CN214776520U

CN214776520U - Screw, power component and aircraft

Info

Publication number: CN214776520U
Application number: CN202120119854.7U
Authority: CN
Inventors: 韩杰星; 柯树翰
Original assignee: SZ DJI Technology Co Ltd
Current assignee: SZ DJI Technology Co Ltd
Priority date: 2021-01-15
Filing date: 2021-01-15
Publication date: 2021-11-19
Anticipated expiration: 2031-01-15

Abstract

The application discloses screw, power component and aircraft. The propeller comprises a hub and blades, and the blades are connected to the hub. The angle of attack of the blades is 20.00 ° ± 2.5 ° at a distance from the centre of the hub of 44.8% of the radius of the propeller; the angle of attack of the blades is 17.00 ° ± 2.5 ° at a distance from the centre of the hub of 59.7% of the radius of the propeller; the angle of attack of the blades is 13.00 ° ± 2.5 ° at a distance from the centre of the hub of 74.6% of the radius of the propeller; the angle of attack of the blades is 11.00 ° ± 2.5 ° at a distance of 89.6% of the radius of the propeller from the centre of the hub. The propeller with the blades in the specific shape is defined by the parameters, so that the energy consumption can be effectively reduced, the efficiency is improved, the endurance time is increased, and the continuous working time of the aircraft is longer. In addition, when the flying speed of the aircraft is too high, the tension attenuation of the paddle is faster, and the danger caused by continuous high-speed flying is avoided.

Description

Screw, power component and aircraft

Technical Field

The application relates to the technical 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, small-size propellers have small sizes and low Reynolds numbers, so that the propellers have difficulty in ensuring pneumatic performance under low tension, and the idle time and range of a small aircraft are seriously influenced.

SUMMERY OF THE UTILITY MODEL

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 44.8% of the radius of the propeller from the center of the hub, the angle of attack of the blades is 20.00 ° ± 2.5 °; at 59.7% of the radius of the propeller from the center of the hub, the angle of attack of the blades is 17.00 ° ± 2.5 °; at a distance of 74.6% of the radius of the propeller from the center of the hub, the angle of attack of the blades is 13.00 ° ± 2.5 °; the angle of attack of the blades is 11.00 ° ± 2.5 ° at 89.6% of the radius of the propeller from the center of the hub.

In certain embodiments, the angle of attack of the blades is 22.00 ° ± 2.5 ° at 29.9% of the radius of the propeller from the center of the hub; and/or the angle of attack of the blades is 9.00 ° ± 2.5 ° at a distance from the centre of the hub of 98.5% of the radius of the propeller; and/or the angle of attack of the blades is 2.00 ° ± 2.5 ° at a distance from the centre of the hub of 100% of the radius of the propeller; and/or the angle of attack of the blades is 22.00 ° at 20mm from the centre of the hub; and/or the angle of attack of the blades is 20.00 ° at 30mm from the centre of the hub; and/or the angle of attack of the blades is 17.00 ° at 40mm from the centre of the hub; and/or the angle of attack of the blades is 13.00 ° at a distance of 50mm from the centre of the hub; and/or the angle of attack of the blades is 11.00 ° at a distance of 60mm from the centre of the hub; and/or the angle of attack of the blades is 9.00 ° at 66mm from the centre of the hub; and/or the angle of attack of the blade is 2.00 ° at 67mm from the centre of the hub.

In some embodiments, the projected length of the chord length of the blade within the rotor disc is 17.19mm ± 1.72mm at 44.8% of the radius of the propeller from the center of the hub; and/or the projected length of the chord length of the blade in a paddle disk is 16.03mm +/-1.60 mm at the position which is 59.7% of the radius of the propeller from the center of the paddle hub; and/or the projected length of the chord length of the blade in a paddle disk is 14.23mm +/-1.42 mm at a position which is 74.6 percent of the radius of the propeller from the center of the paddle hub; and/or the projected length of the chord length of the blade in the paddle disk is 10.56mm +/-1.06 mm at the position which is 89.6 percent of the radius of the propeller from the center of the paddle hub; and/or the projection length of the chord length of the blade in the paddle disc is 17.19mm at the position 30mm away from the center of the paddle hub; and/or the projection length of the chord length of the blade in the paddle disc is 16.03mm at the position 40mm away from the center of the paddle hub; and/or the projection length of the chord length of the blade in the paddle disc is 14.23mm at the position 50mm away from the center of the paddle hub; and/or the projected length of the chord length of the blade in the paddle disk is 10.56mm at the position 60mm away from the center of the paddle hub.

In some embodiments, the projected length of the chord length of the blade within the rotor disc is 11.21mm ± 1.12mm at 14.9% of the radius of the propeller from the center of the hub; and/or the projected length of the chord length of the blade in the paddle disk is 17.52mm +/-1.75 mm at the position which is 29.9% of the radius of the propeller from the center of the paddle hub; and/or the projected length of the chord length of the blade in the paddle disk is 6.26mm +/-0.63 mm at the position which is 98.5% of the radius of the propeller from the center of the paddle hub; and/or the projected length of the chord length of the blade in the paddle disk is 4.64mm +/-0.46 mm at the position which is 100% of the radius of the propeller from the center of the paddle hub; and/or the projection length of the chord length of the blade in the paddle disc is 11.21mm at a position 10mm away from the center of the paddle hub; and/or the projection length of the chord length of the blade in the paddle disc is 17.52mm at the position 20mm away from the center of the paddle hub; and/or the projected length of the chord length of the blade in the paddle disk is 6.26mm at the position 66mm away from the center of the paddle hub; and/or the projected length of the chord length of the blade in the paddle disk is 4.64mm at the position 67mm away from the center of the paddle hub.

In certain embodiments, the diameter of the propeller is 134mm ± 13.4 mm; and/or the pitch of the blades is 2.8 plus or minus 0.28 inches.

In some embodiments, the blade includes 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.

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 three, and included angles between any two adjacent blades connected to the propeller hub are equal; 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.

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

In the present embodiment, since the angle of attack of the blades is 20.00 ° ± 2.5 ° at a distance from the center of the hub of 44.8% of the radius of the propeller; at 59.7% of the radius of the propeller from the center of the hub, the angle of attack of the blades is 17.00 ° ± 2.5 °; at a distance of 74.6% of the radius of the propeller from the center of the hub, the angle of attack of the blades is 13.00 ° ± 2.5 °; the angle of attack of the blades is 11.00 ° ± 2.5 ° at 89.6% of the radius of the propeller from the center of the hub. Therefore, the propeller with the propeller blade in the specific shape is defined by the parameters, so that the energy consumption can be effectively reduced, the efficiency is improved, the endurance time is increased, and the continuous working time of the aircraft is longer. In addition, when the flying speed of the aircraft is too high, the tension attenuation of the paddle is faster, and the danger caused by continuous high-speed flying is avoided.

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;

FIG. 2 is a cross-sectional view of section A-A of the propeller of the embodiment shown in FIG. 1 at a distance of 10mm from the center of the hub;

FIG. 3 is a cross-sectional view of the section B-B in the propeller of the embodiment shown in FIG. 1 at 20mm from the center of the hub;

FIG. 4 is a cross-sectional view of the section C-C in the propeller of the embodiment shown in FIG. 1 at 30mm from the center of the hub;

FIG. 5 is a cross-sectional view of the propeller of the embodiment shown in FIG. 1 taken along the D-D section at a distance of 40mm from the center of the hub;

FIG. 6 is a cross-sectional view of section E-E of the propeller of the embodiment shown in FIG. 1 at 50mm from the center of the hub;

FIG. 7 is a cross-sectional view of the section F-F in the propeller of the embodiment shown in FIG. 1 at 60mm from the center of the hub;

FIG. 8 is a cross-sectional view of the section G-G at 66mm from the center of the hub in the propeller of the embodiment shown in FIG. 1;

FIG. 9 is a cross-sectional view of the section H-H at 67mm from the center of the hub in the propeller of the embodiment shown in FIG. 1;

FIG. 10 is a perspective view of a propeller from one perspective provided by an embodiment of the present application;

FIG. 11 is a perspective view of another perspective of a propeller according to embodiments of the present application;

fig. 12 is a schematic plan view of an aircraft according to an embodiment of the present application.

Detailed Description

Embodiments of the present application will be further described below with reference to the accompanying drawings. The same or similar reference numbers in the drawings identify the same or similar elements or elements having the same or similar functionality throughout.

In addition, the embodiments of the present application described below in conjunction with the accompanying drawings are exemplary and are only for the purpose of explaining the embodiments of the present application, and are not to be construed as limiting the present application.

In this application, unless expressly stated or limited otherwise, the first feature "on" or "under" the second feature may be directly contacting the first and second features or indirectly contacting the first and second features through intervening media. Also, a first feature "on," "over," and "above" a second feature may be directly or diagonally above the second feature, or may simply indicate that the first feature is at a higher level than the second feature. A first feature being "under," "below," and "beneath" a second feature may be directly under or obliquely under the first feature, or may simply mean that the first feature is at a lesser elevation than the second feature.

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 and 4 to 7, 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 formed integrally with the hub 10, or may be separately machined and then fixedly mounted as a single piece. At 44.8% of the radius of the propeller 100 from the center of the hub 10 (at O in fig. 1) D3, the angle of attack α 3 of the blades 20 is 20.00 ° ± 2.5 °; at a distance D4 of 59.7% of the radius of the propeller 100 from the center of the hub 10, the angle of attack α 4 of the blades 20 is 17.00 ° ± 2.5 °; d5 at 74.6% of the radius of the propeller 100 from the center of the hub 10, the angle of attack α 5 of the blades 20 being 13.00 ° ± 2.5 °; at a distance D6 of 89.6% of the radius of the propeller 100 from the center of the hub 10, the angle of attack α 6 of the blades 20 is 11.00 ° ± 2.5 °.

In the present embodiment, since D3 is located 44.8% of the radius of the propeller 100 from the center of the hub 10, the angle of attack α 3 of the blade 20 is 20.00 ° ± 2.5 °; at a distance D4 of 59.7% of the radius of the propeller 100 from the center of the hub 10, the angle of attack α 4 of the blades 20 is 17.00 ° ± 2.5 °; d5 at 74.6% of the radius of the propeller 100 from the center of the hub 10, the angle of attack α 5 of the blades 20 being 13.00 ° ± 2.5 °; at a distance D6 of 89.6% of the radius of the propeller 100 from the center of the hub 10, the angle of attack α 6 of the blades 20 is 11.00 ° ± 2.5 °. Therefore, by defining a blade 20 having a specific shape according to the above parameters, the propeller 100 using the blade 20 can effectively reduce energy consumption, improve efficiency, increase endurance, and allow the aircraft 1000 (shown in fig. 12) to operate for a longer time. Furthermore, when the flight speed of the aircraft 1000 is too high, the tension of the blade 20 is attenuated more rapidly, avoiding the danger caused by continuous high-speed flight.

At a distance D3 of 44.8% of the radius of the propeller 100 from the center of the hub 10, the angle of attack α 3 of the blade 20 is 20.00 ° ± 2.5 °, and the projected length L3 of the chord length of the blade 20 within the rotor disc is 17.19mm ± 1.72 mm. At a distance D4 of 59.7% of the radius of the propeller 100 from the center of the hub 10, the angle of attack α 4 of the blade 20 is 17.00 ° ± 2.5 °, and the projected length L4 of the chord length of the blade 20 within the rotor disc is 16.03mm ± 1.60 mm. At a distance D5 of 74.6% of the radius of the propeller 100 from the center of the hub 10, the angle of attack α 5 of the blade 20 is 13.00 ° ± 2.5 °, and the projected length L5 of the chord length of the blade 20 within the rotor disc is 14.23mm ± 1.42 mm. At a distance D6 of 89.6% of the radius of the propeller 100 from the center of the hub 10, the angle of attack α 6 of the blade 20 is 11.00 ° ± 2.5 °, and the projected length L6 of the chord length of the blade 20 within the rotor disc is 10.56mm ± 1.06 mm. It should be noted that the paddle wheel refers to a plane formed by the rotating blades 20 when the propeller 100 rotates, and the paddle wheel is referred to hereinafter and will not be described again.

In the present embodiment, since D3 is located at 44.8% of the radius of the propeller 100 from the center of the hub 10, the angle of attack α 3 of the blade 20 is 20.00 ° ± 2.5 °, and the length of the chord of the blade 20 projected in the disk L3 is 17.19mm ± 1.72 mm. At a distance D4 of 59.7% of the radius of the propeller 100 from the center of the hub 10, the angle of attack α 4 of the blade 20 is 17.00 ° ± 2.5 °, and the projected length L4 of the chord length of the blade 20 within the rotor disc is 16.03mm ± 1.60 mm. At a distance D5 of 74.6% of the radius of the propeller 100 from the center of the hub 10, the angle of attack α 5 of the blade 20 is 13.00 ° ± 2.5 °, and the projected length L5 of the chord length of the blade 20 within the rotor disc is 14.23mm ± 1.42 mm. At a distance D6 of 89.6% of the radius of the propeller 100 from the center of the hub 10, the angle of attack α 6 of the blade 20 is 11.00 ° ± 2.5 °, and the projected length L6 of the chord length of the blade 20 within the rotor disc is 10.56mm ± 1.06 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 energy consumption, improve efficiency, increase endurance time, and make the aircraft 1000 operate continuously for a longer time. Furthermore, when the flight speed of the aircraft 1000 is too high, the tension of the blade 20 is attenuated more rapidly, avoiding the danger caused by continuous high-speed flight.

Referring to table 1, taking the same blade diameter as an example, the propeller 100 provided in this embodiment can reduce the power consumption of the blade compared to the current propeller on the market under 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, adopt this application paddle 20 can also be when the flying speed is too high, and the pulling force decay is very fast, avoids lasting the danger that high-speed flight leads to.

TABLE 1

Referring to fig. 1 and 4, at a distance D3 of 44.8% 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 any one of or any value between 17.50 ° or 20.00 ° or 22.50 °, or 17.62 °, 18.18 °, 18.75 °, 19.30 °, 19.92 °, 20.50 °, 21.12 °, 21.72 °, 22.00 °, 22.48 °, etc., and the projected length L3 of the chord of the blade 20 within the paddle disk may be any one of or any value between 15.47mm or 17.19mm or 18.91mm, or 15.57mm, 16.00mm, 16.40mm, 16.72mm, 17.13mm, 17.38mm, 17.75mm, 18.08mm, 18.50mm, 18.88mm, etc.

Referring to fig. 1 and 5, at 59.7% of the radius of the propeller 100 from the center of the hub 10, D4, the angle of attack α 4 of the blade 20 may be 14.50 °, or 17.00 °, or 19.50 °, or any one of 14.58 °, 15.09 °, 15.59 °, 16.28 °, 16.82 °, 17.58 °, 18.10 °, 18.62 °, 19.00 °, 19.45 °, or any value therebetween, and the projected length L4 of the chord length of the blade 20 within the paddle disk may be 14.43mm, or 16.03mm, or 17.63mm, or any one of 14.55mm, 14.80mm, 15.21mm, 15.52mm, 15.93mm, 16.38mm, 16.65mm, 16.98mm, 17.20mm, 17.55mm, or any one of the above two.

Referring to fig. 1 and 6, at a distance D5 of 74.6% 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 10.50 °, or 13.00 °, or 15.50 °, or any one of or any value between 10.58 °, 11.12 °, 11.79 °, 12.30 °, 12.92 °, 13.50 °, 13.90 °, 14.42 °, 14.90 °, 15.45 °, etc., and the projected length L5 of the chord of the blade 20 within the paddle disk may be 12.81mm, or 14.23mm, or 15.65mm, or any one of or any value between 12.95mm, 13.20mm, 13.51mm, 13.82mm, 14.19mm, 14.38mm, 14.65mm, 14.98mm, 15.20mm, 15.55mm, etc.

Referring to fig. 1 and 7, at a distance D6 of 89.6% 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 8.50 °, or 11.00 °, or 13.50 °, or any one of or any value between 8.60 °, 9.09 °, 9.69 °, 10.28 °, 10.92 °, 11.58 °, 12.00 °, 12.52 °, 12.90 °, 13.45 °, etc., and the projected length L6 of the chord of the blade 20 within the paddle disk may be 9.50mm, or 10.56mm, or 11.62mm, or any one of or any value between 9.60mm, 9.80mm, 10.01mm, 10.22mm, 10.49mm, 10.70mm, 10.95mm, 11.08mm, 11.20mm, 11.55mm, 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 be elongated, and the blades 20 are connected to the hub 10 and extend in a radial direction of the hub 10.

Referring to fig. 1 and 2, in the present embodiment, optionally, at a position D1 that is 14.9% of the radius of the propeller 100 from the center of the hub 10, the projected length L1 of the chord length of the blade 20 in the blade disc is 11.21mm ± 1.12mm, so as to further reduce the energy consumption of the propeller 100, improve the efficiency, and facilitate the improvement of the cruising ability of the aircraft 1000. In addition, when the flying speed is too high, the tension attenuation speed can be further improved, and the danger caused by continuous high-speed flying is avoided. The projection length L1 of the chord length of the blade 20 in the paddle disk may be 10.09mm, 11.21mm or 12.33mm, or any one of 10.19mm, 10.39mm, 10.60mm, 10.89mm, 11.19mm, 11.30mm, 11.51mm, 11.73mm, 11.93mm, 12.28mm, etc. or a value between any two of the above.

Referring to fig. 1 and 3, in the present embodiment, optionally, at a position D2 that is 29.9% of the radius of the propeller 100 from the center of the hub 10, the angle of attack α 2 of the blade 20 is 22.00 ° ± 2.5 °, and the length of the chord of the blade 20 projected in the rotor disc L2 is 17.52mm ± 1.75mm, so as to further reduce the energy consumption of the propeller 100, improve the efficiency, and facilitate the improvement of the cruising ability of the aircraft 1000. In addition, when the flying speed is too high, the tension attenuation speed can be further improved, and the danger caused by continuous high-speed flying is avoided. Wherein the angle of attack α 2 of the blade 20 may be 19.50 °, 22.00 ° or 24.50 °, or may be any one of 19.60 °, 20.19 °, 20.70 °, 21.30 °, 21.90 °, 22.40 °, 22.90 °, 23.50 °, 23.95 °, 24.45 °, or any two of the above, and the projected length L2 of the chord length of the blade 20 in the paddle disk may be 15.77mm, 17.52mm, or 19.27mm, or any one of 15.85mm, 16.20mm, 16.60mm, 17.03mm, 17.40mm, 17.93mm, 18.20mm, 18.68mm, 18.88mm, 19.17mm, or any one of the above or any two of the above.

Referring to fig. 1 and 8, in the present embodiment, optionally, at a position D7 that is 98.5% 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 9.00 ° ± 2.5 °, and the length of the chord of the blade 20 projected in the rotor disc L7 is 6.26mm ± 0.63mm, so as to further reduce the energy consumption of the propeller 100, improve the efficiency, and facilitate the improvement of the cruising ability of the aircraft 1000. In addition, when the flying speed is too high, the tension attenuation speed can be further improved, and the danger caused by continuous high-speed flying is avoided. Wherein the angle of attack α 7 of the blade 20 may be 6.50 °, 9.00 °, 11.50 °, or any one or a number between any two of 6.60 °, 7.19 °, 7.70 °, 8.30 °, 8.90 °, 9.40 °, 9.90 °, 10.50 °, 10.95 °, 11.45 °, etc., and the projected length L7 of the chord length of the blade 20 within the paddle disk may be 5.63mm, 6.26mm, or 6.89mm, or any one or a number between any two of 5.65mm, 5.80mm, 5.90mm, 6.03mm, 6.20mm, 6.33mm, 6.40mm, 6.58mm, 6.68mm, 6.79mm, etc.

Referring to fig. 1 and 9, in the present embodiment, optionally, at a position D8 that is 100% of the radius of the propeller 100 from the center of the hub 10, the angle of attack α 8 of the blade 20 is 2.00 ° ± 2.5 °, and the length of the chord of the blade 20 projected in the paddle L8 is 4.64mm ± 0.46mm, so as to further reduce the energy consumption of the propeller 100, improve the efficiency, and facilitate the improvement of the cruising ability of the aircraft 1000. In addition, when the flying speed is too high, the tension attenuation speed can be further improved, and the danger caused by continuous high-speed flying is avoided. Wherein the angle of attack α 8 of the blade 20 may be 0.00 ° or 2.00 ° or 4.50 °, or any one or a number between any two of 0.02 °, 0.50 °, 1.01 °, 1.50 °, 1.90 °, 2.40 °, 2.90 °, 3.40 °, 3.95 °, 4.45 °, etc., and the projected length L8 of the chord length of the blade 20 within the paddle disk may be 4.18mm or 4.64mm or 5.10mm, or any one or a number between any two of 4.25mm, 4.32mm, 4.40mm, 4.49mm, 4.59mm, 4.63mm, 4.70mm, 4.88mm, 4.98mm, 5.05mm, etc.

Referring to fig. 1 and 4 to 7, in the present embodiment, the diameter of the propeller 100 is optionally 134.00mm ± 13.4 mm. At a distance of 30mm from the center of the hub 10, D3, the angle of attack α 3 of the blade 20 is 20.00 ° ± 2.5 °, and the projected length L3 of the chord length of the blade 20 within the rotor disc is 17.19mm ± 1.72 mm. At a distance of 40mm from the center of the hub 10, D4, the angle of attack α 4 of the blade 20 is 17.00 ° ± 2.5 °, and the projected length L4 of the chord length of the blade 20 within the rotor disc is 16.03mm ± 1.60 mm. At a distance of 50mm from the center of the hub 10, D5, the angle of attack α 5 of the blade 20 is 13.00 ° ± 2.5 °, and the projected length L5 of the chord length of the blade 20 within the rotor disc is 14.23mm ± 1.42 mm. At a distance of 60mm from the center of hub 10, D6, the angle of attack α 6 of blade 20 is 11.00 ° ± 2.5 °, and the projected length of the chord length of blade 20 within the rotor disc, L6, is 10.56mm ± 1.06 mm. In this way, the parameter limitation in the present embodiment can further reduce the energy consumption of the propeller 100, improve the efficiency, and is beneficial to improving the endurance of the aircraft 1000. In addition, when the flying speed is too high, the tension attenuation speed can be further improved, and the danger caused by continuous high-speed flying is avoided. The diameter of the propeller 100 may be 120.60mm, 134.00mm or 147.40mm, or 120.70mm, 123.45mm, 126.00mm, 129.80mm, 132.90mm, 134.90mm, 137.62mm, 140.40mm, 144.00mm, 147.35mm, or any one or a value between the foregoing two.

Referring to fig. 1 to 3 and 8 to 9, in the present embodiment, the diameter of the propeller 100 is optionally 134.00mm ± 13.4 mm. The projected length L1 of the chord length of the blade 20 within the rotor disc at 10mm from the center of the hub 10D 1 was 11.21mm ± 1.12 mm. At 20mm from the center of the hub 10, D2, the angle of attack α 2 of the blade 20 is 22.00 ° ± 2.5 °, and the projected length L2 of the chord length of the blade 20 within the rotor disc is 17.52mm ± 1.75 mm. At 66mm from the center of the hub 10, D7, the angle of attack α 7 of the blade 20 is 9.00 ° ± 2.5 °, and the projected length of the chord length of the blade 20 within the rotor disc, L7, is 6.26mm ± 0.63 mm. At 67mm from the center of the hub 10, D8, the angle of attack α 8 of the blade 20 is 2.00 ° ± 2.5 °, and the projected length of the chord length of the blade 20 within the rotor disc, L8, is 4.64mm ± 0.46 mm. In this way, the parameter limitation in the present embodiment can further reduce the energy consumption of the propeller 100, improve the efficiency, and is beneficial to improving the endurance of the aircraft 1000. In addition, when the flying speed is too high, the tension attenuation speed can be further improved, and the danger caused by continuous high-speed flying is avoided. The diameter of the propeller 100 may be 120.60mm, 134.00mm or 147.40mm, or 120.70mm, 123.45mm, 126.00mm, 129.80mm, 132.90mm, 134.90mm, 137.62mm, 140.40mm, 144.00mm, 147.35mm, or any one or a value between the foregoing two.

In certain embodiments, the pitch of the blades 20 is optionally 2.80 ± 0.28 inches. From this, can effectual reduction energy consumption, raise the efficiency, increase duration, make aircraft 1000 duration time of working more of a specified duration. Wherein the pitch of the blades 20 may be 2.52 inches, 2.80 inches, or 3.08 inches, or any one or a number between any of 2.60 inches, 2.69 inches, 2.78 inches, 2.85 inches, 2.90 inches, 2.95 inches, 3.00 inches, etc.

Referring to fig. 1, 10 and 11, in the embodiment of the present application, the blade 20 optionally includes a root 21, a tip 22 facing away from the root 21, and opposite pressure and suction surfaces 23 and 24. Wherein pressure surface 23 is the surface of blade 20 that faces the ground during normal flight of aircraft 1000 (as shown in fig. 12), and suction surface 24 is the surface of blade 20 that faces the sky during normal flight of aircraft 1000.

In the embodiment of the present application, optionally, both the suction surface 24 and the pressure surface 23 are 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. 12) of the aircraft 1000, thereby reducing the overall noise of the aircraft 1000.

In the embodiment of the present application, the blade 20 further includes a front edge 25 connected to one side of the pressure surface 23 and the suction surface 24, and a rear edge 26 connected to the other side of the pressure surface 23 and the suction surface 24. 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 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 some embodiments, the blade 20 further comprises a swept portion 27 formed at the tip 22, the swept portion 27 extending obliquely from the leading edge 25 to the trailing edge 26, which can also further improve the drag of the blade 20 and the efficiency of the propeller 100.

In some embodiments, leading edge 25 extends obliquely from root 21 in a span-wise direction toward the side where pressure surface 23 is located and is inversely oblique at a portion near tip 21 toward the side where suction surface 22 is located and meets trailing edge 26 at tip 21. The sweep 27 extends obliquely from the leading edge 25 to the trailing edge 26. The air resistance can be reduced, the pulling force and the efficiency are improved, the relay distance of the aircraft is increased, the flight performance of the aircraft is improved, and meanwhile, the noise generated by the blades 20 during operation is reduced, so that the aircraft is quieter when hovering, and the user experience is improved.

In some embodiments, the sides of the free end of the tip 22 may be planar. Thus, the planar free end may enhance the aesthetic appearance of the propeller 100.

Referring to fig. 10, in some embodiments, the number of blades 20 in the propeller 100 is three, and three blades 20 are connected to the hub 10, wherein the included angle between any two adjacent blades 20 is equal. That is, three blades 20 are evenly distributed about hub 10. The propeller 100 including three blades 20 can raise the pulling force of the propeller 100 compared to the propeller 100 provided with only two blades 20.

In some embodiments, the propeller 100 is D2 at 29.9% of the radius of the propeller 100 from the center of the hub 10, the angle of attack α 2 of the blades 20 is 22.00 ° ± 2.5 °; and/or

At a distance D7 of 98.5% of the radius of the propeller 100 from the center of the hub 10, the angle of attack α 7 of the blades 20 is 9.00 ° ± 2.5 °; and/or

At a distance D8 from the center of hub 10 of 100% of the radius of propeller 100, angle of attack α 8 of blade 20 is 2.00 ° ± 2.5 °; and/or

At 20mm from the center of hub 10, D2, the angle of attack α 2 of blade 20 is 22.00 °; and/or

At 30mm from the center of hub 10, D3, the angle of attack α 3 of blade 20 is 20.00 °; and/or

At 40mm from the center of hub 10, D4, the angle of attack α 4 of blade 20 is 17.00 °; and/or

At 50mm from the centre of the hub 10D 5, the angle of attack α 5 of the blade 20 is 13.00 °; and/or

At 60mm from the center of hub 10, D6, the angle of attack α 6 of blade 20 is 11.00 °; and/or

At 66mm from the center of hub 10, D7, the angle of attack α 7 of blade 20 is 9.00 °; and/or

At 67mm from the centre of the hub 10D 8, the angle of attack α 8 of the blade 20 is 2.00 °.

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

(1) the propeller 100 has an angle of attack α 2 of the blades 20 of 22.00 ° ± 2.5 ° at a distance D2 from the center of the hub 10 of 29.9% of the radius of the propeller 100;

(2) the propeller 100 is D7 at a distance of 98.5% of the radius of the propeller 100 from the center of the hub 10, the angle of attack α 7 of the blades 20 is 9.00 ° ± 2.5 °;

(3) the propeller 100 is at a distance D8 from the center of the hub 10 of 100% of the radius of the propeller 100, the angle of attack α 8 of the blades 20 being 2.00 ° ± 2.5 °;

(4) the propeller 100 has an angle of attack α 2 of the blades 20 of 22.00 ° at 20mm from the centre of the hub 10D 2;

(5) the propeller 100 has an angle of attack α 3 of the blades 20 of 20.00 ° at 30mm from the centre of the hub 10D 3;

(6) propeller 100 has an angle of attack α 4 of blades 20 of 17.00 ° at 40mm from the center of hub 10D 4;

(7) the propeller 100 has an angle of attack α 5 of the blades 20 of 13.00 ° at a distance D5 of 50mm from the centre of the hub 10;

(8) the propeller 100 has an angle of attack α 6 of the blades 20 of 11.00 ° at a distance D6 of 60mm from the center of the hub 10;

(9) propeller 100 has an angle of attack α 7 of 9.00 ° at 66mm from the center of hub 10D 7 for blade 20;

(10) propeller 100 has an angle of attack α 8 of 2.00 ° at 67mm from the center of hub 10D 8 for blade 20;

(11) the propeller 100 has an angle of attack α 2 of the blades 20 of 22.00 ° ± 2.5 ° at a distance D2 from the center of the hub 10 of 29.9% of the radius of the propeller; and, at a distance D7 of 98.5% of the radius of the propeller 100 from the center of the hub 10, the angle of attack α 7 of the blades 20 is 9.00 ° ± 2.5 °; and, at a distance D8 from the center of hub 10 of 100% of the radius of propeller 100, angle of attack α 8 of blade 20 is 2.00 ° ± 2.5 °; and, at a distance D2 of 20mm from the center of hub 10, the angle of attack α 2 of blade 20 is 22.00 °; and, at a distance D3 of 30mm from the center of hub 10, angle of attack α 3 of blade 20 is 20.00 °; and, at a distance of 40mm from the centre of hub 10, D4, the angle of attack α 4 of blade 20 is 17.00 °; and, at a distance of 50mm from the centre of the hub 10, D5, the angle of attack α 5 of the blade 20 is 13.00 °; and, at a distance of 60mm from the centre of hub 10, D6, the angle of attack α 6 of blade 20 is 11.00 °; and, at 66mm from the centre of the hub 10D 7, the angle of attack α 7 of the blade 20 is 9.00 °; and an angle of attack α 8 of the blades 20 of 2.00 ° at 67mm from the centre of the hub 10D 8.

In some embodiments, the propeller 100 is at 44.8% of the radius of the propeller 100 from the center of the hub 10, D3, and the projected length L3 of the chord length of the blades 20 within the rotor disc is 17.19mm ± 1.72 mm; and/or

The projected length L4 of the chord length of the blade 20 in the rotor disc at a distance D4 of 59.7 percent of the radius of the propeller 100 from the center of the rotor hub 10 is 16.03mm +/-1.60 mm; and/or

At a distance D5 of 74.6% of the radius of the propeller 100 from the center of the hub 10, the projected length L5 of the chord length of the blade 20 within the rotor disc is 14.23mm ± 1.42 mm; and/or

The projected length L6 of the chord length of the blade 20 in the rotor disc at a distance D6 of 89.6 percent of the radius of the propeller 100 from the center of the rotor hub 10 is 10.56mm +/-1.06 mm; and/or

The projection length L3 of the chord length of the blade 20 in the paddle disk at the position D3 which is 30mm away from the center of the hub 10 is 17.19 mm; and/or

The projection length L4 of the chord length of the blade 20 in the paddle disk at the position D4 which is 40mm away from the center of the paddle hub 10 is 16.03 mm; and/or

The projection length L5 of the chord length of the blade 20 in the paddle disk at the position D5 which is 50mm away from the center of the paddle hub 10 is 14.23 mm; and/or

The projected length of the chord of the blade 20 within the rotor disc at 60mm from the centre of the hub 10D 6, L6 was 10.56 mm.

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

(1) the propeller 100 is D3 at a position which is 44.8% of the radius of the propeller 100 from the center of the hub 10, and the projection length L3 of the chord length of the blade 20 in the paddle disk is 17.19mm +/-1.72 mm;

(2) the propeller 100 is D4 at the position 59.7% of the radius of the propeller 100 from the center of the hub 10, and the projection length L4 of the chord length of the blade 20 in the paddle disk is 16.03mm +/-1.60 mm;

(3) the propeller 100 is D5 at a position 74.6% of the radius of the propeller 100 from the center of the hub 10, and the projection length L5 of the chord length of the blade 20 in the paddle disk is 14.23mm +/-1.42 mm;

(4) the propeller 100 is D6 at a position 89.6% of the radius of the propeller 100 from the center of the hub 10, and the projection length L6 of the chord length of the blade 20 in the paddle disk is 10.56mm +/-1.06 mm;

(5) the propeller 100 is at a position 30mm away from the center of the hub 10, D3, and the projection length L3 of the chord length of the blade 20 in the blade disc is 17.19 mm;

(6) the propeller 100 is at a position 40mm away from the center of the hub 10, D4, and the projection length L4 of the chord length of the blade 20 in the blade disc is 16.03 mm;

(7) the propeller 100 is at a position 50mm away from the center of the hub 10, D5, and the projection length L5 of the chord length of the blade 20 in the blade disc is 14.23 mm;

(8) the propeller 100 is at a position 60mm away from the center of the hub 10, D6, and the projection length L6 of the chord length of the blade 20 in the paddle disk is 10.56 mm;

(9) the propeller 100 is D3 at a position which is 44.8% of the radius of the propeller 100 from the center of the hub 10, and the projection length L3 of the chord length of the blade 20 in the paddle disk is 17.19mm +/-1.72 mm; and, at a distance D4 of 59.7% of the radius of the propeller 100 from the center of the hub 10, the projected length L4 of the chord length of the blades 20 in the rotor disc is 16.03mm ± 1.60 mm; and, at a distance D5 of 74.6% of the radius of the propeller 100 from the center of the hub 10, the projected length L5 of the chord length of the blades 20 within the rotor disc is 14.23mm ± 1.42 mm; and, at a distance D6 of 89.6% of the radius of the propeller 100 from the center of the hub 10, the projected length L6 of the chord length of the blades 20 in the rotor disc is 10.56mm ± 1.06 mm; and, at a distance of 30mm from the center of the hub 10, D3, the projected length L3 of the chord length of the blade 20 in the disk is 17.19 mm; and, at a distance of 40mm from the center of the hub 10, D4, the projected length L4 of the chord length of the blade 20 in the disk is 16.03 mm; and, at a distance of 50mm from the center of the hub 10, D5, the projected length L5 of the chord length of the blade 20 in the disk is 14.23 mm; and the projection length L6 of the chord length of the blade 20 in the paddle disk at the position D6 which is 60mm away from the center of the paddle hub 10 is 10.56 mm.

In some embodiments, the propeller 100 is at 14.9% of the radius of the propeller 100 from the center of the hub 10, D1, and the projected length of the chord of the blades 20 within the rotor disc, L1, is 11.21mm ± 1.12 mm; and/or

At a distance D2 of 29.9% of the radius of the propeller 100 from the center of the hub 10, the projected length L2 of the chord length of the blade 20 within the rotor disc is 17.52mm ± 1.75 mm; and/or

At a distance D7 of 98.5% of the radius of the propeller 100 from the center of the hub 10, the projection length L7 of the chord length of the blade 20 in the paddle disk is 6.26mm +/-0.63 mm; and/or

The projected length L8 of the chord length of the blades 20 within the rotor disc at a distance D8 from the center of the hub 10 of 100% of the radius of the rotor 100 is 4.64mm ± 0.46 mm; and/or

The projection length L1 of the chord length of the blade 20 in the paddle disk at a position D1 which is 10mm away from the center of the paddle hub 10 is 11.21 mm; and/or

The projection length L2 of the chord length of the blade 20 in the paddle disk at a position D2 which is 20mm away from the center of the hub 10 is 17.52 mm; and/or

The projection length L7 of the chord length of the blade 20 in the paddle disk at 66mm from the center of the hub 10, D7, is 6.26 mm; and/or

The projected length L8 of the chord length of the blade 20 within the rotor disc at 67mm from the center of the hub 10D 8 was 4.64 mm.

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

(1) the propeller 100 is D1 at a position which is 14.9% of the radius of the propeller 100 from the center of the hub 10, and the projection length L1 of the chord length of the blade 20 in the paddle disk is 11.21mm +/-1.12 mm;

(2) the propeller 100 is D2 at the position 29.9% of the radius of the propeller 100 from the center of the hub 10, and the projection length L2 of the chord length of the blade 20 in the paddle disk is 17.52mm +/-1.75 mm;

(3) the propeller 100 is D7 at a position which is 98.5 percent of the radius of the propeller 100 from the center of the hub 10, and the projection length L7 of the chord length of the blade 20 in the blade disc is 6.26mm +/-0.63 mm;

(4) the propeller 100 is D8 at the position which is 100% of the radius of the propeller 100 and is away from the center of the hub 10, and the projection length L8 of the chord length of the blade 20 in the paddle disk is 4.64mm +/-0.46 mm;

(5) the propeller 100 is at a position 10mm away from the center of the hub 10, D1, and the projection length L1 of the chord length of the blade 20 in the blade disc is 11.21 mm;

(6) the propeller 100 is at a position 20mm away from the center of the hub 10, D2, the projection length L2 of the chord length of the blade 20 in the blade disc is 17.52 mm;

(7) the propeller 100 is at 66mm distance D7 from the center of the hub 10, and the projection length L7 of the chord length of the blade 20 in the paddle disk is 6.26 mm;

(8) the propeller 100 is at 67mm from the center of the hub 10, D8, and the projection length L8 of the chord length of the blade 20 in the paddle disk is 4.64 mm;

(9) the propeller 100 is D1 at a position which is 14.9% of the radius of the propeller 100 from the center of the hub 10, and the projection length L1 of the chord length of the blade 20 in the paddle disk is 11.21mm +/-1.12 mm; and, at 29.9% of the radius of the propeller 100 from the center of the hub 10, D2, the projected length L2 of the chord length of the blades 20 within the rotor disc is 17.52mm ± 1.75 mm; and, at a distance D7 of 98.5% of the radius of the propeller 100 from the center of the hub 10, the projected length L7 of the chord length of the blades 20 in the rotor disc is 6.26mm ± 0.63 mm; and, at a distance D8 of 100% of the radius of the propeller 100 from the center of the hub 10, the projected length L8 of the chord length of the blades 20 within the rotor disc is 4.64mm ± 0.46 mm; and, at 10mm from the center of the hub 10D 1, the projected length L1 of the chord length of the blade 20 in the disk is 11.21 mm; and, at a distance of 20mm from the center of the hub 10, D2, the projected length L2 of the chord length of the blade 20 in the disk is 17.52 mm; and, at 66mm from the center of the hub 10D 7, the projected length L7 of the chord length of the blade 20 within the rotor disc is 6.26 mm; and the projected length L8 of the chord length of the blade 20 in the paddle disk at 67mm from the center of the hub 10D 8 is 4.64 mm.

Referring to fig. 12, 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 may be an electric motor, and one driving member 30 may be used to rotate one or more propellers 100, and in the embodiment of the present application, one driving 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 α 3 of the blades 20 is 20.00 ° ± 2.5 ° due to D3 at 44.8% of the radius of the propeller 100 from the center of the hub 10; at a distance D4 of 59.7% of the radius of the propeller 100 from the center of the hub 10, the angle of attack α 4 of the blades 20 is 17.00 ° ± 2.5 °; d5 at 74.6% of the radius of the propeller 100 from the center of the hub 10, the angle of attack α 5 of the blades 20 being 13.00 ° ± 2.5 °; at a distance D6 of 89.6% of the radius of the propeller 100 from the center of the hub 10, the angle of attack α 6 of the blades 20 is 11.00 ° ± 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 energy consumption, improve efficiency and increase endurance time. In addition, when the flying speed is too high, the tension of the blade 20 is attenuated more quickly, and the danger caused by continuous high-speed flying is avoided.

Referring again to fig. 12, 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. 12 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 α 3 of the blades 20 is 20.00 ° ± 2.5 ° due to D3 at a distance from the center of the hub 10 of 44.8% of the radius of the propeller 100; at a distance D4 of 59.7% of the radius of the propeller 100 from the center of the hub 10, the angle of attack α 4 of the blades 20 is 17.00 ° ± 2.5 °; d5 at 74.6% of the radius of the propeller 100 from the center of the hub 10, the angle of attack α 5 of the blades 20 being 13.00 ° ± 2.5 °; at a distance D6 of 89.6% of the radius of the propeller 100 from the center of the hub 10, the angle of attack α 6 of the blades 20 is 11.00 ° ± 2.5 °. Therefore, by defining the blades 20 with a specific shape according to the above parameters, the propeller 100 using the blades 20 can effectively reduce energy consumption, improve efficiency, increase endurance time, and enable the aircraft 1000 to operate for a longer time. Furthermore, when the flying speed of the aircraft 1000 is too high, the tension of the blade 20 can be quickly attenuated, avoiding the danger caused by continuous high-speed flight.

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

1. A propeller comprising a hub and blades attached to said hub;

at 44.8% of the radius of the propeller from the center of the hub, the angle of attack of the blades is 20.00 ° ± 2.5 °;

at 59.7% of the radius of the propeller from the center of the hub, the angle of attack of the blades is 17.00 ° ± 2.5 °;

at a distance of 74.6% of the radius of the propeller from the center of the hub, the angle of attack of the blades is 13.00 ° ± 2.5 °;

the angle of attack of the blades is 11.00 ° ± 2.5 ° at 89.6% of the radius of the propeller from the center of the hub.

2. The propeller of claim 1, wherein:

at 29.9% of the radius of the propeller from the center of the hub, the angle of attack of the blades is 22.00 ° ± 2.5 °; and/or

The angle of attack of the blades is 9.00 ° ± 2.5 ° at a distance from the centre of the hub of 98.5% of the radius of the propeller; and/or

The angle of attack of the blades is 2.00 ° ± 2.5 ° at a distance from the centre of the hub of 100% of the radius of the propeller; and/or

At 20mm from the centre of the hub, the angle of attack of the blade is 22.00 °; and/or

At 30mm from the centre of the hub, the angle of attack of the blade is 20.00 °; and/or

At 40mm from the centre of the hub, the angle of attack of the blade is 17.00 °; and/or

At 50mm from the centre of the hub, the angle of attack of the blade is 13.00 °; and/or

At 60mm from the centre of the hub, the angle of attack of the blade is 11.00 °; and/or

At 66mm from the centre of the hub, the angle of attack of the blade is 9.00 °; and/or

At 67mm from the centre of the hub, the angle of attack of the blade is 2.00 °.

3. The propeller of claim 1, wherein:

the projected length of the chord length of the blade in the paddle disk is 17.19mm +/-1.72 mm at the position which is 44.8% of the radius of the propeller from the center of the paddle hub; and/or

The projected length of the chord length of the blade in the paddle disk is 16.03mm +/-1.60 mm at the position which is 59.7 percent of the radius of the propeller from the center of the paddle hub; and/or

The projected length of the chord length of the blade in the paddle disk is 14.23mm +/-1.42 mm at the position which is 74.6 percent of the radius of the propeller from the center of the paddle hub; and/or

The projected length of the chord length of the blade in the paddle disk is 10.56mm +/-1.06 mm at the position which is 89.6 percent of the radius of the propeller from the center of the paddle hub; and/or

The projected length of the chord length of the blade in the paddle disk is 17.19mm at the position 30mm away from the center of the paddle hub; and/or

The projection length of the chord length of the blade in the paddle disc is 16.03mm at the position 40mm away from the center of the paddle hub; and/or

The projection length of the chord length of the blade in the paddle disc is 14.23mm at the position 50mm away from the center of the paddle hub; and/or

The projected length of the chord length of the blade within the rotor disc at 60mm from the centre of the hub is 10.56 mm.

4. The propeller of claim 3, wherein:

the projected length of the chord length of the blade in the paddle disk is 11.21mm +/-1.12 mm at the position which is 14.9% of the radius of the propeller from the center of the paddle hub; and/or

The projected length of the chord length of the blade in the paddle disk is 17.52mm +/-1.75 mm at the distance of 29.9% of the radius of the propeller from the center of the paddle hub; and/or

The projected length of the chord length of the blade in the paddle disk is 6.26mm +/-0.63 mm at the position which is 98.5 percent of the radius of the propeller from the center of the paddle hub; and/or

The projected length of the chord length of the blade in a blade disc is 4.64mm +/-0.46 mm at the position which is 100% of the radius of the propeller from the center of the hub; and/or

The projection length of the chord length of the blade in the paddle disc is 11.21mm at the position 10mm away from the center of the paddle hub; and/or

The projection length of the chord length of the blade in the paddle disc is 17.52mm at the position 20mm away from the center of the paddle hub; and/or

The projected length of the chord length of the blade in the paddle disk at 66mm from the center of the paddle hub is 6.26 mm; and/or

The projected length of the chord length of the blade within the disc at 67mm from the centre of the hub is 4.64 mm.

5. The propeller of claim 1, wherein the propeller has a diameter of 134mm ± 13.4 mm; and/or

The pitch of the blade is 2.80 + -0.28 inches.

6. 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 to one side edge of the pressure surface and the suction surface, the rear edge is connected to the other side edge of the pressure surface and the suction surface, and the sweepback portion is formed on the blade tip and extends from the front edge to the rear edge in an inclined mode.

7. 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 three, and included angles between any two adjacent blades connected to the propeller hub are equal; and/or

The suction surface and the pressure surface are both curved surfaces.

8. A power assembly comprising a drive member and the propeller of any one of claims 1 to 7, wherein the propeller is connected to the drive member by the hub.

9. An aircraft comprising a fuselage and the power assembly of claim 8, wherein the power assembly is coupled to the fuselage.

10. The aircraft of claim 9 wherein the aircraft includes a plurality of power assemblies that rotate in different directions, the aircraft being a multi-rotor aircraft.