Unmanned aerial vehicle with rotor wing structure

Abstract

The unmanned aerial vehicle with the rotor wing structure comprises an aerial vehicle body, the top of the aerial vehicle body is connected with a horizontally-arranged unpowered rotor wing through a clutch driving device, the two sides of the aerial vehicle body are fixedly connected with wings, the bottom side wall of each wing is fixedly connected with a mounting rod, and the bottom side wall of each wing is fixedly connected with a rotating shaft. The bottom sides of the two ends of each mounting rod are connected with horizontal propellers through first driving motors, and the tail of the aircraft fuselage is connected with a vertically-arranged tail rotor wing through a direction driving device. According to the aircraft, the advantages that an unmanned aerial vehicle takes off without a runway, takes off and lands vertically, hovers freely and flies flexibly are perfectly combined with the advantages that a rotorcraft is simple in structure, saves energy and is high in safety, and finally the purposes that the carrying capacity is larger, the flight time is longer, the voyage is farther and the flight is safer are achieved.

Description

Technical Field

[0001] The present invention relates to the technical field of unmanned aerial vehicles, and in particular to an unmanned aerial vehicle with a rotor structure. Background Art

[0002] Unmanned aerial vehicles (UAVs) are unmanned aircraft that are controlled by radio remote control equipment and self-contained program control devices. UAVs generally use four or six rotors. By precisely controlling the speed and tilt angle of each rotor, they can hover, climb, descend, and move in the forward, backward, left, and right directions.

[0003] At present, drones on the market mainly use lithium polymer batteries as their main power source. Since all the lift and forward and backward thrust of the drone come from the rotors, when multiple rotors are driven together, not only will the energy consumption be large and the endurance be short, but also due to the multiple rotors, once a motor fails or the battery is exhausted, the drone's flight posture will be out of control and there will be a risk of falling and damage. Summary of the invention

[0004] The present invention provides an unmanned aerial vehicle with a rotor structure to solve the problems raised in the above background technology.

[0005] In order to achieve the above object, the present invention adopts the following technical solutions: An unmanned aerial vehicle with a rotor structure comprises an aircraft fuselage, the top of the aircraft fuselage is connected to a horizontally arranged unpowered rotor through a clutch drive device, wings are fixedly connected to both sides of the aircraft fuselage, a mounting rod is fixedly connected to the bottom side wall of each wing, the bottom sides of both ends of each mounting rod are connected to a horizontal propeller through a first drive motor, and the tail of the aircraft fuselage is connected to a vertically arranged tail rotor through a direction drive device.

[0006] Preferably, the clutch drive device includes a fixed cylinder, which is fixedly connected to the top of the aircraft fuselage, and a second drive motor is fixedly connected to the inside of the fixed cylinder. The output shaft of the second drive motor is connected to the first rotating rod through an electromagnetic clutch coupling, and the first rotating rod passes through the upper side wall of the fixed cylinder. The unpowered rotor is fixedly connected to the upper end of the first rotating rod. The electromagnetic clutch coupling can connect the output shaft of the second drive motor with the first rotating rod and transmit torque when power is turned on, so that the output shaft of the second drive motor rotates with the first rotating rod. When the electromagnetic clutch coupling is powered off, the connection is disconnected, and the output shaft of the first rotating rod and the second drive motor will rotate independently.

[0007] Preferably, the unpowered rotor is made of high-strength, low-weight carbon fiber material.

[0008] Preferably, the direction driving device includes a control cavity, which is opened in the tail part of the aircraft fuselage, and the tail part of the aircraft fuselage is opened with a horizontally arranged arc groove, an electric telescopic cylinder is fixedly connected in the control cavity, and the output end of the electric telescopic cylinder is fixedly connected to a rack plate, and a steering gear is meshed and connected on the side wall of the rack plate, and a rotating column is fixedly connected to the bottom side of the steering gear, and the rotating column is rotatably connected to the side wall of the control cavity, and a third drive motor is fixedly connected to the upper side of the steering gear, and the output shaft of the third drive motor is fixedly connected to a second rotating rod, the second rotating rod passes through the arc groove and is slidably connected to the arc groove, and the tail rotor is fixedly connected to one end of the second rotating rod.

[0009] Preferably, the directional drive device may also use a rudder to control the spin direction.

[0010] Preferably, two support frames are fixedly connected to the bottom side of the aircraft fuselage.

[0011] Preferably, the method for using the unmanned aerial vehicle includes: The first step is that when it is necessary to fly, the four first drive motors can be controlled to drive the four horizontal propellers to rotate. The lift generated by the rotation of the multiple horizontal propellers can make the aircraft fuselage take off vertically. After the aircraft fuselage is fully lifted off, the third drive motor at the tail is started. The third drive motor drives the tail rotor to rotate through the second rotating rod, so that the tail rotor generates horizontal forward thrust, which can make the aircraft fuselage fly forward steadily in the air. When the aircraft fuselage flies horizontally, the unpowered rotor rotates against the wind to generate lift. At this time, the four horizontal propellers can temporarily stop moving because they do not need to provide lift. Only the tail rotor needs to rotate in the vertical direction to push the aircraft fuselage forward. Therefore, the power output of the aircraft fuselage is greatly reduced, which greatly reduces the power consumption of the whole aircraft, thereby achieving the purpose of extending the flight time and increasing the flight distance. The second step is to close the vertical tail rotor at the tail when landing is required, and drive the four horizontal propellers to rotate to achieve vertical landing function and achieve a smooth landing; The third step is that when the aircraft fuselage has a power failure in the air or even an active parking order, the aircraft falls due to insufficient lift. The airflow generated by the fall pushes the unpowered rotor to keep rotating and generate lift, thus achieving a smooth landing in the case of no power or insufficient power, greatly improving the safety of the flight.

[0012] Preferably, when the aircraft fuselage is launched while carrying heavier cargo, the second drive motor and the electromagnetic clutch coupling can be started while the multiple horizontal propellers are rotating. The electromagnetic clutch coupling is energized so that the output shaft of the second drive motor rotates together with the first rotating rod. The second drive motor can drive the unpowered rotor to rotate through the first rotating rod. The rotation of the unpowered rotor can provide lift, which is superimposed on the lift generated by the rotation of the multiple horizontal propellers to achieve the purpose of improving the carrying capacity.

[0013] Preferably, during the horizontal flight of the aircraft fuselage, when the direction of the aircraft fuselage needs to be controlled, the rack plate can be driven to move horizontally by the extension of the electric telescopic cylinder. The horizontal movement of the rack plate can drive the steering gear to rotate. The rotation of the steering gear can drive the tail rotor to rotate through the third drive motor and the second rotating rod, thereby changing the flight direction of the aircraft fuselage.

[0014] Compared with the prior art, the present invention has the following beneficial effects: The aircraft of the present invention perfectly combines the advantages of UAVs, such as no need for runway take-off, vertical take-off and landing, free hovering, and flexible flight, with the advantages of rotorcrafts, such as simple structure, energy saving, and high safety, and ultimately achieves the purpose of greater carrying capacity, longer flight time, longer range, and safer flight.

[0015] The above description is only an overview of the technical solution of the present invention. In order to more clearly understand the technical means of the present invention and implement it according to the contents of the specification, the following is a detailed description of the preferred embodiments of the present invention in conjunction with the accompanying drawings. The specific implementation of the present invention is given in detail by the following embodiments and their accompanying drawings. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] The drawings described herein are used to provide a further understanding of the present invention and constitute a part of this application. The exemplary embodiments of the present invention and their descriptions are used to explain the present invention and do not constitute an improper limitation of the present invention. In the drawings: Figure 1 A schematic diagram of the three-dimensional structure of an unmanned aerial vehicle with a rotor structure proposed by the present invention; Figure 2 This is a front view structural schematic diagram of an unmanned aerial vehicle with a rotor structure proposed by the present invention; Figure 3 This is a schematic diagram of the front structure of an unmanned aerial vehicle with a rotor structure proposed by the present invention; Figure 4 This is a schematic diagram of the internal structure of the fixed cylinder proposed by the present invention; Figure 5 This is a schematic diagram of the cross-sectional structure of the tail of the aircraft fuselage proposed by the present invention; Figure 6This is a schematic diagram of the tail structure of the aircraft fuselage proposed by the present invention.

[0017] In the accompanying drawings, the components represented by the reference numerals are listed as follows: 1. Aircraft fuselage; 2. Fixed cylinder; 3. Support frame; 4. First drive motor; 5. Horizontal propeller; 6. Mounting rod; 7. Tail rotor; 8. First rotating rod; 9. Unpowered rotor; 10. Wing; 11. Second drive motor; 12. Electromagnetic clutch coupling; 13. Second rotating rod; 14. Arc groove; 15. Electric telescopic cylinder; 16. Rack plate; 17. Rotating column; 18. Third drive motor; 19. Steering gear; 20. Control chamber. DETAILED DESCRIPTION

[0018] The principles and features of the present invention are described below in conjunction with the accompanying drawings. The examples given are only used to explain the present invention and are not used to limit the scope of the present invention. The present invention is described in more detail by way of example with reference to the accompanying drawings in the following paragraphs. It should be noted that the accompanying drawings are all in a very simplified form and are not in precise proportions, and are only used to facilitate and clearly assist in explaining the purpose of the embodiments of the present invention.

[0019] See also Figure 1 to Figure 6 In an embodiment of the present invention, an unmanned aerial vehicle with a rotor structure includes an aircraft fuselage 1, two support frames 3 are fixedly connected to the bottom side of the aircraft fuselage 1, a horizontally arranged unpowered rotor 9 is connected to the top of the aircraft fuselage 1 through a clutch drive device, the clutch drive device includes a fixed cylinder 2, the fixed cylinder 2 is fixedly connected to the top of the aircraft fuselage 1, a second drive motor 11 is fixedly connected to the inside of the fixed cylinder 2, an output shaft of the second drive motor 11 is connected to a first rotating rod 8 through an electromagnetic clutch coupling 12, the first rotating rod 8 passes through the upper side wall of the fixed cylinder 2, the unpowered rotor 9 is fixedly connected to the upper end of the first rotating rod 8, and the leading edge of the blade of the unpowered rotor 9 is thin and sharp so as to reduce the friction when cutting the air. Resistance and improve lift efficiency, the trailing edge of the blade of the unpowered rotor 9 is thicker to increase the structural strength of the blade and optimize the aerodynamic performance, the unpowered rotor 9 is made of high-strength, low-weight carbon fiber material, (the electromagnetic clutch coupling 12 adopts the DLY series tooth-type electromagnetic clutch of Tianjin Wenda Hengye Electromagnetic Clutch Manufacturing Co., Ltd., and its specific structure is not described in detail here), the electromagnetic clutch coupling 12 can connect the output shaft of the second drive motor 11 and the first rotating rod 8 when powered on and transmit torque, so that the output shaft of the second drive motor 11 rotates with the first rotating rod 8, and the electromagnetic clutch coupling 12 is disconnected when the power is off, and the first rotating rod 8 and the output shaft of the second drive motor 11 will rotate independently; Wings 10 are fixedly connected to both sides of the aircraft fuselage 1, and a mounting rod 6 is fixedly connected to the bottom side wall of each wing 10. The bottom sides of both ends of each mounting rod 6 are connected to horizontal propellers 5 through a first drive motor 4. The tail of the aircraft fuselage 1 is connected to a vertically arranged tail rotor 7 through a direction driving device. The direction driving device includes a control cavity 20. The control cavity 20 is opened in the tail of the aircraft fuselage 1. The tail of the aircraft fuselage 1 is opened with a horizontally arranged arc groove 14, and the arc groove 14 is connected to the control cavity 20. An electric telescopic cylinder 15 is fixedly connected in the control cavity 20, and the output end of the electric telescopic cylinder 15 is fixedly connected to a rack plate 16. A steering gear 19 is meshed and connected on the side wall of the rack plate 16, and a rotating column 17 is fixedly connected to the bottom side of the steering gear 19. The bottom end of the rotating column 17 is rotatably connected to the side wall of the control chamber 20 through a bearing, and the upper side of the steering gear 19 is fixedly connected to the third drive motor 18, and the output shaft of the third drive motor 18 is fixedly connected to the second rotating rod 13, and the second rotating rod 13 passes through the arc groove 14 and is slidably connected to the arc groove 14, and the tail rotor 7 is fixedly connected to one end of the second rotating rod 13. During the horizontal flight of the aircraft fuselage 1, when it is necessary to control the flight direction of the aircraft fuselage 1, the electric telescopic cylinder 15 can be used to extend and retract to drive the rack plate 16 to move horizontally, and the horizontal movement of the rack plate 16 can drive the steering gear 19 to rotate. The rotation of the steering gear 19 can drive the tail rotor 7 to rotate through the third drive motor 18 and the second rotating rod 13, thereby changing the flight direction of the aircraft fuselage 1.

[0020] The method of using the unmanned aerial vehicle includes: In the first step, when it is necessary to fly, the four first drive motors 4 can be controlled to drive the four horizontal propellers 5 to rotate. The lift generated by the rotation of the multiple horizontal propellers 5 can make the aircraft fuselage 1 take off vertically. After the aircraft fuselage 1 is completely lifted off, the third drive motor 18 at the tail is started. The third drive motor 18 drives the tail rotor 7 to rotate through the second rotating rod 13, so that the tail rotor 7 generates a horizontal forward thrust, which can make the aircraft fuselage 1 fly forward steadily in the air. When the aircraft fuselage 1 flies horizontally, the unpowered rotor 9 rotates against the wind to generate lift. At this time, the four horizontal propellers 5 can temporarily stop the action because they do not need to provide lift. Only the tail rotor 7 in the vertical direction needs to rotate to push the aircraft fuselage 1 forward. Therefore, the power output of the aircraft fuselage 1 is greatly reduced, which greatly reduces the power consumption of the whole machine, thereby achieving the purpose of extending the flight time and increasing the flight distance. It should be noted that when the aircraft fuselage 1 is lifted off carrying heavy cargo, the multiple horizontal propellers 5 can be rotated while the second drive motor 11 and the electromagnetic clutch coupling 12 can be started. The electromagnetic clutch coupling 12 is energized so that the output shaft of the second drive motor 11 rotates together with the first rotating rod 8. The second drive motor 11 can drive the unpowered rotor 9 to rotate through the first rotating rod 8. The rotation of the unpowered rotor 9 can provide lift, which is superimposed on the lift generated by the rotation of the multiple horizontal propellers 5 to achieve the purpose of improving the carrying capacity. The second step is to close the vertical tail rotor 7 at the tail when landing is required, and drive the four horizontal propellers 5 to rotate to realize the vertical landing function, achieve a smooth landing, and hovering function; In the third step, when the aircraft fuselage 1 has a power failure in the air or even an active parking is performed manually, the aircraft falls due to insufficient lift. The airflow generated by the fall pushes the unpowered rotor 9 to keep rotating to generate lift, thereby achieving a smooth landing in the case of no power or insufficient power, greatly improving the safety of the flight.

[0021] The above description is only a preferred embodiment of the present invention and does not limit the present invention in any form. Any ordinary technician in the industry can smoothly implement the present invention as shown in the drawings and described above. However, any equivalent changes, modifications and evolutions made by technicians familiar with the profession without departing from the scope of the technical solution of the present invention using the technical content disclosed above are all equivalent embodiments of the present invention. At the same time, any equivalent changes, modifications and evolutions made to the above embodiments based on the essential technology of the present invention are still within the protection scope of the technical solution of the present invention.

Claims

1. An unmanned aerial vehicle with a rotor structure, comprising an aerial vehicle fuselage (1), characterized in that: The top of the aircraft fuselage (1) is connected to a horizontally arranged non-powered rotor (9) via a clutch drive device, wings (10) are fixedly connected to both sides of the aircraft fuselage (1), a mounting rod (6) is fixedly connected to the bottom side wall of each wing (10), and the bottom sides of both ends of each mounting rod (6) are connected to a horizontal propeller (5) via a first drive motor (4), and the tail of the aircraft fuselage (1) is connected to a vertically arranged tail rotor (7) via a directional drive device.

2. The unmanned aerial vehicle with a rotor structure according to claim 1, characterized in that: The clutch drive device comprises a fixed cylinder (2), the fixed cylinder (2) being fixedly connected to the top of the aircraft fuselage (1), the interior of the fixed cylinder (2) being fixedly connected to a second drive motor (11), the output shaft of the second drive motor (11) being connected to a first rotating rod (8) via an electromagnetic clutch coupling (12), the first rotating rod (8) penetrating the upper side wall of the fixed cylinder (2), the unpowered rotor (9) being fixedly connected to the upper end of the first rotating rod (8), the electromagnetic clutch coupling (12) being able to connect the output shaft of the second drive motor (11) and the first rotating rod (8) and transmit torque when power is on, so that the output shaft of the second drive motor (11) and the first rotating rod (8) rotate together, and the electromagnetic clutch coupling (12) being disconnected when power is off, so that the output shaft of the first rotating rod (8) and the output shaft of the second drive motor (11) rotate independently.

3. The unmanned aerial vehicle with a rotor structure according to claim 2, characterized in that: The unpowered rotor (9) is made of high-strength, low-weight carbon fiber material.

4. The unmanned aerial vehicle with a rotor structure according to claim 3, characterized in that: The direction drive device comprises a control chamber (20), the control chamber (20) being provided in the tail of the aircraft fuselage (1), the tail of the aircraft fuselage (1) being provided with a horizontally arranged arc groove (14), an electric telescopic cylinder (15) being fixedly connected in the control chamber (20), an output end of the electric telescopic cylinder (15) being fixedly connected to a rack plate (16), a side wall of the rack plate (16) being meshingly connected to a steering gear (19), a bottom side of the steering gear (19) being fixedly connected to a rotating column (17), the rotating column (17) being rotatably connected to the side wall of the control chamber (20), an upper side of the steering gear (19) being fixedly connected to a third drive motor (18), an output shaft of the third drive motor (18) being fixedly connected to a second rotating rod (13), the second rotating rod (13) passing through the arc groove (14) and being slidably connected to the arc groove (14), and the tail rotor (7) being fixedly connected to one end of the second rotating rod (13).

5. The unmanned aerial vehicle with a rotor structure according to claim 4, characterized in that: Two support frames (3) are fixedly connected to the bottom side of the aircraft fuselage (1).

6. The unmanned aerial vehicle with a rotor structure according to claim 5, characterized in that: The method of using the unmanned aerial vehicle includes: The first step is to control the four first drive motors (4) to drive the four horizontal propellers (5) to rotate when it is necessary to fly. The lift generated by the rotation of the multiple horizontal propellers (5) can enable the aircraft fuselage (1) to take off vertically. After the aircraft fuselage (1) is completely lifted off, the third drive motor (18) at the tail is started. The third drive motor (18) drives the tail rotor (7) to rotate through the second rotating rod (13), so that the tail rotor (7) generates a horizontal forward thrust, so that the aircraft fuselage (1) can fly forward steadily in the air. When the aircraft fuselage (1) is flying horizontally, the unpowered rotor (9) rotates against the wind to generate lift. At this time, the four horizontal propellers (5) can temporarily stop moving because they do not need to provide lift. Only the tail rotor (7) in the vertical direction needs to rotate to push the aircraft fuselage (1) forward. Therefore, the power output of the aircraft fuselage (1) is greatly reduced, and the power consumption of the entire aircraft is greatly reduced, so as to achieve the purpose of extending the flight time and increasing the flight distance. The second step is to close the vertical tail rotor (7) at the tail when landing is required, and drive the four horizontal propellers (5) to rotate to realize the vertical landing function and achieve a smooth landing; In the third step, when the aircraft fuselage (1) experiences a power failure in the air, or even when the aircraft is stopped manually, the aircraft falls due to insufficient lift, and the airflow generated by the fall pushes the unpowered rotor (9) to keep rotating to generate lift, thereby achieving a smooth landing in the absence of power or insufficient power, greatly improving the safety of the flight.

7. The unmanned aerial vehicle with a rotor structure according to claim 6, characterized in that: When the aircraft fuselage (1) is lifted off carrying heavy cargo, the plurality of horizontal propellers (5) are rotated, and the second drive motor (11) and the electromagnetic clutch coupling (12) are started. The electromagnetic clutch coupling (12) is energized so that the output shaft of the second drive motor (11) rotates together with the first rotating rod (8). The second drive motor (11) can drive the unpowered rotor (9) to rotate via the first rotating rod (8). The rotation of the unpowered rotor (9) can provide lift, which is superimposed on the lift generated by the rotation of the plurality of horizontal propellers (5) to achieve the purpose of improving the carrying capacity.

8. The unmanned aerial vehicle with a rotor structure according to claim 7, characterized in that: During the horizontal flight of the aircraft fuselage (1), when the direction of the aircraft fuselage (1) needs to be controlled, the rack plate (16) can be driven to move horizontally by telescoping the electric telescopic cylinder (15), and the horizontal movement of the rack plate (16) can drive the steering gear (19) to rotate, and the rotation of the steering gear (19) can drive the tail rotor (7) to rotate through the third drive motor (18) and the second rotating rod (13), thereby changing the flight direction of the aircraft fuselage (1).

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