CN114466791A

CN114466791A - Screw, power component and aircraft

Info

Publication number: CN114466791A
Application number: CN202080069096.0A
Authority: CN
Inventors: 周炜翔; 李齐; 陈旭
Original assignee: SZ DJI Technology Co Ltd
Current assignee: SZ DJI Technology Co Ltd
Priority date: 2020-04-21
Filing date: 2020-12-10
Publication date: 2022-05-10
Also published as: WO2021212869A1; CN213323651U

Abstract

A propeller (100) comprises a hub (10) and blades (20), the blades (20) are connected to the hub (10), and the angles of attack of the blades (20) are 19.74 DEG + -2.5 DEG, 17.51 DEG + -2.5 DEG, 14.67 DEG + -2.5 DEG and 11.70 DEG + -2.5 DEG, respectively, at a distance of 43.7%, 54.7%, 65.6% and 76.6% from the center of the hub (10) of the radius of the propeller (100). A power assembly (200) comprises a driver (30) and a propeller (100), the propeller (100) being connected to the driver (30) by a hub (10). An aircraft (1000) includes a fuselage (50) and a power assembly (200), the power assembly (200) being coupled to the fuselage (50). According to the arrangement, air resistance can be reduced, the pulling force of the paddle is improved, the overall noise of the aircraft is reduced, the pulling force and the propeller efficiency of the paddle are improved, the front flying working condition of the aircraft can be optimized, and the good force effect, the pulling force and the rotating speed characteristic can be achieved under the condition that the front flying working condition is guaranteed, so that the front flying performance of the whole aircraft is guaranteed.

Description

Screw, power component and aircraft

PRIORITY INFORMATION

The present application claims priority and benefit from the patent application No. 202020607009.X filed from the chinese intellectual property office on 21/04 in 2020, and is incorporated herein by reference in its entirety.

Technical Field

The application relates to the field of aircrafts, in particular to a propeller, a power assembly and an aircraft.

Background

Propellers on aircraft, which are important key components of aircraft, are used to convert the rotation of a rotating shaft in a motor or an engine into thrust or lift. Generally, in a propeller product, small-sized blades cause too large hovering power consumption due to too high load of a blade disc, and large-sized blades cause too large blade profile resistance and low efficiency due to the fact that an airfoil deviates from a design working point to work.

Disclosure of Invention

The embodiment of the application provides a propeller, a power assembly and an aircraft.

The propeller of the embodiment of the application comprises a hub and blades, wherein the blades are connected to the hub. At 43.7% of the radius of the propeller from the center of the hub, the angle of attack of the blades is 19.74 ° ± 2.5 °; at 54.7% of the radius of the propeller from the center of the hub, the angle of attack of the blade is 17.51 ° ± 2.5 °; the angle of attack of the blades is 14.67 ° ± 2.5 ° at 65.6% of the radius of the propeller from the center of the hub; the angle of attack of the blades is 11.70 ° ± 2.5 ° at 76.6% of the radius of the propeller from the center of the hub.

In certain embodiments, the angle of attack of the blades is 21.62 ° ± 2.5 ° at 26.2% of the radius of the propeller from the center of the hub; and/or the angle of attack of the blades is 21.47 ° ± 2.5 ° at a distance from the centre of the hub of 32.8% of the radius of the propeller; and/or the angle of attack of the blades is 8.75 ° ± 2.5 ° at a distance from the centre of the hub of 87.5% of the radius of the propeller; and/or the angle of attack of the blades is 4.29 ° ± 2.5 ° at a distance from the centre of the hub of 98.4% of the radius of the propeller; and/or the angle of attack of the blade is 21.62 ° at 24mm from the centre of the hub; and/or the angle of attack of the blades is 21.47 ° at 30mm from the centre of the hub; and/or the angle of attack of the blades is 19.74 ° at 40mm from the centre of the hub; and/or the angle of attack of the blade is 17.51 ° at 50mm from the centre of the hub; and/or the angle of attack of the blades is 14.67 ° at 60mm from the centre of the hub; and/or the angle of attack of the blades is 11.70 ° at 70mm from the centre of the hub; and/or the angle of attack of the blades is 8.75 ° at a distance of 80mm from the centre of the hub; and/or the angle of attack of the blades is 4.29 ° at 90mm from the centre of the hub.

In certain embodiments, the chord length of the blades is 20.24mm ± 2.02mm at 43.7% of the radius of the propeller from the center of the hub; and/or the chord length of the blade is 18.57mm ± 1.86mm at a distance of 54.7% of the radius of the propeller from the centre of the hub; and/or the chord length of the blades is 16.75mm ± 1.68mm at a distance of 65.6% of the radius of the propeller from the centre of the hub; and/or the chord length of the blades is 14.74mm + -1.47 mm at a distance of 76.6% of the radius of the propeller from the center of the hub; and/or the chord length of the blade is 20.24mm at a distance of 40mm from the center of the hub; and/or the chord length of the blade is 18.57mm at a distance of 50mm from the center of the hub; and/or the chord length of the blade is 16.75mm at a distance of 60mm from the center of the hub; and/or the chord length of the blade is 14.74mm at a distance of 70mm from the centre of the hub.

In some embodiments, the chord length of the blade is 20.74mm ± 2.07mm at 26.2% of the radius of the propeller from the center of the hub; and/or the chord length of the blades is 21.63mm ± 2.16mm at a distance of 32.8% of the radius of the propeller from the centre of the hub; and/or the chord length of the blades is 12.44mm ± 1.24mm at 87.5% of the radius of the propeller from the center of the hub; and/or the chord length of the blades is 6.05mm +/-0.61 mm at a distance of 98.4% of the radius of the propeller from the center of the hub; and/or the chord length of the blade is 20.74mm at a distance of 24mm from the centre of the hub; and/or the chord length of the blade is 21.63mm at a distance of 30mm from the center of the hub; and/or the chord length of the blade is 12.44mm at a distance of 80mm from the center of the hub; and/or the chord length of the blade is 6.05mm at 90mm from the center of the hub.

In certain embodiments, the diameter of the propeller is 182.88mm ± 18.0 mm; and/or the pitch of the blade is 3.66 + -0.6 inches.

In some embodiments, the blade comprises a blade root, a blade tip facing away from the blade root, opposite pressure and suction surfaces, a leading edge connected to one side of the pressure and suction surfaces, a trailing edge connected to the other side of the pressure and suction surfaces, and a sweep formed at the blade tip, the sweep extending obliquely from the leading edge to the trailing edge; the blade tip extends obliquely towards the side where the suction surface is located along the span direction of the blade.

In some embodiments, the blade forms a return bend near the tip, the leading edge extends obliquely from the return bend in the span direction of the blade towards the side on which the suction surface is located, the sweep extends obliquely from the return bend from the leading edge to the trailing edge, and the return bend is 91.9% of the radius of the propeller from the center of the hub.

In some embodiments, the trailing edge is convexly formed with a curved trailing edge camber proximate the root; and/or the number of the blades is at least two, and the at least two blades are connected to the hub and are in central symmetry with the center of the hub; and/or the blade has a central axis passing through the center of the hub, the leading edge has a leading edge tangent parallel to the central axis, the trailing edge has a trailing edge tangent parallel to the central axis, the sweep is located between the leading edge tangent and the trailing edge tangent; and/or the suction surface and the pressure surface are both curved surfaces.

The power assembly of an embodiment of the present application comprises a drive member and the propeller of any of the above embodiments, the propeller being connected to the drive member via the hub.

In certain embodiments, the drive is an electric motor having a KV value of 1860 ± 60 revolutions per minute-volt.

The aircraft of the embodiment of the application comprises a fuselage and the power assembly of any one of the above embodiments, wherein the power assembly is connected with the fuselage.

In certain embodiments, the aircraft includes a plurality of power assemblies that rotate in different directions, and the aircraft is a multi-rotor aircraft.

In the aircraft, the power assembly and the propeller of the embodiment of the application, the attack angle of the blades is 19.74 degrees +/-2.5 degrees at the position which is 43.7 percent of the radius of the propeller away from the center of the propeller hub; at a distance of 54.7% of the radius of the propeller from the center of the hub, the angle of attack of the blades is 17.51 ° ± 2.5 °; the angle of attack of the blades is 14.67 ° ± 2.5 ° at a distance from the centre of the hub of 65.6% of the radius of the propeller; the angle of attack of the blades is 11.70 degrees plus or minus 2.5 degrees at a position which is 76.6 percent of the radius of the propeller away from the center of the propeller hub; therefore, the propeller with the blades in the specific shape is limited by the parameters, the hovering power consumption can be effectively reduced by the propeller with the blades, the efficiency is improved, the endurance time is increased, and the flight performance of the aircraft is improved. In addition, the design of the paddle can also optimize the front flying working condition of the aircraft, and ensure that the front flying working condition can also have good force effect and tensile force-rotating speed characteristics, thereby ensuring the front flying performance of the whole aircraft.

Additional aspects and advantages of embodiments of the present application will be set forth in part in the description which follows and, in part, will be obvious from the description, or may be learned by practice of embodiments of the present application.

Drawings

The above and/or additional aspects and advantages of the present application will become apparent and readily appreciated from the following description of the embodiments, taken in conjunction with the accompanying drawings of which:

fig. 1 is a schematic plan view of a propeller provided in an embodiment of the present application.

Figure 2 is a cross-sectional view of section a-a at 24mm from the center of the hub in the propeller of the embodiment shown in figure 1.

Figure 3 is a cross-sectional view of the section B-B in the propeller of the embodiment shown in figure 1 at 30mm from the centre of the hub.

Figure 4 is a cross-sectional view of the C-C section at 40mm from the center of the hub in the propeller of the embodiment shown in figure 1.

Figure 5 is a cross-sectional view of the propeller of the embodiment of figure 1 taken along the D-D section at a distance of 50mm from the center of the hub.

Figure 6 is a cross-sectional view of the section E-E at 60mm from the center of the hub in the propeller of the embodiment shown in figure 1.

Figure 7 is a cross-sectional view of the section F-F in the propeller of the embodiment shown in figure 1 at a distance of 70mm from the centre of the hub.

Figure 8 is a cross-sectional view of the G-G section at 80mm from the center of the hub in the propeller of the embodiment shown in figure 1.

Figure 9 is a cross-sectional view of the H-H section in the propeller of the embodiment shown in figure 1 at 90mm from the centre of the hub.

Fig. 10 is a perspective view of a blade of a propeller according to an embodiment of the present application.

Fig. 11 is a front view of the blades of the propeller of the embodiment shown in fig. 10.

Fig. 12 is a bottom view of the blades of the propeller of the embodiment shown in fig. 10.

Fig. 13 is a top view of the blades of the propeller of the embodiment shown in fig. 10.

Fig. 14 is a right side view of the blades of the propeller of the embodiment shown in fig. 10.

Fig. 15 is a schematic plan view of an aircraft according to an embodiment of the present application.

Fig. 16 is a blade tension-force effect diagram of a propeller provided in an embodiment of the present application.

Detailed Description

Reference will now be made in detail to the exemplary embodiments, examples of which are illustrated in the accompanying drawings. When the following description refers to the accompanying drawings, like numbers in different drawings represent the same or similar elements unless otherwise indicated. The embodiments described in the following exemplary embodiments do not represent all embodiments consistent with the present application. Rather, they are merely examples of apparatus and methods consistent with certain aspects of the present application, as detailed in the appended claims.

The terminology used herein is for the purpose of describing particular embodiments only and is not intended to be limiting of the application. As used in this application and the appended claims, the singular forms "a", "an", and "the" are intended to include the plural forms as well, unless the context clearly indicates otherwise. 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 is to be understood that although the terms first, second, third, etc. may be used herein to describe various information, such information should not be limited to these terms. These terms are only used to distinguish one type of information from another. For example, first information may also be referred to as second information, and similarly, second information may also be referred to as first information, without departing from the scope of the present application. The word "if" as used herein may be interpreted as "at … …" or "when … …" or "in response to a determination", depending on the context.

The terms upper, lower, etc. are used in this embodiment with reference to the propeller after it is mounted on the aircraft and to the normal operating attitude of the aircraft and should not be considered limiting.

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

Referring to fig. 1, the present embodiment provides a propeller 100, and the propeller 100 includes a hub 10 and blades 20. Blades 20 are attached to hub 10. Of course, the blades 20 may be integrally formed with the hub 10, or may be separately machined and then fixedly mounted as a single piece.

Referring to fig. 4-7, at a distance D3 of 43.7% of the radius of the propeller 100 from the center of the hub 10, the angle of attack of the blades is 19.74 ° ± 2.5 °; at a distance D4 of 54.7% of the radius of the propeller 100 from the center of the hub 10, the angle of attack of the blades is 17.51 ° ± 2.5 °; at a distance D5 of 65.6% of the radius of the propeller 100 from the center of the hub 10, the angle of attack of the blades is 14.67 ° ± 2.5 °; at a distance D6 of 76.6% of the radius of the propeller 100 from the center of the hub 10, the angle of attack of the blades is 11.70 ° ± 2.5 °.

In the present embodiment, since D3 is located 43.7% of the radius of the propeller 100 from the center of the hub 10, the angle of attack of the blades is 19.74 ° ± 2.5 °; at a distance D4 of 54.7% of the radius of the propeller 100 from the center of the hub 10, the angle of attack of the blades is 17.51 ° ± 2.5 °; at a distance D5 of 65.6% of the radius of the propeller 100 from the center of the hub 10, the angle of attack of the blades is 14.67 ° ± 2.5 °; at a distance D6 of 76.6% of the radius of the propeller 100 from the center of the hub 10, the angle of attack of the blades is 11.70 ° ± 2.5 °; therefore, the specific shape of the blade 20 is defined by the above parameters, and the propeller 100 using the blade 20 can effectively reduce hovering power consumption, improve efficiency, increase endurance time, and improve flight performance of the aircraft 1000 (shown in fig. 15). In addition, the design of the paddle 20 can also optimize the front flying working condition of the aircraft 1000, and ensure that the front flying working condition can also have good force effect and tensile force-rotating speed characteristics, thereby ensuring the front flying performance of the whole aircraft.

With continued reference to fig. 1 and 4-7, embodiments of the present application provide a propeller 100, the propeller 100 including a hub 10 and blades 20. At a distance D3 of 43.7% of the radius of the propeller 100 from the centre of the hub 10, the angle of attack α 3 of the blade 20 is 19.74 ° ± 2.5 °, and the chord length L3 of the blade 20 is 20.24mm ± 2.02 mm. At a distance D4 of 54.7% of the radius of the propeller 100 from the centre of the hub 10, the angle of attack α 4 of the blade 20 is 17.51 ° ± 2.5 °, and the chord length L4 of the blade 20 is 18.57mm ± 1.86 mm. At a distance D5 of 65.6% of the radius of the propeller 100 from the centre of the hub 10, the angle of attack α 5 of the blade 20 is 14.67 ° ± 2.5 °, and the chord length L5 of the blade 20 is 16.75mm ± 1.68 mm. At a distance D6 of 76.6% of the radius of the propeller 100 from the centre of the hub 10, the angle of attack α 6 of the blade 20 is 11.70 ° ± 2.5 °, and the chord length L6 of the blade 20 is 14.74mm ± 1.47 mm.

In the present embodiment, the angle of attack α 3 of the blade 20 is 19.74 ° ± 2.5 ° and the chord length L3 of the blade 20 is 20.24mm ± 2.02mm at a distance D3 of 43.7% of the radius of the propeller 100 from the center of the hub 10. At a distance D4 of 54.7% of the radius of the propeller 100 from the centre of the hub 10, the angle of attack α 4 of the blade 20 is 17.51 ° ± 2.5 °, and the chord length L4 of the blade 20 is 18.57mm ± 1.86 mm. At a distance D5 of 65.6% of the radius of the propeller 100 from the centre of the hub 10, the angle of attack α 5 of the blade 20 is 14.67 ° ± 2.5 °, and the chord length L5 of the blade 20 is 16.75mm ± 1.68 mm. At a distance D6 of 76.6% of the radius of the propeller 100 from the centre of the hub 10, the angle of attack α 6 of the blade 20 is 11.70 ° ± 2.5 °, and the chord length L6 of the blade 20 is 14.74mm ± 1.47 mm. Thus, the specific shape of the blade 20 is defined by the above parameters, and the propeller 100 using the blade 20 can effectively reduce hovering power consumption, improve efficiency, increase endurance time, and improve flight performance of the aircraft 1000 (shown in fig. 15). In addition, the design of the paddle 20 can also optimize the front flying working condition of the aircraft 1000, and ensure that the front flying working condition can also have good force effect and tensile force-rotating speed characteristics, thereby ensuring the front flying performance of the whole aircraft.

Referring to table 1 and fig. 16, taking the same blade diameter as an example, the propeller 100 provided in this embodiment has improved blade efficiency compared to the current market with the same blade disk area and the same pulling force. That is, under the condition of lower power, the pulling force is larger, so that the electric quantity loss is reduced, and the cruising distance is increased.

In addition, the propeller of many rotors flies the poor problem of efficiency before ubiquitous, and the paddle 20 design that adopts this application can also optimize the preceding operating mode that flies of aircraft 1000, guarantees to fly the operating mode in the front and also can possess good power effect and pulling force-rotational speed characteristic to guarantee the preceding performance of flying of complete machine.

TABLE 1

	Conventional same-quantity-stage propeller	Propeller of the present application
Pulling force (g)	140	140
Blade force effect (g/w)	13.8	14.5
Amount of lift	NA	5.07％

Referring to fig. 1 and 4, at a distance D3 of 43.7% of the radius of the propeller 100 from the center of the hub 10, the angle of attack α 3 of the blade 20 may be 17.24 ° or 19.74 ° or 22.24 °, or any one of or any value between 17.50 °, 18.50 °, 18.90 °, 19.48 °, 19.70 °, 20.00 °, 20.40 °, 21.20 °, 21.85 °, 22.00 °, etc., and the chord length L3 of the blade 20 may be 18.22mm or 20.24mm or 22.26mm, or any one of or any value between 18.50mm, 19.20mm, 19.80mm, 20.50mm, 20.80mm, 21.30mm, 21.70mm, 21.90mm, 22.10mm, 22.20mm, etc.

Referring to fig. 1 and 5, at a distance D4 of 54.7% of the radius of the propeller 100 from the center of the hub 10, the angle of attack α 4 of the blade 20 may be any one of or any value between 15.01 °, 17.51 °, 20.01 °, 15.20 °, 15.50 °, 15.90 °, 16.40 °, 17.00 °, 18.10 °, 18.50 °, 19.05 °, 19.50 °, 19.90 °, etc., and the chord length L4 of the blade 20 may be any one of or any value between 16.71mm, 18.57mm, 20.43mm, or any one of or any two of 16.80mm, 17.30mm, 17.70mm, 18.00mm, 18.80mm, 19.15mm, 19.70mm, 19.99mm, 20.10mm, 20.30mm, etc.

Referring to fig. 1 and 6, at a distance D5 of 65.6% of the radius of the propeller 100 from the center of the hub 10, the angle of attack α 5 of the blade 20 may be 12.17 ° or 14.67 ° or 17.17 °, or any one of or any value between 12.50 °, 13.00 °, 13.20 °, 14.00 °, 14.30 °, 14.80 °, 15.00 °, 15.50 °, 16.00 °, 16.90 °, etc., and the chord length L5 of the blade 20 may be 15.08mm or 16.75mm or 18.43mm, or any one of or any value between 15.20mm, 15.90mm, 16.10mm, 16.20mm, 16.95mm, 17.10mm, 17.50mm, 17.90mm, 18.10mm, 18.20mm, etc.

Referring to fig. 1 and 7, at a distance D6 of 76.6% of the radius of the propeller 100 from the center of the hub 10, the angle of attack α 6 of the blade 20 may be 9.20 °, or 11.70 °, or 14.20 °, or any one of or any value between 9.50 °, 9.99 °, 10.10 °, 11.50 °, 11.00 °, 11.50 °, 12.00 °, 12.50 °, 13.80 °, 14.00 °, etc., and the chord length L6 of the blade 20 may be 13.27mm, or 14.74mm, or 16.21mm, or any one of or any value between 13.69mm, 14.06mm, 14.70mm, 14.90mm, 15.00mm, 15.50mm, 15.70mm, 15.94mm, 16.00mm, 16.12mm, etc.

The hub 10 may be cylindrical, or the cross section of the hub 10 may be elliptical, rhombic, or the like. The center of the propeller hub 10 is provided with a connecting hole which is used for being sleeved on the output end of the motor. The blades 20 may have an elongated shape, and the blades 20 are connected to the hub 10 and extend in a radial direction of the connection hole of the hub 10.

Referring to fig. 1 and fig. 2 together, in the present embodiment, optionally, at a position D1 which is 26.2% of the radius of the propeller 100 from the center of the hub 10, the attack angle α 1 of the blade 20 is 21.62 ° ± 2.5 °, and the chord length L1 of the blade 20 is 20.74mm ± 2.07mm, so as to further reduce the hovering power consumption of the propeller 100 and improve the pulling force and the efficiency. Wherein the angle of attack α 1 of the blade 20 may be 19.12 °, or 21.62 °, or 24.12 °, or any one of or a value between 19.50 °, 20.10 °, 20.90 °, 21.00 °, 21.50 °, 22.00 °, 22.50 °, 23.30 °, 23.80 °, 24.00 °, etc., and the chord length L1 of the blade 20 may be 18.67mm, or 20.74mm, or 22.81mm, or any one of or a value between 18.90mm, 19.10mm, 19.20mm, 19.50mm, 20.00mm, 20.80mm, 21.00mm, 21.60mm, 22.30mm, 22.62mm, etc.

Referring to fig. 1 and fig. 3 together, in the present embodiment, optionally, at a position D2 which is 32.8% of the radius of the propeller 100 from the center of the hub 10, the attack angle α 2 of the blade 20 is 21.47 ° ± 2.5 °, and the chord length L2 of the blade 20 is 21.63mm ± 2.16mm, so as to further reduce the hovering power consumption of the propeller 100 and improve the pulling force and the efficiency. Wherein the angle of attack α 2 of the blade 20 may be 18.97 °, or 21.47 °, or 23.97 °, or any one or a number between 19.05 °, 19.50 °, 19.70 °, 20.20 °, 20.70 °, 21.10 °, 21.80 °, 22.20 °, 22.70 °, 23.50 °, etc., and the chord length L2 of the blade 20 may be 19.47mm, or 21.63mm, or 23.79mm, or any one or a number between 19.70mm, 20.00mm, 20.50mm, 20.80mm, 21.30mm, 21.80mm, 22.50mm, 22.82mm, 23.00mm, 23.60mm, etc.

Referring to fig. 1 and 8 together, in the present embodiment, optionally, at a position D7 which is 87.5% of the radius of the propeller 100 from the center of the hub 10, the angle of attack α 7 of the blade 20 is 8.75 ° ± 2.5 °, and the chord length L7 of the blade 20 is 12.44mm ± 1.24mm, so as to further reduce the hovering power consumption of the propeller 100 and improve the pulling force and the efficiency. Wherein the angle of attack α 7 of the blade 20 may be 6.25 ° or 8.75 ° or 11.25 °, or may be any one of 6.50 °, 7.10 °, 7.70 °, 7.90 °, 8.10 °, 8.70 °, 9.00 °, 9.50 °, 10.70 °, 11.00 °, or the like, or a value therebetween, and the chord length L7 of the blade 20 may be 11.20mm or 12.44mm or 13.68mm, or may be any one of 11.70mm, 11.90mm, 12.00mm, 12.33mm, 12.70mm, 12.90mm, 13.11mm, 13.20mm, 13.32mm, 13.50mm, or the like, or a value therebetween.

Referring to fig. 1 and 9 together, in the present embodiment, optionally, at a position D8 which is 98.4% of the radius of the propeller 100 from the center of the hub 10, the attack angle α 8 of the blade 20 is 4.29 ° ± 2.5 °, and the chord length L8 of the blade 20 is 6.05mm ± 0.61mm, so as to further reduce the hovering power consumption of the propeller 100 and improve the pulling force and the efficiency. Wherein the angle of attack α 8 of the blade 20 may be 1.79 ° or 4.29 ° or 6.79 °, or any one or a number between any two of 1.82 °, 2.50 °, 2.80 °, 3.40 °, 3.70 °, 4.00 °, 5.05 °, 5.50 °, 5.70 °, 6.20 °, etc., and the chord length L8 of the blade 20 may be 5.45mm or 6.05mm or 6.66mm, or any one or a number between any two of 5.55mm, 5.60mm, 5.80mm, 5.92mm, 6.00mm, 6.10mm, 6.20mm, 6.30mm, 6.41mm, 6.50mm, etc.

Referring to fig. 1 to 3 and 8 to 9, in the present embodiment, the diameter of the propeller 100 is 182.88mm ± 18.0 mm. At a distance D1 of 26.2% of the radius of the propeller 100 from the centre of the hub 10, the angle of attack α 1 of the blade 20 is 21.62 ° and the chord length L1 of the blade 20 is 20.74 mm. At a distance D2 of 32.8% of the radius of the propeller 100 from the centre of the hub 10, the angle of attack α 2 of the blade 20 is 21.47 ° and the chord length L2 of the blade 20 is 21.63 mm. At 87.5% of the radius of the propeller 100 from the centre of the hub 10D 7, the angle of attack α 7 of the blade 20 is 8.75 ° and the chord length L7 of the blade 20 is 12.44 mm. At a distance D8 of 98.4% of the radius of the propeller 100 from the centre of the hub 10, the angle of attack α 8 of the blade 20 is 4.29 ° and the chord length L8 of the blade 20 is 6.05 mm.

In this way, the parameter definition in the present embodiment can further reduce the air resistance of the propeller 100, and improve the pulling force and efficiency. The diameter of the propeller 100 may be 164.88mm, 182.88mm or 200.88mm, or any one of 165.00mm, 166.50mm, 167.26mm, 177.00mm, 177.46mm, 185.50mm, 190.79mm, 195.88mm, 199.75mm, 200.00mm, or the like, or a value between any two of the foregoing.

In certain embodiments, the pitch of the blades 20 is optionally 3.66 ± 0.6 inches. Thereby, the drag of the air can be reduced, and the pulling force of the blade 20 can be increased. Wherein the pitch of the blades 20 may be 3.06 inches, 3.66 inches, or 4.26 inches, or any one or a number between any of 3.10 inches, 3.22 inches, 3.33 inches, 3.44 inches, 3.55 inches, 3.76 inches, 3.87 inches, 3.98 inches, 4.19 inches, etc.

Referring to fig. 1, 10 to 14, in the present embodiment, optionally, the blade 20 includes a root 21, a tip 22 facing away from the root 21, and opposite pressure and suction surfaces 23 and 24. Wherein the pressure surface 23 is a ground-facing surface of the blades 20 during normal flight of the aircraft 1000 (as shown in fig. 15), and the suction surface 24 is a skyward surface of the blades 20 during normal flight of the aircraft 1000.

In the present embodiment, the angle of attack of the blades 20 is optionally gradually reduced in a direction from 26.2% of the radius of the propeller 100 from the center of the hub 10 to the tip 21. In this manner, the propeller 100 can further reduce air resistance, improve drag and efficiency, and increase the fly-by distance of the aircraft 1000 (as shown in fig. 15) to improve flight performance of the aircraft 1000.

In the present embodiment, optionally, the suction surface 24 and the pressure surface 23 are both curved surfaces. The suction surface 24 and the pressure surface 23 are curved aerodynamic profiles, which not only can reduce air resistance and improve the pulling force of the blades 20, but also can prevent turbulence generated by each part of the blades 20 and downwash airflow from directly impacting the fuselage 50 (as shown in fig. 15) of the aircraft 1000, thereby reducing the overall noise of the aircraft 1000.

In this embodiment, the blade 20 further includes a front edge 25 connected to one side of the pressure surface 23 and the suction surface 24, a rear edge 26 connected to the other side of the pressure surface 23 and the suction surface 24, and a swept back portion 27 formed at the tip 22. Leading edge 25 has a curved leading edge bulge 251 formed in an outwardly convex manner adjacent to blade root 21, and trailing edge 26 has a curved trailing edge bulge 261 formed in an outwardly convex manner adjacent to blade root 21. The sweep 27 extends obliquely from the leading edge 25 to the trailing edge 26. The curved shape of the leading-edge camber portion 251 and the trailing-edge camber portion 261 has an effect of improving the drag of the blade 20 and the efficiency of the propeller 100.

In the present embodiment, optionally, the blade 20 forms a return bend MM near the tip 22, the leading edge 25 extends obliquely from the return bend MM in the span direction of the blade 20 toward the side where the suction surface 24 is located, and the sweep 27 extends obliquely from the return bend MM from the leading edge 25 toward the trailing edge 26, the return bend MM being 91.9% of the radius of the propeller 100 from the center of the hub 10. Thus, the return bend MM is away from the center of hub 10, enhancing the overall aesthetics of blade 20.

In the present embodiment, the tip 22 optionally extends obliquely in the span direction of the blade 20 towards the side where the suction surface 24 is located. In this way, noise generated by the blades 20 during operation is reduced, so that the aircraft 1000 is quieter when hovering, and user experience is improved.

In this embodiment, optionally, there are at least two blades 20, and at least two blades 20 are connected to hub 10 and are symmetric about the center of hub 10. As such, the at least two blades 20 can improve the balance of the propeller 100 as compared to a single blade 20.

In this embodiment, optionally, the sides of the free end of the tip 22 are planar. Thus, the planar free end may enhance the aesthetic appearance of the propeller 100.

Referring to fig. 1 and 14, in the present embodiment, optionally, the blade 20 has a central axis O-O ' passing through the center of the hub 10, the leading edge 25 has a leading edge tangent N-N ' parallel to the central axis O-O ', the trailing edge 26 has a trailing edge tangent P-P ' parallel to the central axis O-O ', and the root 21 is located between the leading edge tangent N-N ' and the trailing edge tangent P-P '. Wherein the leading edge tangent line N-N 'passes through the leading edge camber portion 251 and the trailing edge tangent line P-P' passes through the trailing edge camber portion 261. Thus, the root 21 not only reduces the air resistance of the propeller 100, improves the maneuverability of the aircraft 1000 (as shown in fig. 15), and makes the aircraft 1000 smoother, but also reduces the turbulence and downwash generated by the blades 20, thereby reducing the turbulence and downwash hitting the fuselage 50 of the aircraft 1000 and further reducing the overall noise of the aircraft 1000.

In some embodiments, at 26.2% of the radius of the propeller 100 from the center of the hub 10, D1, the angle of attack α 1 of the blades 20 is 21.62 ° ± 2.5 °; and/or

At 32.8% of the radius of the propeller 100 from the center of the hub 10, D2, the angle of attack α 2 of the blades 20 is 21.47 ° ± 2.5 °; and/or

At 87.5% of the radius of the propeller 100 from the center of the hub 10, D7, the angle of attack α 7 of the blades 20 is 8.75 ° ± 2.5 °; and/or

At a distance D8 of 98.4% of the radius of the propeller 100 from the center of the hub 10, the angle of attack α 8 of the blades 20 is 4.29 ° ± 2.5 °; and/or

At 24mm from the center of hub 10, the angle of attack α 1 of blade 20 is 21.62 °; and/or

At 30mm from the centre of hub 10, angle of attack α 2 of blade 20 is 21.47 °; and/or

At 40mm from the centre of hub 10, angle of attack α 3 of blade 20 is 19.74 °; and/or

At 50mm from the centre of hub 10, angle of attack α 4 of blade 20 is 17.51 °; and/or

At 60mm from the center of hub 10, angle of attack α 5 of blade 20 is 14.67 °; and/or

At 70mm from the centre of the hub 10, the angle of attack α 6 of the blade 20 is 11.70 °; and/or

At 80mm from the centre of the hub 10, the angle of attack α 7 of the blade 20 is 8.75 °; and/or

At 90mm from the center of hub 10, angle of attack α 8 of blade 20 is 4.29 °.

The discussion herein includes, but is not limited to, the following:

(1) the propeller 100 has an angle of attack α 1 of the blades 20 of 21.62 ° ± 2.5 ° at a distance D1 from the center of the hub 10 of 26.2% of the radius of the propeller 100;

(2) the propeller 100 has an angle of attack α 2 of the blades 20 of 21.47 ° ± 2.5 ° at a distance D2 from the center of the hub 10 of 32.8% of the radius of the propeller 100;

(3) the propeller 100 has an angle of attack α 7 of the blades 20 of 8.75 ° ± 2.5 ° at a distance D7 from the center of the hub 10 of 87.5% of the radius of the propeller 100;

(4) the propeller 100 has an angle of attack α 8 of 4.29 ° ± 2.5 ° at a distance D8 from the center of the hub 10 that is 98.4% of the radius of the propeller 100;

(5) the angle of attack α 1 of the blades 20 at 24mm from the centre of the hub 10 of the propeller 100 is 21.62 °;

(6) the angle of attack α 2 of the blades 20 at 30mm from the centre of the hub 10 of the propeller 100 is 21.47 °;

(7) the angle of attack α 3 of the blades 20 at the propeller 100 at 40mm from the centre of the hub 10 is 19.74 °;

(8) the angle of attack α 4 of the blades 20 at the propeller 100 at 50mm from the centre of the hub 10 is 17.51 °;

(9) the angle of attack α 5 of the blades 20 at the propeller 100 at 60mm from the centre of the hub 10 is 14.67 °;

(10) the angle of attack α 6 of the blade 20 at the propeller 100 at 70mm from the centre of the hub 10 is 11.70 °;

(11) the angle of attack α 7 of the blades 20 at the propeller 100 at a distance of 80mm from the centre of the hub 10 is 8.75 °;

(12) the angle of attack α 8 of the blades 20 at 90mm from the centre of the hub 10 of the propeller 100 is 4.29 °;

(13) the propeller 100 has an angle of attack α 1 of the blades 20 of 21.62 ° ± 2.5 ° at a distance D1 from the center of the hub 10 of 26.2% of the radius of the propeller 100; and D2 at a distance of 32.8% of the radius of the propeller 100 from the center of the hub 10, the angle of attack α 2 of the blades 20 being 21.47 ° ± 2.5 °; and D7 at 87.5% of the radius of the propeller 100 from the center of the hub 10, the angle of attack α 7 of the blades 20 being 8.75 ° ± 2.5 °; and D8 at a distance of 98.4% of the radius of the propeller 100 from the center of the hub 10, the angle of attack α 8 of the blades 20 being 4.29 ° ± 2.5 °; and an angle of attack α 1 of the blades 20 at 24mm from the centre of the hub 10 of 21.62 °; and an angle of attack α 2 of the blades 20 at 30mm from the centre of the hub 10 of 21.47 °; and an angle of attack α 3 of the blades 20 at 40mm from the centre of the hub 10 of 19.74 °; and an angle of attack α 4 of the blades 20 at 50mm from the centre of the hub 10 of 17.51 °; and an angle of attack α 5 of the blades 20 at 60mm from the centre of the hub 10 of 14.67 °; and the angle of attack α 6 of the blade 20 is 11.70 ° at a distance of 70mm from the centre of the hub 10; and an angle of attack α 7 of the blades 20 at a distance of 80mm from the centre of the hub 10 of 8.75 °; and the angle of attack α 8 of the blade 20 is 4.29 ° at 90mm from the centre of the hub 10.

In some embodiments, the chord length of the blades 20 is 20.24mm ± 2.02mm at 43.7% of the radius of the propeller 100 from the center of the hub 10; and/or

The chord length of the blades 20 is 18.57mm ± 1.86mm at a distance of 54.7% of the radius of the propeller 100 from the centre of the hub 10; and/or

The chord length of the blades 20 is 16.75mm ± 1.68mm at a distance of 65.6% of the radius of the propeller 100 from the centre of the hub 10; and/or

The chord length of the blades 20 is 14.74mm ± 1.47mm at a distance of 76.6% of the radius of the propeller 100 from the centre of the hub 10; and/or

The chord length of the blades 20 is 20.24mm at 40mm from the centre of the hub 10; and/or

At 50mm from the centre of the hub 10, the chord length of the blades 20 is 18.57 mm; and/or

At 60mm from the centre of the hub 10, the chord length of the blades 20 is 16.75 mm; and/or

The chord length of the blade 20 is 14.74mm at 70mm from the centre of the hub 10.

The discussion herein includes, but is not limited to, the following:

(1) the chord length of the blade 20 is 20.24mm +/-2.02 mm at the position of the propeller 100, which is 43.7 percent of the radius of the propeller 100 and away from the center of the propeller hub 10;

(2) the chord length of the blade 20 is 18.57mm +/-1.86 mm at a position of 54.7% of the radius of the propeller 100 away from the center of the propeller hub 10;

(3) the chord length of the blade 20 is 16.75mm +/-1.68 mm at the position of the propeller 100, which is 65.6 percent of the radius of the propeller 100 and away from the center of the propeller hub 10;

(4) the chord length of the blades 20 at a distance of 76.6% of the radius of the propeller 100 from the center of the hub 10 of the propeller 100 is 14.74mm +/-1.47 mm;

(5) the propeller 100 is 40mm away from the center of the hub 10, and the chord length of the blades 20 is 20.24 mm;

(6) the propeller 100 is 50mm away from the center of the hub 10, and the chord length of the blades 20 is 18.57 mm;

(7) the propeller 100 is 60mm away from the center of the hub 10, and the chord length of the blades 20 is 16.75 mm;

(8) the propeller 100 is 70mm away from the center of the hub 10, and the chord length of the blade 20 is 14.74 mm;

(9) the chord length of the blade 20 is 20.24mm +/-2.02 mm at the position of the propeller 100, which is 43.7 percent of the radius of the propeller 100 and away from the center of the propeller hub 10; and the chord length of the blades 20 is 18.57mm + -1.86 mm at a distance of 54.7% of the radius of the propeller 100 from the center of the hub 10; and the chord length of the blades 20 is 16.75mm +/-1.68 mm at a position which is 65.6 percent of the radius of the propeller 100 away from the center of the hub 10; and the chord length of the blades 20 is 14.74mm +/-1.47 mm at a position which is 76.6 percent of the radius of the propeller 100 away from the center of the hub 10; and the chord length of the blades 20 is 20.24mm at a distance of 40mm from the center of the hub 10; and a chord length of the blades 20 at 50mm from the centre of the hub 10 of 18.57 mm; and the chord length of the blades 20 is 16.75mm at a distance of 60mm from the center of the hub 10; and the chord length of the blade 20 is 14.74mm at 70mm from the centre of the hub 10.

In some embodiments, the chord length of the blades 20 is 20.74mm ± 2.07mm at 26.2% of the radius of the propeller 100 from the center of the hub 10; and/or

The chord length of the blades 20 is 21.63mm ± 2.16mm at a distance of 32.8% of the radius of the propeller 100 from the centre of the hub 10; and/or

The chord length of the blades 20 is 12.44mm ± 1.24mm at 87.5% of the radius of the propeller 100 from the centre of the hub 10; and/or

The chord length of the blades 20 is 6.05mm ± 0.61mm at a distance of 98.4% of the radius of the propeller 100 from the center of the hub 10; and/or

At 24mm from the centre of the hub 10, the chord length of the blades 20 is 20.74 mm; and/or

At 30mm from the centre of hub 10, the chord length of blade 20 is 21.63 mm; and/or

At 80mm from the centre of the hub 10, the chord length of the blades 20 is 12.44 mm; and/or

The chord length of the blades 20 is 6.05mm at 90mm from the centre of the hub 10.

The discussion herein includes, but is not limited to, the following:

(1) the propeller 100 is positioned at a distance of 26.2 percent of the radius of the propeller 100 from the center of the propeller hub 10, and the chord length of the blades 20 is 20.74mm +/-2.07 mm;

(2) the chord length of the blade 20 is 21.63mm +/-2.16 mm at the position of the propeller 100, which is 32.8 percent of the radius of the propeller 100 away from the center of the propeller hub 10;

(3) the chord length of the blade 20 is 12.44mm +/-1.24 mm at the position of the propeller 100, which is 87.5 percent of the radius of the propeller 100 and away from the center of the propeller hub 10;

(4) the chord length of the blade 20 is 6.05mm +/-0.61 mm at the position of the propeller 100, which is 98.4 percent of the radius of the propeller 100 and away from the center of the propeller hub 10;

(5) the propeller 100 is 24mm away from the center of the hub 10, and the chord length of the blade 20 is 20.74 mm;

(6) the propeller 100 is 30mm away from the center of the hub 10, and the chord length of the blade 20 is 21.63 mm;

(7) the propeller 100 is 80mm away from the center of the hub 10, and the chord length of the blades 20 is 12.44 mm;

(8) the propeller 100 has a chord length of 6.05mm of the blades 20 at a distance of 90mm from the center of the hub 10.

(9) The chord length of the blade 20 is 20.74mm +/-2.07 mm at the position, which is 26.2% of the radius of the propeller 100, of the propeller 100 away from the center of the propeller hub 10; and the chord length of the blades 20 is 21.63mm +/-2.16 mm at the position which is 32.8 percent of the radius of the propeller 100 away from the center of the propeller hub 10; and the chord length of the blades 20 is 12.44mm + -1.24 mm at a distance of 87.5% of the radius of the propeller 100 from the center of the hub 10; and the chord length of the blade 20 is 6.05mm +/-0.61 mm at the position which is 98.4 percent of the radius of the propeller 100 away from the center of the propeller hub 10; and a chord length of the blades 20 at 24mm from the centre of the hub 10 of 20.74 mm; and the chord length of the blades 20 is 21.63mm at a distance of 30mm from the center of the hub 10; and a chord length of the blades 20 of 12.44mm at a distance of 80mm from the centre of the hub 10; and the chord length of the blade 20 is 6.05mm at 90mm from the centre of the hub 10.

Referring to fig. 15, the present embodiment provides a power assembly 200. The power assembly 200 comprises a driver 30 and the propeller 100 of any embodiment of the present application, the propeller 100 being connected to the driver 30 via the hub 10.

The driving member 30 is a motor, and the KV value of the motor is 1860 ± 60 revolutions/(min · volt), thereby ensuring the power performance of the power assembly 200. A drive member 30 may be used to rotate one or more propellers 100, in the present embodiment, a drive member 30 is used to rotate one propeller 100. In addition, the power assembly 200 may further include a horn 40 and a fastener (not shown). The horn 40 may be adapted to be coupled to the body 50, and specifically, one end of the horn 40 is adapted to be coupled to the body 50, and the other end of the horn 50 is adapted to receive the driving member 30. Fasteners may be used to connect the propeller 100 to a rotating portion of the drive member 30 (e.g., a cover for a motor), such as one or more fasteners connecting one propeller 100 to the rotating portion such that rotation of the rotating portion causes the fastener and the propeller 100 to rotate simultaneously. Wherein the rotating part can rotate with the rotating shaft of the driving member 30, and the fastening member can be a screw, a clamping unit, etc.

In the power assembly 200 of the present application, the angle of attack of the blades is 19.74 ° ± 2.5 ° due to D3 at 43.7% of the radius of the propeller 100 from the center of the hub 10; at a distance D4 of 54.7% of the radius of the propeller 100 from the center of the hub 10, the angle of attack of the blades is 17.51 ° ± 2.5 °; at 65.6% of the radius of the propeller 100 from the center of the hub 10, D5, the angle of attack of the blades is 14.67 ° ± 2.5 °; at a distance D6 of 76.6% of the radius of the propeller 100 from the center of the hub 10, the angle of attack of the blades is 11.70 ° ± 2.5 °; therefore, in the power assembly 200, with the blades 20 having the specific shapes defined by the above parameters, the propeller 100 using the blades 20 can effectively reduce hovering power consumption, improve efficiency, increase endurance time, and improve flight performance of the aircraft 1000. In addition, the design of the paddle 20 can also optimize the front flying working condition of the aircraft 1000, and ensure that the front flying working condition can also have good force effect and tensile force-rotating speed characteristics, thereby ensuring the front flying performance of the whole aircraft.

Referring again to fig. 15, an embodiment of the present application provides an aircraft 1000 including a fuselage 50 and a power assembly 200 according to any embodiment of the present application, the power assembly 200 being coupled to the fuselage 50. A plurality of horn 40 of power assembly 200 are coupled to fuselage 50 to mount power assembly 200 to fuselage 50. The specific structure of the power assembly 200 is similar to the previous embodiments, and is not described herein. That is, the description about the propeller 100 in the above embodiments and embodiments is equally applicable to the aircraft 1000 provided in the embodiments of the present application.

In this embodiment, the aircraft 1000 optionally includes a plurality of power assemblies 200, and the rotation directions of the plurality of power assemblies 200 are partially different. Taking the aircraft 1000 shown in fig. 15 as an example, the rotation directions of the two power assemblies 200 in the diagonal direction may be the same, and the rotation directions of the two power assemblies 200 not in the diagonal direction may be different.

In this embodiment, the aircraft 1000 is optionally a multi-rotor aircraft, such as a quad-rotor unmanned aircraft, an eight-rotor unmanned aircraft, a sixteen-rotor unmanned aircraft, or the like.

In the aircraft 1000 of the present application, the angle of attack of the blades is 19.74 ° ± 2.5 ° due to D3 at a distance from the center of hub 10 of 43.7% of the radius of the propeller 100; at a distance D4 of 54.7% of the radius of the propeller 100 from the center of the hub 10, the angle of attack of the blades is 17.51 ° ± 2.5 °; at 65.6% of the radius of the propeller 100 from the center of the hub 10, D5, the angle of attack of the blades is 14.67 ° ± 2.5 °; at a distance D6 of 76.6% of the radius of the propeller 100 from the center of the hub 10, the angle of attack of the blades is 11.70 ° ± 2.5 °; therefore, with the blades 20 having the specific shape defined by the above parameters, the propeller 100 using the blades 20 can effectively reduce hovering power consumption, improve efficiency, increase endurance time, and improve flight performance of the aircraft 1000. In addition, the design of the paddle 20 can also optimize the front flying working condition of the aircraft 1000, and ensure that the front flying working condition can also have good force effect and tensile force-rotating speed characteristics, thereby ensuring the front flying performance of the whole aircraft.

In the description herein, reference to the description of the terms "certain embodiments," "one embodiment," "some embodiments," "illustrative embodiments," "examples," "specific examples," or "some examples" means that a particular feature, structure, material, or characteristic described in connection with the embodiment or example is included in at least one embodiment or example of the application. In this specification, schematic representations of the above terms do not necessarily refer to the same embodiment or example. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples.

Furthermore, the terms "first", "second" and "first" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one of the feature. In the description of the present application, "a plurality" means at least two, e.g., two, three, unless specifically limited otherwise.

Although embodiments of the present application have been shown and described above, it is understood that the above embodiments are exemplary and should not be construed as limiting the present application, and that variations, modifications, substitutions and alterations of the above embodiments may be made by those of ordinary skill in the art within the scope of the present application, which is defined by the claims and their equivalents.

Claims

A propeller, comprising: a hub and blades attached to said hub, characterized in that:

at 43.7% of the radius of the propeller from the center of the hub, the angle of attack of the blades is 19.74 ° ± 2.5 °;

at 54.7% of the radius of the propeller from the center of the hub, the angle of attack of the blade is 17.51 ° ± 2.5 °;

the angle of attack of the blades is 14.67 ° ± 2.5 ° at 65.6% of the radius of the propeller from the center of the hub;

the angle of attack of the blades is 11.70 ° ± 2.5 ° at 76.6% of the radius of the propeller from the center of the hub.
The propeller of claim 1, wherein:

at 26.2% of the radius of the propeller from the center of the hub, the angle of attack of the blades is 21.62 ° ± 2.5 °; and/or

The angle of attack of the blades is 21.47 ° ± 2.5 ° at a distance of 32.8% of the radius of the propeller from the center of the hub; and/or

The angle of attack of the blades is 8.75 ° ± 2.5 ° at 87.5% of the radius of the propeller from the center of the hub; and/or

The angle of attack of the blades is 4.29 ° ± 2.5 ° at a distance from the centre of the hub of 98.4% of the radius of the propeller; and/or

At 24mm from the centre of the hub, the angle of attack of the blade is 21.62 °; and/or

At 30mm from the centre of the hub, the angle of attack of the blade is 21.47 °; and/or

At 40mm from the centre of the hub, the angle of attack of the blade is 19.74 °; and/or

At 50mm from the centre of the hub, the angle of attack of the blade is 17.51 °; and/or

At 60mm from the centre of the hub, the angle of attack of the blade is 14.67 °; and/or

At 70mm from the centre of the hub, the angle of attack of the blade is 11.70 °; and/or

At 80mm from the centre of the hub, the angle of attack of the blade is 8.75 °; and/or

The angle of attack of the blade is 4.29 ° at 90mm from the centre of the hub.
The propeller of claim 1, wherein:

the chord length of the blade is 20.24mm + -2.02 mm at a distance of 43.7% of the radius of the propeller from the center of the hub; and/or

The chord length of the blade is 18.57mm ± 1.86mm at 54.7% of the radius of the propeller from the center of the hub; and/or

The chord length of the blade is 16.75mm ± 1.68mm at 65.6% of the radius of the propeller from the centre of the hub; and/or

The chord length of the blade is 14.74mm + -1.47 mm at 76.6% of the radius of the propeller from the center of the hub; and/or

The chord length of the blade is 20.24mm at 40mm from the centre of the hub; and/or

The chord length of the blade is 18.57mm at 50mm from the centre of the hub; and/or

The chord length of the blade is 16.75mm at 60mm from the centre of the hub; and/or

At 70mm from the centre of the hub, the chord length of the blade is 14.74 mm.
The propeller of claim 3, wherein:

the chord length of the blade is 20.74mm ± 2.07mm at a distance of 26.2% of the radius of the propeller from the center of the hub; and/or

The chord length of the blade is 21.63mm ± 2.16mm at a distance of 32.8% of the radius of the propeller from the centre of the hub; and/or

The chord length of the blade is 12.44mm ± 1.24mm at 87.5% of the radius of the propeller from the center of the hub; and/or

The chord length of the blade is 6.05mm + -0.61 mm at a distance of 98.4% of the radius of the propeller from the center of the hub; and/or

The chord length of the blade at 24mm from the centre of the hub is 20.74 mm; and/or

At 30mm from the centre of the hub, the chord length of the blade is 21.63 mm; and/or

At 80mm from the centre of the hub, the chord length of the blade is 12.44 mm; and/or

The chord length of the blade is 6.05mm at 90mm from the centre of the hub.
The propeller of claim 1, wherein the propeller has a diameter of 182.88mm ± 18.0 mm; and/or

The pitch of the blade is 3.66 + -0.6 inches.
The propeller of any one of claims 1 to 5, wherein:

the blade comprises a blade root, a blade tip, a pressure surface and a suction surface, wherein the blade tip is deviated from the blade root, the pressure surface and the suction surface are opposite, the front edge is connected with one side edge of the pressure surface and the suction surface, the rear edge is connected with the other side edge of the pressure surface and the suction surface, and the sweepback part is formed on the blade tip and extends from the front edge to the rear edge in an inclined mode;

the blade tip extends obliquely towards the side where the suction surface is located along the span direction of the blade.
The propeller of claim 6 wherein the blade forms a return bend proximate the tip, the leading edge extending obliquely from the return bend in a span-wise direction of the blade toward a side of the suction surface, the sweep extending obliquely from the return bend from the leading edge to the trailing edge, the return bend being 91.9% of a radius of the propeller from a center of the hub.
The propeller as recited in claim 6, wherein said trailing edge is convexly formed with a curved trailing edge camber proximate said root; and/or

The number of the blades is at least two, and the at least two blades are connected to the hub and are in central symmetry with respect to the center of the hub; and/or

The blade having a central axis passing through the center of the hub, the leading edge having a leading edge tangent parallel to the central axis, the trailing edge having a trailing edge tangent parallel to the central axis, the sweep being located between the leading edge tangent and the trailing edge tangent; and/or

The suction surface and the pressure surface are both curved surfaces.
A power assembly comprising a drive member and the propeller of any one of claims 1 to 8, wherein the propeller is connected to the drive member by the hub.
A power assembly according to claim 9, wherein the drive member is an electric motor having KV values of 1860 ± 60 revolutions/(min-volt).
An aircraft comprising a fuselage and the power assembly of claim 9, the power assembly being coupled to the fuselage.
The aircraft of claim 10 wherein the aircraft includes a plurality of power assemblies that rotate in different directions, the aircraft being a multi-rotor aircraft.