WO2019148879A1 - Propeller, power component and aircraft - Google Patents

Propeller, power component and aircraft Download PDF

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Publication number
WO2019148879A1
WO2019148879A1 PCT/CN2018/109068 CN2018109068W WO2019148879A1 WO 2019148879 A1 WO2019148879 A1 WO 2019148879A1 CN 2018109068 W CN2018109068 W CN 2018109068W WO 2019148879 A1 WO2019148879 A1 WO 2019148879A1
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WO
WIPO (PCT)
Prior art keywords
blade
hub
center
propeller
distance
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PCT/CN2018/109068
Other languages
French (fr)
Chinese (zh)
Inventor
刘翊涵
陈鹏
邓涛
Original Assignee
深圳市大疆创新科技有限公司
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Application filed by 深圳市大疆创新科技有限公司 filed Critical 深圳市大疆创新科技有限公司
Publication of WO2019148879A1 publication Critical patent/WO2019148879A1/en

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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
    • B64C11/02—Hub construction
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
    • B64C11/16—Blades
    • B64C11/20—Constructional features

Definitions

  • Embodiments of the present invention relate to the field of aircraft, and more particularly to propellers, power components, and aircraft.
  • the propeller on the aircraft is used to convert the rotation of the shaft of the motor or engine into thrust or lift.
  • the propeller is rotating, and the turbulence of each part of the blade and the downwashing airflow impinging on the outer casing structure of the aircraft generate a large noise. It is often superimposed with motor noise and structural vibration noise, and amplifies noise in certain frequency bands, resulting in a large overall noise of the aircraft and poor user experience.
  • Embodiments of the present invention provide a propeller, a power assembly, and an aircraft.
  • a propeller of an embodiment of the invention includes a hub and a blade, the blade being coupled to the hub, wherein:
  • the angle of attack of the blade is 24.60 ° ⁇ 2.5 ° at a distance of 42.9% of the radius of the propeller from the center of the hub;
  • the angle of attack of the blade is 23.50 ° ⁇ 2.5 ° at a distance of 52.4% of the radius of the propeller from the center of the hub;
  • the angle of attack of the blade is 21.82 ° ⁇ 2.5 ° at a distance of 61.9% of the radius of the propeller from the center of the hub;
  • the blade At an angle of 71.4% of the radius of the propeller from the center of the hub, the blade has an angle of attack of 19.97 ° ⁇ 2.5 °.
  • the angle of attack of the blade is 24.60° ⁇ 2.5° at a distance of 42.9% of the radius of the propeller from the center of the hub, and the chord length of the blade is 26.49 mm ⁇ 5 mm; at a distance of 52.4% of the radius of the propeller from the center of the hub, the angle of attack of the blade is 23.50° ⁇ 2.5°, and the chord length of the blade is 25.16 mm ⁇ 5 mm;
  • the distance from the center of the hub is 61.9% of the radius of the propeller, the angle of attack of the blade is 21.82 ° ⁇ 2.5 °, the chord length of the blade is 23.59 mm ⁇ 5 mm;
  • the center of the hub is 71.4% of the radius of the propeller, the angle of attack of the blade is 19.97° ⁇ 2.5°, and the chord length of the blade is 21.69 mm ⁇ 5 mm.
  • the diameter of the propeller is 210 mm ⁇ 21 mm; at an angle of 45 mm from the center of the hub, the angle of attack of the blade is 24.60 °, the chord length of the blade is 26.49 mm; At 55 mm from the center of the hub, the blade has an angle of attack of 23.50°, the blade has a chord length of 25.16 mm; at a distance of 65 mm from the center of the hub, the blade is attacked The angle is 21.82°, the chord length of the blade is 23.59 mm; the angle of attack of the blade is 19.97° at a distance of 75 mm from the center of the hub, and the chord length of the blade is 21.69 mm.
  • the blade at 23.8% of the radius of the propeller from the center of the hub, the blade has an angle of attack of 23.40° ⁇ 2.5° and the blade has a chord length of 21.21 mm. ⁇ 5mm.
  • the diameter of the propeller is 210 mm ⁇ 21 mm; at 25 mm from the center of the hub, the blade has an angle of attack of 23.40° and the blade has a chord length of 21.21 mm.
  • the blade at 33.3% of the radius of the propeller from the center of the hub, the blade has an angle of attack of 26.20° ⁇ 2.5° and the blade has a chord length of 27.38 mm. ⁇ 5mm.
  • the diameter of the propeller is 210 mm ⁇ 21 mm; at 35 mm from the center of the hub, the blade has an angle of attack of 26.20° and the blade has a chord length of 27.38 mm.
  • the blade at an angle of 81.0% of the radius of the propeller from the center of the hub, the blade has an angle of attack of 17.97° ⁇ 2.5° and the blade has a chord length of 19.45 mm. ⁇ 5mm.
  • the diameter of the propeller is 210 mm ⁇ 21 mm; at 85 mm from the center of the hub, the blade has an angle of attack of 17.97° and the blade has a chord length of 19.45 mm.
  • the angle of attack of the blade is 16.61° ⁇ 2.5° at a distance of 90.5% of the radius of the propeller from the center of the hub, and the chord length of the blade is 15.78 mm ⁇ 5mm.
  • the diameter of the propeller is 210 mm ⁇ 21 mm;
  • the blade At an angle of 95 mm from the center of the hub, the blade has an angle of attack of 16.61° and the blade has a chord length of 15.78 mm.
  • the angle of attack of the blade is 9.39° ⁇ 2.5° at a distance of 100% of the radius of the propeller from the center of the hub, and the chord length of the blade is 4.94 mm ⁇ 2mm.
  • the diameter of the propeller is 210 mm ⁇ 21 mm; at 105 mm from the center of the hub, the angle of attack of the blade is 9.39 ° and the chord length of the blade is 4.94 mm.
  • the paddle includes a paddle root, a blade tip facing away from the paddle root, a opposing pressure surface, and a suction surface; the tip of the blade is oriented toward the suction in a direction in which the blade is spanned The side where the face is located extends obliquely.
  • the blade further includes a leading edge connected to one side of the pressure surface and the suction surface, a trailing edge connected to the pressure surface and the other side of the suction surface, And a swept portion formed on the tip of the blade, the swept portion extending obliquely from the leading edge toward the trailing edge.
  • the blade forms a back bend at the position of the tip, the leading edge starting from the bend back along the direction of the blade toward the suction side
  • the side slope extends, and the swept portion extends obliquely from the leading edge to the trailing edge from the return bend.
  • the center of the back bend from the hub is 82.5% of the radius.
  • leading edge is convexly formed with a curved leading edge bulging portion near the paddle
  • trailing edge is convexly formed with a curved shape near the paddle. The edge of the arch.
  • the blades are at least two, and at least two of the blades are coupled to the hub and are centrally symmetric about a center of the hub.
  • the paddle has a central axis passing through a center of the hub, the leading edge having a leading edge tangent parallel to the central axis, the trailing edge having a parallel to the middle A trailing edge of the axis is tangent, the swept portion being between the leading edge tangent and the trailing edge tangent.
  • the suction side and the pressure side are both curved surfaces.
  • the pitch of the paddle is 3.6 ⁇ 0.5 inches.
  • a power assembly includes a driving member and a propeller according to any one of the above embodiments, wherein the propeller is coupled to the driving member through the hub.
  • the drive member is a motor having a KV value of 360 to 810 rpm / (minute volts).
  • An aircraft provided by an embodiment of the present invention includes a fuselage and the power assembly of claim 22 or 23, and the power component is coupled to the fuselage.
  • the aircraft includes a plurality of power components that rotate in different directions.
  • the aircraft is a multi-rotor aircraft.
  • the propeller, the power assembly and the aircraft provided by the embodiments of the present invention have an angle of attack of 24.60° ⁇ 2.5° at a distance of 42.9% of the radius of the propeller from the center of the hub; and a propeller at the center of the hub; At 52.4% of the radius, the angle of attack of the blade is 23.50° ⁇ 2.5°; at 61.9% of the radius of the propeller from the center of the hub, the angle of attack of the blade is 21.82 ° ⁇ 2.5 °; at the distance from the hub The center is 71.4% of the radius of the propeller, and the angle of attack of the blade is 19.97° ⁇ 2.5°.
  • the propeller using the blade can reduce the air resistance, increase the pulling force and efficiency, and increase the flight distance of the aircraft to improve the flight of the aircraft. Performance, while also increasing the maximum pulling force of the aircraft while reducing efficiency, reducing the risk of aircraft out of control, improving flight safety, and further reducing the noise generated by the blades during operation, making the aircraft more hovering. Quiet and improved user experience.
  • FIG. 1 is a schematic plan view of a propeller according to an embodiment of the present invention.
  • Figure 2 is a cross-sectional view of the C-C section of the propeller of the embodiment of Figure 1 at a distance of 45 mm from the center of the hub.
  • Figure 3 is a cross-sectional view of the D-D section of the propeller of the embodiment of Figure 1 at a distance of 55 mm from the center of the hub.
  • Figure 4 is a cross-sectional view of the E-E section of the propeller of the embodiment of Figure 1 at a distance of 65 mm from the center of the hub.
  • Figure 5 is a cross-sectional view of the F-F section of the propeller of the embodiment of Figure 1 at a distance of 75 mm from the center of the hub.
  • Fig. 6 is a schematic diagram showing the frequency response curve of the propeller of the present invention and the existing propeller under the same hovering condition acoustic performance test conditions.
  • Figure 7 is a cross-sectional view of the A-A section of the propeller of the embodiment of Figure 1 taken at a distance of 25 mm from the center of the hub.
  • Figure 8 is a cross-sectional view of the B-B section of the propeller of the embodiment of Figure 1 at a distance of 35 mm from the center of the hub.
  • Figure 9 is a cross-sectional view of the G-G section of the propeller of the embodiment of Figure 1 at a distance of 85 mm from the center of the hub.
  • Figure 10 is a cross-sectional view of the H-H section of the propeller of the embodiment of Figure 1 at a distance of 95 mm from the center of the hub.
  • Figure 11 is a cross-sectional view of the I-I section of the propeller of the embodiment of Figure 1 at a distance of 105 mm from the center of the hub.
  • FIG. 12 is a perspective view of a propeller according to an embodiment of the present invention.
  • FIG. 13 is a schematic plan view of a propeller according to an embodiment of the present invention.
  • FIG. 14 is a schematic plan view of a propeller according to an embodiment of the present invention.
  • FIG. 15 is a schematic plan view of a propeller according to an embodiment of the present invention.
  • Figure 16 is a parametric diagram of the swept portion of the propeller of Figure 1 extending obliquely from the leading edge to the trailing edge.
  • Figure 17 is a parametric diagram in which the tip of the propeller of Figure 1 extends obliquely along the direction of the blade toward the side where the suction surface is located.
  • FIG. 18 is a schematic plan view of an aircraft according to an embodiment of the present invention.
  • Propeller 100 hub 10, paddle 20, paddle 21, tip 22, swept portion 221, pressure surface 23, suction surface 24, leading edge 25, leading edge arch 251, trailing edge 26, trailing edge arch Starting portion 261, bend back 27;
  • Power assembly 200 drive member 30, arm 40;
  • Aircraft 1000 fuselage 50;
  • first, second, third, etc. may be used to describe various information in the present invention, such information should not be limited to these terms. These terms are only used to distinguish the same type of information from each other.
  • first information may also be referred to as the second information without departing from the scope of the invention.
  • second information may also be referred to as the first information.
  • word "if” as used herein may be interpreted as "when” or “when” or “in response to a determination.”
  • an embodiment of the present invention provides a propeller 100 that includes a hub 10 and a blade 20 .
  • the paddle 20 is attached to the hub 10.
  • the paddles 20 may be integrally formed with the hub 10, or may be separately processed and fixedly assembled.
  • the angle of attack ⁇ 3 of the blade 20 is 24.60° ⁇ 2.5°.
  • the angle of attack ⁇ 4 of the blade 20 is 23.50° ⁇ 2.5°.
  • the angle of attack ⁇ 5 of the blade 20 is 21.82° ⁇ 2.5°.
  • the angle of attack ⁇ 6 of the blade 20 is 19.97° ⁇ 2.5°.
  • the angle of attack ⁇ 3 of the blade 20 is 24.60° ⁇ 2.5°; at the center of the hub 10 is the radius of the propeller 100 At 52.4%, D4, the angle of attack ⁇ 4 of the blade 20 is 23.50° ⁇ 2.5°; at the center of the hub 10, 61.9% of the radius of the propeller 100, D5, the angle of attack ⁇ 5 of the blade 20 is 21.82° ⁇ 2.5 °; at the center of the hub 10, 71.4% of the radius of the propeller 100, D6, the angle of attack ⁇ 6 of the blade 20 is 19.97 ° ⁇ 2.5 °; therefore, the propeller 100 using the blade 20 can reduce air resistance and increase the pulling force And efficiency, increasing the relay distance of the aircraft 1000 (shown in FIG.
  • an embodiment of the present invention provides a propeller 100 that includes a hub 10 and a paddle 20 .
  • the angle of attack ⁇ 3 of the blade 20 is 24.60° ⁇ 2.5°, and the chord length L3 of the blade 20 is 26.49 mm ⁇ 5 mm.
  • the angle of attack ⁇ 4 of the blade 20 is 23.50° ⁇ 2.5°, and the chord length L4 of the blade 20 is 25.16 mm ⁇ 5 mm.
  • the angle of attack ⁇ 5 of the blade 20 is 21.82° ⁇ 2.5°, and the chord length L5 of the blade 20 is 23.59 mm ⁇ 5 mm.
  • the angle of attack ⁇ 6 of the blade 20 is 19.97° ⁇ 2.5°, and the chord length L6 of the blade 20 is 21.69 mm ⁇ 5 mm.
  • the chord length L3 of the blade 20 is 26.49 mm ⁇ 5 mm.
  • the angle of attack ⁇ 4 of the blade 20 is 23.50° ⁇ 2.5°, and the chord length L4 of the blade 20 is 25.16 mm ⁇ 5 mm;
  • the center of 10 is D5 at 61.9% of the radius of the propeller 100, the angle of attack ⁇ 5 of the blade 20 is 21.82° ⁇ 2.5°, the chord length L5 of the blade 20 is 23.59 mm ⁇ 5 mm, and the propeller is at the center of the hub 10
  • the angle of attack ⁇ 6 of the blade 20 is 19.97° ⁇ 2.5°, and the chord length L6 of the blade 20 is 21.69 mm ⁇ 5 mm; therefore, the propeller 100 using the blade 20 can reduce air resistance, Increasing the pulling force and efficiency, increasing the relay distance of the aircraft 1000 to improve the flight performance of the aircraft 1000, while increasing the maximum pulling force of the aircraft 1000 without reducing the efficiency, reducing
  • the comparison between the propeller 100 and the test results of the existing propeller provided in this embodiment can be seen from Table 1.
  • the propeller 100 provided by the present embodiment has lower power. That is, under smaller power conditions, there is greater pulling force, thereby reducing power consumption and increasing the cruising distance. Therefore, the propeller 100 provided by the present embodiment can significantly increase the pulling force in the extreme case where the lifting density is high in a high-altitude region with a reduced density or a low-altitude region, thereby ensuring sufficient power while prolonging the endurance time and improving flight performance.
  • the loudness of the propeller 100 provided by this embodiment is significantly lower than that of the existing propeller. Therefore, the propeller 100 provided in the embodiment can effectively reduce high frequency noise, reduce the discomfort caused by high frequency noise and improve the user experience.
  • the propeller 100 provided in this embodiment can be applied to scenes with high sound requirements, such as detection, aerial photography (recording images and audio during aerial photography), and the like.
  • the angle of attack ⁇ 3 of the blade 20 may be 22.10° or 24.60° or 27.10°, or 22.60°, 23.10°, 23.60°, 24.10°, Any one of 25.10°, 25.60°, 26.10°, 26.60°, etc., or any of the above, the chord length L3 of the blade 20 may be 21.49 mm or 26.49 mm or 31.49 mm, or 22.49 mm.
  • the angle of attack ⁇ 4 of the blade 20 may be 21.00° or 23.50° or 26.00°, or 21.50°, 22.00°, 22.50°, 23.00°, The value of any one of 24.00°, 24.50°, 25.00°, 25.50°, etc., or any of the above, the chord length L4 of the blade 20 may be 20.16 mm or 25.16 mm or 30.16 mm, or 21.16 mm, 22.16.
  • the angle of attack ⁇ 5 of the blade 20 may be 19.32° or 21.82° or 24.32°, or 19.82°, 20.32°, 20.82°, 21.32°, The value between any of 22.32°, 22.82°, 23.32°, 23.82°, etc., or any of the above, the chord length L5 of the blade 20 may be 18.59 mm or 23.59 mm or 28.59 mm, or 19.59 mm, 20.59.
  • the angle of attack ⁇ 6 of the blade 20 may be 17.47° or 19.97° or 22.47°, or 17.97°, 18.47°, 18.97°, 19.47°,
  • the value between any of 20.47°, 20.97°, 21.47°, 21.97°, or the like, or the chord length L6 of the blade 20 may be 16.69 mm or 21.69 mm or 26.69 mm, or 17.69 mm, 18.69. Any of mm, 19.69 mm, 20.69 mm, 22.69 mm, 23.69 mm, 24.69 mm, 25.69 mm, etc., or any of the above.
  • the angle of attack ⁇ 1 of the blade 20 is 23.40° ⁇ 2.5°
  • the blade The chord length L1 of 20 is 21.21 mm ⁇ 5 mm to further reduce the air resistance of the propeller 100, increase the pulling force and efficiency, and reduce noise.
  • the angle of attack ⁇ 1 of the blade 20 may be 20.90° or 23.40° or 25.90°, or any one of 21.40°, 21.90°, 22.40°, 22.90°, 23.90°, 24.40°, 24.90°, 25.40°, and the like.
  • chord length L1 of the blade 20 may be 16.21 mm or 21.21 mm or 26.21 mm, or 17.21 mm, 18.21 mm, 19.21 mm, 20.21 mm, 22.21 mm, 23.21 mm, 24.21 mm. Any one of 25.21 mm or the like or a value between any two of the above.
  • the angle of attack ⁇ 2 of the blade 20 is 26.20° ⁇ 2.5°, the blade The chord length L2 of 20 is 27.38 mm ⁇ 5 mm.
  • the angle of attack ⁇ 2 of the blade 20 may be 23.70° or 26.20° or 28.70°, or any one of 24.20°, 24.70°, 25.20°, 25.70°, 26.70°, 27.20°, 27.70°, 28.20°, and the like.
  • chord length L2 of the blade 20 may be 22.38 mm or 27.38 mm or 32.38 mm, or 23.38 mm, 24.38 mm, 25.38 mm, 26.38 mm, 28.38 mm, 29.38 mm, 30.38 mm. Any one of 31.38 mm or the like or a value between any of the above.
  • the angle of attack ⁇ 7 of the blade 20 is 17.97° ⁇ 2.5°
  • the blade The chord length L7 of 20 is 19.45 mm ⁇ 5 mm to further reduce the air resistance of the propeller 100, increase the pulling force and efficiency, and reduce noise.
  • the angle of attack ⁇ 7 of the blade 20 may be 15.47° or 17.97° or 20.47°, or any one of 15.97°, 16.47°, 16.97°, 17.47°, 18.47°, 18.97°, 19.47°, 19.97°, and the like.
  • chord length L7 of the blade 20 may be 14.45 mm or 19.45 mm or 24.45 mm, or 15.45 mm, 16.45 mm, 17.45 mm, 18.45 mm, 20.45 mm, 21.45 mm, 22.45 mm. Any one of 23.45 mm or the like or a value between any of the above.
  • the angle of attack ⁇ 8 of the blade 20 is 16.61 ° ⁇ 2.5 °
  • the blade The chord length L8 of 20 is 15.78 mm ⁇ 5 mm.
  • the angle of attack ⁇ 8 of the blade 20 may be 14.11° or 16.61° or 19.11°, or any one of 14.61°, 15.11°, 15.61°, 16.11°, 17.11°, 17.61°, 18.11°, 18.61°, and the like.
  • chord length L8 of the blade 20 may be 10.78 mm or 15.78 mm or 20.78 mm, or 11.78 mm, 12.78 mm, 13.78 mm, 14.78 mm, 16.78 mm, 17.78 mm, 18.78 mm. Any one of 19.78 mm or the like or a value between any of the above.
  • the angle of attack ⁇ 9 of the blade 20 is 9.39° ⁇ 2.5°
  • the blade The chord length L9 of 20 is 4.94 mm ⁇ 2 mm.
  • the angle of attack ⁇ 9 of the blade 20 may be 6.89° or 9.39° or 11.89°, or any one of 7.39°, 7.89°, 8.39°, 8.89°, 9.89°, 10.39°, 10.89°, 11.39°, and the like.
  • chord length L9 of the blade 20 may be 2.94 mm or 4.94 mm or 6.94 mm, or 3.44 mm, 3.94 mm, 4.44 mm, 5.44 mm, 5.94 mm, 6.44 mm, or the like. Any one or a value between any two of the above.
  • the diameter of the propeller 100 is 210 mm ⁇ 21 mm.
  • the angle of attack ⁇ 3 of the blade 20 is 24.60°, and the chord length L3 of the blade 20 is 26.49 mm.
  • the angle of attack ⁇ 4 of the blade 20 is 23.50°, and the chord length L4 of the blade 20 is 25.16 mm.
  • the angle of attack ⁇ 5 of the blade 20 is 21.82°, and the chord length L5 of the blade 20 is 23.59 mm.
  • the diameter of the propeller 100 may be 189 mm or 210 mm or 231 mm, or any one of 193 mm, 197 mm, 201 mm, 205 mm, 209 mm, 213 mm, 217 mm, 221 mm, 225 mm, 229 mm, or the like, or a value between any two of the above.
  • the diameter of the propeller 100 is 210 mm ⁇ 21 mm.
  • the angle of attack ⁇ 1 of the blade 20 is 23.40°, and the chord length L1 of the blade 20 is 21.21 mm.
  • the diameter of the propeller 100 may be 189 mm or 210 mm or 231 mm, or any one of 193 mm, 197 mm, 201 mm, 205 mm, 209 mm, 213 mm, 217 mm, 221 mm, 225 mm, 229 mm, or the like, or a value between any two of the above.
  • the diameter of the propeller 100 is 210 mm ⁇ 21 mm.
  • the angle of attack ⁇ 2 of the blade 20 is 26.20°, and the chord length L2 of the blade 20 is 27.38 mm.
  • the diameter of the propeller 100 may be 189 mm or 210 mm or 231 mm, or any one of 193 mm, 197 mm, 201 mm, 205 mm, 209 mm, 213 mm, 217 mm, 221 mm, 225 mm, 229 mm, or the like, or a value between any two of the above.
  • the diameter of the propeller 100 is 210 mm ⁇ 21 mm.
  • the angle of attack ⁇ 7 of the blade 20 is 17.97°, and the chord length L7 of the blade 20 is 19.45 mm.
  • the diameter of the propeller 100 may be 189 mm or 210 mm or 231 mm, or any one of 193 mm, 197 mm, 201 mm, 205 mm, 209 mm, 213 mm, 217 mm, 221 mm, 225 mm, 229 mm, or the like, or a value between any two of the above.
  • the diameter of the propeller 100 is 210 mm ⁇ 21 mm.
  • the angle of attack ⁇ 8 of the blade 20 is 16.61°, and the chord length L8 of the blade 20 is 15.78 mm.
  • the diameter of the propeller 100 may be 189 mm or 210 mm or 231 mm, or any one of 193 mm, 197 mm, 201 mm, 205 mm, 209 mm, 213 mm, 217 mm, 221 mm, 225 mm, 229 mm, or the like, or a value between any two of the above.
  • the diameter of the propeller 100 is 210 mm ⁇ 21 mm.
  • the angle of attack ⁇ 9 of the blade 20 is 9.39°, and the chord length L9 of the blade 20 is 4.94 mm.
  • the diameter of the propeller 100 may be 189 mm or 210 mm or 231 mm, or any one of 193 mm, 197 mm, 201 mm, 205 mm, 209 mm, 213 mm, 217 mm, 221 mm, 225 mm, 229 mm, or the like, or a value between any two of the above.
  • the paddle 20 optionally includes a paddle root 21 , a tip end 22 facing away from the blade root 21 , a pressure surface 23 opposite to each other, and a suction surface 24 .
  • the tip 22 extends obliquely along the direction of the blade 20 toward the side on which the suction surface 24 is located. As such, the noise generated by the blade 20 during operation is reduced, making the aircraft 1000 quieter when hovering, improving the user experience.
  • the pressure surface 23 is a surface facing the ground of the blade 20 during normal flight of the aircraft 1000
  • the suction surface 24 is a surface facing the sky of the blade 20 when the aircraft 1000 is normally flying.
  • the suction surface 24 and the pressure surface 23 are curved surfaces.
  • the suction surface 24 and the pressure surface 23 are curved aerodynamic shapes, which can prevent the turbulence generated by the various portions of the blade 20 and the downwashing airflow from directly impacting the fuselage 50 of the aircraft 1000, thereby reducing the overall noise of the aircraft 1000.
  • the paddle 20 further includes a leading edge 25 connected to one side of the pressure surface 23 and the suction surface 24 , and the other side of the pressure surface 23 and the suction surface 24 .
  • the trailing edge 26 and the swept portion 221 formed on the blade tip 22 extend obliquely from the leading edge 25 toward the trailing edge 26. In this way, the effect of further increasing the pulling force and efficiency of the propeller 100 is achieved.
  • the paddle 20 forms a return bend 27 at the position of the blade tip 22, and the swept portion 221 extends obliquely from the front edge 25 to the trailing edge 26 from the corner bend 27, and the swept portion 221 is self-returned.
  • the bend 27 extends obliquely from the leading edge 25 to the trailing edge 26.
  • the position of the return bend 27 is indicated by MM.
  • the back bend 27 is 82.5% of the radius of the propeller 100 from the center of the hub 10.
  • the return bend 27 is away from the center of the hub 10 to enhance the aesthetics of the blade 20.
  • leading edge 25 is convexly formed with a curved leading edge arching portion 251 near the paddle root 21, and the trailing edge 26 is convexly formed with a curved trailing edge near the paddle root 21.
  • the leading edge arching portion 251 and the trailing edge arching portion 231 have a curved shape to further increase the pulling force of the blade 20.
  • the blades 20 are at least two, and at least two blades 20 are coupled to the hub 10 and are centrally symmetric with respect to the center of the hub 10. Thereby, the balance of the propeller 100 can be improved.
  • the hub 10 includes a paddle 11 and a mounting portion 12, and the paddle 20 is fixed to the mounting portion 12 by the paddle 11 .
  • the center of the hub 10 is provided with a connecting hole 13 for arranging on the output end of the motor, and the mounting portion 12 is for fixing the hub 10 to the output end of the motor.
  • the blade 20 may be in the form of a strip, the blade 20 being coupled to the hub 10 and extending in the radial direction of the hub 10.
  • the paddle 20 has a central axis NN that passes through the center of the hub 10, the leading edge 25 has a leading edge tangent OO parallel to the central axis NN, and the trailing edge 26 has a parallel to the central axis NN
  • the trailing edge tangent PP, the swept portion 221 is located between the leading edge tangent OO and the trailing edge tangent PP.
  • the swept portion 221 can reduce the turbulence and the downwash flow generated by the blade 20, thereby reducing the turbulence and the downwashing airflow hitting the fuselage 50 of the aircraft 1000, reducing the air resistance of the propeller 100, and improving the aircraft.
  • the maneuverability of 1000 makes the aircraft 1000 more stable while further reducing the overall noise of the aircraft 1000.
  • the swept portion 221 extends obliquely from the leading edge 25 toward the trailing edge 26.
  • the abscissa Blade Radius (mm) of Table 3 and FIG. 16 indicates the distance from the center of the hub 10 at a certain position (such as MM) of the paddle 20 extending along the blade 20.
  • the Sweep Length (mm) is the distance of the swept or swept forward. Among them, the positive value of the Sweep Length (mm) is swept back, and the negative value is swept forward.
  • the return bend 27 is 82.5% of the radius of the propeller 100 from the center of the hub 10
  • the swept portion 221 starts from the front.
  • the rim 25 extends obliquely to the trailing edge 26, i.e., begins to sweep when the distance of the blade 20 from the center of the hub 10 is 86.625 mm.
  • the swept portion 221 regularly extends obliquely from the leading edge 25 to the trailing edge 26, which can reduce turbulence and downwashing due to interaction of the plurality of blades 20, and reduce
  • the turbulent flow and the lower washing airflow on the fuselage 50 of the aircraft 1000 reduce the air resistance received by the blade 20, further improve the pulling force and efficiency of the propeller 100, improve the maneuverability of the aircraft 1000, and make the aircraft 1000 more stable.
  • the noise generated by the turbulence and the downwash airflow impinging on the fuselage 50 of the aircraft 1000 is further reduced.
  • the blade tip 22 extends obliquely along the direction of the blade 20 toward the side where the suction surface 24 is located.
  • the abscissa of the table 4 is Blade Radius ( Mm) represents the distance from the center of the hub 10 at a certain position (such as MM) of the paddle 20 of the blade 20.
  • the starting point is the center of the hub 10, at which point the distance of the blade 20 from the center of the hub 10 is 0 mm, the end is the free end of the tip 22, and the distance of the free end from the center of the hub 10 is 105 mm.
  • the ordinate Anhedral Length (mm) is the upper or lower inverse distance. Among them, the positive value of the ordinate Anhedral Length (mm) is the upper and the reverse, and the negative value is the lower.
  • the return bend 27 is 82.5% of the radius of the propeller 100 from the center of the hub 10.
  • the leading edge 25 begins to extend obliquely from the corner of the blade 27 toward the side of the suction surface 24 along the direction of the blade 20, i.e., when the distance of the blade 20 from the center of the hub 10 is 86.625 mm.
  • the leading edge 25 is regularly inclined from the corner bend 27 along the side of the blade 20 along the direction of the suction surface 24, which can reduce the interaction due to the plurality of blades 20.
  • the generated turbulence and under-washing airflow reduce the turbulence and downwashing airflow on the arm 40 and the fuselage 50 of the aircraft 1000.
  • the lift point of the blade 20 can be rated to enable the aircraft 1000 to be automatically corrected.
  • the flight attitude increases the inertia stability of the aircraft 1000, making the aircraft 1000 more stable during flight, while further reducing the noise generated by the turbulence and downwash airflow impinging on the fuselage 50 of the aircraft 1000.
  • the pitch of the blade 20 is 3.6 ⁇ 0.5 inches.
  • the resistance of the air can be reduced and the pulling force of the blade 20 can be increased.
  • the pitch of the blade 20 may be 3.1 inches or 3.6 inches or 4.1 inches, or any one of 3.2 inches, 3.3 inches, 3.4 inches, 3.5 inches, 3.7 inches, 3.8 inches, 3.9 inches, 4.0 inches, etc. or the above The value between any two. In this way, in the case where the efficiency is not lowered, the maximum pulling force of the propeller 100 is increased, the risk of the aircraft 1000 being out of control is reduced, and the flight safety is improved.
  • the propeller 100 using the blade of the above embodiment of the present invention can significantly increase the pulling force in the plateau region, thereby ensuring sufficient power redundancy.
  • the performance is balanced to a certain extent, the following distance is increased, and the flight performance of the aircraft 1000 is improved.
  • the propeller 100 using the blade has a greater pulling force under a smaller power condition, thereby reducing power consumption and increasing the cruising distance.
  • it can significantly increase the pulling force, ensure sufficient power while prolonging the battery life and improving flight performance.
  • the propeller 100 employing the blade 20 of the above-described embodiment of the present invention has a lower loudness than the existing propeller under most of the same frequency conditions. Especially under the same high frequency conditions, the loudness of the propeller 100 provided by this embodiment is significantly lower than that of the existing propeller. Therefore, the propeller 100 provided in the embodiment can effectively reduce high frequency noise, reduce the discomfort caused by high frequency noise and improve the user experience. The overall is lower than the existing propeller. Thus, the propeller 100 provided in this embodiment can effectively reduce noise.
  • the propeller 100 is at a distance D1 from the center of the hub 10 that is 23.8% of the radius of the propeller 100, and the angle of attack ⁇ 1 of the blade 20 is 23.40° ⁇ 2.5°; and/or
  • the angle of attack ⁇ 2 of the blade 20 is 26.20° ⁇ 2.5°;
  • the angle of attack ⁇ 7 of the blade 20 is 17.97° ⁇ 2.5°;
  • the angle of attack ⁇ 8 of the blade 20 is 16.61° ⁇ 2.5°;
  • the angle of attack ⁇ 9 of the blade 20 is 9.39° ⁇ 2.5°;
  • the angle of attack ⁇ 1 of the blade 20 is 23.40°;
  • the angle of attack ⁇ 2 of the blade 20 is 26.20°;
  • the angle of attack ⁇ 3 of the blade 20 is 24.60°;
  • the angle of attack ⁇ 4 of the blade 20 is 23.50°;
  • the angle of attack ⁇ 5 of the blade 20 is 21.82°;
  • the angle of attack ⁇ 6 of the blade 20 is 19.97°;
  • the angle of attack ⁇ 7 of the blade 20 is 17.97°;
  • the angle of attack ⁇ 8 of the blade 20 is 16.61°;
  • the angle of attack ⁇ 9 of the blade 20 is 9.39.
  • the propeller 100 is D1 at 23.8% of the radius of the propeller 100 from the center of the hub 10, and the angle of attack ⁇ 1 of the blade 20 is 23.40° ⁇ 2.5°;
  • the propeller 100 is at a distance D3 from the center of the hub 10 at 33.3% of the radius of the propeller 100, and the angle of attack ⁇ 2 of the blade 20 is 26.20° ⁇ 2.5°;
  • the propeller 100 is at a distance of 81.0% of the radius of the propeller 100 from the center of the hub 10, D7, and the angle of attack ⁇ 7 of the blade 20 is 17.97 ° ⁇ 2.5 °;
  • the propeller 100 is at a distance of 90.5% of the radius of the propeller 100 from the center of the hub 10, D8, and the angle of attack ⁇ 8 of the blade 20 is 16.61 ° ⁇ 2.5 °;
  • the propeller 100 is at a distance D100 from the center of the hub 10 that is 100% of the radius of the propeller 100, and the angle of attack ⁇ 9 of the blade 20 is 9.39 ° ⁇ 2.5 °;
  • the propeller 100 is at a distance of 25 mm from the center of the hub 10, and the angle of attack ⁇ 1 of the blade 20 is 23.40°;
  • the propeller 100 is at a distance of 35 mm from the center of the hub 10, and the angle of attack ⁇ 2 of the blade 20 is 26.20°;
  • the propeller 100 is at a distance of 45 mm from the center of the hub 10, and the angle of attack ⁇ 3 of the blade 20 is 24.60°;
  • the propeller 100 is at a distance of 55 mm from the center of the hub 10, and the angle of attack ⁇ 4 of the blade 20 is 23.50°;
  • the propeller 100 is at a distance of 65 mm from the center of the hub 10, and the angle of attack ⁇ 5 of the blade 20 is 21.82°;
  • the propeller 100 is at a distance of 75 mm from the center of the hub 10, and the angle of attack ⁇ 6 of the blade 20 is 19.97°;
  • the propeller 100 is at a distance of 85 mm from the center of the hub 10, and the angle of attack ⁇ 7 of the blade 20 is 17.97°;
  • the propeller 100 is at a distance of 95 mm from the center of the hub 10, the angle of attack ⁇ 8 of the blade 20 is 16.61 °;
  • the propeller 100 is at a distance of 10 mm from the center of the hub 10, D9, the angle of attack ⁇ 9 of the blade 20 is 9.39 °;
  • the propeller 100 is at a distance D1 from the center of the hub 10 which is 23.8% of the radius of the propeller 100, and the angle of attack ⁇ 1 of the blade 20 is 23.40° ⁇ 2.5°; and, at the center of the hub 10, the propeller 100 At 33.3% of the radius, D2, the angle of attack ⁇ 2 of the blade 20 is 26.20° ⁇ 2.5°; and, at the center of the hub 10, 81.0% of the radius of the propeller 100, D7, the angle of attack ⁇ 7 of the blade 20 is 17.97.
  • the angle of attack ⁇ 8 of the blade 20 is 16.61° ⁇ 2.5°; and, at the center of the hub 10 is a propeller 100% of the radius of 100, D9, the angle of attack ⁇ 9 of the blade 20 is 9.39 ° ⁇ 2.5 °; and, at a distance of 25 mm from the center of the hub 10, the angle of attack ⁇ 1 of the blade 20 is 23.40 °; At an angle of 35 mm from the center of the hub 10, the angle of attack ⁇ 2 of the blade 20 is 26.20°; and, at a distance of 45 mm from the center of the hub 10, the angle of attack ⁇ 3 of the blade 20 is 24.60°; and, at a distance from the paddle
  • the center angle 55 of the hub 10 is D4, the angle of attack ⁇ 4 of the blade 20 is 23.50°; and, at the distance of 65 mm from the center of the hub 10, the angle of
  • the propeller 100 is D3 at a distance from the center of the hub 10 that is 42.9% of the radius of the propeller 100, and the chord length L3 of the blade 20 is 26.49 mm ⁇ 5 mm; and/or
  • chord length L4 of the blade 20 is 25.16 mm ⁇ 5 mm;
  • the chord length L5 of the blade 20 is 23.59 mm ⁇ 5 mm;
  • the chord length L6 of the blade 20 is 21.69 mm ⁇ 5 mm;
  • chord length L3 of the blade 20 is 26.49 mm;
  • chord length L4 of the blade 20 is 25.16 mm;
  • chord length L5 of the blade 20 is 23.59 mm;
  • chord length L6 of the paddle 20 is 21.69 mm.
  • the propeller 100 is D3 at a distance from the center of the hub 10 of 42.9% of the radius of the propeller 100, and the chord length L3 of the blade 20 is 26.49 mm ⁇ 5 mm;
  • the propeller 100 is at a distance of 52.4% of the radius of the propeller 100 from the center of the hub 10, D4, and the chord length L4 of the blade 20 is 25.16 mm ⁇ 5 mm;
  • the propeller 100 is at a distance of 61.9% of the radius of the propeller 100 from the center of the hub 10, D5, and the chord length L5 of the blade 20 is 23.59 mm ⁇ 5 mm;
  • the propeller 100 is at a distance of 71.4% of the radius of the propeller 100 from the center of the hub 10, D6, and the chord length L6 of the blade 20 is 21.69 mm ⁇ 5 mm;
  • the propeller 100 is at a distance of 45 mm from the center of the hub 10, and the chord length L3 of the blade 20 is 26.49 mm;
  • the propeller 100 is at a distance of 55 mm from the center of the hub 10, and the chord length L4 of the blade 20 is 25.16 mm;
  • the propeller 100 is at a distance of 75 mm from the center of the hub 10, and the chord length L6 of the blade 20 is 21.69 mm;
  • the propeller 100 is D3 at a distance from the center of the hub 10 of 42.9% of the radius of the propeller 100, the chord length L3 of the blade 20 is 26.49 mm ⁇ 5 mm; and, at the center of the hub 10, the radius of the propeller 100 At 52.4%, D4, the chord length L4 of the blade 20 is 25.16 mm ⁇ 5 mm; and, at the center of the hub 10, 61.9% of the radius of the propeller 100, D5, the chord length L5 of the blade 20 is 23.59 mm ⁇ 5mm; and, at the center of the hub 10, 71.4% of the radius of the propeller 100, D6, the chord length L6 of the blade 20 is 21.69 mm ⁇ 5 mm; and, at a distance of 45 mm from the center of the hub 10, D3, paddle
  • the chord length L3 of 20 is 26.49 mm; and, at a distance of 55 mm from the center of the hub 10, the chord length L4 of the blade 20 is 25.16 mm;
  • the propeller 100 is at a distance D1 from the center of the hub 10 that is 23.8% of the radius of the propeller 100, and the chord length L1 of the blade 20 is 21.21 mm ⁇ 5 mm; and/or
  • chord length L2 of the blade 20 is 27.38 mm ⁇ 5 mm;
  • the chord length L7 of the blade 20 is 19.45 mm ⁇ 5 mm;
  • chord length L8 of the blade 20 is 15.78 mm ⁇ 5 mm;
  • the chord length L9 of the blade 20 is 4.94 mm ⁇ 2 mm;
  • chord length L1 of the blade 20 is 21.21 mm;
  • chord length L2 of the blade 20 is 27.38 mm;
  • chord length L7 of the blade 20 is 19.45 mm;
  • chord length L8 of the blade 20 is 15.78 mm;
  • chord length L9 of the paddle 20 is 4.94 mm.
  • the propeller 100 is D1 at a distance from the center of the hub 10 of 23.8% of the radius of the propeller 100, and the chord length L1 of the blade 20 is 21.21 mm ⁇ 5 mm;
  • the propeller 100 is at a distance of 33.3% of the radius of the propeller 100 from the center of the hub 10, and the chord length L2 of the blade 20 is 27.38 mm ⁇ 5 mm;
  • the propeller 100 is at a distance of 81.0% of the radius of the propeller 100 from the center of the hub 10, D7, and the chord length L7 of the blade 20 is 19.45 mm ⁇ 5 mm;
  • the propeller 100 is at a distance of 90.5% of the radius of the propeller 100 from the center of the hub 10, D8, and the chord length L8 of the blade 20 is 15.78 mm ⁇ 5 mm;
  • the propeller 100 is at a distance from the center of the hub 10 at 100% of the radius of the propeller 100, D9, the chord length L9 of the blade 20 is 4.94 mm ⁇ 2 mm;
  • the propeller 100 is at a distance of 25 mm from the center of the hub 10, and the chord length L1 of the blade 20 is 21.21 mm;
  • the propeller 100 is at a distance of 35 mm from the center of the hub 10, and the chord length L2 of the blade 20 is 27.38 mm;
  • the propeller 100 is at a distance of 85 mm from the center of the hub 10, and the chord length L7 of the blade 20 is 19.45 mm;
  • the propeller 100 is at a distance of 85 mm from the center of the hub 10, and the chord length L8 of the blade 20 is 15.78 mm;
  • the propeller 100 is at a distance of 10 mm from the center of the hub 10, D9, the chord length L9 of the blade 20 is 4.94 mm;
  • the propeller 100 is D1 at a distance from the center of the hub 10 of 23.8% of the radius of the propeller 100, and the chord length L1 of the blade 20 is 21.21 mm ⁇ 5 mm; and, at the center of the hub 10, the radius of the propeller 100 At 33.3%, D2, the chord length L2 of the blade 20 is 27.38 mm ⁇ 5 mm; and, at the center of the hub 10, 81.0% of the radius of the propeller 100, D7, the chord length L7 of the blade 20 is 19.45 mm ⁇ 5mm; and, at a distance of 90.5% of the radius of the propeller 100 from the center of the hub 10, D8, the chord length L8 of the blade 20 is 15.78 mm ⁇ 5 mm; and, at the center of the hub 10, the radius of the propeller 100 At 100%, D9, the chord length L9 of the blade 20 is 4.94 mm ⁇ 2 mm; and, at a distance of 25 mm from the center of the hub 10, the chord length L1 of
  • the chord length L2 of the blade 20 is 27.38 mm; and, at a distance of 85 mm from the center of the hub 10, the chord length L7 of the blade 20 is 19.45 mm; and, at a distance of 95 mm from the center of the hub 10.
  • the chord length L8 of the paddle 20 is 15.78 mm; and, at D9, 105 mm from the center of the hub 10, the chord length L9 of the paddle 20 is 4.94 mm.
  • an embodiment of the present invention provides a power assembly 200 including a drive member 30 and a propeller 100 of any embodiment of the present invention.
  • the propeller 100 is coupled to the drive member 30 via a hub 10.
  • Power assembly 200 includes at least two arms 40. At least two arms 40 are coupled to a central position of the propeller 100.
  • the drive member 30 is disposed on the arm 40.
  • the specific structure of the propeller 100 is the same as that of the foregoing embodiment, and details are not described herein again. That is, the description of the propeller 100 in the above embodiments and embodiments is equally applicable to the power assembly 200 provided by the embodiment of the present invention.
  • the angle of attack ⁇ 3 of the blade 20 is 24.60° ⁇ 2.5°; at the center of the hub 10 At 52.4% of the radius of the propeller 100, D4, the angle of attack ⁇ 4 of the blade 20 is 23.50° ⁇ 2.5°; at the center of the hub 10, 61.9% of the radius of the propeller 100, D5, the angle of attack ⁇ 5 of the blade 20 is 21.82 ° ⁇ 2.5 °; at the center of the hub 10 is 71.4% of the radius of the propeller 100 D6, the angle of attack ⁇ 6 of the blade 20 is 19.97 ° ⁇ 2.5 °.
  • the power assembly 200 employing the blade 20 can reduce the air resistance, increase the pulling force and efficiency, increase the relay distance of the aircraft 1000 to improve the flight performance of the aircraft 1000, and increase the aircraft 1000 while the efficiency is not lowered.
  • the maximum pulling force reduces the risk of loss of control of the aircraft 1000, improves flight safety, and further reduces the noise generated by the blade 20 during operation, making the aircraft 1000 quieter when hovering and improving the user experience.
  • the driving member 30 is a motor, and the KV value of the motor is 360 to 810 rpm / (minute volt). Thereby, the dynamic performance of the power unit can be ensured.
  • an embodiment of the present invention provides an aircraft 1000 including a fuselage 50 and a power assembly 200 of any of the embodiments of the present invention.
  • the power assembly 200 is coupled to the fuselage 50.
  • a plurality of arms 40 of the power assembly 200 are coupled to the body 50 to mount the power assembly 200 on the body 50.
  • the specific structure of the power module 200 is the same as that of the foregoing embodiment, and details are not described herein again. That is, the description of the propeller 100 in the above embodiments and embodiments is equally applicable to the aircraft 1000 provided by the embodiment of the present invention.
  • the aircraft 1000 includes a plurality of power components 200, and the plurality of power components 200 have different rotation directions.
  • the aircraft 1000 is a multi-rotor aircraft, such as a quadrotor unmanned aerial vehicle.
  • the angle of attack ⁇ 3 of the blade 20 is 24.60° ⁇ 2.5°; at the center of the hub 10 is the radius of the propeller 100 At 52.4%, D4, the angle of attack ⁇ 4 of the blade 20 is 23.50° ⁇ 2.5°; at the center of the hub 10, 61.9% of the radius of the propeller 100, D5, the angle of attack ⁇ 5 of the blade 20 is 21.82° ⁇ 2.5 °; at the center of the hub 10, 71.4% of the radius of the propeller 100, D6, the angle of attack ⁇ 6 of the blade 20 is 19.97 ° ⁇ 2.5 °; therefore, the propeller 100 using the blade 20 can reduce air resistance and increase the pulling force And efficiency, increasing the flight distance of the aircraft 1000 to improve the flight performance of the aircraft 1000, while also increasing the maximum pulling force of the aircraft 1000 without reducing the efficiency, reducing the risk of loss of the aircraft 1000, improving flight safety, and, The noise generated by

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Abstract

A propeller, a power component and an aircraft. The angle of attack of a blade (20) is 24.60°±2.5° at 42.9% of the radius of the propeller (100) from the center of a hub (10); the angle of attack of the blade (20) is 23.50°±2.5 at 52.4% of the radius of the propeller (100) from the center of the hub (10); the angle of attack of the blade (20) is 21.82°±2.5° at 61.9% of the radius of the propeller (100) from the center of the hub (10); and the angle of attack of the blade (20) is 19.97°±2.5° at 71.4% of the radius of the propeller (100) from the center of the hub (10). Thus, the propeller (100) provided with the blade (20) may reduce air resistance, improve the pulling force and efficiency, increase the continued-flight distance of an aircraft (1000) so as to improve the flight performance of the aircraft (1000), while increasing the maximum pulling force of the aircraft (1000) without reducing the efficiency, reducing the risk of losing control over the aircraft (1000), and improving the flight safety. Moreover, the noise generated by the blade (20) while operating is reduced, so that the aircraft (1000) is quieter when hovering, and the user experience is thus improved.

Description

螺旋桨、动力组件及飞行器Propellers, power components and aircraft 技术领域Technical field
本发明实施例涉及飞行器领域，特别涉及螺旋桨、动力组件及飞行器。Embodiments of the present invention relate to the field of aircraft, and more particularly to propellers, power components, and aircraft.
背景技术Background technique
飞行器上的螺旋桨，作为飞行器的重要关键器件，其用于将电机或发动机中转轴的转动转化为推力或升力。The propeller on the aircraft, as an important key component of the aircraft, is used to convert the rotation of the shaft of the motor or engine into thrust or lift.
现有技术中的螺旋桨在旋转中，桨叶各部分的湍流以及下洗气流冲击飞行器外壳结构会产生较大的噪音。其与电机噪声和结构震动噪声往往会叠加在一起，并放大某些频段噪声，导致飞行器总体噪声较大，使用体验差。In the prior art, the propeller is rotating, and the turbulence of each part of the blade and the downwashing airflow impinging on the outer casing structure of the aircraft generate a large noise. It is often superimposed with motor noise and structural vibration noise, and amplifies noise in certain frequency bands, resulting in a large overall noise of the aircraft and poor user experience.
另外，对于适配有全封闭桨保护罩的动力系统，由于保护罩遮挡了部分气流进出口，导致螺旋桨拉力减小，易导致失控等风险。In addition, for a power system equipped with a fully enclosed paddle cover, since the protective cover blocks part of the airflow inlet and outlet, the tension of the propeller is reduced, which may lead to risk of loss of control.
发明内容Summary of the invention
本发明的实施方式提供了一种螺旋桨、动力组件及飞行器。Embodiments of the present invention provide a propeller, a power assembly, and an aircraft.
本发明实施方式的螺旋桨包括桨毂和桨叶，所述桨叶连接在所述桨毂上，其中：A propeller of an embodiment of the invention includes a hub and a blade, the blade being coupled to the hub, wherein:
在距离所述桨毂的中心为所述螺旋桨的半径的42.9％处，所述桨叶的攻角为24.60°±2.5°；The angle of attack of the blade is 24.60 ° ± 2.5 ° at a distance of 42.9% of the radius of the propeller from the center of the hub;
在距离所述桨毂的中心为所述螺旋桨的半径的52.4％处，所述桨叶的攻角为23.50°±2.5°；The angle of attack of the blade is 23.50 ° ± 2.5 ° at a distance of 52.4% of the radius of the propeller from the center of the hub;
在距离所述桨毂的中心为所述螺旋桨的半径的61.9％处，所述桨叶的攻角为21.82°±2.5°；The angle of attack of the blade is 21.82 ° ± 2.5 ° at a distance of 61.9% of the radius of the propeller from the center of the hub;
在距离所述桨毂的中心为所述螺旋桨的半径的71.4％处，所述桨叶的攻角为19.97°±2.5°。At an angle of 71.4% of the radius of the propeller from the center of the hub, the blade has an angle of attack of 19.97 ° ± 2.5 °.
在某些实施方式中，在距离所述桨毂的中心为所述螺旋桨的半径的42.9％处，所述桨叶的攻角为24.60°±2.5°，所述桨叶的弦长为26.49mm±5mm；在距离所述桨毂的中心为所述螺旋桨的半径的52.4％处，所述桨叶的攻角为23.50°±2.5°，所述桨叶的弦长为25.16mm±5mm；在距离所述桨毂的中心为所述螺旋桨的半径的61.9％处，所述桨叶的攻角为21.82°±2.5°，所述桨叶的弦长为23.59mm±5mm；在距离所述桨毂的中心为所述螺旋桨的半径的71.4％处，所述桨叶的攻角为19.97°±2.5°，所述 桨叶的弦长为21.69mm±5mm。In certain embodiments, the angle of attack of the blade is 24.60° ± 2.5° at a distance of 42.9% of the radius of the propeller from the center of the hub, and the chord length of the blade is 26.49 mm ±5 mm; at a distance of 52.4% of the radius of the propeller from the center of the hub, the angle of attack of the blade is 23.50° ± 2.5°, and the chord length of the blade is 25.16 mm ± 5 mm; The distance from the center of the hub is 61.9% of the radius of the propeller, the angle of attack of the blade is 21.82 ° ± 2.5 °, the chord length of the blade is 23.59 mm ± 5 mm; The center of the hub is 71.4% of the radius of the propeller, the angle of attack of the blade is 19.97° ± 2.5°, and the chord length of the blade is 21.69 mm ± 5 mm.
在某些实施方式中，所述螺旋桨的直径为210mm±21mm；在距离所述桨毂的中心45mm处，所述桨叶的攻角为24.60°，所述桨叶的弦长为26.49mm；在距离所述桨毂的中心55mm处，所述桨叶的攻角为23.50°，所述桨叶的弦长为25.16mm；在距离所述桨毂的中心65mm处，所述桨叶的攻角为21.82°，所述桨叶的弦长为23.59mm；在距离所述桨毂的中心75mm处，所述桨叶的攻角为19.97°，所述桨叶的弦长为21.69mm。In some embodiments, the diameter of the propeller is 210 mm ± 21 mm; at an angle of 45 mm from the center of the hub, the angle of attack of the blade is 24.60 °, the chord length of the blade is 26.49 mm; At 55 mm from the center of the hub, the blade has an angle of attack of 23.50°, the blade has a chord length of 25.16 mm; at a distance of 65 mm from the center of the hub, the blade is attacked The angle is 21.82°, the chord length of the blade is 23.59 mm; the angle of attack of the blade is 19.97° at a distance of 75 mm from the center of the hub, and the chord length of the blade is 21.69 mm.
在某些实施方式中，在距离所述桨毂的中心为所述螺旋桨的半径的23.8％处，所述桨叶的攻角为23.40°±2.5°，所述桨叶的弦长为21.21mm±5mm。In certain embodiments, at 23.8% of the radius of the propeller from the center of the hub, the blade has an angle of attack of 23.40° ± 2.5° and the blade has a chord length of 21.21 mm. ±5mm.
在某些实施方式中，所述螺旋桨的直径为210mm±21mm；在距离所述桨毂的中心25mm处，所述桨叶的攻角为23.40°，所述桨叶的弦长为21.21mm。In certain embodiments, the diameter of the propeller is 210 mm ± 21 mm; at 25 mm from the center of the hub, the blade has an angle of attack of 23.40° and the blade has a chord length of 21.21 mm.
在某些实施方式中，在距离所述桨毂的中心为所述螺旋桨的半径的33.3％处，所述桨叶的攻角为26.20°±2.5°，所述桨叶的弦长为27.38mm±5mm。In certain embodiments, at 33.3% of the radius of the propeller from the center of the hub, the blade has an angle of attack of 26.20° ± 2.5° and the blade has a chord length of 27.38 mm. ±5mm.
在某些实施方式中，所述螺旋桨的直径为210mm±21mm；在距离所述桨毂的中心35mm处，所述桨叶的攻角为26.20°，所述桨叶的弦长为27.38mm。In certain embodiments, the diameter of the propeller is 210 mm ± 21 mm; at 35 mm from the center of the hub, the blade has an angle of attack of 26.20° and the blade has a chord length of 27.38 mm.
在某些实施方式中，在距离所述桨毂的中心为所述螺旋桨的半径的81.0％处，所述桨叶的攻角为17.97°±2.5°，所述桨叶的弦长为19.45mm±5mm。In certain embodiments, at an angle of 81.0% of the radius of the propeller from the center of the hub, the blade has an angle of attack of 17.97° ± 2.5° and the blade has a chord length of 19.45 mm. ±5mm.
在某些实施方式中，所述螺旋桨的直径为210mm±21mm；在距离所述桨毂的中心85mm处，所述桨叶的攻角为17.97°，所述桨叶的弦长为19.45mm。In certain embodiments, the diameter of the propeller is 210 mm ± 21 mm; at 85 mm from the center of the hub, the blade has an angle of attack of 17.97° and the blade has a chord length of 19.45 mm.
在某些实施方式中，在距离所述桨毂的中心为所述螺旋桨的半径的90.5％处，所述桨叶的攻角为16.61°±2.5°，所述桨叶的弦长为15.78mm±5mm。In certain embodiments, the angle of attack of the blade is 16.61° ± 2.5° at a distance of 90.5% of the radius of the propeller from the center of the hub, and the chord length of the blade is 15.78 mm ±5mm.
在某些实施方式中，所述螺旋桨的直径为210mm±21mm；In some embodiments, the diameter of the propeller is 210 mm ± 21 mm;
在距离所述桨毂的中心95mm处，所述桨叶的攻角为16.61°，所述桨叶的弦长为15.78mm。At an angle of 95 mm from the center of the hub, the blade has an angle of attack of 16.61° and the blade has a chord length of 15.78 mm.
在某些实施方式中，在距离所述桨毂的中心为所述螺旋桨的半径的100％处，所述桨叶的攻角为9.39°±2.5°，所述桨叶的弦长为4.94mm±2mm。In certain embodiments, the angle of attack of the blade is 9.39° ± 2.5° at a distance of 100% of the radius of the propeller from the center of the hub, and the chord length of the blade is 4.94 mm ±2mm.
在某些实施方式中，所述螺旋桨的直径为210mm±21mm；在距离所述桨毂的中心105mm处，所述桨叶的攻角为9.39°，所述桨叶的弦长为4.94mm。In certain embodiments, the diameter of the propeller is 210 mm ± 21 mm; at 105 mm from the center of the hub, the angle of attack of the blade is 9.39 ° and the chord length of the blade is 4.94 mm.
在某些实施方式中，所述桨叶包括桨根、背离所述桨根的桨尖、相背的压力面及吸力面；所述桨尖沿所述桨叶展向的方向朝所述吸力面所在的一侧倾斜延伸。In some embodiments, the paddle includes a paddle root, a blade tip facing away from the paddle root, a opposing pressure surface, and a suction surface; the tip of the blade is oriented toward the suction in a direction in which the blade is spanned The side where the face is located extends obliquely.
在某些实施方式中，所述桨叶还包括连接于所述压力面及所述吸力面一侧边的前缘、连接于所述压力面及所述吸力面另一侧边的后缘、及形成于所述桨尖的后掠部，所述后掠部自所述前缘向所述后缘倾斜延伸。In some embodiments, the blade further includes a leading edge connected to one side of the pressure surface and the suction surface, a trailing edge connected to the pressure surface and the other side of the suction surface, And a swept portion formed on the tip of the blade, the swept portion extending obliquely from the leading edge toward the trailing edge.
在某些实施方式中，所述桨叶在所述桨尖的位置形成回弯处，所述前缘自所述回弯处开始沿所述桨叶的展向朝所述吸力面所在的一侧倾斜延伸，所述后掠部自所述回弯处从所述前缘向所述后缘倾斜延伸。In some embodiments, the blade forms a back bend at the position of the tip, the leading edge starting from the bend back along the direction of the blade toward the suction side The side slope extends, and the swept portion extends obliquely from the leading edge to the trailing edge from the return bend.
在某些实施方式中，所述回弯处距离所述桨毂的中心为所述的半径的82.5％。In certain embodiments, the center of the back bend from the hub is 82.5% of the radius.
在某些实施方式中，所述前缘外凸形成有靠近所述桨根的呈曲面状的前缘拱起部，所述后缘外凸形成有靠近所述桨根的呈曲面状的后缘拱起部。In some embodiments, the leading edge is convexly formed with a curved leading edge bulging portion near the paddle, and the trailing edge is convexly formed with a curved shape near the paddle. The edge of the arch.
在某些实施方式中，所述桨叶为至少两个，至少两个所述桨叶连接在所述桨毂上并关于所述桨毂的中心呈中心对称。In certain embodiments, the blades are at least two, and at least two of the blades are coupled to the hub and are centrally symmetric about a center of the hub.
在某些实施方式中，所述桨叶具有穿过所述桨毂的中心的中轴线，所述前缘具有平行于所述中轴线的前缘切线，所述后缘具有平行于所述中轴线的后缘切线，所述后掠部位于所述前缘切线与所述后缘切线之间。In certain embodiments, the paddle has a central axis passing through a center of the hub, the leading edge having a leading edge tangent parallel to the central axis, the trailing edge having a parallel to the middle A trailing edge of the axis is tangent, the swept portion being between the leading edge tangent and the trailing edge tangent.
在某些实施方式中，所述吸力面和所述压力面均为曲面。In some embodiments, the suction side and the pressure side are both curved surfaces.
在某些实施方式中，所述桨叶的螺距为3.6±0.5英寸。In certain embodiments, the pitch of the paddle is 3.6 ± 0.5 inches.
本发明实施例提供的动力组件，包括驱动件和上述任意一项实施方式所述的螺旋桨，所述螺旋桨通过所述桨毂与所述驱动件连接。A power assembly according to an embodiment of the present invention includes a driving member and a propeller according to any one of the above embodiments, wherein the propeller is coupled to the driving member through the hub.
在某些实施方式中，所述驱动件为电机，所述电机的KV值为360至810转/(分钟·伏特)。In certain embodiments, the drive member is a motor having a KV value of 360 to 810 rpm / (minute volts).
本发明实施例提供的飞行器包括机身和权利要求22或23所述的动力组件，所述动力组件与所述机身连接。An aircraft provided by an embodiment of the present invention includes a fuselage and the power assembly of claim 22 or 23, and the power component is coupled to the fuselage.
在某些实施方式中，所述飞行器包括多个动力组件，所述多个动力组件的转动方向不同。In certain embodiments, the aircraft includes a plurality of power components that rotate in different directions.
在某些实施方式中，所述飞行器为多旋翼飞行器。In certain embodiments, the aircraft is a multi-rotor aircraft.
本发明实施例提供的螺旋桨、动力组件及飞行器，由于在距离桨毂的中心为螺旋桨的半径的42.9％处，桨叶的攻角为24.60°±2.5°；在距离桨毂的中心为螺旋桨的半径的52.4％处，桨叶的攻角为23.50°±2.5°；在距离桨毂的中心为螺旋桨的半径的61.9％处，桨叶的攻角为21.82°±2.5°；在距离桨毂的中心为螺旋桨的半径的71.4％处，桨叶的攻角为19.97°±2.5°；因此，采用桨叶的螺旋桨能够减少空气阻力，提 高拉力和效率，增加飞行器的继航距离以提高飞行器的飞行性能，同时还在效率不降低的情况下，增大飞行器的最大拉力，降低了飞行器失控风险，提高飞行安全，再者，减少了桨叶在工作时产生的噪声，使得飞行器在悬停时更安静，提高了用户体验。The propeller, the power assembly and the aircraft provided by the embodiments of the present invention have an angle of attack of 24.60°±2.5° at a distance of 42.9% of the radius of the propeller from the center of the hub; and a propeller at the center of the hub; At 52.4% of the radius, the angle of attack of the blade is 23.50° ± 2.5°; at 61.9% of the radius of the propeller from the center of the hub, the angle of attack of the blade is 21.82 ° ± 2.5 °; at the distance from the hub The center is 71.4% of the radius of the propeller, and the angle of attack of the blade is 19.97°±2.5°. Therefore, the propeller using the blade can reduce the air resistance, increase the pulling force and efficiency, and increase the flight distance of the aircraft to improve the flight of the aircraft. Performance, while also increasing the maximum pulling force of the aircraft while reducing efficiency, reducing the risk of aircraft out of control, improving flight safety, and further reducing the noise generated by the blades during operation, making the aircraft more hovering. Quiet and improved user experience.
本发明的实施方式的附加方面和优点将在下面的描述中部分给出，部分将从下面的描述中变得明显，或通过本发明的实施方式的实践了解到。The additional aspects and advantages of the embodiments of the present invention will be set forth in part in the description which follows.
附图说明DRAWINGS
本发明的上述和/或附加的方面和优点从结合下面附图对实施方式的描述中将变得明显和容易理解，其中：新增附图修改、说明书中的图示说明The above and/or additional aspects and advantages of the present invention will become apparent and readily understood from
图1是本发明实施例提供的一种螺旋桨的平面示意图。FIG. 1 is a schematic plan view of a propeller according to an embodiment of the present invention.
图2是图1所示实施例的螺旋桨中距离桨毂的中心45mm处的C-C剖面的剖视图。Figure 2 is a cross-sectional view of the C-C section of the propeller of the embodiment of Figure 1 at a distance of 45 mm from the center of the hub.
图3是图1所示实施例的螺旋桨中距离桨毂的中心55mm处的D-D剖面的剖视图。Figure 3 is a cross-sectional view of the D-D section of the propeller of the embodiment of Figure 1 at a distance of 55 mm from the center of the hub.
图4是图1所示实施例的螺旋桨中距离桨毂的中心65mm处的E-E剖面的剖视图。Figure 4 is a cross-sectional view of the E-E section of the propeller of the embodiment of Figure 1 at a distance of 65 mm from the center of the hub.
图5是图1所示实施例的螺旋桨中距离桨毂的中心75mm处的F-F剖面的剖视图。Figure 5 is a cross-sectional view of the F-F section of the propeller of the embodiment of Figure 1 at a distance of 75 mm from the center of the hub.
图6是本发明的螺旋桨与现有的螺旋桨在相同的悬停工况声学性能测试条件下的频响曲线示意图。Fig. 6 is a schematic diagram showing the frequency response curve of the propeller of the present invention and the existing propeller under the same hovering condition acoustic performance test conditions.
图7是图1所示实施例的螺旋桨中距离桨毂中心25mm处的A-A剖面的剖视图。Figure 7 is a cross-sectional view of the A-A section of the propeller of the embodiment of Figure 1 taken at a distance of 25 mm from the center of the hub.
图8是图1所示实施例的螺旋桨中距离桨毂的中心35mm处的B-B剖面的剖视图。Figure 8 is a cross-sectional view of the B-B section of the propeller of the embodiment of Figure 1 at a distance of 35 mm from the center of the hub.
图9是图1所示实施例的螺旋桨中距离桨毂中心85mm处的G-G剖面的剖视图。Figure 9 is a cross-sectional view of the G-G section of the propeller of the embodiment of Figure 1 at a distance of 85 mm from the center of the hub.
图10是图1所示实施例的螺旋桨中距离桨毂的中心95mm处的H-H剖面的剖视图。Figure 10 is a cross-sectional view of the H-H section of the propeller of the embodiment of Figure 1 at a distance of 95 mm from the center of the hub.
图11是图1所示实施例的螺旋桨中距离桨毂的中心105mm处的I-I剖面的剖视图。Figure 11 is a cross-sectional view of the I-I section of the propeller of the embodiment of Figure 1 at a distance of 105 mm from the center of the hub.
图12是本发明实施例提供的一种螺旋桨的立体图。FIG. 12 is a perspective view of a propeller according to an embodiment of the present invention.
图13是本发明实施例提供的一种螺旋桨的平面示意图。FIG. 13 is a schematic plan view of a propeller according to an embodiment of the present invention.
图14是本发明实施例提供的一种螺旋桨的平面示意图。FIG. 14 is a schematic plan view of a propeller according to an embodiment of the present invention.
图15是本发明实施例提供的一种螺旋桨的平面示意图。FIG. 15 is a schematic plan view of a propeller according to an embodiment of the present invention.
图16是图1中螺旋桨的后掠部自前缘向后缘倾斜延伸的参数图。Figure 16 is a parametric diagram of the swept portion of the propeller of Figure 1 extending obliquely from the leading edge to the trailing edge.
图17是图1中螺旋桨的桨尖沿桨叶的展向朝吸力面所在的一侧倾斜延伸的参数图。Figure 17 is a parametric diagram in which the tip of the propeller of Figure 1 extends obliquely along the direction of the blade toward the side where the suction surface is located.
图18是本发明实施例提供的一种飞行器的平面示意图。FIG. 18 is a schematic plan view of an aircraft according to an embodiment of the present invention.
主要元件符号说明：The main component symbol description:
螺旋桨100、桨毂10、桨叶20、桨根21、桨尖22、后掠部221、压力面23、吸力面24、前缘25、前缘拱起部251、后缘26、后缘拱起部261、回弯处27； Propeller 100, hub 10, paddle 20, paddle 21, tip 22, swept portion 221, pressure surface 23, suction surface 24, leading edge 25, leading edge arch 251, trailing edge 26, trailing edge arch Starting portion 261, bend back 27;
动力组件200、驱动件30、机臂40； Power assembly 200, drive member 30, arm 40;
飞行器1000、机身50； Aircraft 1000, fuselage 50;
具体实施方式Detailed ways
这里将详细地对示例性实施例进行说明，其示例表示在附图中。下面的描述涉及附图时，除非另有表示，不同附图中的相同数字表示相同或相似的要素。以下示例性实施例中所描述的实施方式并不代表与本发明相一致的所有实施方式。相反，它们仅是与如所附权利要求书中所详述的、本发明的一些方面相一致的装置和方法的例子。Exemplary embodiments will be described in detail herein, examples of which are illustrated in the accompanying drawings. The following description refers to the same or similar elements in the different figures unless otherwise indicated. The embodiments described in the following exemplary embodiments do not represent all embodiments consistent with the present invention. Instead, they are merely examples of devices and methods consistent with aspects of the invention as detailed in the appended claims.
在本发明使用的术语是仅仅出于描述特定实施例的目的，而非旨在限制本发明。在本发明和所附权利要求书中所使用的单数形式的“一种”、“所述”和“该”也旨在包括多数形式，除非上下文清楚地表示其他含义。还应当理解，本文中使用的术语“和/或”是指并包含一个或多个相关联的列出项目的任何或所有可能组合。The terminology used in the present invention is for the purpose of describing particular embodiments, and is not intended to limit the invention. The singular forms "a", "the" and "the" It should also be understood that the term "and/or" as used herein refers to and encompasses any and all possible combinations of one or more of the associated listed items.
应当理解，尽管在本发明可能采用术语第一、第二、第三等来描述各种信息，但这些信息不应限于这些术语。这些术语仅用来将同一类型的信息彼此区分开。例如，在不脱离本发明范围的情况下，第一信息也可以被称为第二信息，类似地，第二信息也可以被称为第一信息。取决于语境，如在此所使用的词语“如果”可以被解释成为“在……时”或“当……时”或“响应于确定”。It should be understood that although the terms first, second, third, etc. may be used to describe various information in the present invention, such information should not be limited to these terms. These terms are only used to distinguish the same type of information from each other. For example, the first information may also be referred to as the second information without departing from the scope of the invention. Similarly, the second information may also be referred to as the first information. Depending on the context, the word "if" as used herein may be interpreted as "when" or "when" or "in response to a determination."
本实施例中出现的上、下等方位用语是以螺旋桨安装于飞行器以后所述螺旋桨以及所述飞行器的常规运行姿态为参考，而不应该认为具有限制性。The terms of the upper and lower orientations appearing in this embodiment are based on the conventional propeller of the propeller and the aircraft after the propeller is mounted on the aircraft, and should not be considered as limiting.
下面结合附图，对本发明的螺旋桨、动力组件及飞行器进行详细说明。在不冲突的情况下，下述的实施例及实施方式中的特征可以相互组合。The propeller, power assembly and aircraft of the present invention will be described in detail below with reference to the accompanying drawings. The features of the embodiments and embodiments described below may be combined with each other without conflict.
请参见图1至图5，本发明实施例提供一种螺旋桨100，螺旋桨100包括桨毂10和桨叶20。Referring to FIGS. 1 to 5 , an embodiment of the present invention provides a propeller 100 that includes a hub 10 and a blade 20 .
桨叶20连接在桨毂10上。当然，桨叶20可以与桨毂10一体成型，也可以分别加工再固定安装成一体。在距离桨毂10的中心为螺旋桨100的半径的42.9％处D3，桨叶20的攻角α3为24.60°±2.5°。在距离桨毂10的中心为螺旋桨100的半径的52.4％处D4，桨叶20的攻角α4为23.50°±2.5°。在距离桨毂10的中心为螺旋桨 100的半径的61.9％处D5，桨叶20的攻角α5为21.82°±2.5°。在距离桨毂10的中心为螺旋桨100的半径的71.4％处D6，桨叶20的攻角α6为19.97°±2.5°。The paddle 20 is attached to the hub 10. Of course, the paddles 20 may be integrally formed with the hub 10, or may be separately processed and fixedly assembled. At an angle D3 from the center of the hub 10 which is 42.9% of the radius of the propeller 100, the angle of attack α3 of the blade 20 is 24.60° ± 2.5°. At an angle D4 from the center of the hub 10 which is 52.4% of the radius of the propeller 100, the angle of attack α4 of the blade 20 is 23.50° ± 2.5°. At an angle D5 from the center of the hub 10 which is 61.9% of the radius of the propeller 100, the angle of attack α5 of the blade 20 is 21.82° ± 2.5°. At an angle D6 from the center of the hub 10 which is 71.4% of the radius of the propeller 100, the angle of attack α6 of the blade 20 is 19.97° ± 2.5°.
本实施例中，由于在距离桨毂10的中心为螺旋桨100的半径的42.9％处D3，桨叶20的攻角α3为24.60°±2.5°；在距离桨毂10的中心为螺旋桨100的半径的52.4％处D4，桨叶20的攻角α4为23.50°±2.5°；在距离桨毂10的中心为螺旋桨100的半径的61.9％处D5，桨叶20的攻角α5为21.82°±2.5°；在距离桨毂10的中心为螺旋桨100的半径的71.4％处D6，桨叶20的攻角α6为19.97°±2.5°；因此，采用桨叶20的螺旋桨100能够减少空气阻力，提高拉力和效率，增加飞行器1000(图18所示)的继航距离以提高飞行器1000的飞行性能，同时还在效率不降低的情况下，增大飞行器1000的最大拉力，降低了飞行器1000失控风险，提高飞行安全，再者，减少了桨叶20在工作时产生的噪声，使得飞行器1000在悬停时更安静，提高了用户体验。In the present embodiment, since D3 is 42.9% of the radius of the propeller 100 from the center of the hub 10, the angle of attack α3 of the blade 20 is 24.60° ± 2.5°; at the center of the hub 10 is the radius of the propeller 100 At 52.4%, D4, the angle of attack α4 of the blade 20 is 23.50°±2.5°; at the center of the hub 10, 61.9% of the radius of the propeller 100, D5, the angle of attack α5 of the blade 20 is 21.82°±2.5 °; at the center of the hub 10, 71.4% of the radius of the propeller 100, D6, the angle of attack α6 of the blade 20 is 19.97 ° ± 2.5 °; therefore, the propeller 100 using the blade 20 can reduce air resistance and increase the pulling force And efficiency, increasing the relay distance of the aircraft 1000 (shown in FIG. 18) to improve the flight performance of the aircraft 1000, while increasing the maximum pulling force of the aircraft 1000 without reducing the efficiency, reducing the risk of loss of control of the aircraft 1000, and improving Flight safety, in addition, reduces the noise generated by the blade 20 during operation, making the aircraft 1000 quieter when hovering, improving the user experience.
请再次参见图1至图5，本发明实施例提供一种螺旋桨100，螺旋桨100包括桨毂10和桨叶20。Referring again to FIGS. 1 through 5 , an embodiment of the present invention provides a propeller 100 that includes a hub 10 and a paddle 20 .
在距离桨毂10的中心为螺旋桨100的半径的42.9％处D3，桨叶20的攻角α3为24.60°±2.5°，桨叶20的弦长L3为26.49mm±5mm。在距离桨毂10的中心为螺旋桨100的半径的52.4％处D4，桨叶20的攻角α4为23.50°±2.5°，桨叶20的弦长L4为25.16mm±5mm。在距离桨毂10的中心为螺旋桨100的半径的61.9％处D5，桨叶20的攻角α5为21.82°±2.5°，桨叶20的弦长L5为23.59mm±5mm。在距离桨毂10的中心为螺旋桨100的半径的71.4％处D6，桨叶20的攻角α6为19.97°±2.5°，桨叶20的弦长L6为21.69mm±5mm。At an angle D3 from the center of the hub 10 which is 42.9% of the radius of the propeller 100, the angle of attack α3 of the blade 20 is 24.60° ± 2.5°, and the chord length L3 of the blade 20 is 26.49 mm ± 5 mm. At a distance D4 from the center of the hub 10 which is 52.4% of the radius of the propeller 100, the angle of attack α4 of the blade 20 is 23.50° ± 2.5°, and the chord length L4 of the blade 20 is 25.16 mm ± 5 mm. At an angle D5 from the center of the hub 10 which is 61.9% of the radius of the propeller 100, the angle of attack α5 of the blade 20 is 21.82° ± 2.5°, and the chord length L5 of the blade 20 is 23.59 mm ± 5 mm. At a distance D6 from the center of the hub 10 which is 71.4% of the radius of the propeller 100, the angle of attack α6 of the blade 20 is 19.97° ± 2.5°, and the chord length L6 of the blade 20 is 21.69 mm ± 5 mm.
本实施例中，由于在距离桨毂10的中心为螺旋桨100的半径的42.9％处D3，桨叶20的攻角α3为24.60°±2.5°，桨叶20的弦长L3为26.49mm±5mm；在距离桨毂10的中心为螺旋桨100的半径的52.4％处D4，桨叶20的攻角α4为23.50°±2.5°，桨叶20的弦长L4为25.16mm±5mm；在距离桨毂10的中心为螺旋桨100的半径的61.9％处D5，桨叶20的攻角α5为21.82°±2.5°，桨叶20的弦长L5为23.59mm±5mm；在距离桨毂10的中心为螺旋桨100的半径的71.4％处D6，桨叶20的攻角α6为19.97°±2.5°，桨叶20的弦长L6为21.69mm±5mm；因此，采用桨叶20的螺旋桨100能够减少空气阻力，提高拉力和效率，增加飞行器1000的继航距离以提高飞行器1000的飞行性能，同时还在效率不降低的情况下，增大飞行器1000的最大拉力， 降低了飞行器1000失控风险，提高飞行安全，再者，减少了桨叶20在工作时产生的噪声，使得飞行器1000在悬停时更安静，提高了用户体验。In the present embodiment, since the angle of attack α3 of the blade 20 is 24.60°±2.5° at the point 42.9% of the radius of the propeller 100 from the center of the hub 10, the chord length L3 of the blade 20 is 26.49 mm±5 mm. At an angle of D4 from the center of the hub 10 which is 52.4% of the radius of the propeller 100, the angle of attack α4 of the blade 20 is 23.50°±2.5°, and the chord length L4 of the blade 20 is 25.16 mm±5 mm; The center of 10 is D5 at 61.9% of the radius of the propeller 100, the angle of attack α5 of the blade 20 is 21.82° ± 2.5°, the chord length L5 of the blade 20 is 23.59 mm ± 5 mm, and the propeller is at the center of the hub 10 At 71.4% of the radius of 100, D6, the angle of attack α6 of the blade 20 is 19.97°±2.5°, and the chord length L6 of the blade 20 is 21.69 mm±5 mm; therefore, the propeller 100 using the blade 20 can reduce air resistance, Increasing the pulling force and efficiency, increasing the relay distance of the aircraft 1000 to improve the flight performance of the aircraft 1000, while increasing the maximum pulling force of the aircraft 1000 without reducing the efficiency, reducing the risk of loss of control of the aircraft 1000, improving flight safety, and then Reduces the noise generated by the blade 20 during operation, making the aircraft 1000 more secure when hovering To improve the user experience.
请参见表1，本实施例所提供的螺旋桨100与现有的螺旋桨的测试结果的比对，由表1中可看出，在相同的拉力下，本实施方式所提供螺旋桨100的功率更低，也即：在较小的功率条件下，具有更大的拉力，从而降低电量损耗，增加续航距离。由此，本实施方式提供的螺旋桨100在密度降低的高海拔区域或者低海拔地区起飞重量较大的极端情况下，其可以显著提高拉力，保证足够动力同时延长续航时间，提高飞行性能。Referring to Table 1, the comparison between the propeller 100 and the test results of the existing propeller provided in this embodiment can be seen from Table 1. Under the same pulling force, the propeller 100 provided by the present embodiment has lower power. That is, under smaller power conditions, there is greater pulling force, thereby reducing power consumption and increasing the cruising distance. Therefore, the propeller 100 provided by the present embodiment can significantly increase the pulling force in the extreme case where the lifting density is high in a high-altitude region with a reduced density or a low-altitude region, thereby ensuring sufficient power while prolonging the endurance time and improving flight performance.
表1Table 1
Figure PCTCN2018109068-appb-000001
Figure PCTCN2018109068-appb-000001
请一并参阅表2及图6，本实施方式提供的螺旋桨100与现有的螺旋桨的测试结果的比对。由表2中可看出，在相同的悬停工况声学性能测试条件下，本实施例所提供的螺旋桨100产生的噪音与现有的螺旋桨产生的噪音相比，本实施例所提供的螺旋桨100的噪音整体低于现有的螺旋桨。由此，本实施例所提供的螺旋桨100能有效减小噪音。另外，由图6中的频响曲线(Frequency(Hz)-Loudness(dB-A))可看出，在大部分相同频率的条件下，本实施例所提供的螺旋桨100的响度低于现有的螺旋桨。特别是在相同的高频条件下，本实施例所提供的螺旋桨100的响度明显低于现有的螺旋桨的响度。由此，本实施例所提供的螺旋桨100能有效减小高频噪音，减轻了高频噪音引起人耳的不适感，提高了用户体验。除此之外，本实施例所提供的螺旋桨100能应用在对声音要求高的场景中，比如侦查、航拍(航拍时录入影像及音频)等。Please refer to Table 2 and FIG. 6 together, and compare the test results of the propeller 100 provided by the present embodiment with the existing propeller. It can be seen from Table 2 that under the same hovering condition acoustic performance test conditions, the propeller 100 provided by the present embodiment generates noise compared with the noise generated by the existing propeller, and the propeller provided in this embodiment The noise of 100 is lower overall than the existing propeller. Thus, the propeller 100 provided in this embodiment can effectively reduce noise. In addition, it can be seen from the frequency response curve (Frequency (Hz)-Loudness (dB-A)) in FIG. 6 that the loudness of the propeller 100 provided in this embodiment is lower than that under the condition of most of the same frequency. Propeller. Especially under the same high frequency conditions, the loudness of the propeller 100 provided by this embodiment is significantly lower than that of the existing propeller. Therefore, the propeller 100 provided in the embodiment can effectively reduce high frequency noise, reduce the discomfort caused by high frequency noise and improve the user experience. In addition, the propeller 100 provided in this embodiment can be applied to scenes with high sound requirements, such as detection, aerial photography (recording images and audio during aerial photography), and the like.
表2Table 2
Figure PCTCN2018109068-appb-000002
Figure PCTCN2018109068-appb-000002
在距离桨毂10的中心为螺旋桨100的半径的42.9％处D3，桨叶20的攻角α3可以为22.10°或24.60°或27.10°，或者是22.60°、23.10°、23.60°、24.10°、25.10°、25.60°、26.10°、26.60°等中的任意一个或上述任意二者之间的任一数值，桨叶20的弦长L3可以为21.49mm或26.49mm或31.49mm，或者是22.49mm、23.49mm、24.49mm、25.49mm、27.49mm、28.49mm、29.49mm、30.49mm等中的任意一个或上 述任意二者之间的数值。在距离桨毂10的中心为螺旋桨100的半径的52.4％处D4，桨叶20的攻角α4可以为21.00°或23.50°或26.00°，或者是21.50°、22.00°、22.50°、23.00°、24.00°、24.50°、25.00°、25.50°等中的任意一个或上述任意二者之间的数值，桨叶20的弦长L4可以为20.16mm或25.16mm或30.16mm，或者是21.16mm、22.16mm、23.16mm、24.16mm、26.16mm、27.16mm、28.16mm、29.16mm等中的任意一个或上述任意二者之间的数值。在距离桨毂10的中心为螺旋桨100的半径的61.9％处D5，桨叶20的攻角α5可以为19.32°或21.82°或24.32°，或者是19.82°、20.32°、20.82°、21.32°、22.32°、22.82°、23.32°、23.82°等中的任意一个或上述任意二者之间的数值，桨叶20的弦长L5可以为18.59mm或23.59mm或28.59mm，或者是19.59mm、20.59mm、21.59mm、22.59mm、24.59mm、25.59mm、26.59mm、27.59mm等中的任意一个或上述任意二者之间的数值。在距离桨毂10的中心为螺旋桨100的半径的71.4％处D6，桨叶20的攻角α6可以为17.47°或19.97°或22.47°，或者是17.97°、18.47°、18.97°、19.47°、20.47°、20.97°、21.47°、21.97°等中的任意一个或上述任意二者之间的数值，桨叶20的弦长L6可以为16.69mm或21.69mm或26.69mm，或者是17.69mm、18.69mm、19.69mm、20.69mm、22.69mm、23.69mm、24.69mm、25.69mm等中的任意一个或上述任意二者之间的数值。At an angle D3 from the center of the hub 10 which is 42.9% of the radius of the propeller 100, the angle of attack α3 of the blade 20 may be 22.10° or 24.60° or 27.10°, or 22.60°, 23.10°, 23.60°, 24.10°, Any one of 25.10°, 25.60°, 26.10°, 26.60°, etc., or any of the above, the chord length L3 of the blade 20 may be 21.49 mm or 26.49 mm or 31.49 mm, or 22.49 mm. Any one of 23.49 mm, 24.49 mm, 25.49 mm, 27.49 mm, 28.49 mm, 29.49 mm, 30.49 mm, or the like, or a value between any of the above. At an angle D4 from the center of the hub 10 that is 52.4% of the radius of the propeller 100, the angle of attack α4 of the blade 20 may be 21.00° or 23.50° or 26.00°, or 21.50°, 22.00°, 22.50°, 23.00°, The value of any one of 24.00°, 24.50°, 25.00°, 25.50°, etc., or any of the above, the chord length L4 of the blade 20 may be 20.16 mm or 25.16 mm or 30.16 mm, or 21.16 mm, 22.16. Any of mm, 23.16 mm, 24.16 mm, 26.16 mm, 27.16 mm, 28.16 mm, 29.16 mm, etc., or any of the above. At an angle D5 from the center of the hub 10 which is 61.9% of the radius of the propeller 100, the angle of attack α5 of the blade 20 may be 19.32° or 21.82° or 24.32°, or 19.82°, 20.32°, 20.82°, 21.32°, The value between any of 22.32°, 22.82°, 23.32°, 23.82°, etc., or any of the above, the chord length L5 of the blade 20 may be 18.59 mm or 23.59 mm or 28.59 mm, or 19.59 mm, 20.59. Any of mm, 21.59 mm, 22.59 mm, 24.59 mm, 25.59 mm, 26.59 mm, 27.59 mm, etc., or any of the above. At an angle D6 from the center of the hub 10 that is 71.4% of the radius of the propeller 100, the angle of attack α6 of the blade 20 may be 17.47° or 19.97° or 22.47°, or 17.97°, 18.47°, 18.97°, 19.47°, The value between any of 20.47°, 20.97°, 21.47°, 21.97°, or the like, or the chord length L6 of the blade 20 may be 16.69 mm or 21.69 mm or 26.69 mm, or 17.69 mm, 18.69. Any of mm, 19.69 mm, 20.69 mm, 22.69 mm, 23.69 mm, 24.69 mm, 25.69 mm, etc., or any of the above.
请参见图7所示，本实施例中，可选地，在距离桨毂10的中心为螺旋桨100的半径的23.8％处D1，桨叶20的攻角α1为23.40°±2.5°，桨叶20的弦长L1为21.21mm±5mm，以进一步减少螺旋桨100的空气阻力，提高拉力和效率，及降低噪音。其中，桨叶20的攻角α1可以为20.90°或23.40°或25.90°，或者是21.40°、21.90°、22.40°、22.90°、23.90°、24.40°、24.90°、25.40°等中的任意一个或上述任意二者之间的数值，桨叶20的弦长L1可以为16.21mm或21.21mm或26.21mm，或者是17.21mm、18.21mm、19.21mm、20.21mm、22.21mm、23.21mm、24.21mm、25.21mm等中的任意一个或上述任意二者之间的数值。Referring to FIG. 7, in the present embodiment, optionally, at an angle D1 of 23.8% of the radius of the propeller 100 from the center of the hub 10, the angle of attack α1 of the blade 20 is 23.40°±2.5°, the blade The chord length L1 of 20 is 21.21 mm ± 5 mm to further reduce the air resistance of the propeller 100, increase the pulling force and efficiency, and reduce noise. Wherein, the angle of attack α1 of the blade 20 may be 20.90° or 23.40° or 25.90°, or any one of 21.40°, 21.90°, 22.40°, 22.90°, 23.90°, 24.40°, 24.90°, 25.40°, and the like. Or the value between any two of the above, the chord length L1 of the blade 20 may be 16.21 mm or 21.21 mm or 26.21 mm, or 17.21 mm, 18.21 mm, 19.21 mm, 20.21 mm, 22.21 mm, 23.21 mm, 24.21 mm. Any one of 25.21 mm or the like or a value between any two of the above.
请参见图8所示，本实施例中，可选地，在距离桨毂10的中心为螺旋桨100的半径的33.3％处D2，桨叶20的攻角α2为26.20°±2.5°，桨叶20的弦长L2为27.38mm±5mm。以进一步减少螺旋桨100的空气阻力，提高拉力和效率，及降低噪音。其中，桨叶20的攻角α2可以为23.70°或26.20°或28.70°，或者是24.20°、24.70°、25.20°、25.70°、26.70°、27.20°、27.70°、28.20°等中的任意一个或上述任意二者之间的数值，桨叶20的弦长L2可以为22.38mm或27.38mm或32.38mm，或者是 23.38mm、24.38mm、25.38mm、26.38mm、28.38mm、29.38mm、30.38mm、31.38mm等中的任意一个或上述任意二者之间的数值。Referring to FIG. 8, in the present embodiment, optionally, at an angle D3 from the center of the hub 10 which is 33.3% of the radius of the propeller 100, the angle of attack α2 of the blade 20 is 26.20°±2.5°, the blade The chord length L2 of 20 is 27.38 mm ± 5 mm. To further reduce the air resistance of the propeller 100, increase the pulling force and efficiency, and reduce noise. Wherein, the angle of attack α2 of the blade 20 may be 23.70° or 26.20° or 28.70°, or any one of 24.20°, 24.70°, 25.20°, 25.70°, 26.70°, 27.20°, 27.70°, 28.20°, and the like. Or the value between any two of the above, the chord length L2 of the blade 20 may be 22.38 mm or 27.38 mm or 32.38 mm, or 23.38 mm, 24.38 mm, 25.38 mm, 26.38 mm, 28.38 mm, 29.38 mm, 30.38 mm. Any one of 31.38 mm or the like or a value between any of the above.
请参见图9所示，本实施例中，可选地，在距离桨毂10的中心为螺旋桨100的半径的81.0％处D7，桨叶20的攻角α7为17.97°±2.5°，桨叶20的弦长L7为19.45mm±5mm，以进一步减少螺旋桨100的空气阻力，提高拉力和效率，及降低噪音。其中，桨叶20的攻角α7可以为15.47°或17.97°或20.47°，或者是15.97°、16.47°、16.97°、17.47°、18.47°、18.97°、19.47°、19.97°等中的任意一个或上述任意二者之间的数值，桨叶20的弦长L7可以为14.45mm或19.45mm或24.45mm，或者是15.45mm、16.45mm、17.45mm、18.45mm、20.45mm、21.45mm、22.45mm、23.45mm等中的任意一个或上述任意二者之间的数值。Referring to FIG. 9, in the present embodiment, optionally, at the center of the hub 10, 81.0% of the radius of the propeller 100, D7, the angle of attack α7 of the blade 20 is 17.97°±2.5°, the blade The chord length L7 of 20 is 19.45 mm ± 5 mm to further reduce the air resistance of the propeller 100, increase the pulling force and efficiency, and reduce noise. Wherein, the angle of attack α7 of the blade 20 may be 15.47° or 17.97° or 20.47°, or any one of 15.97°, 16.47°, 16.97°, 17.47°, 18.47°, 18.97°, 19.47°, 19.97°, and the like. Or the value between any two of the above, the chord length L7 of the blade 20 may be 14.45 mm or 19.45 mm or 24.45 mm, or 15.45 mm, 16.45 mm, 17.45 mm, 18.45 mm, 20.45 mm, 21.45 mm, 22.45 mm. Any one of 23.45 mm or the like or a value between any of the above.
请参见图10所示，本实施例中，可选地，在距离桨毂10的中心为螺旋桨100的半径的90.5％处D8，桨叶20的攻角α8为16.61°±2.5°，桨叶20的弦长L8为15.78mm±5mm。以进一步减少螺旋桨100的空气阻力，提高拉力和效率，及降低噪音。其中，桨叶20的攻角α8可以为14.11°或16.61°或19.11°，或者是14.61°、15.11°、15.61°、16.11°、17.11°、17.61°、18.11°、18.61°等中的任意一个或上述任意二者之间的数值，桨叶20的弦长L8可以为10.78mm或15.78mm或20.78mm，或者是11.78mm、12.78mm、13.78mm、14.78mm、16.78mm、17.78mm、18.78mm、19.78mm等中的任意一个或上述任意二者之间的数值。Referring to FIG. 10, in the present embodiment, optionally, at a distance of 90.5% of the radius of the propeller 100 from the center of the hub 10, D8, the angle of attack α8 of the blade 20 is 16.61 ° ± 2.5 °, the blade The chord length L8 of 20 is 15.78 mm ± 5 mm. To further reduce the air resistance of the propeller 100, increase the pulling force and efficiency, and reduce noise. Wherein, the angle of attack α8 of the blade 20 may be 14.11° or 16.61° or 19.11°, or any one of 14.61°, 15.11°, 15.61°, 16.11°, 17.11°, 17.61°, 18.11°, 18.61°, and the like. Or the value between any two of the above, the chord length L8 of the blade 20 may be 10.78 mm or 15.78 mm or 20.78 mm, or 11.78 mm, 12.78 mm, 13.78 mm, 14.78 mm, 16.78 mm, 17.78 mm, 18.78 mm. Any one of 19.78 mm or the like or a value between any of the above.
请参见图11所示，本实施例中，可选地，在距离桨毂10的中心为螺旋桨100的半径的100％处D9，桨叶20的攻角α9为9.39°±2.5°，桨叶20的弦长L9为4.94mm±2mm。以进一步减少螺旋桨100的空气阻力，提高拉力和效率，及降低噪音。其中，桨叶20的攻角α9可以为6.89°或9.39°或11.89°，或者是7.39°、7.89°、8.39°、8.89°、9.89°、10.39°、10.89°、11.39°等中的任意一个或上述任意二者之间的数值，桨叶20的弦长L9可以为2.94mm或4.94mm或6.94mm，或者是3.44mm、3.94mm、4.44mm、5.44mm、5.94mm、6.44mm等中的任意一个或上述任意二者之间的数值。Referring to FIG. 11, in the present embodiment, optionally, at a distance D10 from the center of the hub 10 which is 100% of the radius of the propeller 100, the angle of attack α9 of the blade 20 is 9.39°±2.5°, the blade The chord length L9 of 20 is 4.94 mm ± 2 mm. To further reduce the air resistance of the propeller 100, increase the pulling force and efficiency, and reduce noise. Wherein, the angle of attack α9 of the blade 20 may be 6.89° or 9.39° or 11.89°, or any one of 7.39°, 7.89°, 8.39°, 8.89°, 9.89°, 10.39°, 10.89°, 11.39°, and the like. Or the value between any two of the above, the chord length L9 of the blade 20 may be 2.94 mm or 4.94 mm or 6.94 mm, or 3.44 mm, 3.94 mm, 4.44 mm, 5.44 mm, 5.94 mm, 6.44 mm, or the like. Any one or a value between any two of the above.
请再次参见图1至图5所示，本实施例中，可选地，螺旋桨100的直径为210mm±21mm。在距离桨毂10的中心45mm处D3，桨叶20的攻角α3为24.60°，桨叶20的弦长L3为26.49mm。在距离桨毂10的中心55mm处D4，桨叶20的攻角α4为23.50°，桨叶20的弦长L4为25.16mm。在距离桨毂10的中心65mm处D5，桨叶20的攻角α5为21.82°，桨叶20的弦长L5为23.59mm。在距离桨毂10的中心75mm处D6， 桨叶20的攻角α6为19.97°，桨叶20的弦长L6为21.69mm。由此，可进一步减少螺旋桨100的空气阻力，提高拉力和效率，及降低噪音。其中，螺旋桨100的直径可以为189mm或210mm或231mm，或者是193mm、197mm、201mm、205mm、209mm、213mm、217mm、221mm、225mm、229mm等中的任意一个或上述任意二者之间的数值。Referring again to FIG. 1 to FIG. 5, in the present embodiment, optionally, the diameter of the propeller 100 is 210 mm ± 21 mm. At an angle D3 45 mm from the center of the hub 10, the angle of attack α3 of the blade 20 is 24.60°, and the chord length L3 of the blade 20 is 26.49 mm. At an angle of 55 mm from the center of the hub 10, the angle of attack α4 of the blade 20 is 23.50°, and the chord length L4 of the blade 20 is 25.16 mm. At an angle of 65 mm from the center of the hub 10, the angle of attack α5 of the blade 20 is 21.82°, and the chord length L5 of the blade 20 is 23.59 mm. At an angle of 75 mm from the center of the hub 10, the angle of attack α6 of the blade 20 is 19.97°, and the chord length L6 of the blade 20 is 21.69 mm. Thereby, the air resistance of the propeller 100 can be further reduced, the pulling force and efficiency can be improved, and the noise can be reduced. The diameter of the propeller 100 may be 189 mm or 210 mm or 231 mm, or any one of 193 mm, 197 mm, 201 mm, 205 mm, 209 mm, 213 mm, 217 mm, 221 mm, 225 mm, 229 mm, or the like, or a value between any two of the above.
请再次参见图7所示，本实施例中，可选地，螺旋桨100的直径为210mm±21mm。在距离桨毂10的中心25mm处D1，桨叶20的攻角α1为23.40°，桨叶20的弦长L1为21.21mm。由此，可进一步减少螺旋桨100的空气阻力，提高拉力和效率，及降低噪音。其中，螺旋桨100的直径可以为189mm或210mm或231mm，或者是193mm、197mm、201mm、205mm、209mm、213mm、217mm、221mm、225mm、229mm等中的任意一个或上述任意二者之间的数值。Referring again to FIG. 7, in the present embodiment, optionally, the diameter of the propeller 100 is 210 mm ± 21 mm. At an angle of 25 mm from the center of the hub 10, the angle of attack α1 of the blade 20 is 23.40°, and the chord length L1 of the blade 20 is 21.21 mm. Thereby, the air resistance of the propeller 100 can be further reduced, the pulling force and efficiency can be improved, and the noise can be reduced. The diameter of the propeller 100 may be 189 mm or 210 mm or 231 mm, or any one of 193 mm, 197 mm, 201 mm, 205 mm, 209 mm, 213 mm, 217 mm, 221 mm, 225 mm, 229 mm, or the like, or a value between any two of the above.
再次参见图8所示，本实施例中，可选地，螺旋桨100的直径为210mm±21mm。在距离桨毂10的中心35mm处D2，桨叶20的攻角α2为26.20°，桨叶20的弦长L2为27.38mm。由此，可进一步减少螺旋桨100的空气阻力，提高拉力和效率，及降低噪音。其中，螺旋桨100的直径可以为189mm或210mm或231mm，或者是193mm、197mm、201mm、205mm、209mm、213mm、217mm、221mm、225mm、229mm等中的任意一个或上述任意二者之间的数值。Referring again to FIG. 8, in the present embodiment, optionally, the diameter of the propeller 100 is 210 mm ± 21 mm. At an angle of 35 mm from the center of the hub 10, the angle of attack α2 of the blade 20 is 26.20°, and the chord length L2 of the blade 20 is 27.38 mm. Thereby, the air resistance of the propeller 100 can be further reduced, the pulling force and efficiency can be improved, and the noise can be reduced. The diameter of the propeller 100 may be 189 mm or 210 mm or 231 mm, or any one of 193 mm, 197 mm, 201 mm, 205 mm, 209 mm, 213 mm, 217 mm, 221 mm, 225 mm, 229 mm, or the like, or a value between any two of the above.
请再次参见图9所示，本实施例中，可选地，螺旋桨100的直径为210mm±21mm。在距离桨毂10的中心85mm处D7，桨叶20的攻角α7为17.97°，桨叶20的弦长L7为19.45mm。由此，可进一步减少螺旋桨100的空气阻力，提高拉力和效率，及降低噪音。其中，螺旋桨100的直径可以为189mm或210mm或231mm，或者是193mm、197mm、201mm、205mm、209mm、213mm、217mm、221mm、225mm、229mm等中的任意一个或上述任意二者之间的数值。Referring again to FIG. 9, in the present embodiment, optionally, the diameter of the propeller 100 is 210 mm ± 21 mm. At an angle of 85 mm from the center of the hub 10, the angle of attack α7 of the blade 20 is 17.97°, and the chord length L7 of the blade 20 is 19.45 mm. Thereby, the air resistance of the propeller 100 can be further reduced, the pulling force and efficiency can be improved, and the noise can be reduced. The diameter of the propeller 100 may be 189 mm or 210 mm or 231 mm, or any one of 193 mm, 197 mm, 201 mm, 205 mm, 209 mm, 213 mm, 217 mm, 221 mm, 225 mm, 229 mm, or the like, or a value between any two of the above.
再次参见图10所示，本实施例中，可选地，螺旋桨100的直径为210mm±21mm。在距离桨毂10的中心95mm处D8，桨叶20的攻角α8为16.61°，桨叶20的弦长L8为15.78mm。由此，可进一步减少螺旋桨100的空气阻力，提高拉力和效率，及降低噪音。其中，螺旋桨100的直径可以为189mm或210mm或231mm，或者是193mm、197mm、201mm、205mm、209mm、213mm、217mm、221mm、225mm、229mm等中的任意一个或上述任意二者之间的数值。Referring again to FIG. 10, in the present embodiment, optionally, the diameter of the propeller 100 is 210 mm ± 21 mm. At an angle of 85 mm from the center of the hub 10, the angle of attack α8 of the blade 20 is 16.61°, and the chord length L8 of the blade 20 is 15.78 mm. Thereby, the air resistance of the propeller 100 can be further reduced, the pulling force and efficiency can be improved, and the noise can be reduced. The diameter of the propeller 100 may be 189 mm or 210 mm or 231 mm, or any one of 193 mm, 197 mm, 201 mm, 205 mm, 209 mm, 213 mm, 217 mm, 221 mm, 225 mm, 229 mm, or the like, or a value between any two of the above.
再次参见图11所示，本实施例中，可选地，螺旋桨100的直径为210mm±21mm。 在距离桨毂10的中心105mm处D9，桨叶20的攻角α9为9.39°，桨叶20的弦长L9为4.94mm。由此，可进一步减少螺旋桨100的空气阻力，提高拉力和效率，及降低噪音。其中，螺旋桨100的直径可以为189mm或210mm或231mm，或者是193mm、197mm、201mm、205mm、209mm、213mm、217mm、221mm、225mm、229mm等中的任意一个或上述任意二者之间的数值。Referring again to FIG. 11, in the present embodiment, optionally, the diameter of the propeller 100 is 210 mm ± 21 mm. At an angle of 10 mm from the center of the hub 10, D9, the angle of attack α9 of the blade 20 is 9.39°, and the chord length L9 of the blade 20 is 4.94 mm. Thereby, the air resistance of the propeller 100 can be further reduced, the pulling force and efficiency can be improved, and the noise can be reduced. The diameter of the propeller 100 may be 189 mm or 210 mm or 231 mm, or any one of 193 mm, 197 mm, 201 mm, 205 mm, 209 mm, 213 mm, 217 mm, 221 mm, 225 mm, 229 mm, or the like, or a value between any two of the above.
请参见图12至图15，本实施例中，可选地，桨叶20包括桨根21、背离桨根21的桨尖22、相背的压力面23及吸力面24。桨尖22沿桨叶20的展向朝吸力面24所在的一侧倾斜延伸。如此，减少了桨叶20在工作时产生的噪声，使得飞行器1000在悬停时更安静，提高了用户体验。Referring to FIG. 12 to FIG. 15 , in the present embodiment, the paddle 20 optionally includes a paddle root 21 , a tip end 22 facing away from the blade root 21 , a pressure surface 23 opposite to each other, and a suction surface 24 . The tip 22 extends obliquely along the direction of the blade 20 toward the side on which the suction surface 24 is located. As such, the noise generated by the blade 20 during operation is reduced, making the aircraft 1000 quieter when hovering, improving the user experience.
其中，压力面23为飞行器1000正常飞行时桨叶20的朝向地面的表面，吸力面24为飞行器1000正常飞行时桨叶20的朝向天空的表面。Wherein, the pressure surface 23 is a surface facing the ground of the blade 20 during normal flight of the aircraft 1000, and the suction surface 24 is a surface facing the sky of the blade 20 when the aircraft 1000 is normally flying.
本实施例中，可选地，吸力面24和压力面23均为曲面。吸力面24和压力面23为曲面的气动外形，能避免桨叶20各部分产生的湍流以及下洗气流直接冲击飞行器1000的机身50，从而减小飞行器1000整体的噪音。In this embodiment, optionally, the suction surface 24 and the pressure surface 23 are curved surfaces. The suction surface 24 and the pressure surface 23 are curved aerodynamic shapes, which can prevent the turbulence generated by the various portions of the blade 20 and the downwashing airflow from directly impacting the fuselage 50 of the aircraft 1000, thereby reducing the overall noise of the aircraft 1000.
请结合图1，本实施例中，可选地，桨叶20还包括连接于压力面23及吸力面24一侧边的前缘25、连接于压力面23及吸力面24另一侧边的后缘26、及形成于桨尖22的后掠部221，后掠部221自前缘25向后缘26倾斜延伸。如此，以起到进一步提高螺旋桨100的拉力及效率的效果。Referring to FIG. 1 , in the embodiment, the paddle 20 further includes a leading edge 25 connected to one side of the pressure surface 23 and the suction surface 24 , and the other side of the pressure surface 23 and the suction surface 24 . The trailing edge 26 and the swept portion 221 formed on the blade tip 22 extend obliquely from the leading edge 25 toward the trailing edge 26. In this way, the effect of further increasing the pulling force and efficiency of the propeller 100 is achieved.
本实施例中，可选地，桨叶20在桨尖22的位置形成回弯处27，后掠部221自回弯处27开始从前缘25向后缘26倾斜延伸，后掠部221自回弯处27从前缘25向后缘26倾斜延伸。回弯处27的位置用MM表示。In the present embodiment, optionally, the paddle 20 forms a return bend 27 at the position of the blade tip 22, and the swept portion 221 extends obliquely from the front edge 25 to the trailing edge 26 from the corner bend 27, and the swept portion 221 is self-returned. The bend 27 extends obliquely from the leading edge 25 to the trailing edge 26. The position of the return bend 27 is indicated by MM.
本实施例中，可选地，回弯处27距离桨毂10的中心为螺旋桨100的半径的82.5％。回弯处27远离桨毂10的中心，提升桨叶20的美观。In the present embodiment, optionally, the back bend 27 is 82.5% of the radius of the propeller 100 from the center of the hub 10. The return bend 27 is away from the center of the hub 10 to enhance the aesthetics of the blade 20.
本实施例中，可选地，前缘25外凸形成有靠近桨根21的呈曲面状的前缘拱起部251，后缘26外凸形成有靠近桨根21的呈曲面状的后缘拱起部261。前缘拱起部251及后缘拱起部231为曲面状起到进一步提高桨叶20的拉力的效果。In this embodiment, optionally, the leading edge 25 is convexly formed with a curved leading edge arching portion 251 near the paddle root 21, and the trailing edge 26 is convexly formed with a curved trailing edge near the paddle root 21. The arched portion 261. The leading edge arching portion 251 and the trailing edge arching portion 231 have a curved shape to further increase the pulling force of the blade 20.
本实施例中，可选地，桨叶20为至少两个，至少两个桨叶20连接在桨毂10上并关于桨毂10的中心呈中心对称。由此，可提高螺旋桨100的平衡性。其中，桨毂10包括桨夹11及安装部12，桨叶20通过桨夹11固定在安装部12上。桨毂10中心设有连接孔13，连接孔13用于套设在电机的输出端上，安装部12用于将桨毂10固定 在电机的输出端上。桨叶20可以呈长条状，桨叶20与桨毂10连接，并沿桨毂10的径向延伸。In the present embodiment, optionally, the blades 20 are at least two, and at least two blades 20 are coupled to the hub 10 and are centrally symmetric with respect to the center of the hub 10. Thereby, the balance of the propeller 100 can be improved. The hub 10 includes a paddle 11 and a mounting portion 12, and the paddle 20 is fixed to the mounting portion 12 by the paddle 11 . The center of the hub 10 is provided with a connecting hole 13 for arranging on the output end of the motor, and the mounting portion 12 is for fixing the hub 10 to the output end of the motor. The blade 20 may be in the form of a strip, the blade 20 being coupled to the hub 10 and extending in the radial direction of the hub 10.
本实施例中，可选地，桨叶20具有穿过桨毂10的中心的中轴线N-N，前缘25具有平行于中轴线N-N的前缘切线O-O，后缘26具有平行于中轴线N-N的后缘切线P-P，后掠部221位于前缘切线O-O与后缘切线P-P之间。由此，后掠部221能够减小桨叶20产生的湍流及下洗气流，从而减少打到飞行器1000的机身50上的湍流及下洗气流，在减小螺旋桨100的空气阻力，提高飞行器1000的可操纵性，使飞行器1000更加平稳的同时进一步减小飞行器1000整体的噪音。In the present embodiment, optionally, the paddle 20 has a central axis NN that passes through the center of the hub 10, the leading edge 25 has a leading edge tangent OO parallel to the central axis NN, and the trailing edge 26 has a parallel to the central axis NN The trailing edge tangent PP, the swept portion 221 is located between the leading edge tangent OO and the trailing edge tangent PP. Thereby, the swept portion 221 can reduce the turbulence and the downwash flow generated by the blade 20, thereby reducing the turbulence and the downwashing airflow hitting the fuselage 50 of the aircraft 1000, reducing the air resistance of the propeller 100, and improving the aircraft. The maneuverability of 1000 makes the aircraft 1000 more stable while further reducing the overall noise of the aircraft 1000.
请一并参阅表3、图1及图16，本实施方式中，后掠部221自前缘25向后缘26倾斜延伸。具体地，表3及图16的横坐标Blade Radius(mm)表示沿桨叶20的展向上桨叶20的某一位置(比如MM处)距离桨毂10中心的距离。纵坐标Sweep Length(mm)为后掠或前掠的距离。其中，纵坐标Sweep Length(mm)的正值为后掠，负值为前掠。Referring to Table 3, FIG. 1 and FIG. 16, in the present embodiment, the swept portion 221 extends obliquely from the leading edge 25 toward the trailing edge 26. Specifically, the abscissa Blade Radius (mm) of Table 3 and FIG. 16 indicates the distance from the center of the hub 10 at a certain position (such as MM) of the paddle 20 extending along the blade 20. The Sweep Length (mm) is the distance of the swept or swept forward. Among them, the positive value of the Sweep Length (mm) is swept back, and the negative value is swept forward.
表3table 3
Figure PCTCN2018109068-appb-000003
Figure PCTCN2018109068-appb-000003
由表3可知，在桨叶20距离桨毂10的中心的距离为86.625mm时，即回弯处27为距离桨毂10的中心为螺旋桨100的半径的82.5％处，后掠部221开始自前缘25向后缘26倾斜延伸，即在桨叶20距离桨毂10的中心的距离为86.625mm时开始后掠。在多个桨叶20同时工作时，后掠部221有规律地自前缘25向后缘26倾斜延伸，能够减小由于多个桨叶20相互作用而产生的湍流及下洗气流，及并减少打到飞行器1000 的机身50上的湍流及下洗气流，减小桨叶20受到的空气阻力，进一步提高了螺旋桨100的拉力及效率，提高了飞行器1000的可操纵性，使飞行器1000更加平稳，同时，进一步减小了由于湍流及下洗气流冲击飞行器1000的机身50产生的噪音。As can be seen from Table 3, when the distance between the blade 20 and the center of the hub 10 is 86.625 mm, that is, the return bend 27 is 82.5% of the radius of the propeller 100 from the center of the hub 10, the swept portion 221 starts from the front. The rim 25 extends obliquely to the trailing edge 26, i.e., begins to sweep when the distance of the blade 20 from the center of the hub 10 is 86.625 mm. When the plurality of blades 20 are simultaneously operated, the swept portion 221 regularly extends obliquely from the leading edge 25 to the trailing edge 26, which can reduce turbulence and downwashing due to interaction of the plurality of blades 20, and reduce The turbulent flow and the lower washing airflow on the fuselage 50 of the aircraft 1000 reduce the air resistance received by the blade 20, further improve the pulling force and efficiency of the propeller 100, improve the maneuverability of the aircraft 1000, and make the aircraft 1000 more stable. At the same time, the noise generated by the turbulence and the downwash airflow impinging on the fuselage 50 of the aircraft 1000 is further reduced.
请一并参阅表4、图1及图17，本实施方式中，桨尖22沿桨叶20的展向朝吸力面24所在的一侧倾斜延伸，具体地，表4的横坐标Blade Radius(mm)表示沿桨叶20的展向桨叶20的某一位置(比如MM处)距离桨毂10中心的距离。起始处为桨毂10的中心，此时桨叶20距离桨毂10的中心的距离为0mm，终点处为桨尖22的自由端，自由端距离桨毂10的中心的距离为105mm。纵坐标Anhedral Length(mm)为上反或下反距离。其中，纵坐标Anhedral Length(mm)的正值为上反，负值为下反。Referring to Table 4, FIG. 1 and FIG. 17, in the present embodiment, the blade tip 22 extends obliquely along the direction of the blade 20 toward the side where the suction surface 24 is located. Specifically, the abscissa of the table 4 is Blade Radius ( Mm) represents the distance from the center of the hub 10 at a certain position (such as MM) of the paddle 20 of the blade 20. The starting point is the center of the hub 10, at which point the distance of the blade 20 from the center of the hub 10 is 0 mm, the end is the free end of the tip 22, and the distance of the free end from the center of the hub 10 is 105 mm. The ordinate Anhedral Length (mm) is the upper or lower inverse distance. Among them, the positive value of the ordinate Anhedral Length (mm) is the upper and the reverse, and the negative value is the lower.
表4Table 4
Figure PCTCN2018109068-appb-000004
Figure PCTCN2018109068-appb-000004
由表4可知，在桨叶20距离桨毂10的中心的距离为86.625mm时，即回弯处27距离桨毂10的中心为螺旋桨100的半径的82.5％。前缘25自回弯处27开始沿桨叶20的展向朝吸力面24所在的一侧倾斜延伸，即在桨叶20距离桨毂10的中心的距离为86.625mm时开始上反。在多个桨叶20同时工作时，前缘25有规律地自回弯处27沿桨叶20沿展向朝吸力面24所在的一侧倾斜延伸，能够减小由于多个桨叶20相互作用而产生的湍流及下洗气流，并减少打到机臂40上及飞行器1000的机身50上的湍流及下洗气流，另外，还能够额定桨叶20的升力点，使飞行器1000能自动修正飞行姿态，增加了飞行器1000的惯性稳定性，使飞行器1000飞行时更加平稳，同时，进一步减 小了由于湍流及下洗气流冲击飞行器1000的机身50产生的噪音。As can be seen from Table 4, when the distance of the blade 20 from the center of the hub 10 is 86.625 mm, that is, the return bend 27 is 82.5% of the radius of the propeller 100 from the center of the hub 10. The leading edge 25 begins to extend obliquely from the corner of the blade 27 toward the side of the suction surface 24 along the direction of the blade 20, i.e., when the distance of the blade 20 from the center of the hub 10 is 86.625 mm. When the plurality of blades 20 are simultaneously operated, the leading edge 25 is regularly inclined from the corner bend 27 along the side of the blade 20 along the direction of the suction surface 24, which can reduce the interaction due to the plurality of blades 20. The generated turbulence and under-washing airflow reduce the turbulence and downwashing airflow on the arm 40 and the fuselage 50 of the aircraft 1000. In addition, the lift point of the blade 20 can be rated to enable the aircraft 1000 to be automatically corrected. The flight attitude increases the inertia stability of the aircraft 1000, making the aircraft 1000 more stable during flight, while further reducing the noise generated by the turbulence and downwash airflow impinging on the fuselage 50 of the aircraft 1000.
本实施例中，可选地，桨叶20的螺距为3.6±0.5英寸。由此，可减小空气的阻力，提高桨叶20的拉力。其中，桨叶20的螺距可以为3.1英寸或3.6英寸或4.1英寸，或者是3.2英寸、3.3英寸、3.4英寸、3.5英寸、3.7英寸、3.8英寸、3.9英寸、4.0英寸等中的任意一个或上述任意二者之间的数值。如此，在效率不降低的情况下，增大螺旋桨100的最大拉力，降低飞行器1000失控风险，提高飞行安全。In this embodiment, optionally, the pitch of the blade 20 is 3.6 ± 0.5 inches. Thereby, the resistance of the air can be reduced and the pulling force of the blade 20 can be increased. Wherein, the pitch of the blade 20 may be 3.1 inches or 3.6 inches or 4.1 inches, or any one of 3.2 inches, 3.3 inches, 3.4 inches, 3.5 inches, 3.7 inches, 3.8 inches, 3.9 inches, 4.0 inches, etc. or the above The value between any two. In this way, in the case where the efficiency is not lowered, the maximum pulling force of the propeller 100 is increased, the risk of the aircraft 1000 being out of control is reduced, and the flight safety is improved.
综上，采用本发明上述实施例的桨叶的螺旋桨100在高原地区可以显著提高拉力，保证足够的动力冗余。同时，在一定程度上兼顾性能，增加继航距离，提高飞行器1000的飞行性能。和目前市面上已有的螺旋桨100相比，采用该桨叶的螺旋桨100在较小的功率条件下其具有更大的拉力，从而可降低电量损耗，增加续航距离。在密度降低的高海拔区域或者低海拔地区起飞重量较大的极端情况下，其可以显著提高拉力，保证足够动力同时延长续航时间，提高飞行性能。In summary, the propeller 100 using the blade of the above embodiment of the present invention can significantly increase the pulling force in the plateau region, thereby ensuring sufficient power redundancy. At the same time, the performance is balanced to a certain extent, the following distance is increased, and the flight performance of the aircraft 1000 is improved. Compared with the propeller 100 currently available on the market, the propeller 100 using the blade has a greater pulling force under a smaller power condition, thereby reducing power consumption and increasing the cruising distance. In the extreme case of high-altitude areas with reduced density or high take-off weights, it can significantly increase the pulling force, ensure sufficient power while prolonging the battery life and improving flight performance.
另外，在大部分相同频率的条件下，采用本发明上述实施例的桨叶20的螺旋桨100的响度低于现有的螺旋桨。特别是在相同的高频条件下，本实施例所提供的螺旋桨100的响度明显低于现有的螺旋桨的响度。由此，本实施例所提供的螺旋桨100能有效减小高频噪音，减轻了高频噪音引起人耳的不适感，提高了用户体验。整体低于现有的螺旋桨。由此，本实施例所提供的螺旋桨100能有效减小噪音。In addition, the propeller 100 employing the blade 20 of the above-described embodiment of the present invention has a lower loudness than the existing propeller under most of the same frequency conditions. Especially under the same high frequency conditions, the loudness of the propeller 100 provided by this embodiment is significantly lower than that of the existing propeller. Therefore, the propeller 100 provided in the embodiment can effectively reduce high frequency noise, reduce the discomfort caused by high frequency noise and improve the user experience. The overall is lower than the existing propeller. Thus, the propeller 100 provided in this embodiment can effectively reduce noise.
在某些实施方式中，螺旋桨100在距离桨毂10的中心为螺旋桨100的半径的23.8％处D1，桨叶20的攻角α1为23.40°±2.5°；及/或In certain embodiments, the propeller 100 is at a distance D1 from the center of the hub 10 that is 23.8% of the radius of the propeller 100, and the angle of attack α1 of the blade 20 is 23.40° ± 2.5°; and/or
在距离桨毂10的中心为螺旋桨100的半径的33.3％处D2，桨叶20的攻角α2为26.20°±2.5°；及/或At an angle D3 from the center of the hub 10 that is 33.3% of the radius of the propeller 100, the angle of attack α2 of the blade 20 is 26.20° ± 2.5°; and/or
在距离桨毂10的中心为螺旋桨100的半径的81.0％处D7，桨叶20的攻角α7为17.97°±2.5°；及/或At an angle D7 from the center of the hub 10 that is 81.0% of the radius of the propeller 100, the angle of attack α7 of the blade 20 is 17.97° ± 2.5°; and/or
在距离桨毂10的中心为螺旋桨100的半径的90.5％处D8，桨叶20的攻角α8为16.61°±2.5°；及/或At an angle D8 from the center of the hub 10 that is 90.5% of the radius of the propeller 100, the angle of attack α8 of the blade 20 is 16.61° ± 2.5°; and/or
在距离桨毂10的中心为螺旋桨100的半径的100％处D9，桨叶20的攻角α9为9.39°±2.5°；及/或At an angle D9 from the center of the hub 10 that is 100% of the radius of the propeller 100, the angle of attack α9 of the blade 20 is 9.39° ± 2.5°; and/or
在距离桨毂10的中心25mm处D，桨叶20的攻角α1为23.40°；及/或At an angle of 25 mm from the center of the hub 10, the angle of attack α1 of the blade 20 is 23.40°; and/or
在距离桨毂10的中心35mm处D，桨叶20的攻角α2为26.20°；及/或At an angle 35 mm from the center of the hub 10, the angle of attack α2 of the blade 20 is 26.20°; and/or
在距离桨毂10的中心45mm处D，桨叶20的攻角α3为24.60°；及/或At an angle 45 mm from the center of the hub 10, the angle of attack α3 of the blade 20 is 24.60°; and/or
在距离桨毂10的中心55mm处D，桨叶20的攻角α4为23.50°；及/或At an angle of 55 mm from the center of the hub 10, the angle of attack α4 of the blade 20 is 23.50°; and/or
在距离桨毂10的中心65mm处D，桨叶20的攻角α5为21.82°；及/或At an angle of 65 mm from the center of the hub 10, the angle of attack α5 of the blade 20 is 21.82°; and/or
在距离桨毂10的中心75mm处D，桨叶20的攻角α6为19.97°；及/或At an angle of 75 mm from the center of the hub 10, the angle of attack α6 of the blade 20 is 19.97°; and/or
在距离桨毂10的中心85mm处D，桨叶20的攻角α7为17.97°；及/或At an angle of 85 mm from the center of the hub 10, the angle of attack α7 of the blade 20 is 17.97°; and/or
在距离桨毂10的中心95mm处D，桨叶20的攻角α8为16.61°；及/或At an angle of 95 mm from the center of the hub 10, the angle of attack α8 of the blade 20 is 16.61°; and/or
在距离桨毂10的中心105mm处D，桨叶20的攻角α9为9.39°。At an angle 105 mm from the center of the hub 10, the angle of attack α9 of the blade 20 is 9.39.
此处的讨论包括但不限于以下几种方式：(1)螺旋桨100在距离桨毂10的中心为螺旋桨100的半径的23.8％处D1，桨叶20的攻角α1为23.40°±2.5°；The discussion herein includes, but is not limited to, the following ways: (1) the propeller 100 is D1 at 23.8% of the radius of the propeller 100 from the center of the hub 10, and the angle of attack α1 of the blade 20 is 23.40° ± 2.5°;
(2)螺旋桨100在距离桨毂10的中心为螺旋桨100的半径的33.3％处D2，桨叶20的攻角α2为26.20°±2.5°；(2) The propeller 100 is at a distance D3 from the center of the hub 10 at 33.3% of the radius of the propeller 100, and the angle of attack α2 of the blade 20 is 26.20° ± 2.5°;
(3)螺旋桨100在距离桨毂10的中心为螺旋桨100的半径的81.0％处D7，桨叶20的攻角α7为17.97°±2.5°；(3) The propeller 100 is at a distance of 81.0% of the radius of the propeller 100 from the center of the hub 10, D7, and the angle of attack α7 of the blade 20 is 17.97 ° ± 2.5 °;
(4)螺旋桨100在距离桨毂10的中心为螺旋桨100的半径的90.5％处D8，桨叶20的攻角α8为16.61°±2.5°；(4) The propeller 100 is at a distance of 90.5% of the radius of the propeller 100 from the center of the hub 10, D8, and the angle of attack α8 of the blade 20 is 16.61 ° ± 2.5 °;
(5)螺旋桨100在距离桨毂10的中心为螺旋桨100的半径的100％处D9，桨叶20的攻角α9为9.39°±2.5°；(5) The propeller 100 is at a distance D100 from the center of the hub 10 that is 100% of the radius of the propeller 100, and the angle of attack α9 of the blade 20 is 9.39 ° ± 2.5 °;
(6)螺旋桨100在距离桨毂10的中心25mm处D1，桨叶20的攻角α1为23.40°；(6) The propeller 100 is at a distance of 25 mm from the center of the hub 10, and the angle of attack α1 of the blade 20 is 23.40°;
(7)螺旋桨100在距离桨毂10的中心35mm处D2，桨叶20的攻角α2为26.20°；(7) The propeller 100 is at a distance of 35 mm from the center of the hub 10, and the angle of attack α2 of the blade 20 is 26.20°;
(8)螺旋桨100在距离桨毂10的中心45mm处D3，桨叶20的攻角α3为24.60°；(8) The propeller 100 is at a distance of 45 mm from the center of the hub 10, and the angle of attack α3 of the blade 20 is 24.60°;
(9)螺旋桨100在距离桨毂10的中心55mm处D4，桨叶20的攻角α4为23.50°；(9) The propeller 100 is at a distance of 55 mm from the center of the hub 10, and the angle of attack α4 of the blade 20 is 23.50°;
(10)螺旋桨100在距离桨毂10的中心65mm处D5，桨叶20的攻角α5为21.82°；(10) The propeller 100 is at a distance of 65 mm from the center of the hub 10, and the angle of attack α5 of the blade 20 is 21.82°;
(11)螺旋桨100在距离桨毂10的中心75mm处D6，桨叶20的攻角α6为19.97°；(11) The propeller 100 is at a distance of 75 mm from the center of the hub 10, and the angle of attack α6 of the blade 20 is 19.97°;
(12)螺旋桨100在距离桨毂10的中心85mm处D7，桨叶20的攻角α7为17.97°；(12) The propeller 100 is at a distance of 85 mm from the center of the hub 10, and the angle of attack α7 of the blade 20 is 17.97°;
(13)螺旋桨100在距离桨毂10的中心95mm处D8，桨叶20的攻角α8为16.61°；(13) the propeller 100 is at a distance of 95 mm from the center of the hub 10, the angle of attack α8 of the blade 20 is 16.61 °;
(14)螺旋桨100在距离桨毂10的中心105mm处D9，桨叶20的攻角α9为9.39°；(14) The propeller 100 is at a distance of 10 mm from the center of the hub 10, D9, the angle of attack α9 of the blade 20 is 9.39 °;
(15)螺旋桨100在距离桨毂10的中心为螺旋桨100的半径的23.8％处D1，桨叶20的攻角α1为23.40°±2.5°；及，在距离桨毂10的中心为螺旋桨100的半径的33.3％处D2，桨叶20的攻角α2为26.20°±2.5°；及，在距离桨毂10的中心为螺旋桨100的半径的81.0％处D7，桨叶20的攻角α7为17.97°±2.5°；及，在距离桨毂10的中心为螺旋桨100的半径的90.5％处D8，桨叶20的攻角α8为16.61°±2.5°； 及，在距离桨毂10的中心为螺旋桨100的半径的100％处D9，桨叶20的攻角α9为9.39°±2.5°；及，在距离桨毂10的中心25mm处D1，桨叶20的攻角α1为23.40°；及，在距离桨毂10的中心35mm处D2，桨叶20的攻角α2为26.20°；及，在距离桨毂10的中心45mm处D3，桨叶20的攻角α3为24.60°；及，在距离桨毂10的中心55mm处D4，桨叶20的攻角α4为23.50°；及，在距离桨毂10的中心65mm处D5，桨叶20的攻角α5为21.82°；及，在距离桨毂10的中心75mm处D6，桨叶20的攻角α6为19.97°；及，在距离桨毂10的中心85mm处D7，桨叶20的攻角α7为17.97°；及，在距离桨毂10的中心95mm处D8，桨叶20的攻角α8为16.61°；及，在距离桨毂10的中心105mm处D9，桨叶20的攻角α9为9.39°。(15) The propeller 100 is at a distance D1 from the center of the hub 10 which is 23.8% of the radius of the propeller 100, and the angle of attack α1 of the blade 20 is 23.40° ± 2.5°; and, at the center of the hub 10, the propeller 100 At 33.3% of the radius, D2, the angle of attack α2 of the blade 20 is 26.20°±2.5°; and, at the center of the hub 10, 81.0% of the radius of the propeller 100, D7, the angle of attack α7 of the blade 20 is 17.97. °±2.5°; and, at a distance of 90.5% of the radius of the propeller 100 from the center of the hub 10, D8, the angle of attack α8 of the blade 20 is 16.61° ± 2.5°; and, at the center of the hub 10 is a propeller 100% of the radius of 100, D9, the angle of attack α9 of the blade 20 is 9.39 ° ± 2.5 °; and, at a distance of 25 mm from the center of the hub 10, the angle of attack α1 of the blade 20 is 23.40 °; At an angle of 35 mm from the center of the hub 10, the angle of attack α2 of the blade 20 is 26.20°; and, at a distance of 45 mm from the center of the hub 10, the angle of attack α3 of the blade 20 is 24.60°; and, at a distance from the paddle The center angle 55 of the hub 10 is D4, the angle of attack α4 of the blade 20 is 23.50°; and, at the distance of 65 mm from the center of the hub 10, the angle of attack α5 of the blade 20 is 21.82°; and, at the distance from the hub 10 Center 75mm At D6, the angle of attack α6 of the blade 20 is 19.97°; and, at a distance of 85 mm from the center of the hub 10, the angle of attack α7 of the blade 20 is 17.97°; and, at a distance of 95 mm from the center of the hub 10, D8 The angle of attack α8 of the blade 20 is 16.61°; and, at D9, 105 mm from the center of the hub 10, the angle of attack α9 of the blade 20 is 9.39°.
在某些实施方式中，螺旋桨100在距离桨毂10的中心为螺旋桨100的半径的42.9％处D3，桨叶20的弦长L3为26.49mm±5mm；及/或In certain embodiments, the propeller 100 is D3 at a distance from the center of the hub 10 that is 42.9% of the radius of the propeller 100, and the chord length L3 of the blade 20 is 26.49 mm ± 5 mm; and/or
在距离桨毂10的中心为螺旋桨100的半径的52.4％处D4，桨叶20的弦长L4为25.16mm±5mm；及/或At a distance D4 from the center of the hub 10 that is 52.4% of the radius of the propeller 100, the chord length L4 of the blade 20 is 25.16 mm ± 5 mm; and/or
在距离桨毂10的中心为螺旋桨100的半径的61.9％处D5，桨叶20的弦长L5为23.59mm±5mm；及/或At a distance D5 from the center of the hub 10 that is 61.9% of the radius of the propeller 100, the chord length L5 of the blade 20 is 23.59 mm ± 5 mm; and/or
在距离桨毂10的中心为螺旋桨100的半径的71.4％处D6，桨叶20的弦长L6为21.69mm±5mm；及/或At a distance D6 from the center of the hub 10 that is 71.4% of the radius of the propeller 100, the chord length L6 of the blade 20 is 21.69 mm ± 5 mm; and/or
在距离桨毂10的中心45mm处D3，桨叶20的弦长L3为26.49mm；及/或At a distance D3 from the center of the hub 10, the chord length L3 of the blade 20 is 26.49 mm; and/or
在距离桨毂10的中心55mm处D4，桨叶20的弦长L4为25.16mm；及/或At a distance of 45 mm from the center of the hub 10, the chord length L4 of the blade 20 is 25.16 mm; and/or
在距离桨毂10的中心65mm处D5，桨叶20的弦长L5为23.59mm；及/或At a distance of 65 mm from the center of the hub 10, the chord length L5 of the blade 20 is 23.59 mm; and/or
在距离桨毂10的中心75mm处D6，桨叶20的弦长L6为21.69mm。At a distance D6 from the center of the hub 10, the chord length L6 of the paddle 20 is 21.69 mm.
此处的讨论包括但不限于以下几种方式：(1)螺旋桨100在距离桨毂10的中心为螺旋桨100的半径的42.9％处D3，桨叶20的弦长L3为26.49mm±5mm；The discussion herein includes but is not limited to the following ways: (1) the propeller 100 is D3 at a distance from the center of the hub 10 of 42.9% of the radius of the propeller 100, and the chord length L3 of the blade 20 is 26.49 mm ± 5 mm;
(2)螺旋桨100在距离桨毂10的中心为螺旋桨100的半径的52.4％处D4，桨叶20的弦长L4为25.16mm±5mm；(2) The propeller 100 is at a distance of 52.4% of the radius of the propeller 100 from the center of the hub 10, D4, and the chord length L4 of the blade 20 is 25.16 mm ± 5 mm;
(3)螺旋桨100在距离桨毂10的中心为螺旋桨100的半径的61.9％处D5，桨叶20的弦长L5为23.59mm±5mm；(3) The propeller 100 is at a distance of 61.9% of the radius of the propeller 100 from the center of the hub 10, D5, and the chord length L5 of the blade 20 is 23.59 mm ± 5 mm;
(4)螺旋桨100在距离桨毂10的中心为螺旋桨100的半径的71.4％处D6，桨叶20的弦长L6为21.69mm±5mm；(4) The propeller 100 is at a distance of 71.4% of the radius of the propeller 100 from the center of the hub 10, D6, and the chord length L6 of the blade 20 is 21.69 mm ± 5 mm;
(5)螺旋桨100在距离桨毂10的中心45mm处D3，桨叶20的弦长L3为26.49mm；(5) The propeller 100 is at a distance of 45 mm from the center of the hub 10, and the chord length L3 of the blade 20 is 26.49 mm;
(6)螺旋桨100在距离桨毂10的中心55mm处D4，桨叶20的弦长L4为25.16mm；(6) The propeller 100 is at a distance of 55 mm from the center of the hub 10, and the chord length L4 of the blade 20 is 25.16 mm;
(7螺旋桨100在距离桨毂10的中心65mm处D5，桨叶20的弦长L5为23.59mm；(7 propeller 100 at a distance of 65 mm from the center of the hub 10 D5, the chord length L5 of the blade 20 is 23.59 mm;
(8)螺旋桨100在距离桨毂10的中心75mm处D6，桨叶20的弦长L6为21.69mm；(8) The propeller 100 is at a distance of 75 mm from the center of the hub 10, and the chord length L6 of the blade 20 is 21.69 mm;
(9)螺旋桨100在距离桨毂10的中心为螺旋桨100的半径的42.9％处D3，桨叶20的弦长L3为26.49mm±5mm；及，在距离桨毂10的中心为螺旋桨100的半径的52.4％处D4，桨叶20的弦长L4为25.16mm±5mm；及，在距离桨毂10的中心为螺旋桨100的半径的61.9％处D5，桨叶20的弦长L5为23.59mm±5mm；及，在距离桨毂10的中心为螺旋桨100的半径的71.4％处D6，桨叶20的弦长L6为21.69mm±5mm；及，在距离桨毂10的中心45mm处D3，桨叶20的弦长L3为26.49mm；及，在距离桨毂10的中心55mm处D4，桨叶20的弦长L4为25.16mm；及，在距离桨毂10的中心65mm处D5，桨叶20的弦长L5为23.59mm；及，在距离桨毂10的中心75mm处D6，桨叶20的弦长L6为21.69mm。(9) The propeller 100 is D3 at a distance from the center of the hub 10 of 42.9% of the radius of the propeller 100, the chord length L3 of the blade 20 is 26.49 mm ± 5 mm; and, at the center of the hub 10, the radius of the propeller 100 At 52.4%, D4, the chord length L4 of the blade 20 is 25.16 mm ± 5 mm; and, at the center of the hub 10, 61.9% of the radius of the propeller 100, D5, the chord length L5 of the blade 20 is 23.59 mm ± 5mm; and, at the center of the hub 10, 71.4% of the radius of the propeller 100, D6, the chord length L6 of the blade 20 is 21.69 mm ± 5 mm; and, at a distance of 45 mm from the center of the hub 10, D3, paddle The chord length L3 of 20 is 26.49 mm; and, at a distance of 55 mm from the center of the hub 10, the chord length L4 of the blade 20 is 25.16 mm; and, at a distance of 65 mm from the center of the hub 10, D5, the blade 20 The chord length L5 is 23.59 mm; and, at a distance of 75 mm from the center of the hub 10, the chord length L6 of the paddle 20 is 21.69 mm.
在某些实施方式中，螺旋桨100在距离桨毂10的中心为螺旋桨100的半径的23.8％处D1，桨叶20的弦长L1为21.21mm±5mm；及/或In certain embodiments, the propeller 100 is at a distance D1 from the center of the hub 10 that is 23.8% of the radius of the propeller 100, and the chord length L1 of the blade 20 is 21.21 mm ± 5 mm; and/or
在距离桨毂10的中心为螺旋桨100的半径的33.3％处D2，桨叶20的弦长L2为27.38mm±5mm；及/或At a distance D3 from the center of the hub 10 that is 33.3% of the radius of the propeller 100, the chord length L2 of the blade 20 is 27.38 mm ± 5 mm; and/or
在距离桨毂10的中心为螺旋桨100的半径的81.0％处D7，桨叶20的弦长L7为19.45mm±5mm；及/或At a distance D7 from the center of the hub 10 that is 81.0% of the radius of the propeller 100, the chord length L7 of the blade 20 is 19.45 mm ± 5 mm; and/or
在距离桨毂10的中心为螺旋桨100的半径的90.5％处D8，桨叶20的弦长L8为15.78mm±5mm；及/或At a distance D8 from the center of the hub 10 that is 90.5% of the radius of the propeller 100, the chord length L8 of the blade 20 is 15.78 mm ± 5 mm; and/or
在距离桨毂10的中心为螺旋桨100的半径的100％处D9，桨叶20的弦长L9为4.94mm±2mm；及/或At a distance D10 from the center of the hub 10 that is 100% of the radius of the propeller 100, the chord length L9 of the blade 20 is 4.94 mm ± 2 mm; and/or
在距离桨毂10的中心25mm处D1，桨叶20的弦长L1为21.21mm；及/或At a distance of 25 mm from the center of the hub 10, the chord length L1 of the blade 20 is 21.21 mm; and/or
在距离桨毂10的中心35mm处D2，桨叶20的弦长L2为27.38mm；及/或At a distance of 35 mm from the center of the hub 10, the chord length L2 of the blade 20 is 27.38 mm; and/or
在距离桨毂10的中心85mm处D7，桨叶20的弦长L7为19.45mm；及/或At a distance of 85 mm from the center of the hub 10, the chord length L7 of the blade 20 is 19.45 mm; and/or
在距离桨毂10的中心95mm处D8，桨叶20的弦长L8为15.78mm；及/或At a distance of 85 mm from the center of the hub 10, the chord length L8 of the blade 20 is 15.78 mm; and/or
在距离桨毂10的中心105mm处D9，桨叶20的弦长L9为4.94mm。At a distance D10 from the center of the hub 10, the chord length L9 of the paddle 20 is 4.94 mm.
此处的讨论包括但不限于以下几种方式：(1)螺旋桨100在距离桨毂10的中心为螺旋桨100的半径的23.8％处D1，桨叶20的弦长L1为21.21mm±5mm；The discussion herein includes, but is not limited to, the following ways: (1) the propeller 100 is D1 at a distance from the center of the hub 10 of 23.8% of the radius of the propeller 100, and the chord length L1 of the blade 20 is 21.21 mm ± 5 mm;
(2)螺旋桨100在距离桨毂10的中心为螺旋桨100的半径的33.3％处D2，桨叶 20的弦长L2为27.38mm±5mm；(2) The propeller 100 is at a distance of 33.3% of the radius of the propeller 100 from the center of the hub 10, and the chord length L2 of the blade 20 is 27.38 mm ± 5 mm;
(3)螺旋桨100在距离桨毂10的中心为螺旋桨100的半径的81.0％处D7，桨叶20的弦长L7为19.45mm±5mm；(3) The propeller 100 is at a distance of 81.0% of the radius of the propeller 100 from the center of the hub 10, D7, and the chord length L7 of the blade 20 is 19.45 mm ± 5 mm;
(4)螺旋桨100在距离桨毂10的中心为螺旋桨100的半径的90.5％处D8，桨叶20的弦长L8为15.78mm±5mm；(4) The propeller 100 is at a distance of 90.5% of the radius of the propeller 100 from the center of the hub 10, D8, and the chord length L8 of the blade 20 is 15.78 mm ± 5 mm;
(5)螺旋桨100在距离桨毂10的中心为螺旋桨100的半径的100％处D9，桨叶20的弦长L9为4.94mm±2mm；(5) the propeller 100 is at a distance from the center of the hub 10 at 100% of the radius of the propeller 100, D9, the chord length L9 of the blade 20 is 4.94 mm ± 2 mm;
(6)螺旋桨100在距离桨毂10的中心25mm处D1，桨叶20的弦长L1为21.21mm；(6) The propeller 100 is at a distance of 25 mm from the center of the hub 10, and the chord length L1 of the blade 20 is 21.21 mm;
(7)螺旋桨100在距离桨毂10的中心35mm处D2，桨叶20的弦长L2为27.38mm；(7) The propeller 100 is at a distance of 35 mm from the center of the hub 10, and the chord length L2 of the blade 20 is 27.38 mm;
(8)螺旋桨100在距离桨毂10的中心85mm处D7，桨叶20的弦长L7为19.45mm；(8) The propeller 100 is at a distance of 85 mm from the center of the hub 10, and the chord length L7 of the blade 20 is 19.45 mm;
(9)螺旋桨100在距离桨毂10的中心95mm处D8，桨叶20的弦长L8为15.78mm；(9) The propeller 100 is at a distance of 85 mm from the center of the hub 10, and the chord length L8 of the blade 20 is 15.78 mm;
(10)螺旋桨100在距离桨毂10的中心105mm处D9，桨叶20的弦长L9为4.94mm；(10) The propeller 100 is at a distance of 10 mm from the center of the hub 10, D9, the chord length L9 of the blade 20 is 4.94 mm;
(11)螺旋桨100在距离桨毂10的中心为螺旋桨100的半径的23.8％处D1，桨叶20的弦长L1为21.21mm±5mm；及，在距离桨毂10的中心为螺旋桨100的半径的33.3％处D2，桨叶20的弦长L2为27.38mm±5mm；及，在距离桨毂10的中心为螺旋桨100的半径的81.0％处D7，桨叶20的弦长L7为19.45mm±5mm；及，在距离桨毂10的中心为螺旋桨100的半径的90.5％处D8，桨叶20的弦长L8为15.78mm±5mm；及，在距离桨毂10的中心为螺旋桨100的半径的100％处D9，桨叶20的弦长L9为4.94mm±2mm；及，在距离桨毂10的中心25mm处D1，桨叶20的弦长L1为21.21mm；及，在距离桨毂10的中心35mm处D2，桨叶20的弦长L2为27.38mm；及，在距离桨毂10的中心85mm处D7，桨叶20的弦长L7为19.45mm；及，在距离桨毂10的中心95mm处D8，桨叶20的弦长L8为15.78mm；及，在距离桨毂10的中心105mm处D9，桨叶20的弦长L9为4.94mm。(11) The propeller 100 is D1 at a distance from the center of the hub 10 of 23.8% of the radius of the propeller 100, and the chord length L1 of the blade 20 is 21.21 mm ± 5 mm; and, at the center of the hub 10, the radius of the propeller 100 At 33.3%, D2, the chord length L2 of the blade 20 is 27.38 mm ± 5 mm; and, at the center of the hub 10, 81.0% of the radius of the propeller 100, D7, the chord length L7 of the blade 20 is 19.45 mm ± 5mm; and, at a distance of 90.5% of the radius of the propeller 100 from the center of the hub 10, D8, the chord length L8 of the blade 20 is 15.78 mm ± 5 mm; and, at the center of the hub 10, the radius of the propeller 100 At 100%, D9, the chord length L9 of the blade 20 is 4.94 mm ± 2 mm; and, at a distance of 25 mm from the center of the hub 10, the chord length L1 of the blade 20 is 21.21 mm; and, at a distance from the hub 10. At a center 35 mm, D2, the chord length L2 of the blade 20 is 27.38 mm; and, at a distance of 85 mm from the center of the hub 10, the chord length L7 of the blade 20 is 19.45 mm; and, at a distance of 95 mm from the center of the hub 10. At D8, the chord length L8 of the paddle 20 is 15.78 mm; and, at D9, 105 mm from the center of the hub 10, the chord length L9 of the paddle 20 is 4.94 mm.
请参见图18，本发明实施例提供一种动力组件200，包括驱动件30和本发明任意实施例的螺旋桨100，螺旋桨100通过桨毂10与驱动件30连接。动力组件200包括至少两个机臂40。至少两个机臂40连接在螺旋桨100的中心位置。驱动件30设置在机臂40上。其中，螺旋桨100的具体结构与前述实施例相同，此处不再赘述。即如上的实施例和实施方式中关于螺旋桨100的描述同样适用于本发明实施例提供的动力组件200。Referring to FIG. 18, an embodiment of the present invention provides a power assembly 200 including a drive member 30 and a propeller 100 of any embodiment of the present invention. The propeller 100 is coupled to the drive member 30 via a hub 10. Power assembly 200 includes at least two arms 40. At least two arms 40 are coupled to a central position of the propeller 100. The drive member 30 is disposed on the arm 40. The specific structure of the propeller 100 is the same as that of the foregoing embodiment, and details are not described herein again. That is, the description of the propeller 100 in the above embodiments and embodiments is equally applicable to the power assembly 200 provided by the embodiment of the present invention.
在本发明的动力组件200中，由于在距离桨毂10的中心为螺旋桨100的半径的42.9％处D3，桨叶20的攻角α3为24.60°±2.5°；在距离桨毂10的中心为螺旋桨100的半径的52.4％处D4，桨叶20的攻角α4为23.50°±2.5°；在距离桨毂10的中心为螺旋桨100的半径的61.9％处D5，桨叶20的攻角α5为21.82°±2.5°；在距离桨毂10的中心为螺旋桨100的半径的71.4％处D6，桨叶20的攻角α6为19.97°±2.5°。因此，采用桨叶20的动力组件200能够减少空气阻力，提高拉力和效率，增加飞行器1000的继航距离以提高飞行器1000的飞行性能，同时还在效率不降低的情况下，增大飞行器1000的最大拉力，降低了飞行器1000失控风险，提高飞行安全，再者，减少了桨叶20在工作时产生的噪声，使得飞行器1000在悬停时更安静，提高了用户体验。In the power assembly 200 of the present invention, since the angle D3 at 42.9% of the radius of the propeller 100 from the center of the hub 10, the angle of attack α3 of the blade 20 is 24.60° ± 2.5°; at the center of the hub 10 At 52.4% of the radius of the propeller 100, D4, the angle of attack α4 of the blade 20 is 23.50°±2.5°; at the center of the hub 10, 61.9% of the radius of the propeller 100, D5, the angle of attack α5 of the blade 20 is 21.82 ° ± 2.5 °; at the center of the hub 10 is 71.4% of the radius of the propeller 100 D6, the angle of attack α6 of the blade 20 is 19.97 ° ± 2.5 °. Therefore, the power assembly 200 employing the blade 20 can reduce the air resistance, increase the pulling force and efficiency, increase the relay distance of the aircraft 1000 to improve the flight performance of the aircraft 1000, and increase the aircraft 1000 while the efficiency is not lowered. The maximum pulling force reduces the risk of loss of control of the aircraft 1000, improves flight safety, and further reduces the noise generated by the blade 20 during operation, making the aircraft 1000 quieter when hovering and improving the user experience.
本实施例中，可选地，驱动件30为电机，电机的KV值为360至810转/(分钟·伏特)。由此，能够保证动力组件的动力性能。In this embodiment, optionally, the driving member 30 is a motor, and the KV value of the motor is 360 to 810 rpm / (minute volt). Thereby, the dynamic performance of the power unit can be ensured.
请再次参见图18，本发明实施例提供一种飞行器1000，包括机身50和本发明任意实施例的动力组件200，动力组件200与机身50连接。动力组件200的多个机臂40与机身50连接以将动力组件200安装在机身50上。其中动力组件200的具体结构与前述实施例相同，此处不再赘述。即如上的实施例和实施方式中关于螺旋桨100的描述同样适用于本发明实施例提供的飞行器1000。Referring again to FIG. 18, an embodiment of the present invention provides an aircraft 1000 including a fuselage 50 and a power assembly 200 of any of the embodiments of the present invention. The power assembly 200 is coupled to the fuselage 50. A plurality of arms 40 of the power assembly 200 are coupled to the body 50 to mount the power assembly 200 on the body 50. The specific structure of the power module 200 is the same as that of the foregoing embodiment, and details are not described herein again. That is, the description of the propeller 100 in the above embodiments and embodiments is equally applicable to the aircraft 1000 provided by the embodiment of the present invention.
本实施例中，可选地，飞行器1000包括多个动力组件200，多个动力组件200的转动方向不同。In this embodiment, optionally, the aircraft 1000 includes a plurality of power components 200, and the plurality of power components 200 have different rotation directions.
本实施例中，可选地，飞行器1000为多旋翼飞行器，例如为四旋翼无人飞行器。In this embodiment, optionally, the aircraft 1000 is a multi-rotor aircraft, such as a quadrotor unmanned aerial vehicle.
本实施例中，由于在距离桨毂10的中心为螺旋桨100的半径的42.9％处D3，桨叶20的攻角α3为24.60°±2.5°；在距离桨毂10的中心为螺旋桨100的半径的52.4％处D4，桨叶20的攻角α4为23.50°±2.5°；在距离桨毂10的中心为螺旋桨100的半径的61.9％处D5，桨叶20的攻角α5为21.82°±2.5°；在距离桨毂10的中心为螺旋桨100的半径的71.4％处D6，桨叶20的攻角α6为19.97°±2.5°；因此，采用桨叶20的螺旋桨100能够减少空气阻力，提高拉力和效率，增加飞行器1000的继航距离以提高飞行器1000的飞行性能，同时还在效率不降低的情况下，增大飞行器1000的最大拉力，降低了飞行器1000失控风险，提高飞行安全，再者，减少了桨叶20在工作时产生的噪声，使得飞行器1000在悬停时更安静，提高了用户体验。In the present embodiment, since D3 is 42.9% of the radius of the propeller 100 from the center of the hub 10, the angle of attack α3 of the blade 20 is 24.60° ± 2.5°; at the center of the hub 10 is the radius of the propeller 100 At 52.4%, D4, the angle of attack α4 of the blade 20 is 23.50°±2.5°; at the center of the hub 10, 61.9% of the radius of the propeller 100, D5, the angle of attack α5 of the blade 20 is 21.82°±2.5 °; at the center of the hub 10, 71.4% of the radius of the propeller 100, D6, the angle of attack α6 of the blade 20 is 19.97 ° ± 2.5 °; therefore, the propeller 100 using the blade 20 can reduce air resistance and increase the pulling force And efficiency, increasing the flight distance of the aircraft 1000 to improve the flight performance of the aircraft 1000, while also increasing the maximum pulling force of the aircraft 1000 without reducing the efficiency, reducing the risk of loss of the aircraft 1000, improving flight safety, and, The noise generated by the blade 20 during operation is reduced, making the aircraft 1000 quieter when hovering, improving the user experience.
以上仅是本发明的较佳实施例而已，并非对本发明做任何形式上的限制，虽然本 发明已以较佳实施例揭露如上，然而并非用以限定本发明，任何熟悉本专业的技术人员，在不脱离本发明技术方案的范围内，当可利用上述揭示的技术内容做出些许更动或修饰为等同变化的等效实施例，但凡是未脱离本发明技术方案的内容，依据本发明的技术实质对以上实施例所作的任何简单修改、等同变化与修饰，均仍属于本发明技术方案的范围内。The above is only a preferred embodiment of the present invention, and is not intended to limit the scope of the present invention. The present invention has been described above by way of a preferred embodiment, but is not intended to limit the invention, and any person skilled in the art, Equivalent embodiments that may be modified or modified to equivalent variations may be made without departing from the technical scope of the present invention, without departing from the scope of the present invention. It is still within the scope of the technical solution of the present invention to make any simple modifications, equivalent changes and modifications to the above embodiments.
本专利文件披露的内容包含受版权保护的材料。该版权为版权所有人所有。版权所有人不反对任何人复制专利与商标局的官方记录和档案中所存在的该专利文件或者该专利披露。The disclosure of this patent document contains material that is subject to copyright protection. This copyright is the property of the copyright holder. The copyright owner has no objection to the reproduction of the patent document or the patent disclosure in the official records and files of the Patent and Trademark Office.

Claims (27)

  1. 一种螺旋桨，包括：桨毂和桨叶，所述桨叶连接在所述桨毂上，其特征在于：A propeller includes: a hub and a blade, the blade being coupled to the hub, wherein:
    在距离所述桨毂的中心为所述螺旋桨的半径的42.9％处，所述桨叶的攻角为24.60°±2.5°；The angle of attack of the blade is 24.60 ° ± 2.5 ° at a distance of 42.9% of the radius of the propeller from the center of the hub;
    在距离所述桨毂的中心为所述螺旋桨的半径的52.4％处，所述桨叶的攻角为23.50°±2.5°；The angle of attack of the blade is 23.50 ° ± 2.5 ° at a distance of 52.4% of the radius of the propeller from the center of the hub;
    在距离所述桨毂的中心为所述螺旋桨的半径的61.9％处，所述桨叶的攻角为21.82°±2.5°；The angle of attack of the blade is 21.82 ° ± 2.5 ° at a distance of 61.9% of the radius of the propeller from the center of the hub;
    在距离所述桨毂的中心为所述螺旋桨的半径的71.4％处，所述桨叶的攻角为19.97°±2.5°。At an angle of 71.4% of the radius of the propeller from the center of the hub, the blade has an angle of attack of 19.97 ° ± 2.5 °.
  2. 根据权利要求1所述的螺旋桨，其特征在于：A propeller according to claim 1 wherein:
    在距离所述桨毂的中心为所述螺旋桨的半径的23.8％处，所述桨叶的攻角为23.40°±2.5°；及/或The angle of attack of the blade is 23.40° ± 2.5° at 23.8% of the radius of the propeller from the center of the hub; and/or
    在距离所述桨毂的中心为所述螺旋桨的半径的33.3％处，所述桨叶的攻角为26.20°±2.5°；及/或At an angle of 33.3% of the radius of the propeller from the center of the hub, the angle of attack of the blade is 26.20° ± 2.5°; and/or
    在距离所述桨毂的中心为所述螺旋桨的半径的81.0％处，所述桨叶的攻角为17.97°±2.5°；及/或At an angle of 81.0% of the radius of the propeller from the center of the hub, the angle of attack of the blade is 17.97° ± 2.5°; and/or
    在距离所述桨毂的中心为所述螺旋桨的半径的90.5％处，所述桨叶的攻角为16.61°±2.5°；及/或At an angle of 90.5% of the radius of the propeller from the center of the hub, the angle of attack of the blade is 16.61° ± 2.5°; and/or
    在距离所述桨毂的中心为所述螺旋桨的半径的100％处，所述桨叶的攻角为9.39°±2.5°；及/或The angle of attack of the blade is 9.39 ° ± 2.5 ° at a distance of 100% of the radius of the propeller from the center of the hub; and/or
    在距离所述桨毂的中心25mm处，所述桨叶的攻角为23.40°；及/或The blade has an angle of attack of 23.40° at a distance of 25 mm from the center of the hub; and/or
    在距离所述桨毂的中心35mm处，所述桨叶的攻角为26.20°；及/或The blade has an angle of attack of 26.20° at a distance of 35 mm from the center of the hub; and/or
    在距离所述桨毂的中心45mm处，所述桨叶的攻角为24.60°；及/或The blade has an angle of attack of 24.60° at a distance of 45 mm from the center of the hub; and/or
    在距离所述桨毂的中心55mm处，所述桨叶的攻角为23.50°；及/或At 55 mm from the center of the hub, the blade has an angle of attack of 23.50°; and/or
    在距离所述桨毂的中心65mm处，所述桨叶的攻角为21.82°；及/或The blade has an angle of attack of 21.82° at a distance of 65 mm from the center of the hub; and/or
    在距离所述桨毂的中心75mm处，所述桨叶的攻角为19.97°；及/或The blade has an angle of attack of 19.97° at a distance of 75 mm from the center of the hub; and/or
    在距离所述桨毂的中心85mm处，所述桨叶的攻角为17.97°；及/或The blade has an angle of attack of 17.97° at a distance of 85 mm from the center of the hub; and/or
    在距离所述桨毂的中心95mm处，所述桨叶的攻角为16.61°；及/或The blade has an angle of attack of 16.61° at a distance of 95 mm from the center of the hub; and/or
    在距离所述桨毂的中心105mm处，所述桨叶的攻角为9.39°。At an angle of 105 mm from the center of the hub, the blade has an angle of attack of 9.39.
  3. 根据权利要求1所述的螺旋桨，其特征在于：A propeller according to claim 1 wherein:
    在距离所述桨毂的中心为所述螺旋桨的半径的42.9％处，所述桨叶的弦长为26.49mm±5mm；及/或The chord length of the blade is 26.49 mm ± 5 mm at a distance of 42.9% of the radius of the propeller from the center of the hub; and/or
    在距离所述桨毂的中心为所述螺旋桨的半径的52.4％处，所述桨叶的弦长为25.16mm±5mm；及/或The chord length of the blade is 25.16 mm ± 5 mm at a distance of 52.4% of the radius of the propeller from the center of the hub; and/or
    在距离所述桨毂的中心为所述螺旋桨的半径的61.9％处，所述桨叶的弦长为23.59mm±5mm；及/或The chord length of the blade is 23.59 mm ± 5 mm at a distance of 61.9% of the radius of the propeller from the center of the hub; and/or
    在距离所述桨毂的中心为所述螺旋桨的半径的71.4％处，所述桨叶的弦长为21.69mm±5mm；及/或The chord length of the blade is 21.69 mm ± 5 mm at a distance of 71.4% of the radius of the propeller from the center of the hub; and/or
    在距离所述桨毂的中心45mm处，所述桨叶的弦长为26.49mm；及/或The chord length of the blade is 26.49 mm at a distance of 45 mm from the center of the hub; and/or
    在距离所述桨毂的中心55mm处，所述桨叶的弦长为25.16mm；及/或The chord length of the blade is 25.16 mm at a distance of 55 mm from the center of the hub; and/or
    在距离所述桨毂的中心65mm处，所述桨叶的弦长为23.59mm；及/或The chord length of the blade is 23.59 mm at a distance of 65 mm from the center of the hub; and/or
    在距离所述桨毂的中心75mm处，所述桨叶的弦长为21.69mm。At a distance of 75 mm from the center of the hub, the blade has a chord length of 21.69 mm.
  4. 根据权利要求3所述的螺旋桨，其特征在于：A propeller according to claim 3, wherein:
    在距离所述桨毂的中心为所述螺旋桨的半径的23.8％处，所述桨叶的弦长为21.21mm±5mm；及/或The chord length of the blade is 21.21 mm ± 5 mm at 23.8% of the radius of the propeller from the center of the hub; and/or
    在距离所述桨毂的中心为所述螺旋桨的半径的33.3％处，所述桨叶的弦长为27.38mm±5mm；及/或The chord length of the blade is 27.38 mm ± 5 mm at a distance of 33.3% of the radius of the propeller from the center of the hub; and/or
    在距离所述桨毂的中心为所述螺旋桨的半径的81.0％处，所述桨叶的弦长为19.45mm±5mm；及/或The chord length of the blade is 19.45 mm ± 5 mm at a distance of 81.0% of the radius of the propeller from the center of the hub; and/or
    在距离所述桨毂的中心为所述螺旋桨的半径的90.5％处，所述桨叶的弦长为15.78mm±5mm；及/或The chord length of the blade is 15.78 mm ± 5 mm at a distance of 90.5% of the radius of the propeller from the center of the hub; and/or
    在距离所述桨毂的中心为所述螺旋桨的半径的100％处，所述桨叶的弦长为4.94mm±2mm；及/或The chord length of the blade is 4.94 mm ± 2 mm at a distance of 100% of the radius of the propeller from the center of the hub; and/or
    在距离所述桨毂的中心25mm处，所述桨叶的弦长为21.21mm；及/或The chord length of the blade is 21.21 mm at a distance of 25 mm from the center of the hub; and/or
    在距离所述桨毂的中心35mm处，所述桨叶的弦长为27.38mm；及/或The chord length of the blade is 27.38 mm at a distance of 35 mm from the center of the hub; and/or
    在距离所述桨毂的中心85mm处，所述桨叶的弦长为19.45mm；及/或The chord length of the blade is 19.45 mm at a distance of 85 mm from the center of the hub; and/or
    在距离所述桨毂的中心95mm处，所述桨叶的弦长为15.78mm；及/或The chord length of the blade is 15.78 mm at a distance of 95 mm from the center of the hub; and/or
    在距离所述桨毂的中心105mm处，所述桨叶的弦长为4.94mm。At a distance of 105 mm from the center of the hub, the blade has a chord length of 4.94 mm.
  5. 根据权利要求1所述的螺旋桨，其特征在于：A propeller according to claim 1 wherein:
    所述螺旋桨的直径为210mm±21mm；及/或The diameter of the propeller is 210 mm ± 21 mm; and / or
    所述桨叶的螺距为3.6±0.5英寸。The pitch of the paddle is 3.6 ± 0.5 inches.
  6. 根据权利要求1至5中任意一项所述的螺旋桨，其特征在于：A propeller according to any one of claims 1 to 5, characterized in that:
    所述桨叶包括桨根、背离所述桨根的桨尖、相背的压力面及吸力面、连接于所述压力面及所述吸力面一侧边的前缘、连接于所述压力面及所述吸力面另一侧边的后缘、及形成于所述桨尖的后掠部；The blade includes a blade root, a blade tip facing away from the blade root, opposite pressure surfaces and a suction surface, a leading edge connected to the pressure surface and the one side of the suction surface, and is connected to the pressure surface And a trailing edge of the other side of the suction surface and a swept portion formed on the tip of the blade;
    所述后掠部自所述前缘向所述后缘倾斜延伸，所述桨尖沿所述桨叶展向的方向朝所述吸力面所在的一侧倾斜延伸。The swept portion extends obliquely from the leading edge toward the trailing edge, and the tip of the blade extends obliquely toward a side of the suction surface along a direction in which the blade extends.
  7. 根据权利要求6所述的螺旋桨，其特征在于，所述桨叶在所述桨尖的位置形成回弯处，所述前缘自所述回弯处开始沿所述桨叶的展向朝所述吸力面所在的一侧倾斜延伸，所述后掠部自所述回弯处从所述前缘向所述后缘倾斜延伸，所述回弯处距离所述桨毂的中心为所述的半径的82.5％。The propeller according to claim 6, wherein said blade forms a back bend at a position of said tip, said leading edge starting from said return bend along said blade direction One side of the suction surface is obliquely extended, and the swept portion extends obliquely from the leading edge to the trailing edge from the back bend, and the center of the back bend is from the center of the hub 82.5% of the radius.
  8. 根据权利要求6所述的螺旋桨，其特征在于，所述前缘外凸形成有靠近所述桨根的呈曲面状的前缘拱起部，所述后缘外凸形成有靠近所述桨根的呈曲面状的后缘拱起部；及/或The propeller according to claim 6, wherein said leading edge is convexly formed with a curved leading edge bulging portion adjacent said paddle, said trailing edge being convexly formed adjacent to said paddle root a curved trailing edge arch; and/or
    所述桨叶为至少两个，至少两个所述桨叶连接在所述桨毂上并关于所述桨毂的中心呈中心对称；及/或The blades are at least two, at least two of the blades are coupled to the hub and are centrally symmetric about a center of the hub; and/or
    所述桨叶具有穿过所述桨毂的中心的中轴线，所述前缘具有平行于所述中轴线的前缘切线，所述后缘具有平行于所述中轴线的后缘切线，所述后掠部位于所述前缘切线与所述后缘切线之间；及/或The blade has a central axis passing through a 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 swept portion is located between the leading edge tangent and the trailing edge tangent; and/or
    所述吸力面和所述压力面均为曲面。The suction surface and the pressure surface are both curved surfaces.
  9. 一种动力组件，包括驱动件和螺旋桨，其特征在于，所述螺旋桨，包括桨毂和桨叶，所述桨叶连接在所述桨毂上，其特征在于：A power assembly includes a drive member and a propeller, wherein the propeller includes a hub and a blade, the blade being coupled to the hub, wherein:
    在距离所述桨毂的中心为所述螺旋桨的半径的42.9％处，所述桨叶的攻角为24.60°±2.5°；The angle of attack of the blade is 24.60 ° ± 2.5 ° at a distance of 42.9% of the radius of the propeller from the center of the hub;
    在距离所述桨毂的中心为所述螺旋桨的半径的52.4％处，所述桨叶的攻角为23.50°±2.5°；The angle of attack of the blade is 23.50 ° ± 2.5 ° at a distance of 52.4% of the radius of the propeller from the center of the hub;
    在距离所述桨毂的中心为所述螺旋桨的半径的61.9％处，所述桨叶的攻角为21.82°±2.5°；The angle of attack of the blade is 21.82 ° ± 2.5 ° at a distance of 61.9% of the radius of the propeller from the center of the hub;
    在距离所述桨毂的中心为所述螺旋桨的半径的71.4％处，所述桨叶的攻角为19.97°±2.5°；The angle of attack of the blade is 19.97 ° ± 2.5 ° at a distance of 71.4% of the radius of the propeller from the center of the hub;
    所述螺旋桨通过所述桨毂与所述驱动件连接。The propeller is coupled to the drive member through the hub.
  10. 根据权利要求9所述的动力组件，其特征在于：The power assembly of claim 9 wherein:
    在距离所述桨毂的中心为所述螺旋桨的半径的23.8％处，所述桨叶的攻角为23.40°±2.5°；及/或The angle of attack of the blade is 23.40° ± 2.5° at 23.8% of the radius of the propeller from the center of the hub; and/or
    在距离所述桨毂的中心为所述螺旋桨的半径的33.3％处，所述桨叶的攻角为26.20°±2.5°；及/或At an angle of 33.3% of the radius of the propeller from the center of the hub, the angle of attack of the blade is 26.20° ± 2.5°; and/or
    在距离所述桨毂的中心为所述螺旋桨的半径的81.0％处，所述桨叶的攻角为17.97°±2.5°；及/或At an angle of 81.0% of the radius of the propeller from the center of the hub, the angle of attack of the blade is 17.97° ± 2.5°; and/or
    在距离所述桨毂的中心为所述螺旋桨的半径的90.5％处，所述桨叶的攻角为16.61°±2.5°；及/或At an angle of 90.5% of the radius of the propeller from the center of the hub, the angle of attack of the blade is 16.61° ± 2.5°; and/or
    在距离所述桨毂的中心为所述螺旋桨的半径的100％处，所述桨叶的攻角为9.39°±2.5°；及/或The angle of attack of the blade is 9.39 ° ± 2.5 ° at a distance of 100% of the radius of the propeller from the center of the hub; and/or
    在距离所述桨毂的中心25mm处，所述桨叶的攻角为23.40°；及/或The blade has an angle of attack of 23.40° at a distance of 25 mm from the center of the hub; and/or
    在距离所述桨毂的中心35mm处，所述桨叶的攻角为26.20°；及/或The blade has an angle of attack of 26.20° at a distance of 35 mm from the center of the hub; and/or
    在距离所述桨毂的中心45mm处，所述桨叶的攻角为24.60°；及/或The blade has an angle of attack of 24.60° at a distance of 45 mm from the center of the hub; and/or
    在距离所述桨毂的中心55mm处，所述桨叶的攻角为23.50°；及/或At 55 mm from the center of the hub, the blade has an angle of attack of 23.50°; and/or
    在距离所述桨毂的中心65mm处，所述桨叶的攻角为21.82°；及/或The blade has an angle of attack of 21.82° at a distance of 65 mm from the center of the hub; and/or
    在距离所述桨毂的中心75mm处，所述桨叶的攻角为19.97°；及/或The blade has an angle of attack of 19.97° at a distance of 75 mm from the center of the hub; and/or
    在距离所述桨毂的中心85mm处，所述桨叶的攻角为17.97°；及/或The blade has an angle of attack of 17.97° at a distance of 85 mm from the center of the hub; and/or
    在距离所述桨毂的中心95mm处，所述桨叶的攻角为16.61°；及/或The blade has an angle of attack of 16.61° at a distance of 95 mm from the center of the hub; and/or
    在距离所述桨毂的中心105mm处，所述桨叶的攻角为9.39°。At an angle of 105 mm from the center of the hub, the blade has an angle of attack of 9.39.
  11. 根据权利要求9所述的动力组件，其特征在于：The power assembly of claim 9 wherein:
    在距离所述桨毂的中心为所述螺旋桨的半径的42.9％处，所述桨叶的弦长为26.49mm±5mm；及/或The chord length of the blade is 26.49 mm ± 5 mm at a distance of 42.9% of the radius of the propeller from the center of the hub; and/or
    在距离所述桨毂的中心为所述螺旋桨的半径的52.4％处，所述桨叶的弦长为25.16mm±5mm；及/或The chord length of the blade is 25.16 mm ± 5 mm at a distance of 52.4% of the radius of the propeller from the center of the hub; and/or
    在距离所述桨毂的中心为所述螺旋桨的半径的61.9％处，所述桨叶的弦长为23.59mm±5mm；及/或The chord length of the blade is 23.59 mm ± 5 mm at a distance of 61.9% of the radius of the propeller from the center of the hub; and/or
    在距离所述桨毂的中心为所述螺旋桨的半径的71.4％处，所述桨叶的弦长为21.69mm±5mm；及/或The chord length of the blade is 21.69 mm ± 5 mm at a distance of 71.4% of the radius of the propeller from the center of the hub; and/or
    在距离所述桨毂的中心45mm处，所述桨叶的弦长为26.49mm；及/或The chord length of the blade is 26.49 mm at a distance of 45 mm from the center of the hub; and/or
    在距离所述桨毂的中心55mm处，所述桨叶的弦长为25.16mm；及/或The chord length of the blade is 25.16 mm at a distance of 55 mm from the center of the hub; and/or
    在距离所述桨毂的中心65mm处，所述桨叶的弦长为23.59mm；及/或The chord length of the blade is 23.59 mm at a distance of 65 mm from the center of the hub; and/or
    在距离所述桨毂的中心75mm处，所述桨叶的弦长为21.69mm。At a distance of 75 mm from the center of the hub, the blade has a chord length of 21.69 mm.
  12. 根据权利要求11所述的螺旋桨，其特征在于：A propeller according to claim 11 wherein:
    在距离所述桨毂的中心为所述螺旋桨的半径的23.8％处，所述桨叶的弦长为21.21mm±5mm；及/或The chord length of the blade is 21.21 mm ± 5 mm at 23.8% of the radius of the propeller from the center of the hub; and/or
    在距离所述桨毂的中心为所述螺旋桨的半径的33.3％处，所述桨叶的弦长为27.38mm±5mm；及/或The chord length of the blade is 27.38 mm ± 5 mm at a distance of 33.3% of the radius of the propeller from the center of the hub; and/or
    在距离所述桨毂的中心为所述螺旋桨的半径的81.0％处，所述桨叶的弦长为19.45mm±5mm；及/或The chord length of the blade is 19.45 mm ± 5 mm at a distance of 81.0% of the radius of the propeller from the center of the hub; and/or
    在距离所述桨毂的中心为所述螺旋桨的半径的90.5％处，所述桨叶的弦长为15.78mm±5mm；及/或The chord length of the blade is 15.78 mm ± 5 mm at a distance of 90.5% of the radius of the propeller from the center of the hub; and/or
    在距离所述桨毂的中心为所述螺旋桨的半径的100％处，所述桨叶的弦长为4.94mm±2mm；及/或The chord length of the blade is 4.94 mm ± 2 mm at a distance of 100% of the radius of the propeller from the center of the hub; and/or
    在距离所述桨毂的中心25mm处，所述桨叶的弦长为21.21mm；及/或The chord length of the blade is 21.21 mm at a distance of 25 mm from the center of the hub; and/or
    在距离所述桨毂的中心35mm处，所述桨叶的弦长为27.38mm；及/或The chord length of the blade is 27.38 mm at a distance of 35 mm from the center of the hub; and/or
    在距离所述桨毂的中心85mm处，所述桨叶的弦长为19.45mm；及/或The chord length of the blade is 19.45 mm at a distance of 85 mm from the center of the hub; and/or
    在距离所述桨毂的中心95mm处，所述桨叶的弦长为15.78mm；及/或The chord length of the blade is 15.78 mm at a distance of 95 mm from the center of the hub; and/or
    在距离所述桨毂的中心105mm处，所述桨叶的弦长为4.94mm。At a distance of 105 mm from the center of the hub, the blade has a chord length of 4.94 mm.
  13. 根据权利要求9所述的动力组件，其特征在于：The power assembly of claim 9 wherein:
    所述螺旋桨的直径为210mm±21mm；及/或The diameter of the propeller is 210 mm ± 21 mm; and / or
    所述桨叶的螺距为3.6±0.5英寸。The pitch of the paddle is 3.6 ± 0.5 inches.
  14. 根据权利要求9至14中任意一项所述的动力组件，其特征在于：A power assembly according to any one of claims 9 to 14, wherein:
    所述桨叶包括桨根、背离所述桨根的桨尖、相背的压力面及吸力面、连接于所述压力面及所述吸力面一侧边的前缘、连接于所述压力面及所述吸力面另一侧边的后缘、及形成于所述桨尖的后掠部；The blade includes a blade root, a blade tip facing away from the blade root, opposite pressure surfaces and a suction surface, a leading edge connected to the pressure surface and the one side of the suction surface, and is connected to the pressure surface And a trailing edge of the other side of the suction surface and a swept portion formed on the tip of the blade;
    所述后掠部自所述前缘向所述后缘倾斜延伸，所述桨尖沿所述桨叶展向的方向朝所 述吸力面所在的一侧倾斜延伸。The swept portion extends obliquely from the leading edge toward the trailing edge, and the tip of the blade extends obliquely toward a side of the suction surface along a direction in which the blade extends.
  15. 根据权利要求14所述的动力组件，其特征在于，所述桨叶在所述桨尖的位置形成回弯处，所述前缘自所述回弯处开始沿所述桨叶的展向朝所述吸力面所在的一侧倾斜延伸，所述后掠部自所述回弯处从所述前缘向所述后缘倾斜延伸，所述回弯处距离所述桨毂的中心为所述的半径的82.5％。A power assembly according to claim 14 wherein said blade forms a back bend at the position of said tip, said leading edge starting from said return bend along said blade a side of the suction surface extending obliquely, the swept portion extending obliquely from the leading edge to the trailing edge from the back bend, the center of the back bend being the center of the hub The radius of 82.5%.
  16. 根据权利要求14所述的动力组件，其特征在于，所述前缘外凸形成有靠近所述桨根的呈曲面状的前缘拱起部，所述后缘外凸形成有靠近所述桨根的呈曲面状的后缘拱起部；及/或The power assembly according to claim 14, wherein said leading edge is convexly formed with a curved leading edge bulging portion adjacent said paddle, said trailing edge being convexly formed adjacent to said paddle a curved trailing edge arch of the root; and/or
    所述桨叶为至少两个，至少两个所述桨叶连接在所述桨毂上并关于所述桨毂的中心呈中心对称；及/或The blades are at least two, at least two of the blades are coupled to the hub and are centrally symmetric about a center of the hub; and/or
    所述桨叶具有穿过所述桨毂的中心的中轴线，所述前缘具有平行于所述中轴线的前缘切线，所述后缘具有平行于所述中轴线的后缘切线，所述后掠部位于所述前缘切线与所述后缘切线之间；及/或The blade has a central axis passing through a 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 swept portion is located between the leading edge tangent and the trailing edge tangent; and/or
    所述吸力面和所述压力面均为曲面。The suction surface and the pressure surface are both curved surfaces.
  17. 根据权利要求9至16所述的动力组件，其特征在于，所述驱动件为电机，所述电机的KV值为360至810转/(分钟·伏特)。The power unit according to any one of claims 9 to 16, wherein said driving member is a motor having a KV value of 360 to 810 rpm / (minute volt).
  18. 一种飞行器，其特征在于，包括机身和动力组件，所述动力组件与所述机身连接；An aircraft characterized by comprising a fuselage and a power assembly, the power assembly being coupled to the fuselage;
    所述动力组件包括驱动件和螺旋桨，其特征在于，所述螺旋桨通过所述桨毂与所述驱动件连接；The power assembly includes a driving member and a propeller, wherein the propeller is coupled to the driving member through the hub;
    所述螺旋桨，包括：桨毂和桨叶，所述桨叶连接在所述桨毂上，其特征在于：The propeller includes: a hub and a blade, the blade being coupled to the hub, wherein:
    在距离所述桨毂的中心为所述螺旋桨的半径的42.9％处，所述桨叶的攻角为24.60°±2.5°；The angle of attack of the blade is 24.60 ° ± 2.5 ° at a distance of 42.9% of the radius of the propeller from the center of the hub;
    在距离所述桨毂的中心为所述螺旋桨的半径的52.4％处，所述桨叶的攻角为23.50°±2.5°；The angle of attack of the blade is 23.50 ° ± 2.5 ° at a distance of 52.4% of the radius of the propeller from the center of the hub;
    在距离所述桨毂的中心为所述螺旋桨的半径的61.9％处，所述桨叶的攻角为21.82°±2.5°；The angle of attack of the blade is 21.82 ° ± 2.5 ° at a distance of 61.9% of the radius of the propeller from the center of the hub;
    在距离所述桨毂的中心为所述螺旋桨的半径的71.4％处，所述桨叶的攻角为19.97°±2.5°。At an angle of 71.4% of the radius of the propeller from the center of the hub, the blade has an angle of attack of 19.97 ° ± 2.5 °.
  19. 根据权利要求18所述的飞行器，其特征在于：The aircraft of claim 18 wherein:
    在距离所述桨毂的中心为所述螺旋桨的半径的23.8％处，所述桨叶的攻角为23.40°±2.5°；及/或The angle of attack of the blade is 23.40° ± 2.5° at 23.8% of the radius of the propeller from the center of the hub; and/or
    在距离所述桨毂的中心为所述螺旋桨的半径的33.3％处，所述桨叶的攻角为26.20°±2.5°；及/或At an angle of 33.3% of the radius of the propeller from the center of the hub, the angle of attack of the blade is 26.20° ± 2.5°; and/or
    在距离所述桨毂的中心为所述螺旋桨的半径的81.0％处，所述桨叶的攻角为17.97°±2.5°；及/或At an angle of 81.0% of the radius of the propeller from the center of the hub, the angle of attack of the blade is 17.97° ± 2.5°; and/or
    在距离所述桨毂的中心为所述螺旋桨的半径的90.5％处，所述桨叶的攻角为16.61°±2.5°；及/或At an angle of 90.5% of the radius of the propeller from the center of the hub, the angle of attack of the blade is 16.61° ± 2.5°; and/or
    在距离所述桨毂的中心为所述螺旋桨的半径的100％处，所述桨叶的攻角为9.39°±2.5°；及/或The angle of attack of the blade is 9.39 ° ± 2.5 ° at a distance of 100% of the radius of the propeller from the center of the hub; and/or
    在距离所述桨毂的中心25mm处，所述桨叶的攻角为23.40°；及/或The blade has an angle of attack of 23.40° at a distance of 25 mm from the center of the hub; and/or
    在距离所述桨毂的中心35mm处，所述桨叶的攻角为26.20°；及/或The blade has an angle of attack of 26.20° at a distance of 35 mm from the center of the hub; and/or
    在距离所述桨毂的中心45mm处，所述桨叶的攻角为24.60°；及/或The blade has an angle of attack of 24.60° at a distance of 45 mm from the center of the hub; and/or
    在距离所述桨毂的中心55mm处，所述桨叶的攻角为23.50°；及/或At 55 mm from the center of the hub, the blade has an angle of attack of 23.50°; and/or
    在距离所述桨毂的中心65mm处，所述桨叶的攻角为21.82°；及/或The blade has an angle of attack of 21.82° at a distance of 65 mm from the center of the hub; and/or
    在距离所述桨毂的中心75mm处，所述桨叶的攻角为19.97°；及/或The blade has an angle of attack of 19.97° at a distance of 75 mm from the center of the hub; and/or
    在距离所述桨毂的中心85mm处，所述桨叶的攻角为17.97°；及/或The blade has an angle of attack of 17.97° at a distance of 85 mm from the center of the hub; and/or
    在距离所述桨毂的中心95mm处，所述桨叶的攻角为16.61°；及/或The blade has an angle of attack of 16.61° at a distance of 95 mm from the center of the hub; and/or
    在距离所述桨毂的中心105mm处，所述桨叶的攻角为9.39°。At an angle of 105 mm from the center of the hub, the blade has an angle of attack of 9.39.
  20. 根据权利要求18所述的飞行器，其特征在于：The aircraft of claim 18 wherein:
    在距离所述桨毂的中心为所述螺旋桨的半径的42.9％处，所述桨叶的弦长为26.49mm±5mm；及/或The chord length of the blade is 26.49 mm ± 5 mm at a distance of 42.9% of the radius of the propeller from the center of the hub; and/or
    在距离所述桨毂的中心为所述螺旋桨的半径的52.4％处，所述桨叶的弦长为25.16mm±5mm；及/或The chord length of the blade is 25.16 mm ± 5 mm at a distance of 52.4% of the radius of the propeller from the center of the hub; and/or
    在距离所述桨毂的中心为所述螺旋桨的半径的61.9％处，所述桨叶的弦长为23.59mm±5mm；及/或The chord length of the blade is 23.59 mm ± 5 mm at a distance of 61.9% of the radius of the propeller from the center of the hub; and/or
    在距离所述桨毂的中心为所述螺旋桨的半径的71.4％处，所述桨叶的弦长为21.69mm±5mm；及/或The chord length of the blade is 21.69 mm ± 5 mm at a distance of 71.4% of the radius of the propeller from the center of the hub; and/or
    在距离所述桨毂的中心45mm处，所述桨叶的弦长为26.49mm；及/或The chord length of the blade is 26.49 mm at a distance of 45 mm from the center of the hub; and/or
    在距离所述桨毂的中心55mm处，所述桨叶的弦长为25.16mm；及/或The chord length of the blade is 25.16 mm at a distance of 55 mm from the center of the hub; and/or
    在距离所述桨毂的中心65mm处，所述桨叶的弦长为23.59mm；及/或The chord length of the blade is 23.59 mm at a distance of 65 mm from the center of the hub; and/or
    在距离所述桨毂的中心75mm处，所述桨叶的弦长为21.69mm。At a distance of 75 mm from the center of the hub, the blade has a chord length of 21.69 mm.
  21. 根据权利要求20所述的飞行器，其特征在于：The aircraft of claim 20 wherein:
    在距离所述桨毂的中心为所述螺旋桨的半径的23.8％处，所述桨叶的弦长为21.21mm±5mm；及/或The chord length of the blade is 21.21 mm ± 5 mm at 23.8% of the radius of the propeller from the center of the hub; and/or
    在距离所述桨毂的中心为所述螺旋桨的半径的33.3％处，所述桨叶的弦长为27.38mm±5mm；及/或The chord length of the blade is 27.38 mm ± 5 mm at a distance of 33.3% of the radius of the propeller from the center of the hub; and/or
    在距离所述桨毂的中心为所述螺旋桨的半径的81.0％处，所述桨叶的弦长为19.45mm±5mm；及/或The chord length of the blade is 19.45 mm ± 5 mm at a distance of 81.0% of the radius of the propeller from the center of the hub; and/or
    在距离所述桨毂的中心为所述螺旋桨的半径的90.5％处，所述桨叶的弦长为15.78mm±5mm；及/或The chord length of the blade is 15.78 mm ± 5 mm at a distance of 90.5% of the radius of the propeller from the center of the hub; and/or
    在距离所述桨毂的中心为所述螺旋桨的半径的100％处，所述桨叶的弦长为4.94mm±2mm；及/或The chord length of the blade is 4.94 mm ± 2 mm at a distance of 100% of the radius of the propeller from the center of the hub; and/or
    在距离所述桨毂的中心25mm处，所述桨叶的弦长为21.21mm；及/或The chord length of the blade is 21.21 mm at a distance of 25 mm from the center of the hub; and/or
    在距离所述桨毂的中心35mm处，所述桨叶的弦长为27.38mm；及/或The chord length of the blade is 27.38 mm at a distance of 35 mm from the center of the hub; and/or
    在距离所述桨毂的中心85mm处，所述桨叶的弦长为19.45mm；及/或The chord length of the blade is 19.45 mm at a distance of 85 mm from the center of the hub; and/or
    在距离所述桨毂的中心95mm处，所述桨叶的弦长为15.78mm；及/或The chord length of the blade is 15.78 mm at a distance of 95 mm from the center of the hub; and/or
    在距离所述桨毂的中心105mm处，所述桨叶的弦长为4.94mm。At a distance of 105 mm from the center of the hub, the blade has a chord length of 4.94 mm.
  22. 根据权利要求18所述的飞行器，其特征在于：The aircraft of claim 18 wherein:
    所述螺旋桨的直径为210mm±21mm；及/或The diameter of the propeller is 210 mm ± 21 mm; and / or
    所述桨叶的螺距为3.6±0.5英寸。The pitch of the paddle is 3.6 ± 0.5 inches.
  23. 根据权利要求18至22中任意一项所述的飞行器，其特征在于：An aircraft according to any one of claims 18 to 22, characterized in that:
    所述桨叶包括桨根、背离所述桨根的桨尖、相背的压力面及吸力面、连接于所述压力面及所述吸力面一侧边的前缘、连接于所述压力面及所述吸力面另一侧边的后缘、及形成于所述桨尖的后掠部；The blade includes a blade root, a blade tip facing away from the blade root, opposite pressure surfaces and a suction surface, a leading edge connected to the pressure surface and the one side of the suction surface, and is connected to the pressure surface And a trailing edge of the other side of the suction surface and a swept portion formed on the tip of the blade;
    所述后掠部自所述前缘向所述后缘倾斜延伸，所述桨尖沿所述桨叶展向的方向朝所述吸力面所在的一侧倾斜延伸。The swept portion extends obliquely from the leading edge toward the trailing edge, and the tip of the blade extends obliquely toward a side of the suction surface along a direction in which the blade extends.
  24. 根据权利要求23所述的飞行器，其特征在于，所述桨叶在所述桨尖的位置形成回弯处，所述前缘自所述回弯处开始沿所述桨叶的展向朝所述吸力面所在的一侧倾斜延 伸，所述后掠部自所述回弯处从所述前缘向所述后缘倾斜延伸，所述回弯处距离所述桨毂的中心为所述的半径的82.5％。The aircraft according to claim 23, wherein said blade forms a return bend at a position of said tip, said leading edge starting from said return bend along said direction of said blade One side of the suction surface is obliquely extended, and the swept portion extends obliquely from the leading edge to the trailing edge from the back bend, and the center of the back bend is from the center of the hub 82.5% of the radius.
  25. 根据权利要求23所述的飞行器，其特征在于，所述前缘外凸形成有靠近所述桨根的呈曲面状的前缘拱起部，所述后缘外凸形成有靠近所述桨根的呈曲面状的后缘拱起部；及/或The aircraft according to claim 23, wherein said leading edge is convexly formed with a curved leading edge bulging portion adjacent said paddle, said trailing edge being convexly formed adjacent said paddle a curved trailing edge arch; and/or
    所述桨叶为至少两个，至少两个所述桨叶连接在所述桨毂上并关于所述桨毂的中心呈中心对称；及/或The blades are at least two, at least two of the blades are coupled to the hub and are centrally symmetric about a center of the hub; and/or
    所述桨叶具有穿过所述桨毂的中心的中轴线，所述前缘具有平行于所述中轴线的前缘切线，所述后缘具有平行于所述中轴线的后缘切线，所述后掠部位于所述前缘切线与所述后缘切线之间；及/或The blade has a central axis passing through a 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 swept portion is located between the leading edge tangent and the trailing edge tangent; and/or
    所述吸力面和所述压力面均为曲面。The suction surface and the pressure surface are both curved surfaces.
  26. 根据权利要求18至25任一所述的飞行器，其特征在于，所述驱动件为电机，所述电机的KV值为360至810转/(分钟·伏特)。The aircraft according to any one of claims 18 to 25, wherein the driving member is a motor having a KV value of 360 to 810 rpm / (minute volt).
  27. 根据权利要求18至26任一所述的飞行器，其特征在于，所述飞行器包括多个动力组件，所述多个动力组件的转动方向不同，所述飞行器为多旋翼飞行器。The aircraft according to any one of claims 18 to 26, wherein the aircraft comprises a plurality of power components, the plurality of power components having different directions of rotation, and the aircraft is a multi-rotor aircraft.
PCT/CN2018/109068 2018-01-31 2018-09-30 Propeller, power component and aircraft WO2019148879A1 (en)

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CN207917131U (en) * 2018-01-31 2018-09-28 深圳市大疆创新科技有限公司 Propeller, Power Component and aircraft
CN213323651U (en) * 2020-04-21 2021-06-01 深圳市大疆创新科技有限公司 Screw, power component and aircraft

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