CN214524389U - Hybrid energy-saving four-wing flapping wing aircraft - Google Patents

Hybrid energy-saving four-wing flapping wing aircraft Download PDF

Info

Publication number
CN214524389U
CN214524389U CN202022764780.0U CN202022764780U CN214524389U CN 214524389 U CN214524389 U CN 214524389U CN 202022764780 U CN202022764780 U CN 202022764780U CN 214524389 U CN214524389 U CN 214524389U
Authority
CN
China
Prior art keywords
wing
connecting rod
saving
hybrid energy
driving
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.)
Active
Application number
CN202022764780.0U
Other languages
Chinese (zh)
Inventor
王志成
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Guangdong Guoshijian Technology Development Co Ltd
Original Assignee
Guangdong Guoshijian Technology Development Co Ltd
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Guangdong Guoshijian Technology Development Co Ltd filed Critical Guangdong Guoshijian Technology Development Co Ltd
Priority to CN202022764780.0U priority Critical patent/CN214524389U/en
Application granted granted Critical
Publication of CN214524389U publication Critical patent/CN214524389U/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Images

Classifications

    • 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
    • Y02T50/50—On board measures aiming to increase energy efficiency
    • 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

  • Toys (AREA)

Abstract

The utility model discloses a mix energy-conserving four wings flapping wing aircraft that moves, include: a fuselage, a wing device, a run-up device, a motor, and a battery; the running-up device is arranged on the lower side of the machine body; the four groups of wing devices are arranged on two sides of the fuselage, the wing devices and the run-up device are driven by motors, and the motors are powered by batteries; the surface of the machine body is provided with a solar panel; the solar panel is connected with the battery; the utility model discloses a flapping wing flight mode, the flight of imitation birds, the diagonal angle wing links, can effectively promote flight stability, reduces the drop of flapping wing flight orbit, adopts battery powered to set up solar cell panel and carried out the electric power and supply, improved the duration of aircraft, guarantee the stable flight of aircraft, improve the flight distance.

Description

Hybrid energy-saving four-wing flapping wing aircraft
Technical Field
The utility model relates to an aircraft technical field, more specifically the four-wing flapping wing aircraft that says so relates to a thoughtlessly move energy-conservation.
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. And the endurance is deficient, so it is necessary to provide a flapping wing aircraft with simple structure, high flying efficiency and good maneuvering performance.
Therefore, how to provide an ornithopter with simple structure and stable flight is a problem which needs to be solved urgently by the technical personnel in the field.
SUMMERY OF THE UTILITY MODEL
The utility model discloses aim at solving one of the above-mentioned technical problem among the prior art to a certain extent at least.
In view of this, the utility model provides a mix energy-conserving four wings flapping wing aircraft, its flapping wing structure of diagonal angle linkage has effectively reduced the drop of flapping wing flight, makes the flight more steady to installed solar cell panel, can carry out the electric power and supply, improve duration, extension flying distance.
In order to achieve the above purpose, the utility model adopts the following technical scheme:
a hybrid energy-saving four-wing flapping wing aircraft with an auxiliary lifting device comprises: a fuselage, a wing device, a run-up device, a motor, and a battery; the running-up device is arranged on the lower side of the machine body; the four groups of wing devices are arranged on two sides of the fuselage, the wing devices and the run-up device are driven by motors, and the motors are powered by batteries;
the surface of the machine body is provided with a solar panel; the solar panel is connected with the battery;
the wing device comprises a driving assembly, a connecting assembly and a wing;
the driving assembly comprises a driving disc, a first connecting rod and a second connecting rod; the motor spindle is fixedly connected with one side surface of the driving disc, one end of the first connecting rod is fixed on the other side surface of the driving disc, and the other end of the first connecting rod is hinged with one end of the second connecting rod;
the connecting assembly comprises a third connecting rod and a fourth connecting rod; one end of the third connecting rod is fixedly connected with the machine body, the other end of the third connecting rod is hinged with one end of the fourth connecting rod through a universal joint, and the other end of the second connecting rod is fixed with the fourth connecting rod;
the wing is fixedly connected with the other end of the fourth connecting rod.
According to the technical scheme, compared with the prior art, the utility model discloses a hybrid energy-saving four-wing flapping wing aircraft, a motor drives a driving disc to rotate and drives a first connecting rod to rotate along with the driving disc; one end of the second connecting rod is rotatably connected with the first connecting rod; the other end of the solar energy power generation device is fixed with the fourth connecting rod, the second connecting rod and the fourth connecting rod can be pulled through the first connecting rod, the fourth connecting rod is fixedly connected with the second connecting rod, the angle of the second connecting rod is periodically changed under the pulling of the first connecting rod, the wing flaps like wings, the lift force is continuously provided in the flying process, the flying efficiency is improved, the solar cell panel is additionally arranged to assist in charging the battery, the cruising ability is improved, and the flying distance is prolonged.
Preferably, in the hybrid energy-saving four-wing flapping wing aircraft, an output shaft of the motor is connected with a driving gear, a driven gear is engaged with the driving gear and is fixed with a rotating shaft, two ends of the rotating shaft are respectively fixed with a driving sprocket, and two driven sprockets are respectively connected with the two driving sprockets through chains and are respectively fixedly connected with the driving discs arranged at the opposite corners of the aircraft body; synchronizing the motion of diagonally disposed wing devices; the scheme links the opposite-angle flapping wings, and reduces the flying fall of the flapping wings by adjusting the phases of the two opposite-angle flapping wing groups, so that the flying is more stable.
Preferably, in the hybrid energy-saving four-wing flapping wing aircraft, the second connecting rod is an electric push rod, and a power supply is installed.
Preferably, in the hybrid energy-saving four-wing flapping wing aircraft, a solar panel is arranged on the surface of each wing blade and connected with the battery; by adopting the scheme, the auxiliary charging can be carried out on the battery, the cruising ability of the aircraft is improved, and the flying distance is prolonged.
Preferably, in the hybrid power-saving four-wing ornithopter, the battery is provided with a spare set; by adopting the scheme, emergency power supply can be carried out when the power supply battery fails, and the safety of flight is improved.
Preferably, in the hybrid energy-saving four-wing flapping wing aircraft, the wing blades are asymmetric wing-shaped, the top of the wing blades is convex, and the bottom of the wing blades is concave; the scheme is adopted as a preferred embodiment for increasing the flight lift of the wing.
Preferably, in the hybrid energy-saving four-wing ornithopter, the wings are rotor wing 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 the hybrid energy-saving four-wing ornithopter, the rotor mechanism comprises a mounting shaft and rotor blades; the mounting shaft is perpendicular to the plane of the fourth connecting rod and the plane of the machine body and is fixed at the other end of the fourth connecting rod, and the rotor blade 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 hybrid energy-saving four-wing flapping wing aircraft, a bearing is sleeved on the mounting shaft, and the rotor blades are fixedly connected with the bearing.
Preferably, in the hybrid energy-saving four-wing flapping wing aircraft, the rotor blades are provided with a plurality of pieces, and the plurality of pieces of rotor blades are distributed in a clockwise or counterclockwise array by taking the axis of the mounting shaft as a center;
the rotor blades are symmetrical wing-shaped; the scheme is an optimal implementation mode for increasing the flying lift of the wing, the rotation direction of the front edge can be consistent when the blades rotate, the rotation direction of the rotor blades can be kept unchanged in the complete flapping process, the lift is always provided, and the flying efficiency is improved.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required to be 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 one embodiment of the present invention;
FIG. 2 is a schematic diagram of one embodiment of the present invention;
FIG. 3 is a schematic diagram of a wing assembly according to one embodiment of the present invention;
FIG. 4 is a schematic diagram of a wing assembly according to one embodiment of the present invention;
FIG. 5 is a schematic view of a transmission structure of the wing device of the present invention;
FIG. 6 is a force analysis diagram of the flapping process of the wing of the utility model;
FIG. 7 is a force analysis diagram of the wing lifting process of the present invention;
FIG. 8 is a force analysis diagram of a flapping process of a rotor blade according to the present invention;
figure 9 attached figure is the utility model discloses rotor blade rises back stress analysis chart of process.
Detailed Description
The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative work belong to 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", and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, and are only for convenience of description and simplicity of description, and do not indicate or imply that the device or element referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore, should not be construed as limiting the present invention.
In the present invention, unless otherwise expressly stated or limited, the terms "mounted," "connected," and "fixed" are to be construed broadly and may, 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 meaning of the above terms in the present invention can be understood according to specific situations by those skilled in the art.
Referring to the attached drawings, fig. 1-2 show a hybrid energy-saving four-wing flapping wing aircraft, comprising: the device comprises a fuselage 2, a wing device 1, a run-up device 3, a motor and a battery; the running-in device 3 with the empennage 20 arranged on the fuselage 2 is arranged on the lower side of the fuselage 2; the four sets of wing devices are arranged on two sides of the fuselage 2, the wing devices 1 and the run-up device 3 are driven by motors, and the motors are powered by batteries;
the surface of the blade of the machine body 2 is provided with a solar panel; the solar panel is connected with the battery;
the wing device 1 comprises a driving assembly, a connecting assembly and a wing;
the driving assembly comprises a driving disc 11, a first connecting rod 12 and a second connecting rod 13; a main shaft of the motor 10 is fixedly connected with one side surface of the driving disc 11, one end of a first connecting rod 12 is fixed on the other side surface of the driving disc 11, and the other end of the first connecting rod is hinged with one end of a second connecting rod 13;
the connecting assembly comprises a third connecting rod 14 and a fourth connecting rod 15; one end of a third connecting rod 14 is fixedly connected with the machine body 2, the other end of the third connecting rod is hinged with one end of a fourth connecting rod 15 through a universal joint, and the other end of the second connecting rod 13 is fixed with the fourth connecting rod 15;
the wing 16 is fixedly connected with the other end of the fourth connecting rod 15.
The principle of the utility model is that: an output shaft of the steering engine or the servo motor drives the driving disc 11 to rotate in a circular motion manner and drives the first connecting rod 12 to move along with the driving disc 11; one end of a second connecting rod 13 is rotatably connected with the first connecting rod 12, the second connecting rod 13 is pulled by the first connecting rod 12 to periodically change with the angle and the position of the second connecting rod, a fourth connecting rod 15 is fixedly connected with the second connecting rod 13, the wings 16 are fixedly connected with the fourth connecting rod 15, the fourth connecting rod 15 is connected with a third connecting rod 14 through a universal joint, the third connecting rod 14 is fixed on the machine body, and the wings 16 realize the periodic change of the angle and complete the flapping action under the driving of a steering engine;
the solar cell panel is additionally arranged, so that the battery can be charged in a sunshine environment, and the cruising ability is improved.
Referring to fig. 1, 3 and 5, the second connecting rod 13 is an electric push rod and is provided with a battery;
specifically, an output shaft of the motor 10 is connected with a driving gear 190, a driven gear 191 is meshed with the driving gear 190 and is fixed with a rotating shaft, driving sprockets 192 are respectively fixed at two ends of the rotating shaft, and two driven sprockets 193 are respectively connected with the two driving sprockets 192 through chains and are respectively fixedly connected with driving discs 11 arranged at diagonal positions of the machine body 2; the diagonally arranged wing arrangements 1 are synchronised to act.
Specifically, the flight paths of the wing devices 1 forming the diagonal linkage are substantially 90 degrees out of phase.
Specifically, the second connecting rod is an electric push rod and is provided with a power supply.
Specifically, the surface of the blade of the wing 16 is provided with a solar panel and is connected with a battery.
Specifically, the battery is provided with a backup pack.
Specifically, the airfoil 16 is an asymmetric airfoil, with a convex top and a concave bottom.
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;
the opposite angle wing devices are linked, and the phase difference of the flight tracks is adjusted, so that the flying fall of the flapping wings is reduced, and the flying is more stable and safe.
Refer to fig. 6-7, which are graphs for analyzing the force applied to the wings according to the embodiment of the present invention; using the wing 16 as the starting point for the stress analysis, the utility model discloses need to install the use on the aircraft that is equipped with the run-up device, at first the run-up device starts to make the wing leading edge possess 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 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, 4 and 5, in another embodiment of the present invention, the second connecting rod 13 is an electric push rod and is provided with a battery;
specifically, an output shaft of the motor 10 is connected with a driving gear 190, a driven gear 191 is meshed with the driving gear 190 and is fixed with a rotating shaft, driving sprockets 192 are respectively fixed at two ends of the rotating shaft, and two driven sprockets 193 are respectively connected with the two driving sprockets 192 through chains and are respectively fixedly connected with driving discs 11 arranged at diagonal positions of the machine body 2; the diagonally arranged wing arrangements 1 are synchronised to act.
Specifically, the flight paths of the wing devices 1 forming the diagonal linkage are substantially 90 degrees out of phase.
Specifically, the second connecting rod is an electric push rod and is provided with a power supply.
Specifically, the surface of the blade of the wing 16 is provided with a solar panel and is connected with a battery.
Specifically, the battery is provided with a backup pack.
The wing 16 is a rotor mechanism.
Specifically, the rotor mechanism includes a mounting shaft 17 and rotor blades 18; the mounting shaft 17 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 18 is rotatably connected with the mounting shaft 17.
Specifically, the mounting shaft 17 is sleeved with a bearing, and the rotor blade 18 is fixedly connected with the bearing.
Specifically, the rotor blades 18 are provided with a plurality of pieces, and the rotor blades 18 are distributed in a clockwise or counterclockwise array by taking the axis of the mounting shaft 17 as a center;
rotor blades 18 are symmetrical airfoils.
When flapping is carried out on the basis of the flapping wings, the rotor wings are combined, so that the rotor wings move along with the flapping motion, the rotor wing blades 18 are driven to rotate, the lift force is generated, and the flight 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 16, 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 the attached drawings 8-9, for the rotor blade stress analysis chart of the present invention, the maximum position of the wing 16 is used as the initial point for stress analysis, the present invention needs to be installed on an aircraft with a run-up device, and the run-up device is first started to make the front 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;
at the lowest part of the wingDuring the rising movement from the 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;
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 present invention, each component in the wing device 1 is made of carbon fiber composite material.
Specifically, the asymmetric irregular type number is as follows: AH79-100B, AH79-100C, BE6356 or BE 8356.
Specifically, the symmetric irregular models are as follows: NACA0012 or NACA 0016.
Specifically, the motor 10 in the present 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 (10)

1. A hybrid energy-saving four-wing ornithopter comprises: the device comprises a fuselage (2), a wing device (1), a run-up device (3), a motor and a battery; the running-up device (3) is arranged on the lower side of the machine body (2); four groups of wing devices (1) are arranged at two sides of the fuselage (2), the wing devices (1) and the run-up device (3) are driven by motors, and a plurality of motors are powered by batteries,
the surface of the machine body (2) is provided with a solar panel; the solar panel is connected with the battery;
the wing device (1) comprises a driving assembly, a connecting assembly and a wing;
the driving assembly comprises a driving disc (11), a first connecting rod (12) and a second connecting rod (13); a main shaft of the motor (10) is fixedly connected with one side surface of the driving disc (11), one end of the first connecting rod (12) is fixed on the other side surface of the driving disc (11), and the other end of the first connecting rod is hinged with one end of the second connecting rod (13);
the connecting assembly comprises a third link (14) and a fourth link (15); one end of the third connecting rod (14) is fixedly connected with the machine body (2), the other end of the third connecting rod is hinged with one end of the fourth connecting rod (15) through a universal joint, and the other end of the second connecting rod (13) is fixed with the fourth connecting rod (15);
the wing (16) is fixedly connected with the other end of the fourth connecting rod (15).
2. The hybrid energy-saving four-wing ornithopter according to claim 1, wherein the output shaft of the motor (10) is connected with a driving gear (190), a driven gear (191) is meshed with the driving gear (190) and is fixed with a rotating shaft, two ends of the rotating shaft are respectively fixed with a driving sprocket (192), two driven sprockets (193) are respectively connected with the two driving sprockets (192) through chains and are respectively fixedly connected with the driving discs (11) arranged at the diagonal positions of the fuselage (2); the diagonally arranged wing devices (1) are synchronized in their action.
3. The hybrid energy-saving four-wing ornithopter according to claim 2, wherein the second connecting rod (13) is an electric push rod and is provided with a power supply.
4. The hybrid energy-saving four-wing ornithopter according to claim 1 or 3, wherein the surface of the wing (16) is provided with a solar panel and the battery is connected.
5. The hybrid energy efficient four-wing ornithopter of claim 1, wherein the battery is provided with a backup pack.
6. The hybrid energy-saving four-wing ornithopter of claim 5, wherein the wing blades are asymmetric, and have a convex top and a concave bottom.
7. The hybrid energy-saving four-wing ornithopter according to claim 1 or 3, wherein the wing (16) is a rotor mechanism.
8. The hybrid energy-saving four-wing ornithopter according to claim 7, wherein the rotor mechanism comprises a mounting shaft (17) and rotor blades (18); installation axle (17) with fourth connecting rod (15) and fuselage place plane are perpendicular, and fix the other end of fourth connecting rod (15), rotor blade (18) with installation axle (17) rotate and are connected.
9. The hybrid energy-saving four-wing ornithopter according to claim 8, wherein the mounting shaft (17) is sleeved with a bearing, and the rotor blades (18) are fixedly connected with the bearing.
10. The hybrid energy-saving four-wing ornithopter according to claim 9, wherein the blades are provided with a plurality of pieces, and the plurality of pieces are distributed in a clockwise or counterclockwise array around the axis of the mounting shaft (17);
the rotor blades (18) are symmetrical wing-shaped.
CN202022764780.0U 2020-11-26 2020-11-26 Hybrid energy-saving four-wing flapping wing aircraft Active CN214524389U (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN202022764780.0U CN214524389U (en) 2020-11-26 2020-11-26 Hybrid energy-saving four-wing flapping wing aircraft

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN202022764780.0U CN214524389U (en) 2020-11-26 2020-11-26 Hybrid energy-saving four-wing flapping wing aircraft

Publications (1)

Publication Number Publication Date
CN214524389U true CN214524389U (en) 2021-10-29

Family

ID=78289242

Family Applications (1)

Application Number Title Priority Date Filing Date
CN202022764780.0U Active CN214524389U (en) 2020-11-26 2020-11-26 Hybrid energy-saving four-wing flapping wing aircraft

Country Status (1)

Country Link
CN (1) CN214524389U (en)

Similar Documents

Publication Publication Date Title
CN106927030B (en) Oil-electricity hybrid power multi-rotor aircraft and flight control method thereof
EP2551190B1 (en) Convertiplane
US20130026304A1 (en) Convertiplane
CN107662702B (en) Hybrid power double-coaxial same-side reverse tilting rotor aircraft
CN112810811B (en) Double-rotor unmanned aerial vehicle
CN207374648U (en) The double coaxial homonymy reversion tiltrotor aircrafts of hybrid power
CN107352030B (en) Micro flapping rotor wing aircraft with double wings flapping differentially
CN204037909U (en) Flapping-wing aircraft
CN103569360B (en) Translation flapping wing mechanism and flapping-wing aircraft and the aerodone with translation flapping wing mechanism
CN112046745B (en) Portable modularization unmanned aerial vehicle platform
WO2019212744A1 (en) Aircraft
CN107662703B (en) Electric double-coaxial same-side reverse tilting rotor aircraft
CN214524389U (en) Hybrid energy-saving four-wing flapping wing aircraft
CN112141332A (en) Five pole flapping wing aircraft in space based on just gentle coupling
CN112319794A (en) Four-wing flapping wing aircraft capable of adjusting attack angle
CN112441229A (en) Flapping rotor wing device with upward shaft wing capable of vertically running and downward horizontally running
CN109850144B (en) Solar flapping wing bionic aircraft
CN209305857U (en) Fixed-wing electric airplane co-axial contra rotating propeller dynamical system and fixed-wing electric airplane
CN112319793A (en) Flapping wing aircraft with wing pieces capable of adjusting attack angle
CN115973414A (en) Miniature flapping wing aircraft based on cross tail control
CN217893226U (en) Six-rotor electric vertical take-off and landing aircraft
CN112278261A (en) Hybrid energy-saving four-wing flapping wing aircraft with auxiliary lifting device
CN114435590B (en) Variable-incidence-angle ornithopter with wing rotation function
CN112319792A (en) Flapping wing aircraft with gravity center below two wings
CN114394232B (en) Flapping wing-flapping rotor wing multi-flight mode bionic aircraft

Legal Events

Date Code Title Description
GR01 Patent grant
GR01 Patent grant