CN204297091U - A kind of miniature flutter aircraft - Google Patents
A kind of miniature flutter aircraft Download PDFInfo
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- CN204297091U CN204297091U CN201420789292.7U CN201420789292U CN204297091U CN 204297091 U CN204297091 U CN 204297091U CN 201420789292 U CN201420789292 U CN 201420789292U CN 204297091 U CN204297091 U CN 204297091U
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- flutter
- fin
- guide rod
- aircraft
- main shaft
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Abstract
A kind of miniature flutter aircraft, belongs to technical field of aerospace, comprises fuselage, empennage, left flutter device, right flutter device, motor, gear reduction unit, main shaft and undercarriage.Control system, airborne equipment and power-supply device is furnished with in fuselage.The left flutter device left and right sides that be symmetrically arranged in fuselage identical with right flutter apparatus structure, parameter and operation principle.Empennage is made up of tailplane and vertical tail.The two ends of main shaft are connected with right flutter device with left flutter device.Left flutter device comprises rotating disk, slide block, translation guide rod, erects guide rod, linear bearing and fin.The power of motor passes to main shaft after gear reduction unit, and main shaft drives left flutter device and the work of right flutter device, two fin translational vibrations and produce lift and thrust, laterally can not produce horizontal component in the process of flutter.This Flight Vehicle Structure is simple, and efficiency is higher, 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.
Description
Technical field
A kind of miniature flutter aircraft, belongs to technical field of aerospace, particularly relates 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.
Summary of the invention
The object of the invention is the above-mentioned deficiency overcoming existing flapping wing aircraft, invent the simple miniature flutter aircraft of the higher structure of a kind of efficiency.
A kind of miniature flutter aircraft, comprises fuselage, empennage, left flutter device, right flutter device, motor, gear reduction unit, main shaft 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 capture apparatus.Employing lithium battery is control system, airborne equipment and feeding electric motors.Be configured with remote control equipment, adopt 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.Bikini wheel undercarriage after undercarriage adopts.
Motor center ofthe is fixedly mounted on the bottom of fuselage interior, and its output shaft is connected with main shaft by gear reduction unit.Main shaft transverse horizontal is arranged, the two ends, left and right of main shaft are connected with fuselage left and right sides wall by bearing, the left end center that be connected in rotating disk inside vertical with the rotating disk of left flutter device of main shaft; The right-hand member center that be connected in rotating disk inside vertical with the rotating disk of right flutter device of main shaft.The structure of left flutter device is: comprise rotating disk, slide block, translation guide rod, erect guide rod, linear bearing and fin.Fin is 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; Fin flat shape is rectangular, and aerofoil profile adopts flat pattern aerofoil profile under epirelief concave shape or epirelief; Fin is horizontally disposed.Linear bearing is fixedly mounted on the left of fuselage by bearing block and is positioned at directly over rotating disk.Slide block be arranged on outside rotating disk close to edge, slide block can with rotating disk around main shaft revolution can also rotation.Translation guide rod vertical equity is arranged, and is connected with slide block, and slide block can slide along translation guide rod, erects the lower end center position that be fixed on translation guide rod vertical with translation guide rod of guide rod; Top is stretched out through linear bearing in the upper end of erectting guide rod.Fin by its root with erect guide rod be connected in erect guide rod lower end close to translation guide rod place.
Turn right from the left side of this invention aircraft, the operation principle of left flutter device is: the power of motor passes to main shaft after gear reduction unit, main shaft drives rotating disk to rotate clockwise, under the drive of the slide block on rotating disk, translation guide rod is done repeatedly to move up and down and is driven setting guide rod to move up and down in linear bearing again, thus drives fin up-down vibration.Clapping process under fin, is the process that fin is clapped from highest point toward lowest part, and clap under the leading edge of this process fin keeps level substantially, the displacement of clapping under the identical chord positions of spanwise fin is identical, realizes flat bat downwards.Because fin is nonrigid, have certain flexibility and elasticity, in lower bat process trailing edge want delayed leading edge some.Because the aerofoil profile of fin is flat pattern under epirelief concave shape or epirelief, lower bat produces larger lift upwards and less thrust forward.To be fin to raise up extreme higher position from extreme lower position fin arsis process, and the leading edge of this process fin keeps level arsis substantially, and the displacement along spanwise identical chord positions arsis is identical, realizes upwards flat bat.Because fin is nonrigid, have certain flexibility and elasticity, during arsis, the trailing edge of fin also can delayed leading edge.Because the aerofoil profile of 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 fin is larger.During arsis, fin produces larger thrust forward and less lift upwards or does 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 fin is flapped is that the rotating speed by controlling motor carries out regulating.For this aircraft is more flexible, the root of 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 different flight attitudes.Fin does not substantially 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 are driven by a motor jointly, and this Flight Vehicle Structure is simple.The hunting range of the fin of left flutter device and the fin of right flutter device independently separately controls, this aircraft flight maneuverability.
Accompanying drawing explanation
Fig. 1 is the schematic top plan view of a kind of miniature flutter aircraft of the present invention, and Fig. 2 is that schematic diagram is looked, in this figure in a left side for a kind of miniature flutter aircraft of the present invention, left flutter device and right flutter device are in down in the process of flutterring, their fin is all in lower bat, and 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-motor; 6-gear reduction unit; 7-main shaft; 8-undercarriage.
That indicates in the drawings belongs to having of the part of left flutter device 3: 31-rotating disk, 32-slide block, 33-translation guide rod, and 34-erects guide rod, 35-linear bearing, 36-fin.
Detailed description of the invention
Now 1 ~ 2 couple of the present invention is illustrated by reference to the accompanying drawings: a kind of miniature flutter aircraft, comprises fuselage 1, empennage 2, left flutter device 3, right flutter device 4, motor 5, gear reduction unit 6, main shaft 7 and undercarriage 8.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 capture apparatus.Employing lithium battery is that control system, airborne equipment and motor 5 is powered.Be configured with remote control equipment, adopt 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 8 adopts rear bikini wheel undercarriage.
Motor 5 center ofthe is fixedly mounted on the bottom of fuselage 1 inside, and its output shaft is connected with main shaft 7 by gear reduction unit 6.Main shaft 7 transverse horizontal is arranged, the two ends, left and right of main shaft 7 are connected with fuselage 1 left and right sides wall by bearing, the left end center that be connected in rotating disk 31 inside vertical with the rotating disk 31 of left flutter device 3 of main shaft 7; The right-hand member center that be connected in rotating disk inside vertical with the rotating disk of right flutter device 4 of main shaft 7.The structure of left flutter device 3 is: comprise rotating disk 31, slide block 32, translation guide rod 33, erect guide rod 34, linear bearing 35 and fin 36.Fin 36 is 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; Fin 36 flat shape is rectangular, and aerofoil profile adopts flat pattern aerofoil profile under epirelief concave shape or epirelief; Fin 36 is horizontally disposed.Linear bearing 35 is fixedly mounted on the left of fuselage 1 by bearing block and is positioned at directly over rotating disk 31.Slide block 32 be arranged on outside rotating disk 31 close to edge, slide block 32 can with rotating disk 31 around main shaft 7 revolution can also rotation.Translation guide rod 33 vertical equity is arranged, and is connected with slide block 32, and slide block 32 can slide along translation guide rod 33, erects the lower end center position that be fixed on translation guide rod 33 vertical with translation guide rod 33 of guide rod 34; Top is stretched out through linear bearing 35 in the upper end of erectting guide rod 34.Fin 36 by its root with erect guide rod 34 be connected in erect guide rod 34 lower end close to translation guide rod 33 place.
Turn right from the left side of this invention aircraft, the operation principle of left flutter device 3 is: the power of motor 5 passes to main shaft 7 after gear reduction unit 6, main shaft 7 drives rotating disk 31 to rotate clockwise, under the drive of the slide block 32 on rotating disk 31, translation guide rod 33 is done repeatedly to move up and down and is driven setting guide rod 34 to move up and down in linear bearing 35 again, thus drives fin 36 up-down vibration.Fin 36 times claps processes, is the process that fin 36 is clapped from highest point toward lowest part, and clap under the leading edge of this process fin 36 keeps level substantially, the displacement of clapping under the identical chord positions of spanwise fin 36 is identical, realizes flat bat downwards.Because fin 36 is nonrigid, have certain flexibility and elasticity, in lower bat process trailing edge want delayed leading edge some.Because the aerofoil profile of fin 36 is flat patterns under epirelief concave shape or epirelief, lower bat produces larger lift upwards and less thrust forward.To be fin 36 to raise up extreme higher position from extreme lower position fin 36 arsis process, and the leading edge of this process fin 36 keeps level arsis substantially, and the displacement along spanwise identical chord positions arsis is identical, realizes upwards flat bat.Because fin 36 is nonrigid, have certain flexibility and elasticity, during arsis, the trailing edge of fin 36 also can delayed leading edge.Because the aerofoil profile of fin 36 is flat patterns under epirelief concave shape or epirelief, compared with lower bat, the degree of the delayed leading edge of trailing edge of fin 36 is larger.During arsis, fin 36 produces larger thrust forward and less lift upwards or does 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 fin 36 vibrates is that the rotating speed by controlling motor 5 carries out regulating.Fin 36 does not substantially 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.
For this aircraft is more flexible, the root of two fins 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 different flight attitudes.
Left flutter device 3 and right flutter device 4 are driven by a motor 5 jointly, and this Flight Vehicle Structure is simple.The hunting range of the fin 36 of left flutter device 3 and the fin of right flutter device 4 independently separately controls, this aircraft flight maneuverability.
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; Two 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.
This aircraft fuselage adopts the light materials such as carbon fiber to make, and full-size is no more than 15cm.
A kind of miniature 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 (7)
1. a miniature flutter aircraft, is characterized in that: comprise fuselage (1), empennage (2), left flutter device (3), right flutter device (4), motor (5), gear reduction unit (6), main shaft (7) and undercarriage (8); Fuselage is furnished with control system, airborne equipment and power-supply device in (1); Employing lithium battery is the power supply of control system, airborne equipment and motor (5); Be configured with remote control equipment, adopt remote control mode flight; Structure, the parameter of left flutter device (3) and right flutter device (4) are all identical with operation principle, are symmetrically arranged in the left and right sides of fuselage (1); Empennage (2) is made up of tailplane (23) and vertical tail; Tailplane (23) energy switch up and down; 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); It is inner that motor (5) is arranged on fuselage (1), and its output shaft is connected with main shaft (7) by gear reduction unit (6); Main shaft (7) transverse horizontal is arranged, the two ends, left and right of main shaft (7) are connected with fuselage (1) left and right sides wall by bearing, the left end of main shaft (7) center that be connected in rotating disk (31) inner side vertical with the rotating disk (31) of left flutter device (3); The right-hand member of main shaft (7) and the vertical center be connected in inside rotating disk of rotating disk of right flutter device (4); The structure of left flutter device (3) is: comprise rotating disk (31), slide block (32), translation guide rod (33), erect guide rod (34), linear bearing (35) and fin (36); Fin (36) is 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; Fin (36) is horizontally disposed; Linear bearing (35) is fixedly mounted on fuselage (1) left side by bearing block and is positioned at directly over rotating disk (31); Slide block (32) be arranged on rotating disk (31) outside close to edge, slide block (32) can also rotation around main shaft (7) revolution with rotating disk (31); Translation guide rod (33) vertical equity is arranged, and is connected with slide block (32), and slide block (32) can slide along translation guide rod (33), erects the lower end center position that be fixed on translation guide rod (33) vertical with translation guide rod (33) of guide rod (34); Top is stretched out through linear bearing (35) in the upper end of erectting guide rod (34); Fin (36) by its root with erect guide rod (34) be connected in erect guide rod (34) lower end close to translation guide rod (33) place.
2. the miniature flutter aircraft of one according to claim 1, is characterized in that: all fin flat shapes are rectangular, and aerofoil profile all adopts flat pattern aerofoil profile under epirelief concave shape or epirelief.
3. the miniature flutter aircraft of one according to claim 1, is characterized in that: two 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.
4. the miniature 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.
5. the miniature flutter aircraft of one according to claim 1, is characterized in that: with the remote control equipment of ground configurations match on machine.
6. the miniature flutter aircraft of one according to claim 1, is characterized in that: bikini wheel undercarriage after undercarriage (8) adopts.
7. the miniature flutter aircraft of one according to claim 1, is characterized in that: the root of two fins is all equipped with angle of attack stop, adopts servos control; The hunting range of the fin (36) of left flutter device (3) and the fin of right flutter device (4) independently separately controls.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420789292.7U CN204297091U (en) | 2014-12-15 | 2014-12-15 | A kind of miniature flutter aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420789292.7U CN204297091U (en) | 2014-12-15 | 2014-12-15 | A kind of miniature flutter aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN204297091U true CN204297091U (en) | 2015-04-29 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201420789292.7U Withdrawn - After Issue CN204297091U (en) | 2014-12-15 | 2014-12-15 | A kind of miniature flutter aircraft |
Country Status (1)
| Country | Link |
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| CN (1) | CN204297091U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104477389A (en) * | 2014-12-15 | 2015-04-01 | 佛山市神风航空科技有限公司 | Minitype fluttering-wing aircraft |
-
2014
- 2014-12-15 CN CN201420789292.7U patent/CN204297091U/en not_active Withdrawn - After Issue
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104477389A (en) * | 2014-12-15 | 2015-04-01 | 佛山市神风航空科技有限公司 | Minitype fluttering-wing aircraft |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| AV01 | Patent right actively abandoned |
Granted publication date: 20150429 Effective date of abandoning: 20160615 |
|
| C25 | Abandonment of patent right or utility model to avoid double patenting |