CN1629038A - Aircraft with flapping wings - Google Patents
Aircraft with flapping wings Download PDFInfo
- Publication number
- CN1629038A CN1629038A CN 200410067039 CN200410067039A CN1629038A CN 1629038 A CN1629038 A CN 1629038A CN 200410067039 CN200410067039 CN 200410067039 CN 200410067039 A CN200410067039 A CN 200410067039A CN 1629038 A CN1629038 A CN 1629038A
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- aircraft
- flapping wing
- flapping
- gear
- cross bar
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Abstract
This invention relates to a new ornithopter aircraft, which comprises body, ornithopter, power system, control system and other addictive parts.
Description
Technical field
The present invention relates to a kind of aircraft of copying the birds flying method.
Background technology
Centuries, the mankind are exploring a kind of aircraft of copying the birds flying method always, but still do not have practical flapping-wing aircraft to come out so far.Tracing it to its cause, is because people always remove the reciprocating type flapping wing motion of cover biosome.On the basis of drawing forefathers' experience and lessons, we design a kind of rotary flapping wing aircraft.
Summary of the invention
The object of the present invention is to provide a kind of aircraft with flapping wings.
For achieving the above object.Aircraft with flapping wings of the present invention is made of following several parts:
(1) fuselage part: by the service on buses or trains storehouse, power bin, front and back crossbeam (wing beam), compositions such as alighting gear;
(2) flapping wing part: by rotation cross bar (or star-like spider), flapping wing sheet (3-4 sheet), compositions such as modulator;
(3) power pack section: by driving engine, change speed gear box, Transmission, compositions such as fuel tank;
(4) actuating element: by lift control lever, steering arm (pedal), sway joystick.Move forward and backward compositions such as joystick.Wherein, the sway joystick and move forward and backward joystick can a shared bar.Independently method control is taked in three (X-axis, Y-axis, Z axle) control respectively, avoids interacting.
(5) accessory constituent: by aileron, horizontal tail-rotor, tailplane, compositions such as vertical tail.
Description of drawings
Figure (1) is the integral structure scheme drawing of aircraft with flapping wings of the present invention: fuselage 1, front cross rail 2, after cross member 3, rotation cross bar 4, flapping wing sheet 5, flange and modulator 6, joystick 7, driving engine 8, change speed gear box 9, horizontal tail-rotor 10, aileron 11, tailplane 12, vertical tail 13.Flapping wing aircraft has both the advantage of fixed wing aircraft and helicopter, and it is flexible to have a flight maneuver, and oil consumption economizes, and structure is simpler, and manipulation is easier to.Flapping wing aircraft also has very big potentiality now.
Figure (2) is the structural representation of flapping wing part: rotation cross bar axis 1, power transmission gear 2, cross bar support arm 3, flapping wing sheet 4, modulator 5, modulator arm 6, regulation and control wheel chains (or transmission shaft) 7, regulation and control driven gear 8.Its structure is: do the cross bar axis with a hollow aluminum pipe.A slice flange and modulator 5 are installed in one side at the cross bar axis; Another side at the cross bar axis is installed a slice flange and power transmission driven gear 2.4 support arms respectively are installed on the flange on both sides, and corresponding support arm is aligned with each other.4 flapping wing sheets are installed in the outer end of 4 rotation cross bar support arms respectively, under the drive of driving engine, cross bar is rotated, and is referred to as revolution again; The flapping wing sheet is except that following the cross bar revolution, and self also is rotated, and is referred to as rotation.Revolution is 2 with the average ratio of rotation.In rotary course, make the flapping wing sheet when rising, keep plumbness; Under when pouncing on, keep horizontality; At upper-lower position, keep certain angle of attack (0 to+45 degree), can make the lift maximum like this, negative lift minimum (can referring to annex [flapping-wing aircraft investigation summary]).Compare with reciprocating type flapping wing, its movement inertia reusable edible, thereby energy consumption is less, lift is more steady.And, the operating angle that can regulate the flapping wing sheet by modulator, control side-to-side movement.When the fixed point lifting, the flapping wing part can provide lift.When flat flying, the alternative screw propeller of flapping wing part produces pulling force.The theoretical formula that produces lift is: F=∫ Cy*0.5* ρ * V
(⊥) 2* Rd ξ.
Figure (3) is a kind of fin state modulator scheme drawing: modulator case 1, rotation cross bar axis 2, quill 3, large conical gear 4 (52 tooth), small conical gear 5 (16 tooth), transmission shaft 6, small conical gear 7 (10 tooth), flapping wing sheet axis 8, large conical gear 9 (65 tooth), flapping wing sheet 10, modulator arm 11.The similar automobile steering wheel of effect of fin state modulator.The mode of operation of fin state modulator may command flapping wing sheet.Its structure is: modulator case 1 is a circular box, and rotation cross bar axis 2 runs through wherein.Quill 3 is enclosed within on the rotation cross bar axis 2, can rotate flexibly, and quill 3 the insides and large conical gear 4 fix, and quill 3 outsides and modulator arm 11 fix.Large conical gear 4 is meshed with small conical gear 5.In real work, large conical gear 4 does not rotate; Small conical gear 5 is made planet motion around large conical gear 4.And small conical gear 7 is rotated synchronously by transmission shaft 6.Small conical gear 7 is meshed with large conical gear 9 on being fixed on flapping wing sheet axis 8, in order to the spinning motion of control flapping wing sheet.And can manually finely tune by modulator arm 11, with the sway of control flapping wing aircraft.
Figure (4) is the fin state modulator scheme drawing of lower panel angle on a kind of scalable: modulator case 1, rotation cross bar axis 2, quill 3, center elliptic gear 4 (35 tooth), planet elliptic gear 5 (35 tooth), driving gear 6 (21 tooth), imput shaft 7, wheel chain 8, driven gear 9 (15 tooth), flapping wing sheet variable gear 10 (42 tooth), flapping wing sheet 11, flapping wing sheet axis 12, modulator arm 13.Central authorities' elliptic gear and 4 planet elliptic gears are meshed.Then through driving gear 6 (planet elliptic gear 5 with driving gear 6 be fixed on the imput shaft 7), wheel chain 8, driven gear 9, flapping wing sheet variable gear 10 is with the spinning motion of control flapping wing sheet.Central authorities' elliptic gear 4 is controlled by the people through sleeve 3 and arm 13.But its structure reference diagram (3) explanation.The purpose of newly-increased center elliptic gear 4 and planet elliptic gear 5 is in order to change the angle of attack of flapping wing sheet up and down.
Figure (5) is a kind of fin state modulator scheme drawing of digital control: rotation cross bar revolution angle observation circuit 1, flapping wing sheet angle of rotation observation circuit 2, digital processing circuit 3, servo dynamo-electric 4, cross bar revolution angle monitor box 5, digital processing circuit box 6, monitoring of flapping wing sheet angle of rotation and servo dynamo-electric box 7, rotation cross bar axis 8, cross bar support arm 9, flapping wing sheet 10.The fin state modulator of digital control can adopt different control programs to different state of flights, is convenient to realize automatic guidance.Its structure is: cross bar revolution angle monitor box 5, digital processing circuit box 6 are installed on the rotation cross bar axis 8; Monitoring of flapping wing sheet angle of rotation and servo dynamo-electric box 7 are installed on the axis of flapping wing sheet 10.Its principle is: input circuit comprises rotation cross bar revolution angle observation circuit 1 and flapping wing sheet angle of rotation observation circuit 2.3 pairs of incoming signals of digital processing circuit carry out computing, draw control signal, and the output control signal is given servo dynamo-electric 4 (containing deceleration).Figure (3), figure (4), figure (5) is three kinds of different fin state modulators, can select suitable a kind of.
Figure (6) is a kind of flapping wing sheet scheme drawing of scalable area: rotation cross bar axis 1, cross bar support arm 2, flapping wing sheet variable gear 3, fixing flapping wing sheet 4, flexible flapping wing sheet 5, thumb wheel 6, manually (or electronic) driving lever 7.The area of the flapping wing sheet by changing the fuselage both sides is with control left and right sides balance and anterior-posterior balance.The alternative horizontal tail-rotor of small-sized flapping wing aircraft.In addition, can on middle font framework, make simple and easy flapping wing sheet with fabric envelope.
Figure (7) is lifting manipulation and power transmission scheme drawing: driving engine 1, horizontal tail-rotor 2, change speed gear box 3, power transmission chain 4, power transmission gear 5, rotation cross bar 6, engine throttle control stalk 7.By open the throttle wide, improve the rotating speed of flapping wing sheet and horizontal tail-rotor, flapping wing aircraft is risen, otherwise descend.Its structure is: driving engine 1 is the horizontal tail-rotor 2 of direct drive on the one hand; On the other hand doubly, through power transmission chain 4 and 6 revolution of power transmission gear 5 driven rotary cross bares by change speed gear box 3 deceleration 30-40.When the throttle increasing, engine speed improves, and flapping wing aircraft moves up; Otherwise flapping wing aircraft moves down.
Figure (8) is the handling maneuver scheme drawing: pedal 1, driving lever 2, steering arm 3, right angle seesaw 4, rotation cross bar central axle sleeve 5, rotation cross bar 6, kinematic link 7, vertical tail 8.Vertical tail only works when preceding flying.When hovering, the inclination in the running direction difference of may command fuselage two sideway swivel cross bares turns to.Its structure is: pedal 1 makes seesaw 4 deflections of right angle, the left and right sides through driving lever 2 and steering arm 3, and rotation cross bar central axle sleeve 5 is installed on the right angle seesaw 4, also in company with up-and-down movement, makes fuselage two sideway swivel cross bares 6 inclination in the running direction differences at last.
Figure (9) handles scheme drawing for sway: sway joystick 1, modulator arm 2, flange and modulator 3, rotation cross bar 4, kinematic link 5, starboard aileron 6, port aileron 7.Starboard aileron 6 and port aileron 7 only work when preceding flying.When hovering, can reach sway by the degree of dip of fin state modulator control fuselage both sides flapping wing sheet.Joystick moves to left, and flapping wing aircraft is moved to the left, otherwise, move right.
Figure (10) is for moving forward and backward the manipulation scheme drawing: move forward and backward joystick 1, driving lever 2, slip lasso 3, Adjustable length rod 4, horizontal tail-rotor 5, tailplane 6.Tailplane only plays the pitching effect when preceding flying, when hovering, the angle of attack of controllable levels tail-rotor moves forward and backward.Push away before the joystick, the angle of attack of horizontal tail-rotor strengthens, and flapping wing aircraft moves forward, otherwise, move backward.Small-sized flapping wing aircraft can partly be installed in flapping wing on the universal slide plate of fuselage, to realize anterior-posterior balance control and left and right sides balance control.Substitute aforementioned sway manipulation and move forward and backward actuating element, structure is more simplified.
Figure (11) is the flapping wing aircraft front elevation, and flapping wing sheet workflow diagram.
Figure (12) is universal skateboard scheme drawing.All around the balance control bar 1, flapping wing part lower shoe 2, fuselage upper plate 3, slip square frame 4, flapping wing part lower shoe sliding wheel 5, fuselage upper plate sliding wheel 6.When control stalk 1 moved forward and backward, flapping wing part lower shoe 2 relatively moved before and after can doing with slip square frame 4; During control stalk 1 sway, fuselage upper plate 3 relatively moves about can doing with slip square frame 4.Its effect is to regulate lift and gravitational equilibrium.When the artificial destruction balance, flapping wing aircraft can be made front and back or sway.
The specific embodiment
Embodiment 1: existing fixed wing aircraft is adapted as the short take-off and landing flapping wing aircraft.It is the flapping wing part that the wing of fixed wing aircraft is partly changed, and is connected with power, fixes after the modulator adjustment.Its method of operating is identical with former fixed wing aircraft.
Embodiment 2: can implement for aircraft plant and automotive plant.Produce for agricultural tourism, the flapping wing aircraft that air sport etc. use.
Claims (10)
1, a kind of aircraft with flapping wings is characterized in that: this aircraft with flapping wings is by the fuselage part, flapping wing part, power pack section, actuating element and the attaching part formation of grading.
2, aircraft with flapping wings according to claim 1 is characterized in that: each is made up of left and right sides flapping wing part 4 flapping wing sheets, is installed in one and rotates the cross bar outer end and (or be made up of 3 flapping wing sheets, be installed in a star-like spider frame outer end), and controlled by fin state modulator.The rotation cross bar revolves round the sun, and the flapping wing sheet carries out rotation, and revolution is 2 with the average ratio of rotation.
3, aircraft with flapping wings according to claim 1 is characterized in that: basic fin state modulator is meshed by a central large conical gear 4 (52 tooth) and 4 small conical gears 5 (16 tooth).Through transmission shaft 6, gear 7 (10 tooth) and large conical gear 9 (65 tooth) are meshed then, with the rotational angle of control flapping wing sheet.Central authorities' large conical gear 4 is controlled by the people through sleeve 3 and arm 11.
4, aircraft with flapping wings according to claim 1 is characterized in that: angle adjustable fin state modulator is meshed by a central elliptic gear (35 tooth) and 4 planet elliptic gears (35 tooth).Then through driving gear 6 (21 tooth), wheel chain 8, driven gear 9 (15 tooth), flapping wing sheet variable gear 10 (42 tooth) is with the rotational angle of control flapping wing sheet.Central authorities' elliptic gear 4 is controlled by the people through sleeve 3 and arm 13.
5, aircraft with flapping wings according to claim 1 is characterized in that: by cross bar revolution angle observation circuit 1, and flapping wing sheet angle of rotation observation circuit 2, digital processing circuit 3 is formed digital control type fin state modulator servo dynamo-electric 4 (containing deceleration).
6, aircraft with flapping wings according to claim 1 is characterized in that: by fixing flapping wing sheet 4, and flexible flapping wing sheet 5, thumb wheel 6, driving lever 7 is formed the flapping wing sheet of scalable areas.Can be used for regulating left and right sides balance and anterior-posterior balance.
7, aircraft with flapping wings according to claim 1 is characterized in that: by driving engine 1, and horizontal tail-rotor 2, change speed gear box 3, power transmission chain 4, power transmission gear 5, rotation cross bar 6, engine throttle control stalk 7 is formed lifting control.
8, aircraft with flapping wings according to claim 1 is characterized in that: by pedal 1, and driving lever 2, steering arm 3, right angle seesaw 4, rotation cross bar central axle sleeve 5, rotation cross bar 6, kinematic link 7, vertical tail 8 compositions turn to control.
9, aircraft with flapping wings according to claim 1 is characterized in that: by sway joystick 1, and modulator arm 2, flange and modulator 3, rotation cross bar 4, kinematic link 5, starboard aileron 6, port aileron 7 is formed left and right moving control.
10, aircraft with flapping wings according to claim 1 is characterized in that: by moving forward and backward joystick 1, driving lever 2, slip lasso 3, Adjustable length rod 4, horizontal tail-rotor 5, tailplane 6 are formed and are moved forward and backward control.Small-sized flapping wing aircraft can partly be installed in flapping wing on the universal slide plate of fuselage, to realize left and right moving control and to move forward and backward control.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 200410067039 CN1629038A (en) | 2004-10-02 | 2004-10-02 | Aircraft with flapping wings |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 200410067039 CN1629038A (en) | 2004-10-02 | 2004-10-02 | Aircraft with flapping wings |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN1629038A true CN1629038A (en) | 2005-06-22 |
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ID=34846627
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 200410067039 Pending CN1629038A (en) | 2004-10-02 | 2004-10-02 | Aircraft with flapping wings |
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| CN (1) | CN1629038A (en) |
Cited By (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102616375A (en) * | 2012-04-09 | 2012-08-01 | 上海交通大学 | Bevel gear four-wing type flapping wing mini-aircraft |
| CN104477388A (en) * | 2014-12-15 | 2015-04-01 | 佛山市神风航空科技有限公司 | Four-wing flat-flapping flapping-wing aircraft |
| CN104477384A (en) * | 2014-12-15 | 2015-04-01 | 佛山市神风航空科技有限公司 | Flat wing panel ornithopter |
| CN106628171A (en) * | 2016-12-01 | 2017-05-10 | 向仲宇 | Split type flapping wing air vehicle with variable flapping wing area |
| CN106945834A (en) * | 2017-03-29 | 2017-07-14 | 陆昌新 | Flapping wing adjustable and from varying pitch |
| WO2019237252A1 (en) * | 2018-06-12 | 2019-12-19 | 深圳瀚飞科技开发有限公司 | Novel vertical take-off and landing aircraft system |
| CN112407276A (en) * | 2020-11-26 | 2021-02-26 | 广东国士健科技发展有限公司 | Flapping rotor wing device capable of realizing upward half-rotation and downward horizontal operation |
| CN112429215A (en) * | 2020-11-26 | 2021-03-02 | 广东国士健科技发展有限公司 | Simple string type half-rotation flapping type self-rotating rotor wing device |
| CN112441227A (en) * | 2020-11-26 | 2021-03-05 | 广东国士健科技发展有限公司 | Flapping-like rotor aircraft |
| CN112498677A (en) * | 2020-11-26 | 2021-03-16 | 广东国士健科技发展有限公司 | Flapping wing-like device capable of simultaneously generating thrust and lift |
| CN112550697A (en) * | 2020-11-26 | 2021-03-26 | 广东国士健科技发展有限公司 | Flapping rotor wing device capable of realizing coplanar operation of upward vertical operation and downward axial wings |
| CN112550696A (en) * | 2020-11-26 | 2021-03-26 | 广东国士健科技发展有限公司 | Flapping rotor wing device capable of vertically running in uplink and horizontally running in downlink |
-
2004
- 2004-10-02 CN CN 200410067039 patent/CN1629038A/en active Pending
Cited By (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102616375A (en) * | 2012-04-09 | 2012-08-01 | 上海交通大学 | Bevel gear four-wing type flapping wing mini-aircraft |
| CN102616375B (en) * | 2012-04-09 | 2015-04-01 | 上海交通大学 | Bevel gear four-wing type flapping wing mini-aircraft |
| CN104477388A (en) * | 2014-12-15 | 2015-04-01 | 佛山市神风航空科技有限公司 | Four-wing flat-flapping flapping-wing aircraft |
| CN104477384A (en) * | 2014-12-15 | 2015-04-01 | 佛山市神风航空科技有限公司 | Flat wing panel ornithopter |
| CN106628171A (en) * | 2016-12-01 | 2017-05-10 | 向仲宇 | Split type flapping wing air vehicle with variable flapping wing area |
| CN106945834A (en) * | 2017-03-29 | 2017-07-14 | 陆昌新 | Flapping wing adjustable and from varying pitch |
| WO2019237252A1 (en) * | 2018-06-12 | 2019-12-19 | 深圳瀚飞科技开发有限公司 | Novel vertical take-off and landing aircraft system |
| CN112407276A (en) * | 2020-11-26 | 2021-02-26 | 广东国士健科技发展有限公司 | Flapping rotor wing device capable of realizing upward half-rotation and downward horizontal operation |
| CN112429215A (en) * | 2020-11-26 | 2021-03-02 | 广东国士健科技发展有限公司 | Simple string type half-rotation flapping type self-rotating rotor wing device |
| CN112441227A (en) * | 2020-11-26 | 2021-03-05 | 广东国士健科技发展有限公司 | Flapping-like rotor aircraft |
| CN112498677A (en) * | 2020-11-26 | 2021-03-16 | 广东国士健科技发展有限公司 | Flapping wing-like device capable of simultaneously generating thrust and lift |
| CN112550697A (en) * | 2020-11-26 | 2021-03-26 | 广东国士健科技发展有限公司 | Flapping rotor wing device capable of realizing coplanar operation of upward vertical operation and downward axial wings |
| CN112550696A (en) * | 2020-11-26 | 2021-03-26 | 广东国士健科技发展有限公司 | Flapping rotor wing device capable of vertically running in uplink and horizontally running in downlink |
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