rear upper linear bearing and the rectangular layout of rear lower linear bearing are fixedly mounted on the left of fuselage by bearing block.Motor is fixedly mounted on fuselage interior, and its output shaft transverse horizontal is arranged and is connected with fuselage left side wall by bearing.The output center that be connected in rotating disk inside vertical with rotating disk of motor output shaft.Slide block be arranged on outside rotating disk close to edge, slide block can with rotating disk around motor output shaft revolution can also rotation.Translation guide rod vertical equity is arranged, its stage casing is connected with slide block, slide block can slide along translation guide rod, and the front end of translation guide rod is vertical with front setting guide rod is fixed on front stage casing of erectting guide rod, the stage casing that be fixed on rear setting guide rod vertical with rear setting guide rod, rear end of translation guide rod.The lower end of front setting guide rod is through front lower linear bearing, and the upper end of front setting guide rod is connected with the root of front fin through after front upper linear bearing; The lower end of rear setting guide rod is through rear lower linear bearing, and the upper end of rear setting guide rod is connected with the root of rear fin through after rear upper linear bearing.
Turn right from the left side of this invention aircraft, the operation principle of left flutter device is: electric machine rotation drives rotating disk to rotate clockwise, under the drive of the slide block on rotating disk translation guide rod do repeatedly to move up and down and drive again before setting guide rod and rear setting guide rod synchronously move up and down thus drive front fin and rear fin up-down vibration.Lower bat process, it is the process that front fin and rear fin are clapped from highest point toward lowest part, clap under the leading edge of the front fin of this process and rear fin keeps level substantially, the displacement of clapping under the front fin of spanwise chord positions identical with rear fin is identical, realizes flat bat downwards.Because front fin and rear fin are non-rigidity, have certain flexibility and elasticity, in lower bat process trailing edge want delayed leading edge some.Because the aerofoil profile of front fin and rear fin is flat pattern under epirelief concave shape or epirelief, lower bat produces larger lift upwards and less thrust forward.To be front fin and rear fin to raise up extreme higher position from extreme lower position arsis process, and the leading edge of the front fin of this process and rear fin keeps level arsis substantially, and the displacement along spanwise identical chord positions arsis is identical, realizes upwards flat bat.Because front fin and rear fin are non-rigidity, have certain flexibility and elasticity, during arsis, the trailing edge of front fin and rear fin also can delayed leading edge.Because the aerofoil profile of front fin and rear fin is flat pattern under epirelief concave shape or epirelief, compared with lower bat, the degree of the delayed leading edge of trailing edge of front fin and rear fin is larger.During arsis, front fin and rear fin produce larger thrust forward and less lift upwards or do not produce lift, and the size that arsis process produces lift is relevant with the speed flown before this aircraft, and the lift that the front speed flown produces sooner is larger.The speed that front fin and rear fin are flapped is that the rotating speed by controlling motor carries out regulating.For this aircraft is more flexible, the root of each fin is all equipped with angle of attack stop, adopt servos control, the size that the hunting range when flutter by changing fin controls the fin angle of attack controls air force size and Orientation thus realizes various different flight attitude.All fins substantially do not produce horizontal horizontal component in flutter process, and vibration efficiency is high.
The operation principle of right flutter device is identical with the operation principle of left flutter device.
Left flutter device and right flutter device independently separately control, this aircraft flight maneuverability more.
Accompanying drawing explanation
Fig. 1 is the schematic top plan view of a kind of small-sized four wing flutter aircraft of the present invention, Fig. 2 is that schematic diagram is looked on a left side for a kind of small-sized four wing flutter aircraft of the present invention, in this figure, left flutter device and right flutter device are in down in the process of flutterring, their fin is all in lower bat, down, trailing edge upward for the leading edge of fin.
In figure, 1-fuselage; 2-empennage, 21-fixed fin, 22-rudder, 23-tailplane; The left flutter device of 3-; The right flutter device of 4-; 5-undercarriage.
That indicates in the drawings belongs to having of the part of left flutter device 3: 31-motor, 32-rotating disk, 33-slide block, 34-translation guide rod, guide rod is erect before 35-, guide rod is erect, fin before 37-, fin after 38-after 36-, the front upper linear bearing of 311-, the front lower linear bearing of 312-, upper linear bearing after 313, lower linear bearing after 314-.
Detailed description of the invention
Now 1 ~ 2 couple of the present invention is illustrated by reference to the accompanying drawings: a kind of small-sized four wing flutter aircraft, comprise fuselage 1, empennage 2, left flutter device 3, right flutter device 4 and undercarriage 5.Be furnished with control system, airborne equipment and power-supply device in fuselage 1, this aircraft flight attitude is manipulated by control system, and airborne equipment comprises various flight instrumentation instrument and capture apparatus, and employing lithium battery is control system, airborne equipment and all feeding electric motors.Be configured with self-navigation autonomous driving device or remote control equipment, adopt self-navigation autonomous driving mode or remote control mode flight.Left flutter device 3 left and right sides that be symmetrically arranged in fuselage 1 all identical with the structure and parameter of right flutter device 4.Empennage 2 is made up of tailplane 23 and vertical tail.The effect of the upper and lower switch lifting rudder of tailplane 23 energy.Tailplane 23 deflects up and down under the manipulation of control system, thus controls this aircraft landing or pitching flying attitude.Vertical tail is made up of the standing part of leading portion and the movable part of fixed fin 21 and back segment and rudder 22.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.Undercarriage 5 adopts wheel undercarriage.
The structure of left flutter device 3 is: comprise motor 31, rotating disk 32, slide block 33, translation guide rod 34, front setting guide rod 35, rear setting guide rod 36, front fin 37, rear fin 38, front upper linear bearing 311, front lower linear bearing 312, rear upper linear bearing 313 and rear lower linear bearing 314.Front fin 37 is identical with rear fin 38, and they are nonrigid, and leading edge is perfectly round abundant, trailing edge is tapering, and the part near leading edge is comparatively hard, and the part near trailing edge is softer, flat shape is at right angles trapezoidal, and aerofoil profile adopts flat pattern aerofoil profile under epirelief concave shape or epirelief, and they are all horizontally disposed.Front upper linear bearing 311, front lower linear bearing 312, rear upper linear bearing 313 and the rectangular layout of rear lower linear bearing 314 are fixedly mounted on the left of fuselage 1 by bearing block.It is inner that motor 31 is fixedly mounted on fuselage 1, and its output shaft transverse horizontal is arranged and is connected with fuselage 1 left side wall by bearing.The output center that be connected in rotating disk 32 inside vertical with rotating disk 32 of motor 31 output shaft.Slide block 33 be arranged on outside rotating disk 32 close to edge, slide block 33 can with rotating disk 32 around motor 31 output shaft revolution can also rotation.Translation guide rod 34 vertical equity is arranged, its stage casing is connected with slide block 33, slide block 33 can slide along translation guide rod 34, the front end of translation guide rod 34 is vertical with front setting guide rod 35 is fixed on front stage casing of erectting guide rod 35, the stage casing that be fixed on rear setting guide rod 36 vertical with rear setting guide rod 36, rear end of translation guide rod 34.The lower end of front setting guide rod 35 is through front lower linear bearing 312, and the upper end of front setting guide rod 35 is connected with the root of front fin 37 through after front upper linear bearing 311; The lower end of rear setting guide rod 36 is through rear lower linear bearing 314, and the upper end of rear setting guide rod 36 is connected with the root of rear fin 38 through after rear upper linear bearing 313.
Turn right from the left side of this invention aircraft, the operation principle of left flutter device 3 is: motor 31 rotates and drives rotating disk 32 to rotate clockwise, under the drive of the slide block 33 on rotating disk 32 translation guide rod 34 do repeatedly to move up and down and drive again before setting guide rod 35 and rear setting guide rod 36 synchronously move up and down thus drive front fin 37 and rear fin 38 up-down vibration.Lower bat process, it is the process that front fin 37 and rear fin 38 are clapped from highest point toward lowest part, clap under the leading edge of the front fin of this process 37 and rear fin 38 keeps level substantially, the displacement of clapping under the front fin of spanwise 37 and the identical chord positions of rear fin 38 is identical, realizes flat bat downwards.Because front fin 37 and rear fin 38 are nonrigid, have certain flexibility and elasticity, in lower bat process trailing edge want delayed leading edge some.Because the aerofoil profile of front fin 37 and rear fin 38 is flat patterns under epirelief concave shape or epirelief, lower bat produces larger lift upwards and less thrust forward.To be front fin 37 and rear fin 38 to raise up extreme higher position from extreme lower position arsis process, and the leading edge of the front fin of this process 37 and rear fin 38 keeps level arsis substantially, and the displacement along spanwise identical chord positions arsis is identical, realizes upwards flat bat.Because front fin 37 and rear fin 38 are nonrigid, have certain flexibility and elasticity, during arsis, the trailing edge of front fin 37 and rear fin 38 also can delayed leading edge.Because the aerofoil profile of front fin 37 and rear fin 38 is flat patterns under epirelief concave shape or epirelief, compared with lower bat, the degree of the delayed leading edge of trailing edge of front fin 37 and rear fin 38 is larger.During arsis, front fin 37 and rear fin 38 produce larger thrust forward and less lift upwards or do not produce lift, and the size that arsis process produces lift is relevant with the speed flown before this aircraft, and the lift that the front speed flown produces sooner is larger.The speed that front fin 37 and rear fin 38 are flapped is that the rotating speed by controlling motor 31 carries out regulating.For this aircraft is more flexible, the root of each fin is all equipped with angle of attack stop, adopt servos control, the size that the hunting range when flutter by changing fin controls the fin angle of attack controls air force size and Orientation thus realizes various different flight attitude.All fins substantially do not produce horizontal horizontal component in flutter process, and vibration efficiency is high.
The operation principle of right flutter device 4 is identical with the operation principle of left flutter device 3.
Left flutter device 3 and the independent separately control of right flutter device 4, this aircraft flight maneuverability more.
Be furnished with video camera and information processing system in fuselage 1, can take photo by plane, the image information of shooting can be sent to ground installation.Machine can realize remote control distributor with this aircraft of remote control equipment of ground configurations match.
This aircraft adopts hand mode of throwing take off or adopt the runway mode of sliding to take off; Four fins of left flutter device 3 and right flutter device 4 are locked in the high horizontal level crossing the center of gravity of aircraft or higher than the horizontal level crossing aircraft center of gravity, facilitate this aircraft to glide or landing.
A kind of small-sized four wing flutter aircraft of the present invention 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 (8)
1. small-sized four wing flutter aircraft, comprise fuselage (1), empennage (2), left flutter device (3), right flutter device (4) and undercarriage (5), it is characterized in that: fuselage is furnished with control system, airborne equipment and power-supply device in (1), airborne equipment comprises various flight instrumentation instrument and capture apparatus, and employing lithium battery is control system, airborne equipment and all feeding electric motors; Be configured with self-navigation autonomous driving device or remote control equipment, adopt self-navigation autonomous driving mode or remote control mode flight; The structure of left flutter device (3) and right flutter device (4), parameter and all identical left and right sides being symmetrically arranged in fuselage (1) of operation principle; Empennage (2) is made up of tailplane (23) and vertical tail; The effect of the upper and lower switch lifting rudder of tailplane (23) energy; Vertical tail is made up of the standing part of leading portion and the movable part of fixed fin (21) and back segment and rudder (22); Undercarriage (5) adopts wheel undercarriage; The structure of left flutter device (3) is: comprise motor (31), rotating disk (32), slide block (33), translation guide rod (34), front setting guide rod (35), rear setting guide rod (36), front fin (37), rear fin (38), front upper linear bearing (311), front lower linear bearing (312), rear upper linear bearing (313) and rear lower linear bearing (314); Front fin (37) is identical with rear fin (38), and they are nonrigid, and leading edge is perfectly round abundant, and trailing edge is tapering, and the part near leading edge is comparatively hard, and the part near trailing edge is softer, and aerofoil profile adopts flat pattern aerofoil profile under epirelief concave shape or epirelief, and they are all horizontally disposed; Front upper linear bearing (311), front lower linear bearing (312), rear upper linear bearing (313) and rear lower linear bearing (314) rectangular layout are fixedly mounted on fuselage (1) left side by bearing block; It is inner that motor (31) is fixedly mounted on fuselage (1), and its output shaft transverse horizontal is arranged and is connected with fuselage (1) left side wall by bearing; The output of motor (31) the output shaft center that be connected in rotating disk (32) inner side vertical with rotating disk (32); Slide block (33) be arranged on rotating disk (32) outside close to edge, slide block (33) can also rotation around the revolution of motor (31) output shaft with rotating disk (32); Translation guide rod (34) vertical equity is arranged, its stage casing is connected with slide block (33), slide block (33) can slide along translation guide rod (34), the front end of translation guide rod (34) is vertical with front setting guide rod (35) is fixed on front stage casing of erectting guide rod (35), the stage casing that be fixed on rear setting guide rod (36) vertical with rear setting guide rod (36), rear end of translation guide rod (34); The lower end of front setting guide rod (35) is through front lower linear bearing (312), and the upper end of front setting guide rod (35) is connected with the root of front fin (37) afterwards through front upper linear bearing (311); The lower end of rear setting guide rod (36) is through rear lower linear bearing (314), and the upper end of rear setting guide rod (36) is connected with the root of rear fin (38) afterwards through rear upper linear bearing (313).
2. small-sized four wing flutter aircraft of one according to claim 1, is characterized in that: all fin flat shapes are at right angles trapezoidal.
3. small-sized four wing flutter aircraft of one according to claim 1, is characterized in that: left flutter device (3) and the independent separately control of right flutter device (4).
4. small-sized four wing flutter aircraft of one according to claim 1, is characterized in that: four fins can be locked in the high horizontal level crossing the center of gravity of aircraft or higher than the horizontal level crossing aircraft center of gravity.
5. small-sized four wing flutter aircraft of one according to claim 1, is characterized in that: fuselage is furnished with video camera and information processing system in (1), the image information of shooting can be sent to ground installation.
6. small-sized four wing flutter aircraft of one according to claim 1, is characterized in that: with the remote control equipment of ground configurations match on machine.
7. small-sized four wing flutter aircraft of one according to claim 1, is characterized in that: undercarriage (5) adopts wheel undercarriage.
8. small-sized four wing flutter aircraft of one according to claim 1, is characterized in that: the root of each fin is all equipped with angle of attack stop, adopt servos control.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420789412.3U CN204297096U (en) | 2014-12-15 | 2014-12-15 | A kind of small-sized four wing flutter aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420789412.3U CN204297096U (en) | 2014-12-15 | 2014-12-15 | A kind of small-sized four wing flutter aircraft |
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| Publication Number | Publication Date |
|---|---|
| CN204297096U true CN204297096U (en) | 2015-04-29 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201420789412.3U Withdrawn - After Issue CN204297096U (en) | 2014-12-15 | 2014-12-15 | A kind of small-sized four wing flutter aircraft |
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| CN (1) | CN204297096U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104443381A (en) * | 2014-12-15 | 2015-03-25 | 佛山市神风航空科技有限公司 | Small air vehicle with four oscillation wings |
| CN106494618A (en) * | 2016-12-07 | 2017-03-15 | 南昌工程学院 | Plumage formula flapping-wing aircraft |
| CN107444634A (en) * | 2017-06-13 | 2017-12-08 | 大连理工大学 | Double freedom flapping wing mechanism |
-
2014
- 2014-12-15 CN CN201420789412.3U patent/CN204297096U/en not_active Withdrawn - After Issue
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104443381A (en) * | 2014-12-15 | 2015-03-25 | 佛山市神风航空科技有限公司 | Small air vehicle with four oscillation wings |
| CN106494618A (en) * | 2016-12-07 | 2017-03-15 | 南昌工程学院 | Plumage formula flapping-wing aircraft |
| CN106494618B (en) * | 2016-12-07 | 2018-11-06 | 南昌工程学院 | Plumage formula flapping-wing aircraft |
| CN107444634A (en) * | 2017-06-13 | 2017-12-08 | 大连理工大学 | Double freedom flapping wing mechanism |
| CN107444634B (en) * | 2017-06-13 | 2019-11-26 | 大连理工大学 | Double freedom flapping wing mechanism |
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| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| AV01 | Patent right actively abandoned |
Granted publication date: 20150429 Effective date of abandoning: 20160713 |
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| C25 | Abandonment of patent right or utility model to avoid double patenting |