CN112319792A - Flapping wing aircraft with gravity center below two wings - Google Patents
Flapping wing aircraft with gravity center below two wings Download PDFInfo
- Publication number
- CN112319792A CN112319792A CN202011342097.6A CN202011342097A CN112319792A CN 112319792 A CN112319792 A CN 112319792A CN 202011342097 A CN202011342097 A CN 202011342097A CN 112319792 A CN112319792 A CN 112319792A
- Authority
- CN
- China
- Prior art keywords
- wing
- wings
- driving
- connecting rod
- driven
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Withdrawn
Links
- 230000005484 gravity Effects 0.000 title claims abstract description 25
- 230000005540 biological transmission Effects 0.000 claims description 21
- 230000007246 mechanism Effects 0.000 claims description 11
- 238000009434 installation Methods 0.000 claims 2
- 230000009977 dual effect Effects 0.000 abstract 1
- 238000000034 method Methods 0.000 description 17
- 230000008569 process Effects 0.000 description 15
- 230000033001 locomotion Effects 0.000 description 9
- 230000009471 action Effects 0.000 description 5
- 230000008859 change Effects 0.000 description 5
- 230000003247 decreasing effect Effects 0.000 description 4
- 238000010586 diagram Methods 0.000 description 4
- 230000000694 effects Effects 0.000 description 3
- 241000238631 Hexapoda Species 0.000 description 2
- 230000000737 periodic effect Effects 0.000 description 2
- UJCHIZDEQZMODR-BYPYZUCNSA-N (2r)-2-acetamido-3-sulfanylpropanamide Chemical compound CC(=O)N[C@@H](CS)C(N)=O UJCHIZDEQZMODR-BYPYZUCNSA-N 0.000 description 1
- 241000271566 Aves Species 0.000 description 1
- 229920000049 Carbon (fiber) Polymers 0.000 description 1
- 241000288673 Chiroptera Species 0.000 description 1
- 241001669680 Dormitator maculatus Species 0.000 description 1
- 108010066114 cabin-2 Proteins 0.000 description 1
- 239000004917 carbon fiber Substances 0.000 description 1
- 239000002131 composite material Substances 0.000 description 1
- 230000008878 coupling Effects 0.000 description 1
- 238000010168 coupling process Methods 0.000 description 1
- 238000005859 coupling reaction Methods 0.000 description 1
- 238000005265 energy consumption Methods 0.000 description 1
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000000750 progressive effect Effects 0.000 description 1
- 230000000630 rising effect Effects 0.000 description 1
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/22—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/32—Rotors
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C33/00—Ornithopters
- B64C33/02—Wings; Actuating mechanisms therefor
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/02—Aircraft characterised by the type or position of power plants
- B64D27/24—Aircraft characterised by the type or position of power plants using steam or spring force
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Toys (AREA)
Abstract
The invention discloses an ornithopter with a gravity center below two wings, which comprises a wing device, a cockpit and a run-up device, wherein the wing device is provided with a wing opening; the wing device is arranged at the top of the cockpit and comprises a driving cabin body, a driving assembly, a connecting assembly and a wing; the driving assembly is arranged in the driving cabin body, and the connecting assembly and the wings are arranged on the outer side of the driving cabin body; a seat, an armrest and a pedal device are arranged in the cockpit; the tail part of the cabin body is provided with a tail wing, and the tail wing is connected with the handrail through a pull rod; the run-up device is mounted at the bottom of the cockpit; the starting device and the wing device are driven by the motor, the invention adopts a flapping wing form and is combined with the rotor wing on the basis, the flying efficiency is improved, the gravity center is arranged below the wing device, and the stability is higher; accessible electric power and manpower dual mode drive prevent when flight state, the unable safe descending of electric quantity exhaustion, improved the safety guarantee of flight.
Description
Technical Field
The invention relates to the technical field of aircrafts, in particular to an ornithopter with a gravity center below two wings.
Background
At present, insects, birds and bats which can fly in nature all adopt flapping wings to fly, and have the characteristics of high maneuverability and low energy consumption. The flapping wing aircraft is different from fixed wing aircraft and rotor aircraft, is an aircraft adopting insect, bird and bat flying modes, has wide application in military and civil fields, and realizes flying by various flapping wing aircraft.
However, the flying action of birds is complicated. In the prior art, most of the wings of birds are simply simulated to swing up and down, the wings do not extend and retract like birds, and the left and right wings cannot be independently controlled, so that the flight efficiency is low and the maneuvering capability is quite limited. In addition, the conventional aircraft can only be driven by power or energy such as an engine, and when the energy is insufficient, the conventional aircraft cannot land smoothly, so that the danger is extremely high.
Therefore, how to provide an ornithopter with simple structure and safer driving is a problem that needs to be solved urgently by the technical personnel in the field.
Disclosure of Invention
The present invention is directed to solving, at least to some extent, one of the above-mentioned problems in the prior art.
In view of the above, the present invention provides an ornithopter having a center of gravity below two wings; the flapping wing has the flapping flight capability, and the rotor wing is taken as the wing to drive the rotor wing to flap on the premise of flapping wing flight, so that the flight effect is further improved; the electric power and manpower drive mode can be used for driving, and the problem that the landing cannot be safely carried out under the condition that the electric energy is exhausted is avoided.
In order to achieve the purpose, the invention adopts the following technical scheme:
an ornithopter with a center of gravity below two wings is characterized by comprising a wing device, a cockpit and a run-up device;
the wing device is arranged at the top of the cockpit and comprises a driving cabin body, a driving assembly and wings; the drive assembly is arranged in the drive cabin body, and the wings are arranged on the outer side of the drive cabin body;
the driving assembly comprises a driving gear, a driven gear, a first transmission shaft, a first driving chain wheel, a first driven chain wheel, a first connecting rod, a driving disc, a second connecting rod, a third connecting rod, a fourth connecting rod and a fifth connecting rod; the driving gear is meshed with the driven gear, the driven gear is installed on the first transmission shaft, and the two first driving chain wheels are installed at two ends of the first transmission shaft and are respectively connected with the corresponding first driven chain wheels through hinges; the two first driven chain wheels are fixedly connected with one side surface of the driving disc through a first connecting rod; one end of the second connecting rod is fixed with the other side face of the driving disc, the other end of the second connecting rod is rotatably connected with one end of the third connecting rod, the other end of the third connecting rod is fixedly connected with the fourth connecting rod, one end of the fourth connecting rod is fixed with the wing, and the other end of the fourth connecting rod is hinged with one end of the fifth connecting rod through a universal joint; the other end of the fifth connecting rod is fixedly connected with the driving cabin body;
a seat, an armrest and a pedal device are arranged in the cockpit; the tail part of the cabin body is provided with a tail wing, and the tail wing is connected with the handrail through a pull rod;
the pedal device comprises a second driving chain wheel, a second driven chain wheel and a pedal plate; a fixed rod is arranged in the middle of the second driving sprocket, and two ends of the fixed rod are respectively connected with a pedal through a crank; the second driven chain wheel is fixed on the transmission shaft, the second driving chain wheel is driven by stepping on a pedal, and the second driving chain wheel is driven by the chain wheel to rotate so as to drive the driving device to act;
the run-up device is mounted at the bottom of the cockpit;
the run-up device and the wing device are both driven by a motor.
According to the technical scheme, compared with the prior art, the invention discloses the flapping wing air vehicle with the gravity center below the two wings, the motor drives the first driving gear to rotate, and drives the first driven gear, the first driving chain wheel, the first driven chain wheel, the first connecting rod and the driving disk which are meshed with the first driving gear to move; further, the second connecting rod, the third connecting rod and the fourth connecting rod are driven to enable the wing device to generate periodic flapping actions; lift force is continuously provided in the flying process, and the flying efficiency is improved; when the low high volume of power of motor was not enough, the running-board was stepped on in the accessible manpower, drives drive assembly and coupling assembling through second drive sprocket and second driven sprocket and continues the action, carries out safe descending, further promotes the factor of safety of aircraft.
Preferably, in the flapping wing aircraft with the gravity center below the two wings, the third connecting rod is an electric push rod, and a battery is installed; by adopting the scheme, the attack angle can be further increased within the range of the maximum value of the lift coefficient, so that the lift is further improved.
Preferably, in the flapping wing aircraft with the center of gravity below the two wings, the wings are asymmetric wing type, the top is convex, and the bottom is concave; the scheme is adopted as a preferred embodiment for increasing the flight lift of the wing.
Preferably, in an ornithopter of the above kind having a centre of gravity below two wings, the wings are rotor mechanisms; by adopting the scheme, the rotor wing is combined on the basis of flapping wing flight, the flight effect is enhanced, and the flight capability of the aircraft is further improved.
Preferably, in an above-described ornithopter having a center of gravity below both wings, the rotor mechanism comprises a mounting shaft and a rotor; the mounting shaft is perpendicular to the plane of the machine body and is fixed at one end of the fourth connecting rod, and the rotor wing is rotatably connected with the mounting shaft; the scheme is adopted as a preferred embodiment for increasing the flight lift of the wing.
Preferably, in the flapping wing aircraft with the center of gravity below the two wings, the mounting shaft is sleeved with a bearing, and the wing pieces of the rotor wings are fixedly connected with the bearing.
Preferably, in the flapping wing aircraft with the center of gravity below the two wings, the plurality of wings are arranged, and the plurality of wings are distributed in a clockwise or anticlockwise array by taking the axis of the mounting shaft as the center; by adopting the scheme, the rotation direction of the front edge is consistent when the wing panel rotates, the rotation direction of the wing panel of the rotor wing can be kept unchanged in the complete flapping process, the lift force is always provided, and the flying efficiency is improved.
Preferably, in the flapping wing aircraft with the center of gravity below the two wings, the wings of the rotor wing are of a biconvex wing type, and the radian of the bottom part is smaller than or equal to that of the top part; this solution is a preferred embodiment for increasing the wing flight lift.
Preferably, in the flapping wing aircraft with the gravity center below the two wings, the motor adopts a servo motor or a steering engine; by adopting the scheme, the control and the regulation of the action frequency of the aircraft wing are facilitated, and the safety is higher.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, it is obvious that the drawings in the following description are only embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to the provided drawings without creative efforts.
FIG. 1 is a schematic diagram of the structure of one embodiment of the present invention;
FIG. 2 is a schematic diagram of the structure of one embodiment of the present invention;
FIG. 3 is a schematic view of the drive mechanism of the present invention;
FIG. 4 is a schematic view of a wing embodiment of the present invention coupled to a drive mechanism;
FIG. 5 is a schematic view of a wing embodiment of the present invention coupled to a drive mechanism; (ii) a
FIG. 6 is a force analysis diagram of the flapping process of the wing of the present invention;
FIG. 7 is a force analysis graph of the wing lift-back process of the present invention;
FIG. 8 is a graph illustrating force analysis of flapping of a rotor wing according to the present invention;
fig. 9 is a force analysis diagram of the lift-back process of the rotor wing panel according to the present invention.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
In the description of the present invention, it is to be understood that the terms "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate orientations or positional relationships based on those shown in the drawings, and are only for convenience of description and simplicity of description, but do not indicate or imply that the referenced devices or elements must have a particular orientation, be constructed and operated in a particular orientation, and thus, are not to be construed as limiting the present invention.
In the present invention, unless otherwise expressly stated or limited, the terms "mounted," "connected," "secured," and the like are to be construed broadly and can, for example, be fixedly connected, detachably connected, or integrally formed; can be mechanically or electrically connected; either directly or indirectly through intervening media, either internally or in any other relationship. The specific meanings of the above terms in the present invention can be understood by those skilled in the art according to specific situations.
Referring to the drawings, fig. 1-2 show an ornithopter of the present invention with a center of gravity below two wings, comprising:
wing means, cockpit 1 and run-up means 5;
the wing device is arranged at the top of the cockpit 1 and comprises a driving cabin body 3, a driving assembly 2 and wings 4; the driving assembly 2 is arranged in the driving cabin 3, and the wings 4 are arranged on the outer side of the driving cabin 2;
the driving assembly comprises a driving gear 200, a driven gear 201, a first transmission shaft 21, a first driving sprocket 220, a first driven sprocket 221, a first connecting rod 23, a driving disc 24, a second connecting rod 25, a third connecting rod 26, a fourth connecting rod 27 and a fifth connecting rod 28; the driving gear 200 is engaged with a driven gear 201, the driven gear 201 is mounted on the first transmission shaft 21, and two first driving sprockets 220 are mounted at two ends of the first transmission shaft 21 and respectively connected with corresponding first driven sprockets 221 through hinges; two first driven chain wheels 221 are fixedly connected with one side surface of a driving disc 24 through a first connecting rod 23; one end of the second connecting rod 25 is fixed with the other side surface of the driving disc 24, the other end of the second connecting rod is rotatably connected with one end of the third connecting rod 26, the other end of the third connecting rod 26 is fixedly connected with the fourth connecting rod 27, one end of the fourth connecting rod 27 is fixed with the wing 4, and the other end of the fourth connecting rod 27 is hinged with one end of the fifth connecting rod 28 through a universal joint; the other end of the fifth connecting rod 28 is fixedly connected with the driving cabin 3;
a seat, an armrest and a pedal device are arranged in the cockpit 1; the tail part of the cabin body is provided with a tail wing 10, and the tail wing 10 is connected with the handrail through a pull rod;
the pedal device includes a pedal plate 12, a second driving sprocket 110, a second driven sprocket 111, a second transmission shaft 13, a third driving sprocket 140, and a third driven sprocket 141; a fixed rod is arranged in the middle of the second driving sprocket 110, and two ends of the fixed rod are respectively connected with the pedal 12 through cranks; the second driven sprocket 111 is fixed on the second transmission shaft 13, the second transmission shaft 13 is also fixed with a third driving sprocket 140, the third driven sprocket 141 is fixed on the first transmission shaft 21, and the second driving sprocket 110 and the second driven sprocket 111, and the third driving sprocket 140 and the third driven sprocket 141 are all driven by sprockets; the second driving sprocket 110 is driven by stepping on the pedal 12, and the second driven sprocket 111, the third driving sprocket 140 and the corresponding third driven sprocket 141 are driven by the sprockets to rotate, so as to drive the wings 4 to move;
the run-up device 5 is arranged at the bottom of the cockpit 1;
both the run-up device 5 and the wing device are driven by a motor.
The principle of the invention is as follows: when the electric energy is used for supplying power, the output shaft of the motor drives the driving gear 200 to rotate, drives the driven gear 201 and the first transmission shaft 21 to rotate, further drives the first driving sprocket 220 and the first driven sprocket to act, and drives the driving disc 24 to rotate in a circular motion manner through the first connecting rod 23, so that the second connecting rod 25 moves along with the driving disc 24; because one end of the third connecting rod 26 is rotatably connected with the second connecting rod 25, the angle and the position of the third connecting rod 26 are periodically changed under the pulling of the second connecting rod 25, the third connecting rod 26 is fixedly connected with the fourth connecting rod 27, the wing 4 is fixedly connected with one end of the fourth connecting rod 27, the other end of the fourth connecting rod 27 is connected with one end of the fifth connecting rod 28 through a universal joint, the fifth connecting rod 28 is fixed on the driving cabin, and the wing 4 realizes the periodic angle change and completes the flapping action under the driving of the steering engine;
when the electric energy is insufficient, the driver drives the second driven sprocket 110 and the second driven sprocket 111 to rotate through the pedal 12, the third driving sprocket 140 and the third driven sprocket 141 synchronously rotate under the driving of the second transmission shaft 13, and the first transmission shaft 21 is driven to rotate through the second driven sprocket 141, so that the flapping motion under the state of electric energy driving is repeated.
Referring to fig. 1, 3 and 4, in an embodiment of the present invention, the third link 26 is an electric push rod and is provided with a battery;
specifically, the wing 4 is an asymmetric airfoil, the top of which is convex and the bottom of which is concave.
In the flying process, the wings lift back from the lowest point to the highest point; the electric push rod extends to further increase the attack angle of the wing, so that the attack angle of the wing is increased within the range of the maximum value of the lift coefficient, the lift force of the wing in the rising process is further increased according to the rule that the attack angle of the wing is before the maximum value of the lift coefficient and the lift force is increased along with the increase of the attack angle, and the flight capability of the flight mechanism is further enhanced;
referring to fig. 6-7, an analysis view of the wing stress according to an embodiment of the present invention is shown; the invention needs to be installed on an aircraft provided with a run-up device for use, and the run-up device is started to enable the front edge of the wing to have a forward speed V0The steering engine starts to rotate;
in the process of flapping the wings from the highest point to the lowest point; the wings flap downwards to make the rotor blades have a downward speed V1Producing a resultant velocity V in a downward slantCombination of Chinese herbsAnd produce andVcombination of Chinese herbsVertical lifting force FLifting of wine，FLifting of wineIs directed over the wing at a velocity V0Under the condition of no change; the lower flapping speed of the wings from the highest point to the lowest point is gradually reduced after being gradually increased, and F can be obtainedLifting of wineGradually increasing and then gradually decreasing, but always present;
in the process of the back lifting movement of the wing from the lowest point to the highest point; making the rotor blades have an upward speed V1Producing a resultant velocity V in an oblique upward directionCombination of Chinese herbsAnd generating a sum VCombination of Chinese herbsVertical lifting force FLifting of wine，FLifting of wineIs directed over the wing at a velocity V0Under the condition of no change; the echo speed of the wing from the lowest point to the highest point is gradually reduced after being gradually increased, and F can be obtainedLifting of wineGradually increasing and then gradually decreasing, but always present;
in the embodiment, the rotor wing lifts from the lowest point to the highest point; the electric push rod extends to further increase the attack angle of the rotor blade, so that the attack angle of the blade is increased within the range of the maximum value of the lift coefficient, the lift force of the blade in the lift return process is further increased by following the rule that the attack angle of the wing is before the maximum value of the lift coefficient and the lift force is increased along with the increase of the attack angle, and the flight capability of the flight mechanism is further enhanced.
Therefore, lift force is always generated in the whole movement process of the wings, and the flight of the airplane is ensured.
Referring to fig. 2, 3 and 5, in another embodiment of the present invention, the third link 26 is an electric push rod and is provided with a battery;
the wing 4 is a rotor mechanism.
Specifically, the rotor mechanism includes a mounting shaft 40 and rotor blades 41; the mounting shaft 40 is perpendicular to the plane of the fourth link 15 and the fuselage, and is fixed at the other end of the fourth link 15, and the rotor blade 41 is rotatably connected to the mounting shaft 40.
Specifically, the mounting shaft 40 is sleeved with a bearing, and the rotor blade 41 is fixedly connected with the bearing.
Specifically, the rotor blades 41 are provided with a plurality of pieces, and the plurality of rotor blades 41 are distributed in a clockwise or counterclockwise array with the axis of the mounting shaft 40 as the center;
When flapping is carried out on the basis of the flapping wings, the rotor wing is combined to move along with the flapping motion, so that the blades of the rotor wing are driven to rotate, lift force is generated, and the flying capability is enhanced.
Specifically, the electric push rod comprises a motor, a gear set, a lead screw assembly, a push rod and a push rod shell; the power supply, the motor, the gear set, the screw rod assembly and the push rod are all installed in the push rod shell, the motor is connected with a screw rod of the screw rod assembly through the gear set, a screw rod nut of the screw rod assembly is connected with one end of the push rod, the other end of the push rod is connected with the wing 4, the screw rod nut seat of the screw rod assembly reciprocates by driving the screw rod to convert the motor rotation into linear movement, so that the angle of attack of the wing is changed in the motion process of the wing, and the effect of lifting force is achieved.
Referring to FIGS. 8-9, which are graphs of stress analysis of rotor blades according to the present invention, stress analysis is performed using the highest point of the wing 4 as the starting point, and the present invention is installed on an aircraft equipped with a run-up device, wherein the run-up device is first started to make the leading edge of the wing have a forward speed V0The steering engine starts to rotate;
in the process of flapping the wings from the highest point to the lowest point; the wings flap downwards to make the rotor blades have a downward speed V1Producing a resultant velocity V in a downward slantCombination of Chinese herbsAnd generating a sum VCombination of Chinese herbsVertical lifting force FLifting of wine，FLifting of wineIs directed over the wing at a velocity V0Under the condition of no change; the lower flapping speed of the wings from the highest point to the lowest point is gradually reduced after being gradually increased, and F can be obtainedLifting of wineGradually increasing and then gradually decreasing, but always present;
in the process of the back lifting movement of the wing from the lowest point to the highest point; making the rotor blades have an upward speed V1Producing a resultant velocity V in an oblique upward directionCombination of Chinese herbsAnd generating a sum VCombination of Chinese herbsVertical lifting force FLifting of wine，FLifting of wineIs directed above the wing, inVelocity V0Under the condition of no change; the echo speed of the wing from the lowest point to the highest point is gradually reduced after being gradually increased, and F can be obtainedLifting of wineGradually increasing and then gradually decreasing, but always present;
therefore, lift force is always generated in the whole movement process of the wings, and the flight of the airplane is ensured.
In some embodiments of the invention, the components within the wing assembly are made of carbon fiber composite material.
Specifically, the asymmetric airfoil model is as follows: AH79-100B, AH79-100C, BE6356 or BE 8356.
Specifically, the symmetric airfoil type is as follows: NACA0012 or NACA 0016.
Specifically, the motor in the invention is a servo motor or a steering engine.
The embodiments in the present description are described in a progressive manner, each embodiment focuses on differences from other embodiments, and the same and similar parts among the embodiments are referred to each other. The device disclosed by the embodiment corresponds to the method disclosed by the embodiment, so that the description is simple, and the relevant points can be referred to the method part for description.
The previous description of the disclosed embodiments is provided to enable any person skilled in the art to make or use the present invention. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the generic principles defined herein may be applied to other embodiments without departing from the spirit or scope of the invention. Thus, the present invention is not intended to be limited to the embodiments shown herein but is to be accorded the widest scope consistent with the principles and novel features disclosed herein.
Claims (9)
1. An ornithopter with a centre of gravity below two wings, characterized by comprising a wing device, a cockpit (1) and a run-up device (5);
the wing device is arranged at the top of the cockpit (1) and comprises a driving cabin body (3), a driving assembly (2) and wings (4);
the drive assembly (2) is arranged in the drive cabin (3), and the wings (4) are arranged outside the drive cabin (2);
the driving assembly comprises a driving gear (200), a driven gear (201), a first transmission shaft (21), a first driving chain wheel (220), a first driven chain wheel (221), a first connecting rod (23), a driving disc (24), a second connecting rod (25), a third connecting rod (26), a fourth connecting rod (27) and a fifth connecting rod (28); the driving gear (200) is meshed with the driven gear (201), the driven gear (201) is installed on the first transmission shaft (21), and the two first driving chain wheels (220) are installed at two ends of the first transmission shaft (21) and are respectively connected with the corresponding first driven chain wheels (221) through hinges; the two first driven chain wheels (221) are fixedly connected with one side surface of the driving disc (24) through a first connecting rod (23); one end of the second connecting rod (25) is fixed with the other side face of the driving disc (24), the other end of the second connecting rod is rotatably connected with one end of the third connecting rod (26), the other end of the third connecting rod (26) is fixedly connected with the fourth connecting rod (27), one end of the fourth connecting rod (27) is fixed with the wing (4), and the other end of the fourth connecting rod is hinged with one end of the fifth connecting rod (28) through a universal joint; the other end of the fifth connecting rod (28) is fixedly connected with the driving cabin body (3);
a seat, an armrest and a pedal device are arranged in the cockpit (1); a tail wing (10) is arranged at the tail part of the cabin body, and the tail wing (10) is connected with the handrail through a pull rod;
the pedal device comprises a pedal plate (12), a second driving chain wheel (110), a second driven chain wheel (111), a second transmission shaft (13), a third driving chain wheel (140) and a third driven chain wheel (141); a fixed rod is arranged in the middle of the second driving chain wheel (110), and two ends of the fixed rod are respectively connected with the pedal (12) through a crank; the second driven sprocket (111) is fixed on the second transmission shaft (13), the third driving sprocket (140) is further fixed on the second transmission shaft (13), the third driven sprocket (141) is fixed on the first transmission shaft (21), and the second driving sprocket (110), the second driven sprocket (111), the third driving sprocket (140) and the third driven sprocket (141) are driven by sprockets; the second driving chain wheel (110) is driven by stepping on a pedal (12), and the second driven chain wheel (111), the third driving chain wheel (140) and the corresponding third driven chain wheel (141) are driven by the chain wheels to rotate, so that the wings (4) are driven to act;
the run-up device (5) is arranged at the bottom of the cockpit (1);
the run-up device (5) and the wing device are both driven by a motor.
2. The ornithopter of claim 1 wherein the third link (26) is a power push rod and is battery-powered.
3. An ornithopter with a centre of gravity below two wings according to claim 1 or 3, characterized in that the wings (4) are asymmetric and have a convex top and a concave bottom.
4. An ornithopter with a centre of gravity below two wings according to claim 1 or 2, characterised in that the wing (4) is a rotor mechanism.
5. The ornithopter with a center of gravity below two wings of claim 4, wherein the rotor mechanism comprises a mounting shaft (40) and a rotor (41); installation axle (40) and fuselage place plane are perpendicular, and fix the one end of fourth connecting rod (27), rotor (41) with installation axle (40) rotate and are connected.
6. The ornithopter with a center of gravity below two wings as claimed in claim 5, wherein said mounting shaft (40) is sleeved with a bearing, and the wings of said rotor (41) are fixedly connected with said bearing.
7. The ornithopter with a center of gravity below two wings as claimed in claim 6, wherein said fins are provided in a plurality of pieces and the plurality of pieces are arranged in a clockwise or counterclockwise array centered on the axis of said mounting shaft (40).
8. The ornithopter with a center of gravity below two wings of claim 7, wherein the wings of the rotor (41) are biconvex wing type, and the bottom arc is less than or equal to the top arc.
9. An ornithopter with a center of gravity below two wings as claimed in claim 8, wherein the motor is a servo motor or a steering engine.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011342097.6A CN112319792A (en) | 2020-11-26 | 2020-11-26 | Flapping wing aircraft with gravity center below two wings |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011342097.6A CN112319792A (en) | 2020-11-26 | 2020-11-26 | Flapping wing aircraft with gravity center below two wings |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN112319792A true CN112319792A (en) | 2021-02-05 |
Family
ID=74308333
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202011342097.6A Withdrawn CN112319792A (en) | 2020-11-26 | 2020-11-26 | Flapping wing aircraft with gravity center below two wings |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN112319792A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113340557A (en) * | 2021-05-31 | 2021-09-03 | 四川大学 | Water tunnel flow state observation test device for wing suction flow control |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR435141A (en) * | 1911-10-11 | 1912-02-22 | Gerhard Beer | Flying machine with flapping wings operated by pedals or motor |
| CN1239051A (en) * | 1998-06-12 | 1999-12-22 | 樊涛 | Ornithopter |
| CN109625263A (en) * | 2019-01-15 | 2019-04-16 | 成东明 | A kind of left and right wing can change the flapping wing mechanism and Manpower ornithopter of pitch angle automatically |
| CN110171568A (en) * | 2019-06-14 | 2019-08-27 | 山东大学 | One kind can hover flapping wing aircraft |
-
2020
- 2020-11-26 CN CN202011342097.6A patent/CN112319792A/en not_active Withdrawn
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR435141A (en) * | 1911-10-11 | 1912-02-22 | Gerhard Beer | Flying machine with flapping wings operated by pedals or motor |
| CN1239051A (en) * | 1998-06-12 | 1999-12-22 | 樊涛 | Ornithopter |
| CN109625263A (en) * | 2019-01-15 | 2019-04-16 | 成东明 | A kind of left and right wing can change the flapping wing mechanism and Manpower ornithopter of pitch angle automatically |
| CN110171568A (en) * | 2019-06-14 | 2019-08-27 | 山东大学 | One kind can hover flapping wing aircraft |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113340557A (en) * | 2021-05-31 | 2021-09-03 | 四川大学 | Water tunnel flow state observation test device for wing suction flow control |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN110091989A (en) | Imitative four wing micro flapping wing air vehicle of dragonfly | |
| CN110525647B (en) | A transmission mechanism suitable for a miniature quadruple flapping aircraft | |
| CN107662702B (en) | Hybrid power double-coaxial same-side reverse tilting rotor aircraft | |
| KR20110057414A (en) | Winged aircraft | |
| CN110104175A (en) | A kind of coaxial reversed pair is flutterred rotor mechanism | |
| CN108706100B (en) | Bird-like flapping-wing aircraft | |
| CN102249001B (en) | Flapping wing flight adopting compound flapping mode | |
| CN113619337A (en) | Vertical lifting flying vehicle | |
| US20190016453A1 (en) | Vertical take-off and landing (vtol) aircraft and a propulsion system for a vehicle vertical take-off and landing (vtol) | |
| CN112319792A (en) | Flapping wing aircraft with gravity center below two wings | |
| CN210063360U (en) | Bionic mechanical flapping wing machine | |
| CN202098551U (en) | Compound flapping type flapping-wing air vehicle | |
| CN110816827A (en) | A bionic butterfly flapping aircraft | |
| CN107662703B (en) | Electric double-coaxial same-side reverse tilting rotor aircraft | |
| TWI572526B (en) | Miniature aircraft wings drive structure | |
| CN214524392U (en) | Flapping wing aircraft with gravity center between two wings | |
| CN112319793A (en) | Flapping wing aircraft with wing pieces capable of adjusting attack angle | |
| CN112319801A (en) | Flapping-effect-based large high-mobility hovering flapping-wing aircraft | |
| CN112319794A (en) | Four-wing flapping wing aircraft capable of adjusting attack angle | |
| CN107284658B (en) | Composite vertical/short-distance take-off and landing aircraft | |
| CN101412441B (en) | Mini ornithopter | |
| CN215622682U (en) | Novel composite-configuration tilt rotorcraft | |
| CN112498680B (en) | Rotary blade machine | |
| CN214524389U (en) | Hybrid energy-saving four-wing flapping wing aircraft | |
| CN213921489U (en) | A bionic flapping aircraft imitating butterfly wings |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| WW01 | Invention patent application withdrawn after publication |
Application publication date: 20210205 |
|
| WW01 | Invention patent application withdrawn after publication |