Propeller of heavy-load multi-rotor unmanned aerial vehicle

Abstract

The utility model relates to the technical field of unmanned aerial vehicles, in particular to a propeller of a heavy-load multi-rotor unmanned aerial vehicle, which comprises a blade main body, a rotating shaft mounting hole, a propeller clamp and a motor, a first reference section, a second reference section and a third reference section are arranged on the upper side of the blade main body, and a propeller tip is arranged at the other end of the blade main body. The distance between a rotating shaft of the motor and the blade tip is 800 mm, one end of the blade body rotates to one end of the blade clamp through the rotating shaft mounting hole, the distance between the rotating shaft of the motor and the first reference section is 200 mm, the attack angle of the first reference section is 23 degrees, and the chord length of the first reference section is 17.34 mm. The shape of the paddle is limited through the first reference section, the second reference section and the third reference section, the pressure surface and the suction surface of the paddle are changed, the force effect of rated tension and the maximum tension are improved, and the flight performance of the heavy-load unmanned aerial vehicle is improved.

Description

Technical Field

[0001] This utility model relates to the field of unmanned aerial vehicle (UAV) technology, specifically a propeller for a heavy-duty multi-rotor UAV. Background Technology

[0002] Unmanned aerial vehicles (UAVs) are unmanned aircraft controlled by radio remote control equipment and onboard program control devices, or operated autonomously by an onboard computer, either completely or intermittently. The propellers of multi-rotor UAVs, as an important component of the UAV's power system, mainly convert the output torque of the motor into lift for the UAV.

[0003] However, existing propellers for heavy-payload multi-rotor UAVs suffer from low efficiency and low maximum thrust, which hinders the loiter time and maximum flight speed of these UAVs. Therefore, those skilled in the art have provided a propeller for a heavy-payload multi-rotor UAV to address the problems mentioned in the background section. Utility Model Content

[0004] The purpose of this invention is to provide a propeller for a heavy-duty multi-rotor unmanned aerial vehicle (UAV) to solve the problems mentioned in the background art.

[0005] To achieve the above objectives, this utility model provides the following technical solution:

[0006] A propeller for a heavy-duty multi-rotor UAV includes a blade body, a shaft mounting hole, a propeller clamp, and a motor. The shaft mounting hole is located at one end of the blade body, the propeller clamp is located outside the shaft mounting hole, and the motor is located below the propeller clamp. A first reference section, a second reference section, and a third reference section are provided on the upper side of the blade body, and a propeller tip is provided at the other end of the blade body.

[0007] As a further embodiment of this utility model: the distance between the motor shaft and the blade tip is 800mm, and one end of the blade body rotates to the position of one end of the blade clamp through the shaft mounting hole.

[0008] As a further embodiment of this utility model: the distance between the motor shaft and the first reference segment is 200mm, the angle of attack of the first reference segment is 23°, and the chord length of the first reference segment is 17.34mm.

[0009] As a further embodiment of this utility model: the distance between the motor shaft and the second reference segment is 400mm, the angle of attack of the second reference segment is 12°, and the chord length of the second reference segment is 16.24mm.

[0010] As a further embodiment of this utility model: the distance between the motor shaft and the third reference segment is 600mm, the angle of attack of the third reference segment is 6°, and the chord length of the third reference segment is 12.63mm.

[0011] Compared with the prior art, the beneficial effects of this utility model are: the propeller of the heavy-load multi-rotor UAV of this utility model defines the shape of the blade through the first reference section, the second reference section and the third reference section, changes the pressure surface and suction surface of the blade, improves the force efficiency of the rated thrust and the maximum thrust, and improves the flight performance of the heavy-load UAV. Attached Figure Description

[0012] Figure 1 This is a schematic diagram of the propeller structure of a heavy-duty multi-rotor UAV.

[0013] Figure 2 An assembly drawing of the propeller of a heavy-duty multi-rotor UAV;

[0014] Figure 3 for Figure 1 A cross-sectional view of the first reference segment;

[0015] Figure 4 for Figure 1 Cross-sectional view of the second reference section;

[0016] Figure 5 for Figure 1 Cross-sectional view of the third reference section.

[0017] In the diagram: 1. Blade body; 2. Shaft mounting hole; 3. First reference section; 4. Second reference section; 5. Third reference section; 6. Blade tip; 7. Blade clamp; 8. Motor. Detailed Implementation

[0018] Please see Figures 1-5 In this embodiment of the present invention, a propeller for a heavy-duty multi-rotor UAV includes a blade body 1, a shaft mounting hole 2, a propeller clip 7, and a motor 8. The shaft mounting hole 2 is located at one end of the blade body 1, the propeller clip 7 is located outside the shaft mounting hole 2, and the motor 8 is located below the propeller clip 7. A first reference section 3, a second reference section 4, and a third reference section 5 are provided on the upper side of the blade body 1. A propeller tip 6 is provided at the other end of the blade body 1. The distance between the shaft of the motor 8 and the propeller tip 6 is 800mm. One end of the blade body 1 rotates through the shaft mounting hole 2 to one end of the propeller clip 7. The distance between the shaft of the motor 8 and the first reference section 3 is 200mm, and the angle of attack of the first reference section 3 is 23°. (See reference for details.) Figure 3 In the figure, α, the chord length of the first reference segment 3 is 17.34 mm, the distance between the shaft of motor 8 and the second reference segment 4 is 400 mm, and the angle of attack of the second reference segment 4 is 12°. (See reference for details.) Figure 4 In the figure, β, the chord length of the second reference segment 4 is 16.24 mm, the distance between the shaft of motor 8 and the third reference segment 5 is 600 mm, and the angle of attack of the third reference segment 5 is 6°. (See reference for details.) Figure 5 In the γ section, the chord length of the third reference segment 5 is 12.63 mm.

[0019] Furthermore, the allowable error for the chord length of the first reference segment 3, the second reference segment 4, and the third reference segment 5 is 1mm, the allowable error for the angle of attack of the first reference segment 3, the second reference segment 4, and the third reference segment 5 is 1°, and the allowable error for the distance between the shaft of the motor 8 and the tip of the propeller 6 is 2mm.

[0020] To better illustrate the technical effects of the present invention, the following experiments are conducted:

[0021] The propeller in this application is used as an example, and a propeller disclosed in Chinese Patent (CN211766281U) is selected as a comparative example. Parameter comparisons are made, and tests are conducted on the propeller in the comparative example and the propeller in this application. The force efficiency, which is the ratio of the thrust generated by the propeller to the mechanical power, is calculated. It is found that the force efficiency of the propeller in the comparative example is 6.6 g / w, while the force efficiency of the propeller in this application is 7.5 g / w. The maximum thrust is calculated, and it is found that the maximum thrust of the propeller in the comparative example is 55 kg, while the maximum thrust of the propeller in this application is 80 kg. It can be seen that the force efficiency and maximum thrust of the propeller in this application are both higher than those of the propeller in the comparative example, and are superior to the propeller in the comparative example.

[0022] The working principle of this utility model is as follows: First, the blade body 1 is installed to the outer end of the blade clamp 7 through the shaft mounting hole 2, and the motor 8 is installed on the lower side of the blade clamp 7. Then, a heavy-duty multi-rotor drone is in operation. The motor 8 drives the blade body 1 to rotate through the blade clamp 7 to lift and lower the heavy-duty multi-rotor drone. During the lifting and lowering process, the first reference section 3, the second reference section 4 and the third reference section 5 improve the force efficiency of the rated pull and the maximum pull.

[0023] The above description is only a preferred embodiment of the present utility model, but the protection scope of the present utility model is not limited thereto. Any equivalent substitutions or changes made by those skilled in the art within the technical scope disclosed in the present utility model, based on the technical solution and the inventive concept of the present utility model, should be included within the protection scope of the present utility model.

Claims

1. A propeller of a heavy-load multi-rotor unmanned aerial vehicle, comprising a blade body (1), a rotating shaft mounting hole (2), a propeller clamp (7) and a motor (8), the rotating shaft mounting hole (2) is located at one end of the blade body (1), the propeller clamp (7) is located at the outer side of the rotating shaft mounting hole (2), and the motor (8) is located at the lower side of the propeller clamp (7), characterized in that, The upper side of the paddle body (1) is provided with a first reference section (3), a second reference section (4) and a third reference section (5), and the other end of the paddle body (1) is provided with a blade tip (6).

2. The propeller of a heavy load-carrying multi-rotor unmanned aerial vehicle according to claim 1, characterized in that, The distance between the rotating shaft of the motor (8) and the blade tip (6) is 800mm, and one end of the paddle body (1) is rotatable at the position of one end of the paddle clamp (7) through the rotating shaft mounting hole (2).

3. The propeller of a heavy load-carrying multi-rotor unmanned aerial vehicle according to claim 1, characterized in that, The distance between the rotating shaft of the motor (8) and the first reference section (3) is 200mm, the attack angle of the first reference section (3) is 23°, and the chord length of the first reference section (3) is 17.34mm.

4. The propeller of a heavy load carrying multi-copter unmanned aerial vehicle according to claim 1, wherein, The distance between the rotating shaft of the motor (8) and the second reference section (4) is 400mm, the attack angle of the second reference section (4) is 12°, and the chord length of the second reference section (4) is 16.24mm.

5. The propeller of a heavy load carrying multi-copter unmanned aerial vehicle according to claim 1, wherein, The distance between the rotating shaft of the motor (8) and the third reference section (5) is 600mm, the attack angle of the third reference section (5) is 6°, and the chord length of the third reference section (5) is 12.63mm.

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