CN204297085U - A kind of flat-type flapping wing aircraft with servomotor - Google Patents
A kind of flat-type flapping wing aircraft with servomotor Download PDFInfo
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- CN204297085U CN204297085U CN201420789020.7U CN201420789020U CN204297085U CN 204297085 U CN204297085 U CN 204297085U CN 201420789020 U CN201420789020 U CN 201420789020U CN 204297085 U CN204297085 U CN 204297085U
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- flapping wing
- main shaft
- fin
- servomotor
- wing device
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Abstract
With a flat-type flapping wing aircraft for servomotor, belong to technical field of aerospace, form primarily of fuselage, tail undercarriage, left flapping wing device, right flapping wing device, control system, remote control and undercarriage.Left flapping wing device is all identical with right flapping wing device structure, parameter and operation principle and be symmetrically arranged in the left and right sides of fuselage.Right flapping wing device comprises engine, decelerator, main shaft and is evenly distributed on main axial two, three or the identical rotor device of four structures.Each rotor device comprises pivoted arm, servomotor assembly and fin.Fin is that Rectangular Rigid is dull and stereotyped.Flutter under the fin that right flapping wing device was in the right of longitudinal vertical plane of main shaft is in level all the time, the fin being in the left side of longitudinal vertical plane of main shaft is in the state vertical with pivoted arm all the time and raises up.High and the mobility strong of this aircraft efficiency, is applicable to take photo by plane, geographical measurements, traffic duty, militaryly investigates and the multiple-task such as rescue and relief work.
Description
Technical field
With a flat-type flapping wing aircraft for servomotor, belong to technical field of aerospace, particularly relate to a kind of flapping wing aircraft.
Background technology
Traditional flapping-wing aircraft by fin instigate up and down produce lift, when fin raises up, resistance is comparatively large, and efficiency is lower, and the lift that can produce is limited, is difficult to realize heavy-duty flight; Flapping wing lift generating device flapping wing sheet being resetted by flapping wing hoisting mechanism 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, centre position fin is only had to be horizontal, other time fin and horizontal plane all there is an angle, more leave centre position angle larger, the lift produced is the component of the vertical direction of fin active force, the component of horizontal direction has become loss, produces the limited efficacy of lift.
Summary of the invention
The object of the invention is the above-mentioned deficiency overcoming existing flapping-wing aircraft, invent the flat-type flapping wing aircraft of the higher band servomotor of the simple efficiency of a kind of structure.
With a flat-type flapping wing aircraft for servomotor, form primarily of fuselage, tail undercarriage, left flapping wing device, right flapping wing device, control system, remote control and undercarriage.Left flapping wing device is identical with right flapping wing device structure and parameter and be symmetrically arranged in the left and right sides of fuselage, is used for producing lift.On fuselage left and right symmetrical left breach and right breach, they be conveniently left flapping wing device and right flapping wing device running and arrange.Tail undercarriage is driven by small machine, and tail undercarriage Plane of rotation can tilt to the left or to the right, can produce pulling force upwards, to the left or to the right under the manipulation of control system, to realize pitching and the yawed flight attitude of this aircraft.Undercarriage adopts slide-type undercarriage.Left flapping wing device and right flapping wing device are arranged on the left breach of fuselage and right indentation, there respectively.
The concrete structure of right flapping wing device is: it comprises engine, decelerator, main shaft and is evenly distributed on main axial two, three or the identical rotor device of four structures that only wing angle is different.Main shaft is arranged on the right side support of fuselage by bearing, and main shaft vertical equity is arranged, the front end of main shaft is connected with the output shaft of engine by decelerator.Engine is fixedly mounted on the right side support of fuselage.Each rotor device comprises pivoted arm, servomotor assembly and fin.Servomotor assembly comprises battery, servomotor controller, servomotor and wireless receiver.Wireless receiver is the part of remote control; Servomotor controller is the part of control system.One end of pivoted arm is vertical with the rear end of main shaft to be connected, and the other end of pivoted arm and the shell of servomotor are connected.The front of servo motor output shaft and fin is connected in middle in front.Pivoted arm is vertical with servo motor output shaft.Servo motor output shaft and main axis parallel.Main shaft, pivoted arm and servo motor output shaft are in same plane.Fin is that Rectangular Rigid is dull and stereotyped, and servo motor output shaft and fin are in same plane.
The operation principle of right flapping wing device is: from the rear end of this aircraft toward front end, pilot engine, drive shaft turns clockwise, and main shaft drives all rotor devices to rotate clockwise.Under the control of control system, servomotor periodically turns and stops, and namely the direction that servomotor rotates is contrary with main shaft rotates counterclockwise.When pivoted arm is in vertical position directly over main shaft, servomotor starts to rotate, on the right of longitudinal vertical plane of mistake main shaft, control system controls servomotor and main shaft constant speed reverse sync is rotated, drive the counterclockwise rotation of fin, make the fin on the right of the longitudinal vertical plane being in main shaft be in level all the time; When pivoted arm is in vertical position immediately below main shaft, servomotor stops operating and lock-bit fin is vertical with pivoted arm, on the left side of longitudinal vertical plane of mistake main shaft, control system controls servomotor and keeps motionless, makes the fin on the left side of the longitudinal vertical plane being in main shaft be in the state vertical with pivoted arm all the time.Like this, when flutterring under rotor device, the angle of attack of fin is 90 ° always, and when fin is up, the angle of attack is 0 ° always.Right flapping wing device can produce comparatively lift, and the efficiency producing lift is higher.
The operation principle of left flapping wing device is identical with right flapping wing device.Under the driving of the engine of left flapping wing device, the spindle axis counterclockwise of left flapping wing device rotates, and drives the rotor device of left flapping wing device to rotate counterclockwise.Under the control of control system, flutter under the fin being in the left side of longitudinal vertical plane of the main shaft of left flapping wing device is in level all the time; The fin being in the right of longitudinal vertical plane of the main shaft of left flapping wing device is in all the time and raises up with corresponding pivoted arm plumbness.
The small machine of all servomotors and tail undercarriage all adopts the lithium battery power supply of convenient charging.
Left flapping wing device is identical with the engine of right flapping wing device, all adopts internal combustion engine or motor, adopts during internal combustion engine and uses gasoline for the fuel, lithium battery power supply during employing motor.
Be furnished with video camera and information processing system in fuselage, can take photo by plane, the image information of shooting can be sent to ground installation.
Because this aircraft adopts two engines to make active force, mobility strong.
Accompanying drawing explanation
Fig. 1 is the schematic rear view of a kind of flat-type flapping wing aircraft with servomotor of the present invention; Fig. 2 is the schematic top plan view of a kind of flat-type flapping wing aircraft with servomotor of the present invention; Fig. 3 is that schematic diagram is looked on a left side for a kind of flat-type flapping wing aircraft with servomotor of the present invention; Fig. 4 is the structural representation only comprising the right flapping wing device of a rotor device be exaggerated, and in figure, fin is horizontal.In accompanying drawing, the rotor device of left flapping wing device and right flapping wing device is two.In Fig. 1, dotted portion represents that rotor device rotates to the signal of Difference angles.
In figure, 1-fuselage, the left breach of 11-, the right breach of 12-; 2-tail undercarriage, 21-small machine; The left flapping wing device of 3-; The right flapping wing device of 4-, 41-engine, 42-decelerator, 43-main shaft, 44-rotor device, 441-pivoted arm, 442-servomotor assembly, 4421-servo motor output shaft, 443-fin; 5-undercarriage.34A and 34B represents the rotor device being in diverse location of left flapping wing device; 44A and 44B represents the rotor device being in diverse location of right flapping wing device.
Detailed description of the invention
Now 1 ~ 4 couple of the present invention is illustrated by reference to the accompanying drawings: a kind of flat-type flapping wing aircraft with servomotor, forms primarily of fuselage 1, tail undercarriage 2, left flapping wing device 3, right flapping wing device 4, control system, remote control and undercarriage 5.Left flapping wing device 3 is identical with right flapping wing device 4 structure and parameter and be symmetrically arranged in the left and right sides of fuselage 1, is used for producing lift.On fuselage 1 left and right symmetrical left breach 11 and right breach 12, conveniently left flapping wing device 3 and right flapping wing device 4 operate and arrange for they.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, can produce pulling force upwards, to the left or to the right under the manipulation of control system, to realize pitching and the yawed flight attitude of this aircraft.Undercarriage 5 adopts slide-type undercarriage.Left flapping wing device 3 and right flapping wing device 4 are arranged on left breach 11 and right breach 12 place of fuselage 1 respectively.
The concrete structure of right flapping wing device 4 is: it comprises engine 41, decelerator 42, main shaft 43 and is evenly distributed on the identical rotor device 44 of two structures that only fin 443 angle is different around main shaft 43.Main shaft 43 is arranged on the right side support of fuselage 1 by bearing, and main shaft 43 vertical equity is arranged, the front end of main shaft 43 is connected with the output shaft of engine 41 by decelerator 42.Engine 41 is fixedly mounted on the right side support of fuselage 1.Each rotor device 44 comprises pivoted arm 441, servomotor assembly 442 and fin 443.Servomotor assembly 442 comprises battery, servomotor controller, servomotor and wireless receiver.Wireless receiver is the part of remote control; Servomotor controller is the part of control system.One end of pivoted arm 441 is vertical with the rear end of main shaft 43 to be connected, and the other end of pivoted arm 441 and the shell of servomotor are connected.Servo motor output shaft 4421 is connected in middle in front with the front of fin 443.Pivoted arm 441 is vertical with servo motor output shaft 4421.Servo motor output shaft 4421 is parallel with main shaft 43.Main shaft 43, pivoted arm 441 and servo motor output shaft 4421 are in same plane.Fin 443 is that Rectangular Rigid is dull and stereotyped.Servo motor output shaft 4421 and fin 443 are in same plane.
The operation principle of right flapping wing device 4 is: from the rear end of this aircraft toward front end, pilot engine 41, drive shaft 43 turns clockwise, and main shaft 43 drives all rotor device 44A and 44B to rotate clockwise.Under the control of control system, servomotor periodically turns and stops, and namely the direction that servomotor rotates is contrary with main shaft 43 rotates counterclockwise.When pivoted arm 441 is in vertical position directly over main shaft 43, servomotor starts to rotate, on the right of longitudinal vertical plane of mistake main shaft 43, control system controls servomotor and main shaft 43 constant speed reverse sync is rotated, drive fin 443 rotation counterclockwise, flutter under making the fin 443 on the right of the longitudinal vertical plane being in main shaft 43 be in level all the time; When pivoted arm 441 is in vertical position immediately below main shaft 43, servomotor stops operating and lock-bit fin 443 is vertical with pivoted arm 441, on the left side of longitudinal vertical plane of mistake main shaft 43, control system controls servomotor and keeps motionless, makes the fin 443 on the left side of the longitudinal vertical plane being in main shaft 43 be in the state vertical with pivoted arm 441 all the time and raises up.Like this, when rotor device is flutterred for 44 times, the angle of attack of fin 443 is 90 ° always, and when fin 443 is up, the angle of attack is 0 ° always.Right flapping wing device 4 can produce comparatively lift, and the efficiency producing lift is higher.
The operation principle of left flapping wing device 3 is identical with right flapping wing device 4.Under the driving of the engine of left flapping wing device 3, the spindle axis counterclockwise of left flapping wing device 3 rotates, and drives rotor device 34A and 34B of left flapping wing device 3 to rotate counterclockwise.Under the control of control system, flutter under the fin being in the left side of longitudinal vertical plane of the main shaft of left flapping wing device 3 is in level all the time; The fin being in the right of longitudinal vertical plane of the main shaft of left flapping wing device 3 is in all the time and raises up with corresponding pivoted arm plumbness.
The small machine 21 of all servomotors and tail undercarriage 2 all adopts the lithium battery power supply of convenient charging.
Left flapping wing device 3 is identical with the engine of right flapping wing device 4, all adopts internal combustion engine or motor, adopts during internal combustion engine and uses gasoline for the fuel, lithium battery power supply during employing motor.
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.
Fuselage and all fins all adopt carbon fibre material to make, and lightweight, intensity is strong.
Because this aircraft adopts two engines to make active force, mobility strong.
The flight attitude should inventing a kind of flat-type flapping wing aircraft with servomotor is below described further this invention.
Take off: start two engines simultaneously, rotor device 34A and 34B of left flapping wing device 3 and rotor device 44A and 44B of right flapping wing device 4 is driven to rotate, control system is utilized to make left flapping wing device 3 and right flapping wing device 4 produce equal-sized lift upwards, when lift reaches certain value, adjust the pulling force size and Orientation of tail undercarriage 2, make total life be greater than body weight, straight up, this aircraft vertical goes up to the air in the direction of total life.
Before fly: after taking off, control tail undercarriage 2 accelerate, total life is turned forward, flies before aircraft.
After fly: when flying, simultaneously synchronously accelerate left flapping wing device 3 and the velocity of rotation of right flapping wing device 4 or the rotating speed of the tail undercarriage 2 that slows down aloft, fly after this aircraft can be made to realize.
Turning flight: when front flying, the pulling force size and Orientation that simultaneously can be adjusted tail undercarriage 2 by the velocity of rotation improving right flapping wing device 4 can realize flight; Or the pulling force size and Orientation that the rotating speed improving left flapping wing device 3 adjusts tail undercarriage 2 can realize flight of turning right simultaneously.
Hovering: when aloft flying, control left flapping wing device 3 identical with the rotating speed of right flapping wing device 4, what the pulling force size and Orientation adjusting tail undercarriage 2 made left flapping wing device 3, right flapping wing device 4 and tail undercarriage 2 produce makes a concerted effort vertically upward and equals body weight, and after eliminating flight inertia, this aircraft will be in hovering position.
Landing: after this aircraft is adjusted to hovering position, slowly simultaneously reduce the rotating speed of left flapping wing device 3 and right flapping wing device 4, and control afterbody small machine 2 slows down simultaneously, this aircraft can slowly land.
Because two engines individually control, a kind of more convenient realization of flat-type flapping wing aircraft with servomotor of the present invention is sidewindered and hovering turns to.
More than illustrate it is make under the operating mode not having interference in air flow, if there is the existence of interference in air flow, then should carry out repairing partially according to the direction of air-flow and flow velocity.
A kind of flat-type flapping wing aircraft with servomotor of the present invention can be used for taking photo by plane, geographical measurements, traffic duty, militaryly to investigate and the multiple-task such as rescue and relief work.
Claims (6)
1. the flat-type flapping wing aircraft with servomotor, primarily of fuselage (1), tail undercarriage (2), left flapping wing device (3), right flapping wing device (4), control system, remote control and undercarriage (5) composition, it is characterized in that: left flapping wing device (3) is identical with right flapping wing device (4) structure and parameter and be symmetrically arranged in the left and right sides of fuselage (1); The upper left and right of fuselage (1) symmetrical left breach (11) and right breach (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; Undercarriage (5) adopts slide-type undercarriage;
The concrete structure of right flapping wing device (4) is: it comprises engine (41), decelerator (42), main shaft (43) and is evenly distributed on main shaft (43) around two, three or the identical rotor device (44) of four structures that only fin (443) angle is different; Main shaft (43) is arranged on the right side support of fuselage (1) by bearing, and main shaft (43) vertical equity is arranged, the front end of main shaft (43) is connected with the output shaft of engine (41) by decelerator (42); Engine (41) is fixedly mounted on the right side support of fuselage (1); Each rotor device (44) comprises pivoted arm (441), servomotor assembly (442) and fin (443); Servomotor assembly (442) comprises battery, servomotor controller, servomotor and wireless receiver; Wireless receiver is the part of remote control; Servomotor controller is the part of control system; One end of pivoted arm (441) is vertical with the rear end of main shaft (43) to be connected, and the other end of pivoted arm (441) and the shell of servomotor are connected; Servo motor output shaft (4421) is connected in middle in front with the front of fin (443); Pivoted arm (441) is vertical with servo motor output shaft (4421); Servo motor output shaft (4421) is parallel with main shaft (43); Main shaft (43), pivoted arm (441) and servo motor output shaft (4421) are in same plane; Fin (443) is that Rectangular Rigid is dull and stereotyped; Servo motor output shaft (4421) and fin (443) are in same plane; The fin (443) being in the right of longitudinal vertical plane of main shaft (43) is in level all the time; The fin (443) being in the left side of longitudinal vertical plane of main shaft (43) is in the state vertical with pivoted arm (441) all the time;
The operation principle of left flapping wing device (3) is identical with right flapping wing device (4); The fin being in the left side of longitudinal vertical plane of the main shaft of left flapping wing device (3) is in level all the time; The fin being in the right of longitudinal vertical plane of the main shaft of left flapping wing device (3) is in and corresponding pivoted arm plumbness all the time.
2. a kind of flat-type flapping wing aircraft with servomotor according to claim 1, is characterized in that: the small machine (21) of all servomotors and tail undercarriage (2) all adopts the lithium battery power supply of convenient charging.
3. a kind of flat-type flapping wing aircraft with servomotor according to claim 1, it is characterized in that: left flapping wing device (3) is identical with the engine of right flapping wing device (4), all adopt internal combustion engine or motor, adopt during internal combustion engine and use gasoline for the fuel, lithium battery power supply during employing motor.
4. a kind of flat-type flapping wing aircraft with servomotor according to claim 1, is characterized in that: fuselage is furnished with video camera and information processing system in (1), can take photo by plane, the image information of shooting can be sent to ground installation.
5. a kind of flat-type flapping wing aircraft with servomotor according to claim 1, is characterized in that: fuselage (1) and all fins all adopt carbon fibre material to make.
6. a kind of flat-type flapping wing aircraft with servomotor according to claim 1 or 3, is characterized in that: two engines individually control.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420789020.7U CN204297085U (en) | 2014-12-15 | 2014-12-15 | A kind of flat-type flapping wing aircraft with servomotor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420789020.7U CN204297085U (en) | 2014-12-15 | 2014-12-15 | A kind of flat-type flapping wing aircraft with servomotor |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN204297085U true CN204297085U (en) | 2015-04-29 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201420789020.7U Withdrawn - After Issue CN204297085U (en) | 2014-12-15 | 2014-12-15 | A kind of flat-type flapping wing aircraft with servomotor |
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| CN (1) | CN204297085U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104354861A (en) * | 2014-12-15 | 2015-02-18 | 佛山市神风航空科技有限公司 | Flat-plate ornithopter with servo motor |
| CN106986022A (en) * | 2017-04-29 | 2017-07-28 | 潘胜利 | A kind of screw type class flapping wing aircraft and its control method |
| CN112623213A (en) * | 2019-07-12 | 2021-04-09 | 李维农 | Flapping aircraft |
-
2014
- 2014-12-15 CN CN201420789020.7U patent/CN204297085U/en not_active Withdrawn - After Issue
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104354861A (en) * | 2014-12-15 | 2015-02-18 | 佛山市神风航空科技有限公司 | Flat-plate ornithopter with servo motor |
| CN106986022A (en) * | 2017-04-29 | 2017-07-28 | 潘胜利 | A kind of screw type class flapping wing aircraft and its control method |
| CN112623213A (en) * | 2019-07-12 | 2021-04-09 | 李维农 | Flapping aircraft |
| CN112623213B (en) * | 2019-07-12 | 2022-02-18 | 李维农 | Flapping aircraft |
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| Date | Code | Title | Description |
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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: 20160803 |
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| C25 | Abandonment of patent right or utility model to avoid double patenting |