CN210235310U - Screw, power component and aircraft - Google Patents

Abstract

The application discloses screw, power component and aircraft. The propeller comprises a hub and blades, the blades are connected to the hub, and the attack angle of the blades is 18 degrees +/-2.5 degrees at the position which is 41.8 percent of the radius of the propeller away from the center of the hub; the angle of attack of the blades is 16 ° ± 2.5 ° at a distance from the centre of the hub of 58.5% of the radius of the propeller; the angle of attack of the blades is 12 ° ± 2.5 ° at a distance from the center of the hub that is 75.2% of the radius of the propeller; the attack angle of the blades is 8 degrees +/-2.5 degrees at the position which is 91.9 percent of the radius of the propeller from the center of the propeller hub; therefore, the propeller with the blades in the specific shape is defined by the parameters, and the propeller with the blades can effectively reduce energy consumption, improve efficiency, increase endurance time and improve flight performance of an aircraft.

Description

Screw, power component and aircraft

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.

The small-size propeller in the prior art is small in size and low in Reynolds number, so that the propeller is difficult to ensure pneumatic performance under low tension, and the air-leaving time of a micro aircraft is 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 present application comprises a hub and blades attached to the hub, the blades having an angle of attack of 18 ° ± 2.5 ° at a distance of 41.8% of the radius of the propeller from the center of the hub; at 58.5% of the radius of the propeller from the center of the hub, the angle of attack of the blades is 16 ° ± 2.5 °; at 75.2% of the radius of the propeller from the center of the hub, the angle of attack of the blades is 12 ° ± 2.5 °; the angle of attack of the blades is 8 ° ± 2.5 ° at 91.9% of the radius of the propeller from the center of the hub.

In certain embodiments, the angle of attack of the blades is 13 ° ± 2.5 ° at a distance from the center of the hub of 25.1% of the radius of the propeller; and/or the angle of attack of the blades is 4 ° ± 2.5 ° at a distance from the centre of the hub of 96.9% of the radius of the propeller; and/or the angle of attack of the blades is 13 ° at 15mm from the centre of the hub; and/or the angle of attack of the blades is 18 ° at 25mm from the centre of the hub; and/or the angle of attack of the blades is 16 ° at 35mm from the centre of the hub; and/or the angle of attack of the blades is 12 ° at 45mm from the centre of the hub; and/or the angle of attack of the blades is 8 ° at 55mm from the centre of the hub; and/or the angle of attack of the blades is 4 ° at 58mm from the centre of the hub.

In some embodiments, the chord length of the blade is 17.40mm ± 1.74mm at 41.8% of the radius of the propeller from the center of the hub; and/or the chord length of the blade is 15.50mm +/-1.55 mm at a position 58.5% of the radius of the propeller from the center of the propeller hub; and/or the chord length of the blade is 12.11mm +/-1.21 mm at a position which is 75.2% of the radius of the propeller from the center of the propeller hub; and/or the chord length of the blade is 9.69mm +/-0.97 mm at the position which is 91.9% of the radius of the propeller from the center of the propeller hub; and/or the chord length of the blade is 17.40mm at a distance of 25mm from the center of the hub; and/or the chord length of the blade is 15.50mm at a distance of 35mm from the center of the hub; and/or the chord length of the blade is 12.11mm at a distance of 45mm from the center of the hub; and/or the chord length of the blade is 9.69mm at a distance of 55mm from the center of the hub.

In some embodiments, the chord length of the blade is 11.07mm ± 1.11mm at 25.1% of the radius of the propeller from the center of the hub; and/or the chord length of the blade is 6.58mm +/-0.66 mm at a distance of 96.9% of the radius of the propeller from the center of the hub; and/or the chord length of the blade is 11.07mm at a distance of 15mm from the center of the hub; and/or the chord length of the blade is 6.58mm at a distance of 58mm from the center of the hub.

In certain embodiments, the diameter of the propeller is 119.7mm ± 12.0 mm.

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 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 application comprises a fuselage and the power assembly of the above embodiment, wherein the power assembly is connected with the fuselage.

In some 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 18 degrees +/-2.5 degrees at the position which is 41.8 percent of the radius of the propeller away from the center of the propeller hub; the angle of attack of the blades is 16 ° ± 2.5 ° at a distance from the centre of the hub of 58.5% of the radius of the propeller; the angle of attack of the blades is 12 ° ± 2.5 ° at a distance from the center of the hub that is 75.2% of the radius of the propeller; the attack angle of the blades is 8 degrees +/-2.5 degrees at the position which is 91.9 percent of the radius of the propeller from the center of the propeller hub; therefore, the propeller with the blades in the specific shape is defined by the parameters, and the propeller with the blades can effectively reduce energy consumption, improve efficiency, increase endurance time and improve flight performance of an 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: newly-added figure modification, illustration in description

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 the section B-B in the propeller of the embodiment shown in figure 1 at a distance of 25mm from the centre of the hub.

Figure 3 is a cross-sectional view of the section C-C in the propeller of the embodiment shown in figure 1 at 35mm from the centre of the hub.

Figure 4 is a cross-sectional view of the D-D section at 45mm 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 section E-E in the propeller of the embodiment shown in figure 1 at 55mm from the centre of the hub.

Figure 6 is a cross-sectional view of section a-a at 15mm from the hub center in the propeller of the embodiment shown in figure 1.

Figure 7 is a cross-sectional view of the F-F section at 58mm from the center of the hub in the propeller of the embodiment shown in figure 1.

Fig. 8 is a schematic plan view of a blade of a propeller according to an embodiment of the present application.

Fig. 9 is a schematic plan view of an aircraft according to 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 to 5, the present embodiment provides a propeller 100, and the propeller 100 includes a hub 10 and blades 20.

The blades 20 are attached to the hub 10. of course, the blades 20 can be formed integrally with the hub 10 or can be separately machined and fixedly mounted as one piece.D 2 at 41.8% of the radius of the propeller 100 from the center of the hub 10, the angle of attack α 2 of the blades 20 is 18 ° ± 2.5 °, D3 at 58.5% of the radius of the propeller 100 from the center of the hub 10, the angle of attack α 3 of the blades 20 is 16 ° ± 2.5 °, D4 at 75.2% 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 12 ° ± 2.5 °, D5 at 91.9% of the radius of the propeller 100 from the center of the hub 10, and the angle of attack α 5 of the blades 20 is 8 ° ± 2.5 °.

In the present embodiment, since the D2 and the attack angle α 2 of the blade 20 are 18 ° ± 2.5 ° at a distance of 41.8% of the radius of the propeller 100 from the center of the hub 10, the D3 and the attack angle α 3 of the blade 20 are 16 ° ± 2.5 ° at a distance of 58.5% of the radius of the propeller 100 from the center of the hub 10, the D4 and the attack angle α 4 of the blade 20 are 12 ° ± 2.5 ° at a distance of 75.2% of the radius of the propeller 100 from the center of the hub 10, the D5 and the attack angle α 5 of the blade 20 are 8 ° ± 2.5 ° at a distance of 91.9% of the radius of the propeller 100 from the center of the hub 10, the blade 20 having a specific shape is defined by the above parameters, and the propeller 100 using the blade 20 can effectively reduce energy consumption, improve efficiency, increase endurance, and improve flight performance of the aircraft 1000 (as shown in fig. 9).

Referring to fig. 1 to 5, the present embodiment provides a propeller 100, and the propeller 100 includes a hub 10 and blades 20.

D2 at a distance of 41.8% of the radius of the propeller 100 from the center of the hub 10, D α 2 of the blade 20 at 18 ° ± 2.50 °, L2 of the blade 20 at 17.40mm ± 1.74mm, D3 at a distance of 58.5% of the radius of the propeller 100 from the center of the hub 10, D4 at an angle of attack α 3 of the blade 20 at 16 ° ± 2.50 °, L3 of the blade 20 at 15.50mm ± 1.55mm, D5 at a distance of 75.2% of the radius of the propeller 100 from the center of the hub 10, D α 4 of the blade 20 at 12 ° ± 2.50 °, L4 of the blade 20 at 12.11mm ± 1.21mm, D5 at a distance of 91.9% of the radius of the propeller 100 from the center of the hub 10, D α 5 of the blade 20 at 8 ° ± 2.50 and L5 at 9.69mm ± 0.97 mm.

In this embodiment, D2 at a distance of 41.8% of the radius of propeller 100 from the center of hub 10, D2 at an angle of attack α of blade 20 of 18 ° ± 2.50 °, L2 at a length of 17.4mm ± 1.74mm, D3 at a distance of 58.5% of the radius of propeller 100 from the center of hub 10, angle of attack α of blade 20 of 16 ° ± 2.50 °, L3 at a length of 15.5mm ± 1.55mm, D4 at a distance of 75.2% of the radius of propeller 100 from the center of hub 10, angle of attack α of blade 20 of 12 ° ± 2.50 °, L4 at a length of L of 12.11mm ± 1.21mm of blade 20, D5 at a distance of 91.9% of the radius of propeller 100 from the center of hub 10, angle of blade 20 of α at a length of 8 ° ± 2.50 °, L38769 at a length of blade 20 of 589 mm, D5 at a length of blade 20 of 97.9 mm from the center of propeller 100, the above mentioned blade 20, the above mentioned flight parameters being effective to increase the efficiency of the aircraft, and increase the flight time of the above mentioned propeller 20, as shown by the improvement of the flight parameter.

Referring to table 1, taking the same blade diameter as an example, the power consumption of the blade 100 provided by the present embodiment can be reduced by 10% to 30% compared to the current market blades with the same blade area and smaller tension difference. 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. Therefore, the propeller 100 provided by the embodiment can significantly improve the pulling force, ensure sufficient power and prolong the endurance time and improve the flight performance under the extreme condition of large takeoff weight in a high altitude area or a low altitude area with reduced density.

TABLE 1

Referring to fig. 1 to 5, at a distance D2 of 41.8% of the radius of the propeller 100 from the center of the hub 10, the angle of attack α 2 of the blade 20 may be 15.5 ° or 18 ° or 20.5 °, or 16 °, 16.5 °, 17 °, 17.5 °, 18 °, 18.5 °, 19 °, 19.5 °, 20 °, or the like, or any value therebetween, and the chord length L2 of the blade 20 may be 15.66mm or 17.40mm or 19.14mm, or any one or a value therebetween of 16mm, 16.5mm, 17mm, 17.5mm, 18mm, 18.5mm, 19mm, or the like.

At a distance D3 of 58.5% of the radius of the propeller 100 from the centre of the hub 10, the angle of attack α 3 of the blade 20 may be 13.5 ° or 16 ° or 18.5 °, or a value between any one or any two of 14 °, 14.52 °, 15 °, 15.5 °, 16.5 °, 17 °, 17.5 °, 18 °, etc., and the chord length L3 of the blade 20 may be 13.95mm or 15.50mm or 17.05mm, or any one or a value between any two of 14mm, 14.5mm, 15mm, 16mm, 16.5mm, 17mm, etc.

At a distance D4 of 75.2% of the radius of the propeller 100 from the centre of the hub 10, the angle of attack α 4 of the blade 20 may be 9.5 ° or 12 ° or 14.5 °, or any one or a number between any two of 10 °, 10.5 °, 11 °, 11.5 °, 12.5 °, 13 °, 13.5 °, 14 °, etc., and the chord length L4 of the blade 20 may be 10.90mm or 12.11mm or 13.32mm, or any one or a number between any two of 11mm, 11.25mm, 11.5mm, 12mm, 12.25mm, 12.5mm, 13mm, 13.25mm, etc.

At a distance D5 of 91.9% of the radius of the propeller 100 from the centre of the hub 10, the angle of attack α 5 of the blade 20 may be 5.5 ° or 8 ° or 10.5 °, or any one or a number between any two of 6 °, 6.5 °, 7 °, 7.5 °, 8.5 °, 9 °, 9.5 °, 10 °, etc., and the chord length L5 of the blade 20 may be 8.72mm or 9.69mm or 10.66mm, or any one or a number between any two of 9mm, 9.25mm, 9.5mm, 9.75mm, 10mm, 10.25mm, 10.5mm, 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. 6, in the present embodiment, optionally, at a position 25.1% of the radius of the propeller 100 from the center of the hub 10, D1 is provided, the angle of attack α 1 of the blade 20 is 13 ° ± 2.50 °, and the chord length L1 of the blade 20 is 11.07mm ± 1.11mm, so as to further reduce the air resistance of the propeller 100 and improve the drag force and efficiency, wherein the angle of attack α 1 of the blade 20 may be 10.5 ° or 13 ° or 15.5 °, or any one of 11 °, 11.5 °, 12 °, 12.5 °, 13.5 °, 14 °, 14.5 °, 15 °, or any value therebetween, and the chord length L1 of the blade 20 may be 9.96mm or 11.07mm or 12.18mm, or any one of 10mm, 10.25mm, 10.5mm, 11mm, 11.25mm, 11.5mm, 12mm, or any one of the foregoing two.

Referring to fig. 7, in the present embodiment, optionally, at a position D6 which is 96.9% 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 4 ° ± 2.50 °, and the chord length L6 of the blade 20 is 6.58mm ± 0.66mm, so as to further reduce the air resistance of the propeller 100 and improve the drag force and efficiency, wherein the angle of attack α 6 of the blade 20 may be 1.5 ° or 4 ° or 6.5 °, or any one of 2 °, 2.5 °, 3 °, 3.5 °, 4.5 °, 5 °, 5.5 °, 6 ° and the like or a value therebetween, and the chord length L6 of the blade 20 may be 5.92mm or 6.58mm or 7.24mm, or any one of 6mm, 6.2mm, 6.25mm, 6.5mm, 6.75mm, 6.8mm, 7mm and the like or a value therebetween.

Referring to fig. 1 to 5, in the present embodiment, optionally, the diameter of the propeller 100 is 119.7mm ± 12.0mm, D2 is 41.8% 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 18 °, the chord length L2 of the blade 20 is 17.40mm, D3 is 58.5% 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 16 °, the chord length L3 of the blade 20 is 15.50mm, D4 is 75.2% 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 12 °, the chord length L4 of the blade 20 is 12.11, D5 is 91.9% of the radius of the propeller 100 from the center of the hub 10, the angle of the blade α 5 is 8mm, and the chord length L5 of the blade 8620 is 9.69 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. Wherein the diameter of the propeller 100 may be 107.7mm or 119.7mm or 131.7mm, or any one of 110mm, 112mm, 115mm, 118mm, 120mm, 122mm, 125mm, 128mm, 130mm, etc., or a value between any two of the foregoing.

Referring to fig. 1, 6 and 7, in the present embodiment, optionally, the diameter of the propeller 100 is 119.7mm ± 12mm, D1 is 25.1% of the radius of the propeller 100 from the center of the hub 10, the angle of attack α 1 of the blade 20 is 13 °, the chord length L1 of the blade 20 is 11.07mm, D6 is 96.9% 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 4 °, and the chord length L6 of the blade 20 is 6.58mm, so the parameters in the present embodiment define that the air resistance of the propeller 100 can be further reduced, and the drag and efficiency can be improved, wherein the diameter of the propeller 100 can be 107.7mm or 119.7mm or 131.7mm, or any one or both of 110mm, 112mm, 115mm, 118mm, 120mm, 122mm, 125mm, 128mm, 130mm, and the like.

Referring to fig. 1, 2 and 8, 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 pressure surface 23 is the surface of blade 20 that faces the ground during normal flight of aircraft 1000 (as shown in fig. 9), and suction surface 24 is the surface of blade 20 that faces the sky during normal flight of aircraft 1000.

In the present embodiment, the angle of attack of the blades 20 is optionally gradually reduced in a direction from 41.8% 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 range of the aircraft 1000 (as shown in fig. 9) 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 reduces the air resistance and improves the pulling force of the blades 20, but also prevents the turbulence generated by each part of the blades 20 and the downwash from directly impacting the fuselage 50 (as shown in fig. 9) 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, 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 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 the present embodiment, optionally, the blade 20 forms a return bend 27 near the tip 22, the leading edge 25 extends obliquely from the return bend 27 toward the suction surface 24 in the span direction of the blade 20, and the sweep portion 221 extends obliquely from the return bend 27 toward the trailing edge 26 from the leading edge 25. The position of the return bend 27 is indicated by MM.

In this embodiment, the return bend 27 is optionally 91.9% of the radius of the propeller 100 from the center of the hub 10. The return bend 27 is located away from the center of the hub 10, improving the aesthetic appearance of the blades 20 and also reducing the interaction between the propeller 100 and the horn 40 (shown in fig. 9) of the aircraft 1000.

In the present embodiment, at least two blades 20 are optionally provided, and at least two blades 20 are connected to the hub 10 and are centrosymmetric with respect to the center of the 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, the free end 222 of the tip 22 is optionally flat on its side. Thus, the planar free end 222 may enhance the aesthetic appearance of the propeller 100.

Referring to fig. 1, in the present embodiment, optionally, blade 20 has a central axis N-N passing through the center of hub 10, leading edge 25 has a leading edge tangent O-O parallel to central axis N-N, trailing edge 26 has a trailing edge tangent P-P parallel to central axis N-N, and root 21 is located between leading edge tangent O-O and trailing edge tangent P-P. Wherein the leading edge tangent line O-O 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. 9), 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, the propeller 100 has an angle of attack α 1 of 13 ° ± 2.50 ° at a distance D1 from the center of the hub 10 of 25.1% of the radius of the propeller 100 and/or the blades 20

The angle of attack α 6 of the blades 20 is 4 ° ± 2.50 ° at a distance D6 of 96.9% of the radius of the propeller 100 from the center of the hub 10, and/or

An angle of attack α 1 of 13 DEG at 15mm from the center of the hub 10D 1 for the blade 20, and/or

At 25mm from the center of hub 10D 2, angle of attack α 2 of blade 20 is 18 DEG, and/or

At 35mm from the center of the hub 10D 3, the angle of attack α 3 of the blade 20 is 16 DEG, and/or

At a distance D4 of 45mm from the center of hub 10, angle of attack α 4 of blade 20 is 12 DEG, and/or

An angle of attack α 5 of 8 DEG at a distance D5 of 55mm from the center of hub 10, and/or

At 58mm from the center of hub 10, D6, the angle of attack α 6 of blade 20 is 4 °.

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

(1) propeller 100 is at 25.1% of the radius of propeller 100 from the center of hub 10D 1, and the angle of attack α 1 of blades 20 is 13 ° ± 2.50 °;

(2) the propeller 100 is at 96.9% of the radius of the propeller 100 from the center of the hub 10D 6, the angle of attack α 6 of the blades 20 is 4 ° ± 2.50 °;

(3) at 15mm from the center of hub 10, D1, the angle of attack α 1 of blade 20 is 13 °;

(4) propeller 100 at 25mm from the center of hub 10D 2, blade 20 has an angle of attack α 2 of 18 °;

(5) propeller 100 is at 35mm from the center of hub 10D 3, and the angle of attack α 3 of blades 20 is 16 °;

(6) propeller 100 at 45mm from the center of hub 10D 4, angle of attack α 4 of blades 20 is 12 °;

(7) the propeller 100 is at 55mm from the center of the hub 10D 5, the angle of attack α 5 of the blades 20 is 8 °;

(8) propeller 100 at 58mm from the center of hub 10D 6, angle of attack α 6 of blade 20 is 4 °;

(9) the propeller 100 has an angle of attack D1 at 25.1% of the radius of the propeller 100 from the center of the hub 10 and 13 ° ± 2.50 ° for the blades 20, and D6 at 96.9% of the radius of the propeller 100 from the center of the hub 10 and 4 ° ± 2.50 ° for the angles of attack α for the blades 20, and D1 at 15mm from the center of the hub 10 and 13 ° for the angles of attack α for the blades 20, and D2 at 25mm from the center of the hub 10 and 18 ° for the angles of attack α and α for the blades 20, and D3 at 35mm from the center of the hub 10 and 16 ° for the angles of attack α and α for the blades 20, and D4 at 45mm from the center of the hub 10 and 12 ° for the angles of attack α for the blades 20, and D5 at 55mm from the center of the hub 10 and 8mm from the center of the blades 20 and 894 ° for the angles of attack 857 mm and 857 mm from the center of the hub 10 and 857 mm and 36 mm.

In certain embodiments, the propeller 100 is D2 at a distance of 41.8% of the radius of the propeller 100 from the center of the hub 10, the chord length L2 of the blades 20 is 17.40mm ± 1.74 mm; and/or

At a distance D3 of 58.5% of the radius of the propeller 100 from the centre of the hub 10, the chord length L3 of the blade 20 is 15.50mm ± 1.55 mm; and/or

At a distance D4 of 75.2% of the radius of the propeller 100 from the centre of the hub 10, the chord length L4 of the blade 20 is 12.11mm ± 1.21 mm; and/or

At a distance D5 of 91.9% of the radius of the propeller 100 from the centre of the hub 10, the chord length L5 of the blade 20 is 9.69mm ± 0.97 mm; and/or

At 25mm from the centre of the hub 10D 2, the chord length L2 of the blade 20 is 17.40 mm; and/or

At 35mm from the centre of the hub 10D 3, the chord length L3 of the blade 20 is 15.50 mm; and/or

At 45mm from the centre of the hub 10D 4, the chord length L4 of the blade 20 is 12.11 mm; and/or

At 55mm from the centre of the hub 10D 5, the chord length L5 of the blade 20 is 9.69 mm.

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

(1) the propeller 100 is D2 at a distance of 41.8% of the radius of the propeller 100 from the center of the hub 10, and the chord length L2 of the blades 20 is 17.40mm +/-1.74 mm;

(2) the propeller 100 is D3 at a distance of 58.5% of the radius of the propeller 100 from the center of the hub 10, and the chord length L3 of the blades 20 is 15.50mm +/-1.55 mm;

(3) the propeller 100 is D4 at a distance of 75.2% of the radius of the propeller 100 from the center of the hub 10, and the chord length L4 of the blades 20 is 12.11mm +/-1.21 mm;

(4) the propeller 100 is D5 at a distance of 91.9% of the radius of the propeller 100 from the center of the hub 10, and the chord length L5 of the blade 20 is 9.69mm +/-0.97 mm;

(5) the propeller 100 is at 25mm from the center of the hub 10D 2, the chord length L2 of the blades 20 is 17.40 mm;

(6) the propeller 100 is at 35mm from the center of the hub 10D 3, and the chord length L3 of the blade 20 is 15.50 mm;

(7) the propeller 100 is at 45mm from the center of the hub 10D 4, and the chord length L4 of the blade 20 is 12.11 mm;

(8) the propeller 100 has a chord length L5 of 9.69mm at a distance D5 of 55mm from the center of the hub 10 of the blade 20.

(9) The propeller 100 is D2 at a distance of 41.8% of the radius of the propeller 100 from the center of the hub 10, and the chord length L2 of the blades 20 is 17.40mm +/-1.74 mm; and D3 at a distance of 58.5% of the radius of the propeller 100 from the center of the hub 10, the chord length L3 of the blades 20 is 15.50mm ± 1.55 mm; and, D4 at a distance of 75.2% of the radius of the propeller 100 from the center of the hub 10, the chord length L4 of the blades 20 is 12.11mm ± 1.21 mm; and D5 at a distance of 91.9% of the radius of the propeller 100 from the center of the hub 10, the chord length L5 of the blade 20 is 9.69mm ± 0.97 mm; and, at 25mm from the centre of the hub 10D 2, the chord length L2 of the blade 20 is 17.40 mm; and, at 35mm from the centre of the hub 10D 3, the chord length L3 of the blade 20 is 15.50 mm; and, at 45mm from the centre of the hub 10D 4, the chord length L4 of the blade 20 is 12.11 mm; and a chord length L5 of the blade 20 of 9.69mm at a distance D5 of 55mm from the center of the hub 10.

In certain embodiments, the propeller 100 is at a distance of 25.1% of the radius of the propeller 100 from the center of the hub 10, D1, and the chord length L1 of the blades 20 is 11.07mm ± 1.11 mm; and/or

At a distance D6 of 96.9% of the radius of the propeller 100 from the centre of the hub 10, the chord length L6 of the blade 20 is 6.58mm ± 0.66 mm; and/or

At 15mm from the centre of the hub 10D 1, the chord length L1 of the blade 20 is 11.07 mm; and/or

At a distance of 58mm from the centre of the hub 10D 6, the chord length L6 of the blade 20 is 6.58 mm.

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

(1) the propeller 100 is D1 at a distance of 25.1% of the radius of the propeller 100 from the center of the hub 10, and the chord length L1 of the blades 20 is 11.07mm +/-1.11 mm;

(2) the propeller 100 is D6 at a distance of 96.9% of the radius of the propeller 100 from the center of the hub 10, and the chord length L6 of the blades 20 is 6.58mm +/-0.66 mm;

(3) the propeller 100 is at 15mm from the center of the hub 10, D1, and the chord length L1 of the blade 20 is 11.07 mm;

(4) the propeller 100 is at a distance of 58mm from the center of the hub 10D 6, and the chord length L6 of the blade 20 is 6.58 mm;

(5) the propeller 100 is D1 at a distance of 25.1% of the radius of the propeller 100 from the center of the hub 10, and the chord length L1 of the blades 20 is 11.07mm +/-1.11 mm; and the propeller 100 is D6 at a position 96.9% of the radius of the propeller 100 from the center of the hub 10, and the chord length L6 of the blades 20 is 6.58mm +/-0.66 mm; and the propeller 100 is at 15mm from the center of the hub 10D 1, the chord length L1 of the blade 20 is 11.07 mm; and the propeller 100 has a chord length L6 of 6.58mm at a distance D6 of 58mm from the center of the hub 10 of the blade 20.

In summary, with the blade 20 having gradually changed airfoil shape in the above embodiment of the present application, the propeller 100 can significantly increase the tension in the plateau area, and ensure sufficient power redundancy. Meanwhile, the performance is considered to a certain extent, the following flight distance is increased, and the flight performance of the aircraft 1000 (shown in fig. 9) is improved. Compared with the existing propeller 100 on the market, the propeller 100 adopting the paddle 20 has larger pulling force under the condition of lower power, thereby reducing the electric quantity loss and increasing the cruising distance. Under the extreme condition that the takeoff weight is larger in a high-altitude area or a low-altitude area with reduced density, the aircraft can obviously improve the pulling force, ensure enough power and prolong the endurance time at the same time, and improve the flight performance. In addition, the propeller 100 provided by the embodiment can also effectively reduce noise generated by turbulence and downwash airflow impacting the body 50 of the aircraft 1000, reduce discomfort of human ears caused by the noise, and improve user experience.

Referring to fig. 9, 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 power assembly 200 includes at least two horn 40. At least two horn 40 are attached to the propeller assembly 100 at a central location. The drive member 30 is disposed on the horn 40. The specific structure of the propeller 100 is the same as that of the foregoing embodiments, and is not described herein again. That is, the description about the propeller 100 as in the above embodiment and the embodiment is equally applicable to the power assembly 200 provided in the embodiment of the present application.

In the power module 200 of the present application, since the angle of attack 2 of the blade 20 is 18 ° ± 2.5 ° at 41.8% of the radius of the propeller 100 from the center of the hub 10, the angle of attack α of the blade 20 is 18 ° ± 2.5 ° at 58.5% of the radius of the propeller 100 from the center of the hub 10, the angle of attack α of the blade 20 is 16 ° ± 2.5 ° at D4 at 75.2% 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 12 ° ± 2.5 ° and the angle of attack α of the blade 20 is 8 ° ± 2.5 ° at 91.9% of the radius of the propeller 100 from the center of the hub 10, the blade 20 having a specific shape is defined by the above parameters, the propeller 100 using the blade 20 can effectively reduce energy consumption, improve efficiency, increase endurance, and improve flight performance of the aircraft 1000.

Referring again to fig. 9, 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 different.

In this embodiment, optionally, the aircraft 1000 is a multi-rotor aircraft, such as a quad-rotor unmanned aircraft.

In the aircraft 1000 of the present application, since the D2 is located at a distance of 41.8% of the radius of the propeller 100 from the center of the hub 10, the attack angle α of the blade 20 is 18 ° ± 2.5 °, the D3 is located at a distance of 58.5% of the radius of the propeller 100 from the center of the hub 10, the attack angle α of the blade 20 is 16 ° ± 2.5 °, the attack angle D4 is located at a distance of 75.2% of the radius of the propeller 100 from the center of the hub 10, the attack angle α of the blade 20 is 12 ° ± 2.5 °, the D5 is located at a distance of 91.9% of the radius of the propeller 100 from the center of the hub 10, and the attack angle α of the blade 20 is 8 ° ± 2.5 °, 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, and improve flight performance of the aircraft 1000.

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 (11)

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

the angle of attack of the blades is 18 ° ± 2.5 ° at a distance from the centre of the hub of 41.8% of the radius of the propeller;

at 58.5% of the radius of the propeller from the center of the hub, the angle of attack of the blades is 16 ° ± 2.5 °;

at 75.2% of the radius of the propeller from the center of the hub, the angle of attack of the blades is 12 ° ± 2.5 °;

the angle of attack of the blades is 8 ° ± 2.5 ° at 91.9% of the radius of the propeller from the center of the hub.

2. The propeller of claim 1, wherein:

at a distance of 25.1% of the radius of the propeller from the center of the hub, the angle of attack of the blades is 13 ° ± 2.5 °; and/or

At 96.9% of the radius of the propeller from the center of the hub, the angle of attack of the blades is 4 ° ± 2.5 °; and/or

At 15mm from the centre of the hub, the angle of attack of the blade is 13 °; and/or

At 25mm from the centre of the hub, the angle of attack of the blade is 18 °; and/or

At 35mm from the centre of the hub, the angle of attack of the blade is 16 °; and/or

At 45mm from the centre of the hub, the angle of attack of the blade is 12 °; and/or

At 55mm from the centre of the hub, the angle of attack of the blade is 8 °; and/or

At 58mm from the centre of the hub, the angle of attack of the blade is 4 °.

3. The propeller of claim 1, wherein:

the chord length of the blade is 17.40mm ± 1.74mm at a distance of 41.8% of the radius of the propeller from the centre of the hub; and/or

The chord length of the blade is 15.50mm ± 1.55mm at a distance of 58.5% of the radius of the propeller from the centre of the hub; and/or

The chord length of the blade is 12.11mm + -1.21 mm at a distance of 75.2% of the radius of the propeller from the center of the hub; and/or

The chord length of the blade is 9.69mm +/-0.97 mm at the position which is 91.9% of the radius of the propeller from the center of the propeller hub; and/or

At 25mm from the centre of the hub, the chord length of the blade is 17.40 mm; and/or

At 35mm from the centre of the hub, the chord length of the blade is 15.50 mm; and/or

At 45mm from the centre of the hub, the chord length of the blade is 12.11 mm; and/or

The chord length of the blade is 9.69mm at 55mm from the centre of the hub.

4. The propeller of claim 3, wherein:

the chord length of the blade is 11.07mm + -1.11 mm at a distance of 25.1% of the radius of the propeller from the center of the hub; and/or

The chord length of the blade is 6.58mm ± 0.66mm at 96.9% of the radius of the propeller from the center of the hub; and/or

At 15mm from the centre of the hub, the chord length of the blade is 11.07 mm; and/or

At 58mm from the centre of the hub, the chord length of the blade is 6.58 mm.

5. The propeller of claim 1, wherein the propeller has a diameter of 119.7mm ± 12.0 mm.

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 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.

7. 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.

8. 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.

9. 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.

10. An aircraft comprising a fuselage and the power assembly of claim 9, the power assembly being coupled to the fuselage.

11. 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.

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