CN112407276A - Flapping rotor wing device capable of realizing upward half-rotation and downward horizontal operation - Google Patents
Flapping rotor wing device capable of realizing upward half-rotation and downward horizontal operation Download PDFInfo
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- CN112407276A CN112407276A CN202011342138.1A CN202011342138A CN112407276A CN 112407276 A CN112407276 A CN 112407276A CN 202011342138 A CN202011342138 A CN 202011342138A CN 112407276 A CN112407276 A CN 112407276A
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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
- 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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Abstract
The invention discloses a flapping rotor wing device with an upward half-rotation and a downward horizontal operation, which comprises: supporting component, runner assembly, drive assembly and rotor subassembly, supporting component, runner assembly, drive assembly and rotor subassembly linkage cooperation, thereby realized this flapping rotor device rotation main shaft still can carry out the technological effect of rotation along with the revolution of revolution main shaft revolution, make rotor subassembly can remain rotor subassembly plane of revolution and horizontal plane parallel at the in-process down all the time, and then for the aircraft provides vertical ascending lift, rotor subassembly can keep rotor subassembly's plane of revolution and horizontal plane perpendicular or be close perpendicularly at the in-process down, and then reduce the resistance that rotor subassembly went upward the process produced, avoided rotor subassembly to go upward and the offset of the in-process production lift down promptly, provide continuous stable lift for aircraft take-off and hover in the air. The flapping rotor wing device has the advantages of reasonable design, simple structure, easiness in operation, convenience in control, energy conservation, high efficiency and good application prospect.
Description
Technical Field
The invention relates to the technical field of aircrafts, in particular to a flapping rotor wing device capable of running horizontally in an up-going half-rotation mode and a down-going mode.
Background
The flapping wing air vehicle is a flying device designed by simulating flapping motion of insects or birds, the flapping wing air vehicle mainly depends on flapping of blades to generate lift force, and can provide larger lift force for the air vehicle, the flapping wing air vehicle has the functions of vertical take-off and landing, hovering, all-directional motion and the like, and compared with a fixed wing air vehicle and a rotor wing air vehicle, the flapping wing air vehicle has the advantages of simple structure, light weight, low cost, high efficiency and the like. If the flapping wing flight technology and the rotor wing flight technology can be combined, the advantages of vertical lift-off, hovering and the like of a rotor wing aircraft and a helicopter can be achieved, and the advantages of low energy consumption, easiness in control, low flight cost and the like of the aircraft in the flight process can be achieved.
In recent years, some technologies of combining flapping wings and rotor wings have appeared, namely, the flapping wings generate upward lift force and forward thrust force when flapping by utilizing the flexible deformation of the flapping wings, meanwhile, the antisymmetric thrust force forms a couple to drive the flapping wings to rotate in a self-driven manner, and the lift force can be increased through the circumferential motion speed generated by rotation, so that the purpose of integrally increasing the lift force is achieved. Therefore, the existing flapping rotor wing device has the defects of complex structure, heavy body, poor stability, difficult manufacturing and designing, high cost and the like, and the technical defects greatly limit the long-term development of the flapping rotor wing device.
Therefore, it is an urgent need to solve the problems of the art to provide a flapping rotor device with reasonable design, simple structure, easy operation, and capability of providing a larger lift force for the stable flight of an aircraft.
Disclosure of Invention
The invention aims to solve at least one of the technical problems in the prior art to a certain extent, and provides the flapping rotor wing device which has reasonable design, simple structure and easy operation and can provide larger lift force for the stable flight of an aircraft and runs horizontally in an upward half-rotation and downward half-rotation mode.
In order to achieve the purpose, the invention adopts the following technical scheme:
a flapping rotor apparatus for half-turn up and horizontal turn down comprising:
the supporting component is arranged on the side wall of the machine body and is fixedly connected with the machine body;
the rotating assembly comprises a revolution main shaft, a rotating arm and a rotation main shaft, and the revolution main shaft penetrates through the supporting assembly and is in rotating connection with the supporting assembly; the revolution main shaft is perpendicular to and fixedly connected with one end of the rotating arm, the rotation main shaft penetrates through the other end of the rotating arm and is perpendicular to and rotatably connected with the rotating arm, and the axis of the revolution main shaft is parallel to the axis of the rotation main shaft;
the driving assembly comprises a first driving motor and a second driving motor, the first driving motor is fixedly connected to the supporting assembly and is in transmission connection with the revolution spindle, the second driving motor is fixed at one end of the rotation spindle through a connecting piece, and an output shaft of the second driving motor is in transmission connection with the rotation spindle;
the rotary wing assembly comprises a central shaft, a bearing, a rotating disc and wings, wherein one end of the central shaft is vertically and fixedly connected to the rotation main shaft, the bearing is rotatably connected to the central shaft, the rotating disc is fixedly connected to the circumferential side wall of the bearing, one ends of the wings are arranged on the circumferential surface of the rotating disc and are fixedly connected with the rotating disc, the wings are double convex symmetrical wing shapes, the upper wing surfaces and the lower wing surfaces of the wings are arc-shaped, the front edges of the wings are thicker, and the rear edges of the wings are thinner;
the first driving motor drives the revolution spindle to revolve, the revolution spindle drives the rotating arm and the rotation spindle to revolve around the revolution spindle, the second driving motor drives the rotation spindle to rotate, and when the revolution spindle rotates 360 degrees, the second driving motor drives the rotation spindle to rotate 180 degrees; in the process of descending revolution of the rotation main shaft around the revolution main shaft, the second driving motor drives the rotation main shaft to enable the rotating disc and the fins on the rotation main shaft to be always parallel to a horizontal plane, meanwhile, the rotating disc and the fins are enabled to rotate 90 degrees in angle when running from the top end to the bottom end, and in the process of ascending revolution of the rotation main shaft around the revolution main shaft, the second driving motor drives the rotation main shaft and the rotating disc and the fins on the rotation main shaft to rotate 90 degrees.
Through the technical scheme, compared with the prior art, the invention discloses a flapping rotor wing device capable of performing horizontal operation in an up half-rotation and down horizontal mode, the first driving motor is used for driving the revolution spindle to perform revolution, and the second driving motor is used for driving the rotation spindle to perform rotation, so that the revolution spindle in the flapping rotor wing device can drive the rotating arm and the rotation spindle to perform revolution, and simultaneously, the rotation spindle can perform rotation, moreover, the second driving motor is used for driving the rotation spindle to enable the rotor wing assembly arranged on the rotation spindle to be always parallel to the radial direction and the horizontal plane in the down operation process of the rotation spindle in the device, so that the wing panel continuously provides a large vertical lifting force for an aircraft in the high-speed rotation process, and simultaneously, in the up rotation process of the rotation spindle, the second driving motor drives the rotor wing assembly to enable the rotor wing assembly to be vertical to a horizontal plane or close to vertical, so that the ascending process does not generate resistance or generates small resistance, the flapping rotor wing device is guaranteed to flap and rotate under the rotor wing assembly to provide large lift force for an aircraft, and meanwhile, the rotation main shaft is guaranteed to rotate 180 degrees when revolving 360 degrees around the revolution main shaft. The flapping rotor wing device capable of running horizontally in an up-going, half-rotating and down-going mode is reasonable in design, simple in structure, easy to operate and convenient to control, and can stably provide a larger lift force for an aircraft in the revolution and rotation processes of the flapping rotor wing device, so that the aircraft can take off stably and hover in the air.
Furthermore, the support assemblies are support frames, the support frames are arranged in groups, each group of support frames comprises two support frames, a certain distance is formed between the two support frames, the axes of the two support frames are arranged in parallel, and two ends of the revolution spindle respectively penetrate through the two support frames and are perpendicular to and rotatably connected with the two support frames; the rocking arm the rotation main shaft the rotor subassembly first runner with the second runner all is located two between the support frame, just the length of rocking arm is less than the length of support frame.
The beneficial effects that adopt above-mentioned technical scheme to produce are, effectively improved the structural stability of the device, guaranteed the rotation of rotary wing subassembly on the device simultaneously.
Furthermore, the number of the support frames is two or more, and the two or more support frames are symmetrically arranged on two sides of the aircraft fuselage.
The beneficial effect that adopts above-mentioned technical scheme to produce is, has not only guaranteed the stability of aircraft fuselage, also provides great lift for aircraft takes off and hovers in the air simultaneously.
Furthermore, the number of the rotating arms is one or more, the rotating arms are uniformly arranged on the same circumferential surface, and the number of the rotation main shafts and the rotor wing assemblies which are arranged corresponding to the rotating arms is one or more.
The beneficial effect who adopts above-mentioned technical scheme to produce is, can continuously provide stable, great lift for the aircraft.
Furthermore, the number of the rotating arms is three, the three rotating arms are uniformly arranged on the same circumferential surface, and the included angle between any two adjacent rotating arms is 120 degrees.
The beneficial effects that adopt above-mentioned technical scheme to produce are that, can effectively improve driving motor's transmission efficiency, reduce unnecessary energy consumption, provide lasting, stable, great lift for the aircraft simultaneously.
Further, the vanes are uniformly arranged on the circumferential surface of the rotating disc, and the directions of the front edges of the vanes are the same.
Further, the airfoil is one of a NACA0012 airfoil or a NACA0016 airfoil.
The beneficial effect who adopts above-mentioned technical scheme to produce is, can effectively guarantee that the fin lasts and produces great lift at continuous pivoted in-process.
Further, every the rotor subassembly includes two coaxial arrangements the rolling disc, two all be equipped with the fin on the rolling disc, and the upper strata on the rolling disc the fin leading edge direction is with the lower floor on the rolling disc the fin leading edge opposite direction.
The beneficial effect who adopts above-mentioned technical scheme to produce is that, the design of double-deck rotor not only makes the structure of this rotor subassembly compacter, still makes the rotor subassembly can receive bigger lift under the rotation effect of double-deck fin, and simultaneously, leading edge opposite direction's setting makes the fin can offset because the fin rotates and act on the epaxial torsion of center at the rotation in-process in the double-deck fin.
Further, the first driving motor and the second driving motor are both one of a servo motor or a stepping motor.
The beneficial effect who adopts above-mentioned technical scheme to produce is for the structure of the device is simpler, and the operation process is easily controlled, and manufacturing cost is lower.
The driving assembly comprises a driving wheel and a driven wheel, the output end of the first driving motor is in transmission connection with the driving wheel, the driving wheel is meshed with the driven wheel, and the driven wheel is arranged at one end of the revolution main shaft, is concentrically arranged with the revolution main shaft and is fixedly connected with the revolution main shaft.
The technical scheme has the beneficial effects that the effect of matching the rotating speed and transmitting the torque between the driving motor and the revolution main shaft can be achieved, so that the rotating speed of the output shaft of the driving motor is reduced, and the output torque is improved.
Further, still include the rotor frame, the rotor frame is located on the rotation main shaft and with rotation main shaft fixed connection, the rotor frame is located the rotor subassembly is outside, is used for the protection the rotor subassembly avoids the great impact force of air current.
The beneficial effect who adopts above-mentioned technical scheme to produce is, can effectively protect the rotor subassembly to avoid the air current to strike to the life of extension rotor subassembly, and then the security that improves the device operation in-process.
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 trajectory of a flapping rotor apparatus according to the present invention, with half-turn up and half-turn down and horizontal operation;
FIG. 2 is a schematic structural view of a flapping rotor apparatus according to the present invention, with half-turn up and half-turn down and horizontal operation;
FIG. 3 is a top view of an up half turn down horizontal running flapping rotor apparatus according to the present invention;
FIG. 4 is a schematic structural view of a rotor assembly of a flapping rotor apparatus according to the present invention, with half-up rotation and half-down horizontal motion;
FIG. 5 is a schematic structural view of a rotor assembly having dual-layer wings in a flapping rotor assembly according to the present invention, with half-turn up and half-turn down and horizontal operation;
fig. 6 is a schematic structural diagram of a rotor frame in a flapping rotor apparatus according to the present invention, with half-turn up and half-turn down and horizontal operation.
Wherein: 1-support component, 2-rotation component, 21-revolution spindle, 22-rotating arm, 23-rotation spindle, 3-drive component, 31-first drive motor, 32-second drive motor, 4-rotor component, 41-central shaft, 42-bearing, 43-rotating disc, 44-wing panel, 5-transmission component, 51-driving wheel, 52-driven wheel, 6-rotor frame and 7-fuselage.
Detailed Description
Reference will now be made in detail to embodiments of the present invention, examples of which are illustrated in the accompanying drawings, wherein like or similar reference numerals refer to the same or similar elements or elements having the same or similar function throughout. The embodiments described below with reference to the drawings are illustrative and intended to be illustrative of the invention and are not to be construed as limiting the 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.
Furthermore, the terms "first", "second" and "first" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of the present invention, "a plurality" means two or more unless specifically defined otherwise.
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.
In the present invention, unless otherwise expressly stated or limited, "above" or "below" a first feature means that the first and second features are in direct contact, or that the first and second features are not in direct contact but are in contact with each other via another feature therebetween. Also, the first feature being "on," "above" and "over" the second feature includes the first feature being directly on and obliquely above the second feature, or merely indicating that the first feature is at a higher level than the second feature. A first feature being "under," "below," and "beneath" a second feature includes the first feature being directly under and obliquely below the second feature, or simply meaning that the first feature is at a lesser elevation than the second feature.
The invention discloses a flapping rotor wing device with an upward half-rotation and a downward horizontal operation, which comprises:
the supporting component 1 is arranged on the side wall of the machine body 7, and the supporting component 1 is fixedly connected with the machine body 7;
the rotating assembly 2 comprises a revolution spindle 21, a rotating arm 22 and a rotation spindle 23, wherein the revolution spindle 21 penetrates through the support assembly 1 and is rotationally connected with the support assembly 1; the revolution main shaft 21 is vertical and fixedly connected with one end of the rotating arm 22, the rotation main shaft 23 passes through the other end of the rotating arm 22 and is vertical and rotatably connected with the rotating arm 22, and the axis of the revolution main shaft 21 is parallel to the axis of the rotation main shaft 23;
the driving assembly 3, the driving assembly 3 includes the first driving motor 31 and the second driving motor 32, the first driving motor 31 is fixedly connected to supporting assembly 1, and with revolving spindle 21 transmission connection, the second driving motor 32 is fixed on one end of the rotation spindle 23 through the link, and the output shaft of the second driving motor 32 with rotation spindle 23 transmission connection;
the rotor wing assembly 4 comprises a central shaft 41, a bearing 42, a rotating disc 43 and fins 44, wherein one end of the central shaft 41 is vertically and fixedly connected to the rotation main shaft 23, the bearing 42 is rotatably connected to the central shaft 41, the rotating disc 43 is fixedly connected to the circumferential side wall of the bearing 42, one end of each fin 44 is arranged on the circumferential surface of the rotating disc 43 and is fixedly connected with the rotating disc 43, each fin 44 is a double-convex symmetrical wing type with an upper wing surface and a lower wing surface both in an arc shape, the front edge of each fin 44 is thicker, and the rear edge of each fin 44 is thinner;
the first driving motor 31 drives the revolution spindle 21 to revolve, the revolution spindle 21 drives the rotating arm 22 and the rotation spindle 23 to revolve around the revolution spindle 21, the second driving motor 32 drives the rotation spindle 23 to rotate, and when the revolution spindle 21 rotates 360 degrees, the second driving motor 32 drives the rotation spindle 23 to rotate 180 degrees; during the downward revolution of the rotation main shaft 23 around the revolution main shaft 21, the second driving motor 32 drives the rotation main shaft 23 to enable the rotating disc 43 and the fins 44 on the rotation main shaft 23 to be always parallel to the horizontal plane, meanwhile, the rotation disc 43 and the fins 44 are ensured to rotate 90 degrees when moving from the top end to the bottom end, and during the upward revolution of the rotation main shaft 23 around the revolution main shaft 21, the rotation main shaft 23 and the rotating disc 43 and the fins 44 on the rotation main shaft 23 are driven by the second driving motor 32 to rotate 90 degrees.
As shown in fig. 2, according to an alternative embodiment of the present invention, the supporting components 1 are supporting frames, the supporting frames are arranged in groups, each group of supporting frames includes two supporting frames, a certain distance is formed between the two supporting frames, the axes of the two supporting frames are arranged in parallel, and two ends of the revolving spindle 21 respectively pass through the two supporting frames, are perpendicular to the two supporting frames, and are rotatably connected to the two supporting frames; rocking arm 22, rotation main shaft 23, rotor subassembly 4, first runner and second runner all are located between two support frames, and rocking arm 22's length is less than the length of support frame to effectively improved the device's structural stability, guaranteed the rotation of the device rotation wing subassembly simultaneously.
According to an alternative embodiment of the invention, the four groups of support frames are uniformly arranged on two sides of the aircraft body 7 and are symmetrically arranged, so that the stability of the aircraft body is ensured, and a larger lift force is provided for takeoff and hovering of the aircraft.
As shown in fig. 2, according to an alternative embodiment of the present invention, there are two rotating arms 22, and the two rotating arms 22 are uniformly arranged on the same circumferential surface, and there are two rotating spindles 23 and two rotor assemblies 4 arranged corresponding to the two rotating arms 22, so that stable and large lift force can be continuously provided to the aircraft.
As shown in fig. 1 and 3, according to a preferred embodiment of the present invention, there are three rotating arms 22, the three rotating arms 22 are uniformly arranged on the same circumferential surface, and the included angle between any two adjacent rotating arms 22 is 120 °, so that the transmission efficiency of the driving motor can be effectively improved, the unnecessary energy consumption can be reduced, and a continuous, stable and large lift force can be provided for the aircraft.
As shown in fig. 4, according to an alternative embodiment of the present invention, there are three vanes 44, the three vanes 44 are uniformly arranged on the circumferential surface of the rotating disk 43, and the directions of the leading edges of the three vanes 44 are the same; specifically, the airfoil 44 is an airfoil of NACA0016, so as to effectively ensure that the airfoil continuously generates a large lift force during continuous rotation.
As shown in fig. 5, according to an alternative embodiment of the present invention, each rotor assembly 4 includes two coaxially arranged rotating disks 43, the two rotating disks 43 are provided with fins 44, and the direction of the leading edge of the fin 44 on the upper rotating disk 43 is opposite to the direction of the leading edge of the fin 44 on the lower rotating disk 43, the design of the double-layer rotor not only makes the structure of the rotor assembly more compact, but also makes the rotor assembly receive more lift force under the rotation action of the double-layer fin, and at the same time, the opposite arrangement of the leading edges of the double-layer fin makes the fin counteract the torsion force acting on the central shaft due to the rotation of the fin during the rotation process.
According to an alternative embodiment of the present invention, the first driving motor 31 and the second driving motor 32 are both servo motors, so that the device has a simpler structure, an easily controlled operation process, and a lower production cost.
As shown in fig. 2, according to an alternative embodiment of the present invention, the transmission assembly 5 further includes a driving wheel 51 and a driven wheel 52, the output end of the first driving motor 31 is in transmission connection with the driving wheel 51, the driving wheel 51 is meshed with the driven wheel 52, the driven wheel 52 is disposed at one end of the revolution main shaft 21 and is concentrically arranged and fixedly connected with the revolution main shaft 21, and the driving wheel and the driven wheel are arranged to match the rotation speed and transmit torque between the driving motor and the revolution main shaft, so as to increase the output torque while reducing the rotation speed of the output shaft of the first driving motor.
As shown in fig. 6, according to an alternative embodiment of the present invention, the present invention further includes a rotor frame 6, the rotor frame 6 is disposed on the rotation main shaft 23 and is fixedly connected to the rotation main shaft 23, and the rotor frame 6 is located outside the rotor assembly 4 and is used for protecting the rotor assembly 4 from a large impact force of an airflow, so as to effectively protect the rotor assembly from the airflow, prolong the service life of the rotor assembly, and further improve the safety of the device during the operation process.
According to the flapping rotor wing device capable of running horizontally in an up half-rotation mode and a down half-rotation mode, the first driving motor is used for driving the revolution spindle to rotate, and the second driving motor is used for driving the rotation spindle to rotate, so that the revolution spindle in the flapping rotor wing device can drive the rotating arm and the rotation spindle to revolve, and meanwhile, the rotation of the rotation spindle can be achieved. In addition, the second driving motor is connected with the rotation main shaft in a transmission manner, so that the rotation main shaft is driven by the second driving motor to enable the radial direction of a rotor wing assembly arranged on the rotation main shaft to be always parallel to the horizontal plane in the downward running process of the rotation main shaft in the device, and the wing panel continuously provides a larger vertical lift force for the aircraft in the high-speed rotating process. Simultaneously, in the revolution of the rotation main shaft and going upwards, the second driving motor drives the rotor wing assembly to enable the rotor wing assembly to be vertical to the horizontal plane or close to vertical, so that resistance is not generated or smaller resistance is generated in the going upwards process, the flapping rotor wing device is guaranteed to provide larger lift force for an aircraft in the flapping and rotating processes of the rotor wing assembly, and meanwhile, the rotation main shaft can rotate 180 degrees when revolving 360 degrees around the revolution main shaft. The flapping rotor wing device capable of running horizontally in an up-going, half-rotating and down-going mode is reasonable in design, simple in structure, easy to operate and convenient to control, and can stably provide a larger lift force for an aircraft in the revolution and rotation processes of the flapping rotor wing device, so that the aircraft can take off stably and hover in the air.
In the description herein, references to the description of the term "one embodiment," "some embodiments," "an example," "a specific example," or "some examples," etc., mean that a particular feature, structure, material, or characteristic described in connection with the embodiment or example is included in at least one embodiment or example of the invention. In this specification, the schematic representations of the terms used above are not necessarily intended to refer to the same embodiment or example. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples. Furthermore, various embodiments or examples described in this specification can be combined and combined by those skilled in the art.
Although embodiments of the present invention have been shown and described above, it is understood that the above embodiments are exemplary and should not be construed as limiting the present invention, and that variations, modifications, substitutions and alterations can be made to the above embodiments by those of ordinary skill in the art within the scope of the present invention.
Claims (10)
1. A flapping rotor device with half-rotation up-going and horizontal operation down-going functions, comprising:
the supporting component (1) is arranged on the side wall of the machine body (7), and the supporting component (1) is fixedly connected with the machine body (7);
the rotating assembly (2) comprises a revolution main shaft (21), a rotating arm (22) and a rotation main shaft (23), and the revolution main shaft (21) penetrates through the supporting assembly (1) and is in rotating connection with the supporting assembly (1); the revolution main shaft (21) is perpendicular to and fixedly connected with one end of the rotating arm (22), the rotation main shaft (23) penetrates through the other end of the rotating arm (22) and is perpendicular to and rotatably connected with the rotating arm (22), and the axis of the revolution main shaft (21) is parallel to the axis of the rotation main shaft (23);
the driving assembly (3) comprises a first driving motor (31) and a second driving motor (32), the first driving motor (31) is fixedly connected to the supporting assembly (1) and is in transmission connection with the revolution spindle (21), the second driving motor (32) is fixed at one end of the rotation spindle (23) through a connecting piece, and an output shaft of the second driving motor (32) is in transmission connection with the rotation spindle (23);
the rotor assembly (4) comprises a central shaft (41), a bearing (42), a rotating disc (43) and a wing piece (44), one end of the central shaft (41) is vertically and fixedly connected to the rotation spindle (23), the bearing (42) is rotatably connected to the central shaft (41), the rotating disc (43) is fixedly connected to the circumferential side wall of the bearing (42), one end of the wing piece (44) is arranged on the circumferential surface of the rotating disc (43) and fixedly connected with the rotating disc (43), the wing piece (44) is an arc-shaped double-convex symmetrical wing type with an upper wing surface and a lower wing surface, the front edge of the wing piece (44) is thick, and the rear edge of the wing piece (44) is thin;
the first driving motor (31) drives the revolution spindle (21) to revolve, the revolution spindle (21) drives the rotating arm (22) and the rotation spindle (23) to revolve around the revolution spindle (21), the second driving motor (32) drives the rotation spindle (23) to rotate, and when the revolution spindle (21) rotates for 360 degrees, the second driving motor (32) drives the rotation spindle (23) to rotate for 180 degrees; in the process that the rotation main shaft (23) revolves downwards around the revolution main shaft (21), the second driving motor (32) drives the rotation main shaft (23) to enable the rotating disc (43) and the fins (44) on the rotation main shaft (23) to be always parallel to the horizontal plane, meanwhile, the rotation disc (43) and the fins (44) are enabled to rotate 90 degrees in angle when the rotation main shaft (23) runs from the top end to the bottom end, and in the process that the rotation main shaft (23) revolves upwards around the revolution main shaft (21), the second driving motor (32) drives the rotation main shaft (23) and the rotating disc (43) and the fins (44) on the rotation main shaft (23) to rotate 90 degrees.
2. The flapping rotor device according to claim 1, wherein the support assemblies (1) are support frames, the support frames are arranged in groups, each group of support frames comprises two support frames, a certain distance is formed between the two support frames, the axes of the two support frames are arranged in parallel, and two ends of the revolution spindle (21) respectively penetrate through the two support frames and are vertically and rotatably connected with the two support frames; rocking arm (22) rotation main shaft (23) rotor subassembly (4) first rotation wheel with the second rotates the wheel and all is located two between the support frame, just the length of rocking arm (22) is less than the length of support frame.
3. The flapping rotor apparatus of claim 2, wherein said two or more sets of support frames are symmetrically disposed on opposite sides of the aircraft fuselage (7).
4. The flapping rotor apparatus of claim 1, wherein said number of said rotating arms (22) is one or more, and one or more of said rotating arms (22) are uniformly arranged on the same circumference, and said rotating main shaft (23) and said rotor assembly (4) arranged corresponding to one or more of said rotating arms (22) are one or more.
5. The flapping rotor apparatus of claim 4, wherein the number of said rotating arms (22) is three, three of said rotating arms (22) are uniformly arranged on the same circumferential surface, and the included angle between any two adjacent rotating arms (22) is 120 °.
6. The flapping rotor apparatus of claim 1, wherein said plurality of vanes (44) are uniformly arranged on the circumferential surface of said rotating disk (43), and the leading edges of said plurality of vanes (44) are oriented in the same direction.
7. The flapping rotor apparatus of claim 1, wherein each said rotor assembly (4) comprises two said coaxially disposed rotating disks (43), wherein said two rotating disks (43) each have a wing (44) disposed thereon, and wherein the direction of the leading edge of said wing (44) on the upper rotating disk (43) is opposite to the direction of the leading edge of said wing (44) on the lower rotating disk (43).
8. The flapping rotor apparatus of claim 1, wherein said first drive motor (31) and said second drive motor (32) are each one of a servo motor or a stepper motor.
9. The flapping rotor device of claim 1, further comprising a transmission assembly (5), wherein said transmission assembly (5) comprises a driving wheel (51) and a driven wheel (52), an output end of said first driving motor (31) is in transmission connection with said driving wheel (51), said driving wheel (51) is engaged with said driven wheel (52), and said driven wheel (52) is disposed at one end of said revolution spindle (21), and is concentrically disposed and fixedly connected with said revolution spindle (21).
10. The flapping rotor device of claim 1, further comprising a rotor frame (6), wherein said rotor frame (6) is disposed on said autorotation spindle (23) and fixedly connected to said autorotation spindle (23), said rotor frame (6) being disposed outside said rotor assembly (4) for protecting said rotor assembly (4) from high impact forces of air currents.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011342138.1A CN112407276A (en) | 2020-11-26 | 2020-11-26 | Flapping rotor wing device capable of realizing upward half-rotation and downward horizontal operation |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011342138.1A CN112407276A (en) | 2020-11-26 | 2020-11-26 | Flapping rotor wing device capable of realizing upward half-rotation and downward horizontal operation |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN112407276A true CN112407276A (en) | 2021-02-26 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202011342138.1A Withdrawn CN112407276A (en) | 2020-11-26 | 2020-11-26 | Flapping rotor wing device capable of realizing upward half-rotation and downward horizontal operation |
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| CN (1) | CN112407276A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2022110942A1 (en) * | 2020-11-26 | 2022-06-02 | 佛山市神风航空科技有限公司 | Apparatus and method for converting reciprocating motion into continuous rotation and application |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1629038A (en) * | 2004-10-02 | 2005-06-22 | 高晓燕 | Aircraft with flapping wings |
| CN102582832A (en) * | 2012-03-07 | 2012-07-18 | 安徽工业大学 | Flapping-wing aircraft |
| CN202491921U (en) * | 2011-10-17 | 2012-10-17 | 湖南工学院 | Bionic ornithopter |
| WO2018066918A2 (en) * | 2016-10-07 | 2018-04-12 | 이상철 | Flapping flight device having variable wingspan |
-
2020
- 2020-11-26 CN CN202011342138.1A patent/CN112407276A/en not_active Withdrawn
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1629038A (en) * | 2004-10-02 | 2005-06-22 | 高晓燕 | Aircraft with flapping wings |
| CN202491921U (en) * | 2011-10-17 | 2012-10-17 | 湖南工学院 | Bionic ornithopter |
| CN102582832A (en) * | 2012-03-07 | 2012-07-18 | 安徽工业大学 | Flapping-wing aircraft |
| WO2018066918A2 (en) * | 2016-10-07 | 2018-04-12 | 이상철 | Flapping flight device having variable wingspan |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2022110942A1 (en) * | 2020-11-26 | 2022-06-02 | 佛山市神风航空科技有限公司 | Apparatus and method for converting reciprocating motion into continuous rotation and application |
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Application publication date: 20210226 |