CN112441229A - Flapping rotor wing device with upward shaft wing capable of vertically running and downward horizontally running - Google Patents
Flapping rotor wing device with upward shaft wing capable of vertically running and downward horizontally running Download PDFInfo
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- CN112441229A CN112441229A CN202011346904.1A CN202011346904A CN112441229A CN 112441229 A CN112441229 A CN 112441229A CN 202011346904 A CN202011346904 A CN 202011346904A CN 112441229 A CN112441229 A CN 112441229A
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- 238000000034 method Methods 0.000 claims abstract description 27
- 230000005540 biological transmission Effects 0.000 claims abstract description 19
- 230000000712 assembly Effects 0.000 claims description 6
- 238000000429 assembly Methods 0.000 claims description 6
- 230000001174 ascending effect Effects 0.000 abstract description 5
- 230000009286 beneficial effect Effects 0.000 description 11
- 238000005096 rolling process Methods 0.000 description 6
- 238000010586 diagram Methods 0.000 description 3
- 230000000694 effects Effects 0.000 description 3
- 238000005265 energy consumption Methods 0.000 description 3
- 238000005516 engineering process Methods 0.000 description 3
- 238000004519 manufacturing process Methods 0.000 description 3
- 230000007547 defect Effects 0.000 description 2
- 241000238631 Hexapoda Species 0.000 description 1
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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; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/02—Aircraft characterised by the type or position of power plants
- B64D27/24—Aircraft characterised by the type or position of power plants using steam or spring force
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D35/00—Transmitting power from power plants to propellers or rotors; Arrangements of transmissions
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D35/00—Transmitting power from power plants to propellers or rotors; Arrangements of transmissions
- B64D35/02—Transmitting power from power plants to propellers or rotors; Arrangements of transmissions specially adapted for specific power plants
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Abstract
The invention discloses a flapping rotor wing device with an upward shaft wing running vertically and a downward shaft wing running horizontally, which comprises: the support assembly, the runner assembly, drive assembly, rotor subassembly and transmission assembly through support assembly, runner assembly, drive assembly, rotor subassembly and transmission assembly's linkage cooperation, can realize that the rotation main shaft carries out the revolution under the drive of revolution main shaft among this flapping rotor device, and keeps the rotation under second driving motor's drive simultaneously. In the descending revolution process of the rotation spindle in the flapping rotor device, the second driving motor drives the rotating surface which keeps the rotor assembly all the time to be parallel to the horizontal plane, so that the vertical upward lift force is continuously provided for the aircraft, in the ascending revolution process of the rotation spindle, the second driving motor drives the rotating surface which keeps the rotor assembly to be always vertical to the axis of the rotating arm, so that the resistance is not generated or the smaller resistance is generated, the offset of the lift force in the revolution process of the rotor assembly is avoided, and the continuous and stable lift force is provided for the aircraft.
Description
Technical Field
The invention relates to the technical field of aircrafts, in particular to a flapping rotor wing device with an upward shaft wing capable of vertically running and a downward shaft wing capable of horizontally running.
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 high 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 can vertically run by an upward shaft wing and horizontally run by a downward shaft wing.
In order to achieve the purpose, the invention adopts the following technical scheme:
an upward-axis-wing vertically-operating downward-horizontally-operating flapping-rotor device, 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, meanwhile, 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; when the rotating arm rotates to a vertical state, the second driving motor drives the rotation main shaft to enable the rotation surfaces of the rotating disc and the fins to be perpendicular to the rotating arm, namely the rotation surfaces of the rotating disc and the fins are arranged in parallel with a horizontal plane, the second driving motor drives the rotation main shaft to rotate in the process of descending revolution of the rotation main shaft around the revolution main shaft, so that the rotation surfaces of the rotating disc and the fins are always parallel to the horizontal plane, and the second driving motor drives the rotation main shaft to rotate in the process of ascending revolution of the rotation main shaft around the revolution main shaft, so that the rotation surfaces of the rotating disc and the fins are always perpendicular to the axis of the rotating arm. In order to make the effect of the rotation of the wing piece better, a wing piece pre-rotation device is arranged on the rotating disc, and one structure and control form of the pre-rotation device is as follows: the motor is supplied with energy by the battery, and the motor output links to each other through the rolling disc in clutch and the rotor subassembly, lets the rolling disc rotate in advance with the mode of remote control, and the device stop work is revolved in advance after whole flapping rotor device normal operating. The prerotation device is used for enabling the wing pieces to rotate in advance and has the function similar to a rotor prerotation system of a self-rotation rotorcraft;
through the technical scheme, compared with the prior art, the flapping rotor wing device with the upward shaft wings vertically running and the downward horizontal running is disclosed, the first driving motor is used for driving the revolution spindle to revolve, and the second driving motor is used for driving the rotation spindle to rotate, so that the rotation of the rotation spindle can be simultaneously realized while the revolution spindle drives the rotating arm and the rotation spindle to revolve; moreover, by utilizing the transmission connection relationship between the second driving motor and the rotation spindle, in the device, in the process of the downward running of the rotation spindle, the rotation spindle is driven by the second driving motor to enable the rotating surface of the rotor assembly arranged on the rotation spindle to be always parallel to the horizontal plane, so that the wing panel continuously provides a larger vertical upward lift force for the aircraft in the process of high-speed rotation, meanwhile, in the process of the upward running of the rotation spindle in the revolution, the second driving motor drives the rotor assembly to enable the rotating surface of the rotor assembly to be always vertical to the axis of the rotating arm, thereby hardly generating resistance or generating smaller resistance in the process of the upward running of the rotor assembly, ensuring that the vertical upward lift force generated in the process of the downward running of the rotor assembly cannot be offset, further providing a larger lift force for the aircraft, and simultaneously ensuring that the rotation spindle revolves around the revolution spindle for 360 degrees, can also rotate 180 degrees, and has the beneficial effects of energy saving and high efficiency. The flapping rotor wing device with the upward shaft wings running vertically and the downward shaft wings running horizontally is reasonable in design, simple in structure, easy to operate and convenient to control, can continuously provide a larger vertical upward lifting force for an aircraft in the revolution and rotation processes of the flapping rotor wing device, is higher in efficiency, and can realize stable takeoff and hovering of the aircraft 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
FIG. 1 is a diagram of the trajectory of a flapping rotor apparatus with an upper wing shaft running vertically and a lower wing shaft running horizontally according to the present invention;
FIG. 2 is a schematic diagram of a flapping rotor apparatus with an upper wing shaft operating vertically and a lower wing shaft operating horizontally according to the present invention;
FIG. 3 is a schematic representation of three vertical arm assemblies of an ascending axial wing and three vertical arm assemblies of a descending horizontal arm flapping rotor according to the present invention;
FIG. 4 is a schematic structural view of a rotor assembly of a flapping rotor apparatus with an upper rotor wing operating vertically and a lower rotor wing operating horizontally in accordance with the present invention;
fig. 5 is a schematic structural diagram of a double-layer rotor assembly in a flapping rotor device with an upper axial wing vertically operating and a lower axial wing horizontally operating according to the present invention.
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
The following describes embodiments of the present invention in detail.
The invention discloses a flapping rotor wing device with an upward shaft wing running vertically and a downward shaft wing running horizontally, 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, meanwhile, 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; when the turning arm 22 is rotated to the vertical state, the second driving motor 32 drives the rotation main shaft 23 to make the rotation surfaces of the rotation disc 43 and the fins 44 perpendicular to the turning arm 22, that is, the rotation surfaces of the rotation disc 43 and the fins 44 are arranged in parallel with the horizontal plane, 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 rotate, so that the rotation surfaces of the rotation disc 43 and the fins 44 are always parallel to the horizontal plane, during the upward revolution of the rotation main shaft 23 around the revolution main shaft 21, the rotation main shaft 23 is driven to rotate by the second driving motor 32, so that the rotation surfaces of the rotation disc 43 and the fins 44 are always perpendicular to the axis of the turning arm.
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 alternative embodiment of the invention, two groups of support frames are provided, and the two groups of support frames are symmetrically arranged on two sides of the aircraft fuselage 7, so that the stability of the aircraft fuselage is ensured, and a larger lift force is provided for takeoff and hovering of the aircraft.
According to a preferred embodiment of the present invention, there are three rotating arms 22, 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, unnecessary energy consumption can be reduced, and a continuous, stable and large lift force can be provided for the aircraft.
According to an alternative embodiment of the present invention, there are four vanes 44, four vanes 44 are uniformly arranged on the circumferential surface of the rotating disk 43, and the directions of the leading edges of the four 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.
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 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.
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 upward shaft wings vertically operating and the downward horizontally operating, the first driving motor is used for driving the revolution spindle to revolve, and the second driving motor is used for driving the rotation spindle to rotate, so that the rotation of the rotation spindle can be simultaneously realized while the revolution spindle drives the rotating arm and the rotation spindle to revolve; moreover, by utilizing the transmission connection relationship between the second driving motor and the rotation spindle, the rotation spindle is driven by the second driving motor in the device to enable the rotation spindle arranged on the rotation spindle to be always parallel to the horizontal plane in the process of descending operation, so that the wing panel continuously provides a larger vertical upward lift force for the aircraft in the process of high-speed rotation, meanwhile, in the process of ascending revolution of the rotation spindle, the second driving motor drives the rotor assembly to enable the rotation plane of the rotor assembly to be always vertical to the axis of the rotating arm, thereby not generating resistance or generating smaller resistance in the process of ascending the rotor assembly, ensuring that the vertical upward lift force generated by the vehicle in the process of descending the rotor assembly cannot be offset, further providing a larger lift force for the aircraft, and simultaneously ensuring that the rotation spindle revolves around the revolution spindle for 360 degrees, can also rotate 180 degrees, and has the beneficial effects of energy saving and high efficiency. The flapping rotor wing device with the upward shaft wings running vertically and the downward shaft wings running horizontally is reasonable in design, simple in structure, easy to operate and convenient to control, and can continuously provide a larger vertical upward lifting 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 device with an upward shaft wing capable of vertically operating and a downward shaft wing capable of horizontally operating is characterized by 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), meanwhile, 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; when the rotating arm (22) rotates to the vertical state, the second driving motor (32) drives the rotation main shaft (23) to enable the rotation surface of the rotating disc (43) and the wing (44) to be vertical to the rotating arm (22), i.e. the rotational planes of the turn disc (43) and the fins (44) are arranged parallel to the horizontal plane, in the process that the rotation main shaft (23) rotates downwards and revolves around the revolution main shaft (21), the second driving motor (32) drives the rotation main shaft (23) to rotate, so that the rotation surfaces of the rotating disc (43) and the vanes (44) are always parallel to the horizontal plane, 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) to rotate, so that the rotation surfaces of the rotating disc (43) and the fins (44) are always perpendicular to the axis of the rotating arm (22).
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 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 supports are symmetrically disposed on opposite sides of said aircraft fuselage (7).
4. The flapping rotor apparatus according to claim 1, wherein the number of the rotating arms (22) is one or more, and one or more of the rotating arms (22) are uniformly arranged on the same circumference, and the number of the rotating main shaft (23) and the number of the rotor assembly (4) arranged corresponding to one or more of the 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 of said rotor assemblies (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).
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, wherein the flapping rotor device comprises a transmission assembly (5), the transmission assembly (5) comprises 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), and the driven wheel (52) is arranged at one end of the revolution spindle (21), and is concentrically and fixedly connected with the revolution spindle (21).
10. The flapping rotor apparatus according to claim 1, further comprising a rotor frame (6), wherein said rotor frame (6) is disposed on said rotation main shaft (23) and fixedly connected to said rotation main shaft (23), and said rotor frame (6) is disposed outside said rotor assembly (4) for protecting said rotor assembly (4) from a high impact force of the airflow.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011346904.1A CN112441229A (en) | 2020-11-26 | 2020-11-26 | Flapping rotor wing device with upward shaft wing capable of vertically running and downward horizontally running |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011346904.1A CN112441229A (en) | 2020-11-26 | 2020-11-26 | Flapping rotor wing device with upward shaft wing capable of vertically running and downward horizontally running |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN112441229A true CN112441229A (en) | 2021-03-05 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202011346904.1A Withdrawn CN112441229A (en) | 2020-11-26 | 2020-11-26 | Flapping rotor wing device with upward shaft wing capable of vertically running and downward horizontally running |
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| Country | Link |
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| CN (1) | CN112441229A (en) |
Cited By (2)
| 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 |
| WO2022111537A1 (en) * | 2020-11-26 | 2022-06-02 | 广东国士健科技发展有限公司 | Flapping rotor device which vertically operates for ascending and horizontally operates for descending |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6382556B1 (en) * | 1999-12-20 | 2002-05-07 | Roger N. C. Pham | VTOL airplane with only one tiltable prop-rotor |
| CN102582832A (en) * | 2012-03-07 | 2012-07-18 | 安徽工业大学 | Flapping-wing aircraft |
| CN103552687A (en) * | 2013-11-11 | 2014-02-05 | 北京航空航天大学 | Novel flapping rotary wing structure and corresponding micro-miniature flapping rotary wing device |
| CN111377050A (en) * | 2020-02-24 | 2020-07-07 | 深圳联合飞机科技有限公司 | Coaxial rotor wing control device |
-
2020
- 2020-11-26 CN CN202011346904.1A patent/CN112441229A/en not_active Withdrawn
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6382556B1 (en) * | 1999-12-20 | 2002-05-07 | Roger N. C. Pham | VTOL airplane with only one tiltable prop-rotor |
| CN102582832A (en) * | 2012-03-07 | 2012-07-18 | 安徽工业大学 | Flapping-wing aircraft |
| CN103552687A (en) * | 2013-11-11 | 2014-02-05 | 北京航空航天大学 | Novel flapping rotary wing structure and corresponding micro-miniature flapping rotary wing device |
| CN111377050A (en) * | 2020-02-24 | 2020-07-07 | 深圳联合飞机科技有限公司 | Coaxial rotor wing control device |
Cited By (2)
| 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 |
| WO2022111537A1 (en) * | 2020-11-26 | 2022-06-02 | 广东国士健科技发展有限公司 | Flapping rotor device which vertically operates for ascending and horizontally operates for descending |
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Application publication date: 20210305 |
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