WO2019029026A1

WO2019029026A1 - Propeller, power assembly, and aircraft

Info

Publication number: WO2019029026A1
Application number: PCT/CN2017/108494
Authority: WO
Inventors: 刘翊涵; 陈鹏; 王庶
Original assignee: 深圳市大疆创新科技有限公司
Priority date: 2017-08-11
Filing date: 2017-10-31
Publication date: 2019-02-14
Also published as: CN109996723A; CN207403925U

Abstract

A propeller, comprising a propeller hub (10) and propeller blades (20). The propeller blades (20) are connected to the propeller hub (10); at a position whereof the distance to the center of the propeller hub (10) is 40% of the radius of the propeller (100), the propeller blades (20) have angles of attack of 20.37°±2.5° and have chord lengths of 16.95mm±5mm; at a position whereof the distance to the center of the propeller hub (10) is 60% of the radius of the propeller (100), the propeller blades (20) have angles of attack of 14.79°±2.5° and have chord lengths of 13.1mm±5mm; at a position whereof the distance to the center of the propeller hub (10) is 80% of the radius of the propeller (100), the propeller blades (20) have angles of attack of 9.44°±2.5° and have chord lengths of 9.3mm±5mm. Also comprised are a power assembly and an aircraft. The structure of the propeller is optimized, and the flight performance of the aircraft is improved.

Description

Propellers, power components and aircraft

Technical field

The present invention relates to the field of aircraft, and more particularly to propellers, power components and aircraft.

Background technique

The propeller on the aircraft, as an important key component of the aircraft, is used to convert the rotation of the shaft of the motor or engine into thrust or lift.

The propellers in the prior art are mostly rectangular in shape, and have large resistance and low efficiency, resulting in a small flying speed of the aircraft and a short following distance, which seriously affects the flight performance of the aircraft.

Summary of the invention

Embodiments of the present invention provide a propeller, a power assembly, and an aircraft.

A propeller of an embodiment of the present invention includes: a hub and a blade, the blade being coupled to the hub at a distance of 40% of a radius of the propeller from a center of the hub, the blade The angle of attack is 20.37 ° ± 2.5 °, and the chord length of the blade is 16.95 mm ± 5 mm. At 60% of the radius of the propeller from the center of the hub, the blade has an angle of attack of 14.79° ± 2.5° and the blade has a chord length of 13.1 mm ± 5 mm. At an angle of 80% of the radius of the propeller from the center of the hub, the blade has an angle of attack of 9.44 ° ± 2.5 ° and the blade has a chord length of 9.3 mm ± 5 mm.

In certain embodiments, the propeller has a diameter of 136 mm ± 13.6 mm. At an angle of 27.2 mm from the center of the hub, the blade has an angle of attack of 20.37° and the blade has a chord length of 16.95 mm. At an angle of 40.8 mm from the center of the hub, the blade has an angle of attack of 14.79° and the blade has a chord length of 13.1 mm. At an angle of 54.4 mm from the center of the hub, the blade has an angle of attack of 9.44 and the blade has a chord length of 9.3 mm.

In certain embodiments, the angle of attack of the blade is 20.06° ± 2.5° at a distance of 20% of the radius of the propeller from the center of the hub, and the chord length of the blade is 15 mm ± 5mm.

In certain embodiments, the propeller has a diameter of 136 mm ± 13.6 mm. At an angle of 13.6 mm from the center of the hub, the blade has an angle of attack of 20.06° and the blade has a chord length of 15 mm.

In certain embodiments, at 100% of the radius of the propeller from the center of the hub, the blade has an angle of attack of 4.42° ± 2.5° and the blade has a chord length of 7.25 mm ±5mm.

In certain embodiments, the propeller has a diameter of 136 mm ± 13.6 mm. In the distance from the hub At 68 mm, the blade has an angle of attack of 4.42° and the blade has a chord length of 7.25 mm.

In certain embodiments, the paddle includes a downwardly facing lobe, an upwardly facing leaf back, a first side edge coupled to the leaf back and the leaf side, and coupled to the leaf back And a second side edge on the other side of the foliage. The cross section of the leaf surface and the leaf back are both curved, and the first side edge is located below the second side edge.

In some embodiments, the first side edge of the blade is convexly formed with a projection.

In certain embodiments, the paddle includes a connection end coupled to the hub and an end facing away from the hub, the thickness of the blade being tapered from the connection end to the end.

In certain embodiments, the projection is located adjacent the blade at the connection end.

In certain embodiments, the blades are at least two, the at least two blades being centrally symmetric about a center of the hub.

In certain embodiments, the pitch of the paddle is 34 mm.

A power assembly according to an embodiment of the present invention includes a driving member and the propeller according to any one of the above embodiments, wherein the propeller is coupled to the driving member through the hub.

In certain embodiments, the drive member is a motor having a KV value of 2300 ± 100 rpm / (minute volts).

An aircraft according to an embodiment of the present invention includes a power body and a power assembly according to any of the above embodiments, the power assembly being coupled to the body.

In certain embodiments, the aircraft includes a plurality of power components that rotate in different directions.

In certain embodiments, the aircraft is a multi-rotor aircraft.

The propeller, the power assembly and the aircraft provided by the embodiments of the present invention have an angle of attack of 20.37°±2.5° of the blade at a distance of 40% of the radius of the propeller from the center of the hub, and the chord length of the blade is 16.95. Mm ± 5mm. At 60% of the radius of the propeller from the center of the hub, the blade has an angle of attack of 14.79° ± 2.5° and the blade has a chord length of 13.1 mm ± 5 mm. At 80% of the radius of the propeller from the center of the hub, the angle of attack of the blade is 9.44 ° ± 2.5 ° and the chord length of the blade is 9.3 mm ± 5 mm. The blade having a specific shape is defined by the above parameters, and the propeller using the blade can reduce the air resistance, increase the pulling force and efficiency, increase the flight distance of the aircraft and improve the flight performance of the aircraft.

The additional aspects and advantages of the embodiments of the present invention will be set forth in part in the description which follows.

DRAWINGS

The above and/or additional aspects and advantages of the present invention will become apparent from the description of the embodiments in conjunction with the accompanying drawings Obvious and easy to understand, including: new figure modification, graphic description in the manual

FIG. 1 is a schematic plan view of a propeller according to an embodiment of the present invention.

Figure 2 is a cross-sectional view of the B-B section of the propeller of the embodiment of Figure 1 at 27.2 mm from the center of the hub.

Figure 3 is a cross-sectional view of the C-C section of the propeller of the embodiment of Figure 1 at a distance of 40.8 mm from the center of the hub.

Figure 4 is a cross-sectional view of the D-D section of the propeller of the embodiment of Figure 1 at a distance of 54.4 mm from the center of the hub.

Figure 5 is a cross-sectional view of the A-A section of the propeller of the embodiment of Figure 1 at a distance of 13.6 mm from the center of the hub.

Figure 6 is a cross-sectional view of the E-E section of the propeller of the embodiment of Figure 1 at a distance of 68 mm from the center of the hub.

FIG. 7 is a perspective view of a propeller according to an embodiment of the present invention.

FIG. 8 is a schematic plan view of a propeller according to an embodiment of the present invention.

FIG. 9 is a schematic plan view of a propeller according to an embodiment of the present invention.

FIG. 10 is a perspective view of a propeller according to an embodiment of the present invention.

Detailed ways

Exemplary embodiments will be described in detail herein, examples of which are illustrated in the accompanying drawings. The following description refers to the same or similar elements in the different figures unless otherwise indicated. The embodiments described in the following exemplary embodiments do not represent all embodiments consistent with the present invention. Instead, they are merely examples of devices and methods consistent with aspects of the invention as detailed in the appended claims.

The terminology used in the present invention is for the purpose of describing particular embodiments, and is not intended to limit the invention. The singular forms "a", "the" and "the" It should also be understood that the term "and/or" as used herein refers to and encompasses any and all possible combinations of one or more of the associated listed items.

It should be understood that although the terms first, second, third, etc. may be used to describe various information in the present invention, such information should not be limited to these terms. These terms are only used to distinguish the same type of information from each other. For example, the first information may also be referred to as the second information without departing from the scope of the invention. Similarly, the second information may also be referred to as the first information. Depending on the context, the word "if" as used herein may be interpreted as "when" or "when" or "in response to determination."

Embodiments of the present invention provide a propeller, which may be a positive propeller or a reverse propeller. The so-called positive paddle refers to a propeller that rotates clockwise to generate lift from the tail of the motor, such as the tail of the motor. The so-called reverse paddle refers to the propeller that rotates counterclockwise to generate lift from the tail of the motor to the direction of the motor head. . The structure of the positive paddle is mirror symmetrical with the structure of the reverse paddle, so the structure of the propeller will be described below by taking only the positive paddle as an example.

In addition, the terms of the upper and lower orientations appearing in this embodiment are based on the conventional operating posture of the propeller and the aircraft after the propeller is mounted on the aircraft, and should not be considered as limiting.

The propeller, power assembly and aircraft of the present invention will be described in detail below with reference to the accompanying drawings. The features of the embodiments and embodiments described below may be combined with each other without conflict.

Referring to FIGS. 1 through 4, an embodiment of the present invention provides a propeller 100 that includes a hub 10 and a blade 20.

The paddle 20 is attached to the hub 10. Of course, the paddles 20 may be integrally formed with the hub 10, or may be separately processed and fixedly assembled. At an angle D4 from the center of the hub 10 which is 40% of the radius of the propeller 100, the angle of attack α1 of the blade 20 is 20.37° ± 2.5°, and the chord length L1 of the blade 20 is 16.95 mm ± 5 mm. At a distance D3 from the center of the hub 10 that is 60% of the radius of the propeller 100, the angle of attack α2 of the blade 20 is 14.79° ± 2.5°, and the chord length L2 of the blade 20 is 13.1 mm ± 5 mm. At an angle D2 from the center of the hub 10 that is 80% of the radius of the propeller 100, the angle of attack α3 of the blade 20 is 9.44° ± 2.5°, and the chord length L3 of the blade 20 is 9.3 mm ± 5 mm.

In the present embodiment, since the angle of attack α1 of the blade 20 is 20.37°±2.5° at the center of the hub 10 which is 40% of the radius of the propeller 100, the chord length L1 of the blade 20 is 16.95 mm±5 mm. At an angle D6 from the center of the hub 10 that is 60% of the radius of the propeller 100, the angle of attack α2 of the blade 20 is 14.79° ± 2.5°, and the chord length L2 of the blade 20 is 13.1 mm ± 5 mm; The center of 10 is D2 at 80% of the radius of the propeller 100, the angle of attack α3 of the blade 20 is 9.44°±2.5°, and the chord length L3 of the blade 20 is 9.3 mm±5 mm; therefore, the specific parameters are defined by the above parameters. The shape of the blade, the propeller 100 using the blade can reduce air resistance, increase the pulling force and efficiency, increase the aircraft's relay distance and improve the flight performance of the aircraft.

Referring to Table 1, the comparison between the propeller 100 and the test results of the existing propeller provided in this embodiment can be seen from the table. Under the same pulling force, the propeller 100 provided by the embodiment has lower power. That is, under smaller power conditions, there is greater pulling force, thereby reducing power consumption and increasing the cruising distance. Therefore, the propeller 100 provided by the embodiment can significantly increase the pulling force in the extreme case where the lifting density is high in the high-altitude region with reduced density or the low-altitude region, thereby ensuring sufficient power while prolonging the endurance time and improving the flight performance.

Table 1

Wherein, at an angle D4 from the center of the hub 10 which is 40% of the radius of the propeller 100, the angle of attack α1 of the blade 20 may be 17.87° or 20.37° or 22.87°, or 18.37°, 18.87°, 19.37°, 19.87. Any one of °, 20.87°, 21.37°, 21.87°, 22.37°, etc., or any of the above, blade 20 The chord length L1 may be 11.95 mm or 16.95 mm or 21.95 mm, or any one of 12.95 mm, 13.95 mm, 14.95 mm, 15.95 mm, 17.95 mm, 18.95 mm, 19.95 mm, 20.95 mm, or the like, or both The value between. At an angle D3 from the center of the hub 10 that is 60% of the radius of the propeller 100, the angle of attack α2 of the blade 20 may be 12.29° or 14.79° or 17.29°, or 12.79°, 13.29°, 13.79°, 14.29°, The value between any of 15.29°, 15.79°, 16.29°, 16.79°, or the like, or any of the above, the chord length L2 of the blade 20 may be 8.1 mm or 13.1 mm or 18.1 mm, or 9.1 mm, 10.1. A value between any one of mm, 11.1 mm, 12.1 mm, 14.1 mm, 15.1 mm, 16.1 mm, 17.1 mm, or the like. At an angle D2 from the center of the hub 10 that is 80% of the radius of the propeller 100, the angle of attack α3 of the blade 20 may be 6.94° or 9.44° or 11.94°, or 7.44°, 7.94°, 8.44°, 8.94°, The value of any one of 9.94°, 10.44°, 10.94°, 11.44°, or the like, or any of the above, the chord length L3 of the blade 20 may be 4.3 mm or 9.3 mm or 14.3 mm, or 5.3 mm, 6.3. A value between any one of mm, 7.3 mm, 8.3 mm, 10.3 mm, 11.3 mm, 12.3 mm, 13.3 mm, or the like.

The hub 10 may have a cylindrical shape, or the cross section of the hub 10 may have an elliptical shape, a rhombus shape or the like. The center of the hub 10 is provided with a connecting hole for arranging on the output end of the motor. The blade 20 may be in the form of a strip, the blade 20 being coupled to the hub 10 and extending in the radial direction of the hub 10. The angle of attack refers to the angle between the chord of the blade 20 and the incoming flow velocity, and the chord length refers to the length of the cross section of the blade 20.

Referring to FIG. 5, in the present embodiment, optionally, at a distance of 20% from the center of the hub 10 to the radius of the propeller 100, D5, the angle of attack α4 of the blade 20 is 20.06°±2.5°, the blade The chord length L4 of 20 is 15 mm ± 5 mm to further reduce the air resistance of the propeller 100, increasing the pulling force and efficiency. Wherein, the angle of attack α4 of the blade 20 may be 17.56° or 20.06° or 22.56°, or any one of 18.06°, 18.56°, 19.06°, 19.56°, 20.56°, 21.06°, 21.56°, 22.06°, and the like. Or the value between any two of the above, the chord length L4 of the blade 20 may be 10 mm or 15 mm or 20 mm, or any one of 11 mm, 12 mm, 13 mm, 14 mm, 16 mm, 17 mm, 18 mm, 19 mm, or the like. The value between the two.

Referring to FIG. 6, in the present embodiment, optionally, at a distance D1 from the center of the hub 10 that is 100% of the radius of the propeller 100, the angle of attack α5 of the blade 20 is 4.42°±2.5°, the blade The chord length L5 of 20 is 7.25 mm ± 5 mm. To further reduce the air resistance of the propeller 100, increase the pulling force and efficiency. Wherein, the angle of attack α5 of the blade 20 may be 1.92° or 4.42° or 6.92°, or any one of 2.42°, 2.92°, 3.42°, 3.92°, 4.92°, 5.42°, 5.92°, 6.42°, and the like. Or the value between any two of the above, the chord length L5 of the blade 20 may be 2.25 mm or 7.25 mm or 12.25 mm, or 3.25 mm, 4.25 mm, 5.25 mm, 6.25 mm, 8.25 mm, 9.25 mm, 10.25 mm. Any one of 11.25 mm or the like or a value between any two of the above.

Referring again to FIG. 1 to FIG. 4, in the present embodiment, optionally, the diameter of the propeller 100 is 136 mm ± 13.6 mm. At an angle of 27.2 mm from the center of the hub 10, the angle of attack α1 of the blade 20 is 20.37°, the blade The chord length L1 of 20 is 16.95 mm. At an angle D3 of 40.8 mm from the center of the hub 10, the angle of attack α2 of the blade 20 is 14.79°, and the chord length L2 of the blade 20 is 13.1 mm. At an angle D2 of 54.4 mm from the center of the hub 10, the angle of attack α3 of the blade 20 is 9.44°, and the chord length L3 of the blade 20 is 9.3 mm. Thereby, the air resistance of the propeller 100 can be further reduced, and the pulling force and efficiency can be improved. The diameter of the propeller 100 may be 122.4 mm or 136 mm or 149.6 mm, or any one of 122.5 mm, 125 mm, 130 mm, 135 mm, 140 mm, 145 mm, 149 mm, or the like, or a value between any two of the above.

Referring again to FIG. 5, in the present embodiment, optionally, the diameter of the propeller 100 is 136 mm ± 13.6 mm. At an angle D5 of 13.6 mm from the center of the hub 10, the angle of attack α4 of the blade 20 is 20.06°, and the chord length L4 of the blade 20 is 15 mm. Thereby, the air resistance of the propeller 100 can be further reduced, and the pulling force and efficiency can be improved. The diameter of the propeller 100 may be 122.4 mm or 136 mm or 149.6 mm, or any one of 122.5 mm, 125 mm, 130 mm, 135 mm, 140 mm, 145 mm, 149 mm, or the like, or a value between any two of the above.

Referring again to FIG. 6, in the present embodiment, optionally, the diameter of the propeller 100 is 136 mm ± 13.6 mm. At an angle of 68 mm from the center of the hub 10, the angle of attack α5 of the blade 20 is 4.42°, and the chord length L5 of the blade 20 is 7.25 mm. Thereby, the air resistance of the propeller 100 can be further reduced, and the pulling force and efficiency can be improved. The diameter of the propeller 100 may be 122.4 mm or 136 mm or 149.6 mm, or any one of 122.5 mm, 125 mm, 130 mm, 135 mm, 140 mm, 145 mm, 149 mm, or the like, or a value between any two of the above.

Referring to FIG. 6 to FIG. 9, in the present embodiment, optionally, the blade 20 includes a downward facing leaf surface 21, an upward facing leaf back 22, and a first side connected to the leaf back 22 and the leaf surface 21 side. An edge 23, and a second edge 24 joined to the other side of the leaf back 22 and the leaf surface 21. The cross-section of the leaf surface 21 and the leaf back 22 are both curved and the first edge 23 is located below the second edge 24. Since the cross-sections of the leaf surface 21 and the leaf back 22 are both curved and the first edge 23 is located below the second edge 24, the resistance of the air can be reduced and the pulling force of the blade 20 can be increased.

Referring to Fig. 10, in the present embodiment, optionally, the paddle 20 includes a connecting end connected to the hub 10 and an end facing away from the hub 10, and the thickness of the paddle 20 is gradually reduced from the connecting end to the end. Since there is no sharp twist on the blade 20, the stress is relatively uniform, and the stress at the individual position is prevented from being excessively large, the structural strength is high, and it is not easy to be broken, thereby improving the working reliability of the propeller 100. In addition, the end of the blade 20 away from the hub 10 is the thinnest portion of the blade 20, which is advantageous for reducing air resistance.

In this embodiment, optionally, the first edge 23 of the blade 20 is convexly formed with a protrusion 231. Thereby, the pulling force of the blade 20 can be further increased. Wherein, the protruding portion 231 can be located near the connecting end of the blade 20 to further enhance the pulling force of the blade 20.

In this embodiment, optionally, the blades 20 are at least two, and at least two blades 20 are centrally symmetric with respect to the center of the hub 10. Thereby, the balance of the propeller 100 can be improved.

In this embodiment, optionally, the pitch of the blade 20 is 34 mm. Thereby, the resistance of the air can be reduced and the paddle can be increased The tension of the leaf 20.

In summary, the propeller 100 using the blade of the above embodiment of the present invention can significantly increase the pulling force in the plateau region, thereby ensuring sufficient power redundancy. At the same time, to a certain extent, the performance is balanced, the distance of the following is increased, and the flight performance of the aircraft is improved. Compared with the propeller 100 currently available on the market, the propeller 100 using the blade has a greater pulling force under a smaller power condition, thereby reducing power consumption and increasing the cruising distance. In the extreme case of high-altitude areas with reduced density or high take-off weights, it can significantly increase the pulling force, ensure sufficient power while prolonging the battery life and improving flight performance.

Since the structure of the reverse paddle is mirror symmetrical with the structure of the positive paddle, the structure of the reverse paddle will not be described again.

Embodiments of the present invention provide a power assembly including a drive member and a propeller 100 of any of the embodiments of the present invention, the propeller 100 being coupled to the drive member via the hub 10. The specific structure of the propeller 100 is similar to the foregoing embodiment, and details are not described herein again. That is, the description of the propeller 100 in the above embodiments and embodiments is equally applicable to the power assembly provided by the embodiment of the present invention.

In the present embodiment, since the angle of attack α1 of the blade 20 is 20.37°±2.5° at the center of the hub 10 which is 40% of the radius of the propeller 100, the chord length L1 of the blade 20 is 16.95 mm±5 mm. . At a distance D3 from the center of the hub 10 that is 60% of the radius of the propeller 100, the angle of attack α2 of the blade 20 is 14.79° ± 2.5°, and the chord length L2 of the blade 20 is 13.1 mm ± 5 mm. At a distance D2 from the center of the hub 10 which is 80% of the radius of the propeller 100, the angle of attack α3 of the blade 20 is 9.44°±2.5°, and the chord length L3 of the blade 20 is 9.3 mm±5 mm, therefore, the above parameters A blade having a specific shape is defined, and the propeller 100 using the blade can reduce air resistance, increase pulling force and efficiency, increase the travel distance of the aircraft, and improve the flight performance of the aircraft.

In this embodiment, optionally, the motor has a KV value of 2300 ± 100 rpm / (minute volt). Thereby, the dynamic performance of the power unit can be ensured.

Embodiments of the present invention provide an aircraft including a fuselage and a power assembly of any of the embodiments of the present invention, the power assembly being coupled to the fuselage. The specific structure of the power component is similar to the foregoing embodiment, and details are not described herein again. That is, the description of the propeller 100 in the above embodiments and embodiments is equally applicable to the aircraft provided by the embodiment of the present invention.

In this embodiment, optionally, the aircraft includes a plurality of power components, and the plurality of power components have different rotation directions.

In this embodiment, optionally, the aircraft is a multi-rotor aircraft.

In the present embodiment, since the angle of attack α1 of the blade 20 is 20.37°±2.5° at the center of the hub 10 which is 40% of the radius of the propeller 100, the chord length L1 of the blade 20 is 16.95 mm±5 mm. . At a distance D3 from the center of the hub 10 that is 60% of the radius of the propeller 100, the angle of attack α2 of the blade 20 is 14.79° ± 2.5°, and the chord length L2 of the blade 20 is 13.1 mm ± 5 mm. At a distance D2 from the center of the hub 10 which is 80% of the radius of the propeller 100, the angle of attack α3 of the blade 20 is 9.44°±2.5°, and the chord length L3 of the blade 20 is 9.3 mm±5 mm, therefore, the above parameters A blade having a specific shape is defined, and the propeller 100 using the blade can reduce air resistance and improve Pulling and efficiency increase the flight distance of the aircraft and improve the flight performance of the aircraft.

The above is only a preferred embodiment of the present invention, and is not intended to limit the scope of the present invention. The present invention has been described above by way of a preferred embodiment, but is not intended to limit the invention, and any person skilled in the art, Equivalent embodiments that may be modified or modified to equivalent variations may be made without departing from the technical scope of the present invention, without departing from the scope of the present invention. It is still within the scope of the technical solution of the present invention to make any simple modifications, equivalent changes and modifications to the above embodiments.

The disclosure of this patent document contains material that is subject to copyright protection. This copyright is the property of the copyright holder. The copyright owner has no objection to the reproduction of the patent document or the patent disclosure in the official records and files of the Patent and Trademark Office.

Claims

A propeller includes: a hub and a blade, the blade being coupled to the hub, wherein:

At a distance of 40% of the radius of the propeller from the center of the hub, the angle of attack of the blade is 20.37 ° ± 2.5 °, the chord length of the blade is 16.95 mm ± 5 mm;

At a distance of 60% of the radius of the propeller from the center of the hub, the angle of attack of the blade is 14.79 ° ± 2.5 °, the chord length of the blade is 13.1 mm ± 5 mm;

At an angle of 80% of the radius of the propeller from the center of the hub, the blade has an angle of attack of 9.44 ° ± 2.5 ° and the blade has a chord length of 9.3 mm ± 5 mm.
A propeller according to claim 1 wherein:

The diameter of the propeller is 136 mm ± 13.6 mm;

At an angle of 27.2 mm from the center of the hub, the blade has an angle of attack of 20.37°, and the blade has a chord length of 16.95 mm;

The angle of attack of the blade is 14.79° at a distance of 40.8 mm from the center of the hub, and the chord length of the blade is 13.1 mm;

At an angle of 54.4 mm from the center of the hub, the blade has an angle of attack of 9.44 and the blade has a chord length of 9.3 mm.
The propeller according to claim 1, wherein said blade has an angle of attack of 20.06° ± 2.5° at a distance of 20% of a radius of said propeller from a center of said hub, said blade The chord length is 15mm ± 5mm.
A propeller according to claim 3, wherein:

The diameter of the propeller is 136 mm ± 13.6 mm;

At an angle of 13.6 mm from the center of the hub, the blade has an angle of attack of 20.06° and the blade has a chord length of 15 mm.
The propeller according to claim 1, wherein said blade has an angle of attack of 4.42 ° ± 2.5 ° at a distance of 100% of a radius of said propeller from a center of said hub The chord length is 7.25 mm ± 5 mm.
A propeller according to claim 5, wherein:

The diameter of the propeller is 136 mm ± 13.6 mm;

At an angle of 68 mm from the center of the hub, the blade has an angle of attack of 4.42° and the blade has a chord length of 7.25 mm.
A propeller according to any one of claims 1 to 6, wherein:

The paddle includes a downwardly facing leaf surface, an upwardly facing leaf back, a first side edge coupled to the leaf back and the leaf side, and a second side connected to the leaf back and the leaf surface Second side edge of the side;

The cross section of the leaf surface and the leaf back are both curved, and the first side edge is located below the second side edge.
The propeller according to claim 7, wherein the first side edge of the blade is convexly formed with a projection.
The propeller according to claim 8, wherein said blade includes a connecting end connected to said hub and an end facing away from said hub, said blade having a thickness from said connecting end to said The end is gradually reduced.
The propeller according to claim 9, wherein the projection is located at the blade near the connection end.
A propeller according to any one of claims 1 to 6, wherein the blades are at least two, the at least two blades being centrally symmetrical about a center of the hub.
The propeller according to any one of claims 1 to 6, wherein the pitch of the blade is 34 mm.
A power assembly including a drive member and a propeller, characterized by:

The propeller is connected to the driving member through the hub;

The propeller includes a hub and a blade, the blade being coupled to the hub;

At a distance of 40% of the radius of the propeller from the center of the hub, the angle of attack of the blade is 20.37 ° ± 2.5 °, the chord length of the blade is 16.95 mm ± 5 mm;

At a distance of 60% of the radius of the propeller from the center of the hub, the angle of attack of the blade is 14.79 ° ± 2.5 °, the chord length of the blade is 13.1 mm ± 5 mm;

At an angle of 80% of the radius of the propeller from the center of the hub, the angle of attack of the blade is 9.44 ° ± 2.5°, the chord length of the blade is 9.3 mm ± 5 mm;

The drive member is a motor having a KV value of 2300 ± 100 rpm / (minute volt).
The power assembly of claim 13 wherein:

The diameter of the propeller is 136 mm ± 13.6 mm;

At an angle of 27.2 mm from the center of the hub, the blade has an angle of attack of 20.37°, and the blade has a chord length of 16.95 mm;

The angle of attack of the blade is 14.79° at a distance of 40.8 mm from the center of the hub, and the chord length of the blade is 13.1 mm;

At an angle of 54.4 mm from the center of the hub, the blade has an angle of attack of 9.44 and the blade has a chord length of 9.3 mm.
The power assembly of claim 13 wherein said blade has an angle of attack of 20.06° ± 2.5° at a distance of 20% of a radius of said propeller from a center of said hub The chord length of the leaves is 15 mm ± 5 mm.
The power assembly of claim 15 wherein:

The diameter of the propeller is 136 mm ± 13.6 mm;

At an angle of 13.6 mm from the center of the hub, the blade has an angle of attack of 20.06° and the blade has a chord length of 15 mm.
The power assembly of claim 13 wherein said blade has an angle of attack of 4.42° ± 2.5° at a distance of 100% of a radius of said propeller from a center of said hub The chord length of the leaves is 7.25 mm ± 5 mm.
The power assembly of claim 17 wherein:

The diameter of the propeller is 136 mm ± 13.6 mm;

At an angle of 68 mm from the center of the hub, the blade has an angle of attack of 4.42° and the blade has a chord length of 7.25 mm.
A power assembly according to any of claims 13-18, characterized in that:

The blade includes a downwardly facing leaf surface, an upwardly facing leaf back, a first side coupled to the leaf back and the leaf side a rim, and a second side edge connected to the leaf back and the other side of the leaf surface;

The cross section of the leaf surface and the leaf back are both curved, and the first side edge is located below the second side edge.
The power assembly of claim 19 wherein the first side edge of the blade is convexly formed with a projection.
A power assembly according to claim 20, wherein said blade includes a connecting end coupled to said hub and an end facing away from said hub, said blade having a thickness from said connecting end to said The end is gradually reduced.
The power assembly of claim 21 wherein said projection is located adjacent said blade end.
A power assembly according to any one of claims 13-18, wherein the blades are at least two, the at least two blades being centrally symmetrical about the center of the hub.
A power assembly according to any of claims 13-18, wherein the pitch of the blade is 34 mm.
An aircraft comprising a fuselage and a power assembly, characterized by:

The power assembly is coupled to the fuselage, the power assembly including a drive member and a propeller;

The propeller is connected to the driving member through the hub;

The propeller includes a hub and a blade, the blade being coupled to the hub;

At a distance of 40% of the radius of the propeller from the center of the hub, the angle of attack of the blade is 20.37 ° ± 2.5 °, the chord length of the blade is 16.95 mm ± 5 mm;

At a distance of 60% of the radius of the propeller from the center of the hub, the angle of attack of the blade is 14.79 ° ± 2.5 °, the chord length of the blade is 13.1 mm ± 5 mm;

At an angle of 80% of the radius of the propeller from the center of the hub, the angle of attack of the blade is 9.44 ° ± 2.5 °, and the chord length of the blade is 9.3 mm ± 5 mm;

The drive member is a motor having a KV value of 2300 ± 100 rpm / (minute volt).
The aircraft of claim 25 wherein:

The diameter of the propeller is 136 mm ± 13.6 mm;

At an angle of 27.2 mm from the center of the hub, the blade has an angle of attack of 20.37°, and the blade has a chord length of 16.95 mm;

The angle of attack of the blade is 14.79° at a distance of 40.8 mm from the center of the hub, and the chord length of the blade is 13.1 mm;

At an angle of 54.4 mm from the center of the hub, the blade has an angle of attack of 9.44 and the blade has a chord length of 9.3 mm.
The aircraft according to claim 25, wherein said blade has an angle of attack of 20.06° ± 2.5° at a distance of 20% of a radius of said propeller from a center of said hub, said blade The chord length is 15mm ± 5mm.
The aircraft of claim 27 wherein:

The diameter of the propeller is 136 mm ± 13.6 mm;

At an angle of 13.6 mm from the center of the hub, the blade has an angle of attack of 20.06° and the blade has a chord length of 15 mm.
The aircraft according to claim 25, wherein at an angle of 100% of a radius of said propeller from a center of said hub, said blade has an angle of attack of 4.42 ° ± 2.5 °, said blade The chord length is 7.25 mm ± 5 mm.
The aircraft of claim 29 wherein:

The diameter of the propeller is 136 mm ± 13.6 mm;

At an angle of 68 mm from the center of the hub, the blade has an angle of attack of 4.42° and the blade has a chord length of 7.25 mm.
An aircraft according to any one of claims 25-30, characterized in that:

The paddle includes a downwardly facing leaf surface, an upwardly facing leaf back, a first side edge coupled to the leaf back and the leaf side, and a second side connected to the leaf back and the leaf surface Second side edge of the side;

The cross section of the leaf surface and the leaf back are both curved, and the first side edge is located below the second side edge.
The aircraft according to claim 31, wherein the first side edge of the blade is convexly formed with a projection.
The aircraft according to claim 32, wherein said blade includes a connecting end coupled to said hub and an end facing away from said hub, said blade having a thickness from said connecting end to said The end is gradually reduced.
The aircraft according to claim 33, wherein said projection is located at said blade adjacent said connecting end.
An aircraft according to any one of claims 25 to 30, wherein the blades are at least two, the at least two blades being centrally symmetrical about the center of the hub.
An aircraft according to any one of claims 25 to 30, wherein the pitch of the blade is 34 mm.
An aircraft according to any one of claims 25-36, wherein the aircraft comprises a plurality of power components, the plurality of power components having different directions of rotation.
The aircraft of any of claims 25-36, wherein the aircraft is a multi-rotor aircraft.