CN112550697A - Flapping rotor wing device capable of realizing coplanar operation of upward vertical operation and downward axial wings - Google Patents
Flapping rotor wing device capable of realizing coplanar operation of upward vertical operation and downward axial wings Download PDFInfo
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- CN112550697A CN112550697A CN202011346901.8A CN202011346901A CN112550697A CN 112550697 A CN112550697 A CN 112550697A CN 202011346901 A CN202011346901 A CN 202011346901A CN 112550697 A CN112550697 A CN 112550697A
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C33/00—Ornithopters
- B64C33/02—Wings; Actuating mechanisms therefor
- B64C33/025—Wings; Actuating mechanisms therefor the entire wing moving either up or down
Abstract
The invention discloses a flapping rotor wing device with ascending vertical operation and descending shaft wing coplanar operation, which comprises: supporting component, runner assembly, drive assembly, rotor subassembly and transmission assembly, through supporting component, runner assembly, drive assembly, rotor subassembly and transmission assembly's linkage cooperation, can realize that this pounce out rotor assembly is at the in-process that descends in the rotor device, second driving motor drive rotor assembly's rotor face and rocking arm axis remain parallel throughout, rotor subassembly is at the in-process that ascends, second driving motor drive rotor assembly's rotor face perpendicular to horizontal plane all the time, avoided rotor subassembly to go upward the in-process promptly and produced the power of offsetting with the lift, thereby make this pounce out rotor device through the revolution of rotation main shaft and rotation realize providing continuous stable lift for the aircraft, and then realize the steady take-off and the aerial hover of aircraft.
Description
Technical Field
The invention relates to the technical field of aircrafts, in particular to a flapping rotor wing device capable of realizing coplanar operation of ascending vertical operation and descending axial wings.
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 a reasonable design, a simple structure, convenient control, 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 the advantages of reasonable design, simple structure, convenient control and easy operation, can provide larger lift force for the stable flight of an aircraft, runs upwards vertically, runs downwards and runs in a coplanar manner.
In order to achieve the purpose, the invention adopts the following technical scheme:
an upward vertically operating downward wing-in-plane operating flapping rotor apparatus 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 rotor assembly also comprises wing-panel prerotation means for prerotating the rotary disk before the flapping rotor device is started, and the prerotation means is in a structure and control mode: the battery supplies energy to the motor, the output of the motor is connected with a rotating disc in the rotor wing assembly through a clutch, the rotating disc is rotated in advance in a remote control mode, the prerotation device stops working after the whole flapping rotor wing device normally runs, and the prerotation device has the effect similar to a rotor wing prerotation system of a self-rotating rotor wing machine;
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 that the rotation main shaft revolves downwards around the revolution main shaft, the second driving motor drives the rotation main shaft to enable the rotary disc on the rotation main shaft and the rotor wing surfaces of the wing pieces to be always parallel to the axis of the rotating arm, namely the rotary disc and the rotor wing surfaces of the wing pieces rotate 180 degrees along with the rotation of the rotating arm when the rotary disc and the rotor wing surfaces of the wing pieces move from the top end to the bottom end; in the process that the rotation main shaft revolves upwards around the revolution main shaft, the second driving motor drives the rotation main shaft to enable the rotary disc on the rotation main shaft and the rotor wing surfaces of the wing pieces to be always vertical to a horizontal plane, namely the rotary disc and the rotor wing surfaces of the wing pieces rotate by 0 degree when the rotary disc and the rotor wing surfaces of the wing pieces move from the bottom end to the top end along with the rotation of the rotating arm.
According to the technical scheme, compared with the prior art, the flapping rotor wing device capable of realizing coplanar operation of the ascending vertically-operated descending axial wings is disclosed, the first driving motor is used for driving the revolution spindle to revolve, the second driving motor is used for driving the rotation spindle to rotate, and the rotation of the rotation spindle can be simultaneously realized while the revolution spindle drives the rotating arm and the rotation spindle to revolve; in addition, the second driving motor is in transmission connection with the rotation main shaft, so that the rotation main shaft is driven by the second driving motor to enable the rotor surface of the rotor wing assembly arranged on the rotation main shaft to be always parallel to the axis of the rotating arm in the downward running process of the rotation main shaft in the device, and the wing panel continuously provides upward lift force for the aircraft in the high-speed rotation process; in the revolution ascending process of the rotation spindle, the second driving motor drives the rotor wing assembly to enable the rotor wing surface of the rotor wing assembly to be always vertical to the horizontal plane, so that the ascending process of the rotor wing assembly hardly generates any force which offsets with the ascending in-process lift force, 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 spindle can rotate 180 degrees when revolving 360 degrees around the revolution spindle. The flapping rotor wing device capable of realizing coplanar operation of the ascending vertical operation and the descending axial wings has the advantages of reasonable design, simple structure, easiness in operation and convenience in control, is high in efficiency in the revolution and rotation processes of the flapping rotor wing device, and can stably provide larger lift force for an aircraft, 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 four, the four rotating arms are uniformly arranged on the same circumferential surface, and the included angle between every two adjacent rotating arms is 90 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 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.
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.
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 technical solutions of the embodiments of the present invention, the drawings required to be used in the embodiments will be briefly described below.
FIG. 1 is a diagram of the trajectory of an upward vertically traveling downward wing coplanar traveling flapping rotor system according to the present invention;
FIG. 2 is a schematic structural view of an upward vertically operating downward wing coplanar operation flapping rotor system according to the present invention;
FIG. 3 is a schematic representation of four flapping rotor apparatus arms of the present invention with four arms in a co-planar configuration for up-going, vertical operation and down-going axial wings;
FIG. 4 is a schematic structural view of a rotor assembly of an upward vertically operating downward wing coplanar operation flapping rotor assembly according to the present invention;
fig. 5 is a schematic structural diagram of a rotor frame in a flapping rotor apparatus according to the present invention, in which the upper vertical shaft wing and the lower vertical shaft wing operate in a coplanar manner.
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.
The invention discloses a flapping rotor wing device with ascending vertical operation and descending shaft wing coplanar 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 spindle 23 around the revolution spindle 21, the second driving motor 32 drives the rotation spindle 23 so that the rotor surfaces of the rotating disc 43 and the fins 44 on the rotation spindle 23 are always parallel to the axis of the rotating arm 22, i.e. the rotor surfaces of the rotating disc 43 and the fins 44 rotate 180 ° when moving from the top to the bottom with the rotation of the rotating arm 22, and during the upward revolution of the rotation spindle 23 around the revolution spindle 21, the second driving motor 32 drives the rotation spindle 23 so that the rotor surfaces of the rotating disc 43 and the fins 44 on the rotation spindle 23 are always perpendicular to the horizontal plane, i.e. the rotor surfaces of the rotating disc 43 and the fins 44 rotate 0 ° when moving from the bottom to the top with the rotation of the rotating arm 22.
According to an optional embodiment of the present invention, the supporting component 1 is a supporting frame, 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 revolution spindle 21 respectively pass through the two supporting frames and are perpendicular to and rotationally connected with 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 optional embodiment of the invention, six groups of support frames are uniformly distributed and symmetrically distributed on two sides of the aircraft body 7, so that the stability of the aircraft body is ensured, and a larger lift force is provided for takeoff and hovering of the aircraft.
According to an alternative embodiment of the present invention, there are four rotating arms 22, and four rotating arms 22 are uniformly arranged on the same circumferential surface, the included angle between two adjacent rotating arms is 90 °, and the number of the rotation main shafts 23 and the rotor assemblies 4 arranged corresponding to the four rotating arms 22 is four, so as to continuously provide stable and large lift force for the aircraft.
According to an alternative 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 as to effectively improve the transmission efficiency of the driving motor, reduce unnecessary energy consumption, and provide a continuous, stable and large lift force for the aircraft.
According to an alternative embodiment of the present invention, the first driving motor 31 and the second driving motor 32 are both stepping motors, so that the device has a simpler structure, an easily controlled operation process, and a lower production cost.
According to an alternative embodiment of the present invention, there are two vanes 44, the two vanes 44 are uniformly arranged on the circumferential surface of the rotating disk 43, and the leading edges of the two vanes are in the same direction; specifically, the airfoil 44 is an airfoil of NACA0012, so as to effectively ensure that the airfoil continuously generates a large lift force during continuous rotation.
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 under the rotation action of the double-layer fins, and meanwhile, the arrangement of the opposite leading edge directions in the double-layer fins makes the fins counteract the torsion acting on the central shaft due to the rotation of the fins during the rotation process.
According to an alternative embodiment of the present invention, the present invention further comprises a transmission assembly 5, the transmission assembly 5 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 engaged 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, so as to perform the function of matching the rotation speed and transmitting the torque between the driving motor and the revolution main shaft, and reduce the rotation speed of the output shaft of the first driving motor and simultaneously improve the output torque.
According to an optional embodiment of the invention, the wind power generator further comprises a rotor wing frame 6, the rotor wing frame 6 is arranged on the rotation main shaft 23 and is fixedly connected with the rotation main shaft 23, and the rotor wing frame 6 is located outside the rotor wing assembly 4 and is used for protecting the rotor wing assembly 4 from a large impact force of airflow, so that the rotor wing assembly can be effectively protected from the airflow impact, the service life of the rotor wing assembly is prolonged, and the safety of the device in the operation process is further improved.
According to the flapping rotor wing device with the ascending vertical operation and the descending axial wings running in the coplanar mode, the first driving motor is used for driving the revolution spindle to revolve, the second driving motor is used for driving the rotation spindle to rotate, and therefore the rotation of the rotation spindle can be achieved while the revolution spindle drives the rotating arm and the rotation spindle to revolve; and, utilize the transmission connection relation of second driving motor and rotation main shaft, make the rotation main shaft in the device in the operation process of going down, make the rotor face of the rotor subassembly that locates on the rotation main shaft keep parallel with the axis of the rocking arm all the time by the rotation main shaft of second driving motor drive, thus make the wing continuously provide ascending lift for the aircraft in the high-speed rotatory process, meanwhile, in the revolution process of rotation main shaft, second driving motor drive rotor subassembly make its rotor face keep perpendicular with the horizontal plane all the time, thereby make the rotor subassembly go up the process and not produce any and the power that lift in the process of going down and offset, and then guarantee that this flapping rotor device can provide great lift for the aircraft under the rotor subassembly and in the rotatory process, still guaranteed simultaneously that the rotation main shaft can rotate 180 when revolving 360 degrees around the revolution main shaft. The flapping rotor wing device capable of realizing coplanar operation of the ascending vertical operation and the descending axial wings has the advantages of reasonable design, simple structure, easiness in operation and convenience in control, and can stably provide 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.
Claims (10)
1. A flapping rotor apparatus for up-going vertical operation and down-going co-planar operation of the airfoils 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; during the downward revolution of the rotation spindle (23) around the revolution spindle (21), the second driving motor (32) drives the rotation spindle (23) to enable the rotary disc (43) on the rotation spindle (23) and the rotor surfaces of the fins (44) to be always parallel to the axis of the rotating arm (22), namely the rotary disc (43) and the rotor surfaces of the fins (44) rotate 180 degrees in an angle manner when the rotation spindle (23) runs from the top end to the bottom end along with the rotation of the rotating arm (22), and during the upward revolution of the rotation spindle (23) around the revolution spindle (21), the second driving motor (32) drives the rotation spindle (23) to enable the rotary disc (43) on the rotation spindle (23) and the rotor surfaces of the fins (44) to be always vertical to the horizontal plane, namely the rotary disc (43) and the rotor surfaces of the fins (44) rotate 0 degree when the rotation spindle (22) runs from the bottom end to the top end.
2. The flapping rotor device of claim 1, wherein the support assemblies (1) are support frames, the support frames are arranged in groups, each support frame 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 perpendicular to 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 supports are symmetrically disposed on opposite sides of said 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) are one or more arranged corresponding to one or more of said rotating arms (22).
5. The flapping rotor apparatus of claim 4, wherein said number of said arms (22) is four, four of said arms (22) are uniformly arranged on a same circumferential surface, and the angle between two adjacent arms (22) is 90 °.
6. 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.
7. 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.
8. The flapping rotor apparatus of claim 1, wherein each said rotor assembly (4) comprises two coaxially disposed said 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 layer of said rotating disks (43) is opposite to the direction of the leading edge of said wing (44) on the lower layer of said rotating disks (43).
9. The flapping rotor apparatus 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 arranged and fixedly connected with said revolution spindle (21).
10. The flapping rotor apparatus of claim 1, further comprising a rotor frame (6), wherein said rotor frame (6) is disposed on said spinning mast (23) and fixedly connected to said spinning mast (23), said rotor frame (6) being disposed outside said rotor assembly (4) for shielding said rotor assembly (4) from high impact forces of air currents.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011346901.8A CN112550697A (en) | 2020-11-26 | 2020-11-26 | Flapping rotor wing device capable of realizing coplanar operation of upward vertical operation and downward axial wings |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011346901.8A CN112550697A (en) | 2020-11-26 | 2020-11-26 | Flapping rotor wing device capable of realizing coplanar operation of upward vertical operation and downward axial wings |
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| Publication Number | Publication Date |
|---|---|
| CN112550697A true CN112550697A (en) | 2021-03-26 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202011346901.8A Withdrawn CN112550697A (en) | 2020-11-26 | 2020-11-26 | Flapping rotor wing device capable of realizing coplanar operation of upward vertical operation and downward axial wings |
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| CN (1) | CN112550697A (en) |
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 |
| CN1693700A (en) * | 2004-11-16 | 2005-11-09 | 俞嘉华 | Wind-mill generator combined with self rotation and revolution of wind vane for flapping-wing aircraft and its method |
| CN102582832A (en) * | 2012-03-07 | 2012-07-18 | 安徽工业大学 | Flapping-wing aircraft |
| CN104443384A (en) * | 2014-12-15 | 2015-03-25 | 佛山市神风航空科技有限公司 | Rotary wing blade type flapping wing air vehicle |
-
2020
- 2020-11-26 CN CN202011346901.8A patent/CN112550697A/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 |
| CN1693700A (en) * | 2004-11-16 | 2005-11-09 | 俞嘉华 | Wind-mill generator combined with self rotation and revolution of wind vane for flapping-wing aircraft and its method |
| CN102582832A (en) * | 2012-03-07 | 2012-07-18 | 安徽工业大学 | Flapping-wing aircraft |
| CN104443384A (en) * | 2014-12-15 | 2015-03-25 | 佛山市神风航空科技有限公司 | Rotary wing blade type flapping wing air vehicle |
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Application publication date: 20210326 |
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