CN112319793A - Flapping wing aircraft with wing pieces capable of adjusting attack angle - Google Patents
Flapping wing aircraft with wing pieces capable of adjusting attack angle Download PDFInfo
- Publication number
- CN112319793A CN112319793A CN202011342098.0A CN202011342098A CN112319793A CN 112319793 A CN112319793 A CN 112319793A CN 202011342098 A CN202011342098 A CN 202011342098A CN 112319793 A CN112319793 A CN 112319793A
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- CN
- China
- Prior art keywords
- wing
- connecting rod
- ornithopter
- adjustable
- rotor
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- 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.)
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Classifications
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- 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
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/32—Rotors
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C33/00—Ornithopters
- B64C33/02—Wings; Actuating mechanisms therefor
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plant in aircraft; Aircraft characterised thereby
- B64D27/02—Aircraft characterised by the type or position of power plant
- B64D27/24—Aircraft characterised by the type or position of power plant using steam, electricity, or spring force
Abstract
The invention discloses an ornithopter with adjustable attack angle of wing plates, which comprises: a fuselage, a wing device, a run-up device, a motor, and a battery; the tail part of the machine body is provided with a tail wing; the running-up device is arranged on the lower side of the machine body; two sets of the wing device is installed the fuselage both sides, the wing device with the run-up device passes through battery powered by motor drive, and a plurality of motors pass through battery powered, and wherein the wing device adopts the flapping wing form, and the flight of imitation birds to combine together with the rotor on this basis, it is rotatory to drive the rotor wing piece when actuating mechanism carries out the flapping, and the wing piece direction of rotation is the same when flapping down and rising back, provides continuous stable lift, guarantees the stable flight of aircraft, improves flight efficiency.
Description
Technical Field
The invention relates to the technical field of aircrafts, in particular to an ornithopter with adjustable attack angle 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. Therefore, it is necessary to provide an ornithopter with simple structure, high flying efficiency and good maneuverability
Therefore, how to provide an ornithopter with simple structure and high flying efficiency 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 invention provides an ornithopter with wings capable of adjusting an attack angle, which has a simple structure and ornithopter flight capability, and under the premise of ornithopter flight, the rotor wing is used as a wing to drive the rotor wing to flap, so that the flight capability is further improved, and the flight effect is better.
In order to achieve the purpose, the invention adopts the following technical scheme:
an ornithopter with adjustable angle of attack wings, comprising: a fuselage, a wing device, a run-up device, a motor, and a battery; the tail part of the machine body is provided with a tail wing; the running-up device is arranged on the lower side of the machine body; the two groups of wing devices are arranged on two sides of the fuselage, the wing devices and the run-up device are driven by motors, the motors are powered by batteries, and each 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 invention discloses the flapping wing air vehicle with the wing plates capable of adjusting the attack angle, wherein the motor drives the driving disc to rotate and drives the 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 first connecting rod 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 wings flap like wings, the lift force is continuously provided in the flying process, the flying efficiency is improved, and the flapping wings are combined with the rotors through the installation of the rotors, so that the flying capacity of the aircraft is further improved.
Preferably, in the flapping wing aircraft with adjustable attack angle of the wing pieces, the second connecting rod is an electric push rod and is provided with a battery; 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 wings capable of adjusting the attack angle, the wings are asymmetric wing-shaped, 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 the flapping wing aircraft with the adjustable attack angle of the wing panel, the wing is a rotor mechanism; 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 flapping wing aircraft with adjustable attack angle of the wing panel, 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 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 adjustable incidence angle of the wing panel, a bearing is sleeved on the mounting shaft, and the rotor blade is fixedly connected with the bearing.
Preferably, in the flapping wing aircraft with adjustable incidence angle of the wing panel, 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; 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 adjustable attack angle of the wing panel, the rotor wing is symmetrical in wing shape; this solution is a preferred embodiment for increasing the wing flight lift.
Preferably, in the flapping wing aircraft with the wing panels capable of adjusting the attack angle, the motor is 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 the present invention;
FIG. 2 is a schematic diagram of the structure of one embodiment of the present invention;
FIG. 3 is a schematic diagram of the structure of one embodiment of the present invention;
FIG. 4 is a schematic diagram of the structure of one embodiment of the present invention;
FIG. 5 is a block diagram of one embodiment of the wing assembly of the present invention;
FIG. 6 is a block diagram of one embodiment of the wing assembly of the present invention;
FIG. 7 is a block diagram of one embodiment of an airfoil assembly according to the present invention;
FIG. 8 is a block diagram of one embodiment of an airfoil assembly according to the present invention;
FIG. 9 is a force analysis diagram of the flapping process of the wing of the present invention;
FIG. 10 is a force analysis graph of the wing lift-back process of the present invention;
FIG. 11 is a force analysis graph of a flapping process of a rotor wing according to the present invention;
fig. 12 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 fig. 1, a lift mechanism with a variable rotor angle of attack according to the present invention includes:
the device comprises a fuselage 2, a wing device 1, a run-up device 3, a motor and a battery; the tail part of the machine body 2 is provided with a tail wing 20; the run-up device 3 is arranged at the lower side of the body 2; two sets of wing devices are arranged on two sides of the fuselage 2, the wing devices, the run-up device and the empennage are respectively provided with a motor, a plurality of motors are powered by batteries,
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 invention is as follows: 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 the 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, the 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 the 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 the steering engine.
Referring to fig. 9-10, an analysis view of wing stress according to an embodiment of the present invention is shown; the invention needs to be arranged with the wing 16 as the starting point for stress analysisFor use on board an aircraft, the starting device is first actuated to bring the leading edge of the wing to 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 wings 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; providing rotor blades with an upward velocity 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.
Referring to fig. 2, in one embodiment of the present invention, the second link 13 is an electric push rod and is equipped with a battery;
specifically, the airfoil 16 is an asymmetric airfoil, with a convex top and a concave bottom.
In the process of the lifting movement of the wing 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. 3, in one embodiment of the present invention, the wing 16 is a rotor mechanism in this embodiment.
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, a bearing is sleeved on the mounting shaft 17, and the rotor blade 18 is fixedly connected with the bearing.
More specifically, rotor blade 18 is provided with the multiple-disc, and the multiple-disc rotor blade 18 uses installation axle 17 axis to be the clockwise or anticlockwise array distribution for this guarantees that the rotor wing piece can keep syntropy to rotate in flapping and the lift-back in-process down, provides stable lift.
More specifically, rotor blades 18 are symmetrically airfoil shaped to further lift.
More specifically, motor 10 adopts servo motor or steering wheel to the better drive and enough control, reinforcing security.
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 wing pieces of the rotor wings are driven to rotate, the lift force is generated, and the flying capability is enhanced.
Referring to FIGS. 11-12, which are diagrams of the stress analysis of a rotor wing according to the present invention, the stress analysis is performed using the highest point of the wing 16 as the starting point, and the present invention is installed on an aircraft having a run-up device, wherein the run-up device is first activated to make the leading edge of the wing have a forward velocity 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 wings 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;
from lowest point to highest point on the wingDuring the rising movement of the points; providing rotor blades with an upward velocity 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.
Referring to fig. 4, in one embodiment of the present invention, the second link 13 is an electric push rod and is mounted with a battery.
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, a bearing is sleeved on the mounting shaft 17, and the rotor blade 18 is fixedly connected with the bearing.
More specifically, the wing panel is provided with the multiple-disc, and the multiple-disc wing panel is clockwise or anticlockwise array distribution with installation axle 17 axis as the center to this guarantees that the rotor wing panel can keep syntropy to rotate in flapping and the process of rising back down, provides stable lift.
More specifically, rotor blades 18 are symmetrically airfoil shaped to further lift.
More specifically, motor 10 adopts servo motor or steering wheel to the better drive and enough control, reinforcing security.
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 wing panel, so that the attack angle of the wing panel is increased within the range of the maximum value of the lift coefficient, the lift force of the wing panel in the lift return process is further increased by following the rule that the attack angle of the wing panel 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 rotor blades 18 rotate in the same direction during flapping and lifting, and provide lift for flight all the time.
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.
In some embodiments of the present invention, the drive assembly components are made of carbon fiber composite.
Specifically, the connecting components are all made of carbon fiber composite materials.
Specifically, each part in the wing device 1 is made of carbon fiber composite materials.
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.
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 adjustable angle of attack wings, comprising: the device comprises a fuselage (2), a wing device (1), a run-up device (3), a motor and a battery; a tail wing (20) is arranged at the tail part of the machine body (2); the run-up device (3) is arranged at the lower side of the machine body (2); two groups of wing devices are arranged at two sides of the fuselage (2), the wing devices (1) and the run-up device (3) are both powered by motors, and a plurality of motors are powered by batteries,
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 ornithopter with adjustable attack angle wing as claimed in claim 1, wherein the second link (13) is an electric push rod and is equipped with a battery.
3. The ornithopter with adjustable incidence of wing according to claim 1 or 3, characterized in that the wing (16) is asymmetric and has a convex top and a concave bottom.
4. The ornithopter with adjustable wing angle of attack of claim 1 or 2, characterized in that the wing (16) is a rotor mechanism.
5. The ornithopter with adjustable wing angle of attack of claim 4, characterized in that 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.
6. The ornithopter with adjustable wing angle of attack according to claim 5, characterized in that the mounting shaft (17) is provided with a bearing, and the rotor blade (18) is fixedly connected to the bearing.
7. The ornithopter with adjustable attack angle wings as claimed in claim 6, wherein the rotor blades (18) are provided in multiple pieces, and the multiple pieces of rotor blades (18) are distributed in a clockwise or counterclockwise array centered on the axis of the mounting shaft (17).
8. The ornithopter with adjustable wing angle of attack of claim 7, characterized in that the rotor blades (18) are symmetrical airfoil shaped.
9. The ornithopter with adjustable attack angle wings as claimed in claim 8, wherein the motor (10) is a servo motor or a steering engine.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011342098.0A CN112319793A (en) | 2020-11-26 | 2020-11-26 | Flapping wing aircraft with wing pieces capable of adjusting attack angle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011342098.0A CN112319793A (en) | 2020-11-26 | 2020-11-26 | Flapping wing aircraft with wing pieces capable of adjusting attack angle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN112319793A true CN112319793A (en) | 2021-02-05 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202011342098.0A Withdrawn CN112319793A (en) | 2020-11-26 | 2020-11-26 | Flapping wing aircraft with wing pieces capable of adjusting attack angle |
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| CN (1) | CN112319793A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2023055319A1 (en) * | 2021-09-29 | 2023-04-06 | Tusas- Turk Havacilik Ve Uzay Sanayii Anonim Sirketi | A fixed-wing control mechanism |
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|---|---|---|---|---|
| CN1826157A (en) * | 2003-06-18 | 2006-08-30 | 彼得·L·辛克莱 | Motion assisting apparatus for flying objects |
| US20150307191A1 (en) * | 2014-04-28 | 2015-10-29 | Daedalus Flight Systems, LLC | Flapping wing aerial vehicles |
| CN108454850A (en) * | 2018-01-24 | 2018-08-28 | 浙江工业职业技术学院 | A kind of imitative bird flapping flight device of cylindrical cam universal joint |
| CN108557074A (en) * | 2018-01-25 | 2018-09-21 | 西北工业大学 | Using the flapping wing aircraft and method of operating of three rotor mixed layouts |
| CN110171568A (en) * | 2019-06-14 | 2019-08-27 | 山东大学 | One kind can hover flapping wing aircraft |
-
2020
- 2020-11-26 CN CN202011342098.0A patent/CN112319793A/en not_active Withdrawn
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1826157A (en) * | 2003-06-18 | 2006-08-30 | 彼得·L·辛克莱 | Motion assisting apparatus for flying objects |
| US20150307191A1 (en) * | 2014-04-28 | 2015-10-29 | Daedalus Flight Systems, LLC | Flapping wing aerial vehicles |
| CN108454850A (en) * | 2018-01-24 | 2018-08-28 | 浙江工业职业技术学院 | A kind of imitative bird flapping flight device of cylindrical cam universal joint |
| CN108557074A (en) * | 2018-01-25 | 2018-09-21 | 西北工业大学 | Using the flapping wing aircraft and method of operating of three rotor mixed layouts |
| 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 |
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| WO2023055319A1 (en) * | 2021-09-29 | 2023-04-06 | Tusas- Turk Havacilik Ve Uzay Sanayii Anonim Sirketi | A fixed-wing control mechanism |
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Application publication date: 20210205 |