WO2019127028A1 - Propeller, power assembly and aircraft - Google Patents

Propeller, power assembly and aircraft Download PDF

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Publication number
WO2019127028A1
WO2019127028A1 PCT/CN2017/118671 CN2017118671W WO2019127028A1 WO 2019127028 A1 WO2019127028 A1 WO 2019127028A1 CN 2017118671 W CN2017118671 W CN 2017118671W WO 2019127028 A1 WO2019127028 A1 WO 2019127028A1
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WO
WIPO (PCT)
Prior art keywords
blade
propeller
hub
center
angle
Prior art date
Application number
PCT/CN2017/118671
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
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
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
Priority to CN201780023131.3A priority Critical patent/CN109071006B/en
Priority to PCT/CN2017/118671 priority patent/WO2019127028A1/en
Publication of WO2019127028A1 publication Critical patent/WO2019127028A1/en

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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/32—Rotors
    • B64C27/46—Blades
    • B64C27/467—Aerodynamic features
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/32—Rotors
    • B64C27/46—Blades
    • B64C27/473—Constructional features

Definitions

  • the present invention relates 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.
  • the propeller of the embodiment of the invention includes a paddle.
  • the blade includes a paddle root, a blade tip facing away from the blade root, a pressure surface, a suction surface opposite to the pressure surface, a leading edge connected to the pressure surface and a side of the suction surface, and connected to a pressure surface and a trailing edge of the other side of the suction surface, and a swept portion formed at the tip of the blade;
  • the leading edge extends obliquely from the side of the paddle toward the side where the pressure face is located, and is inclined obliquely toward a side of the suction face at a portion close to the tip end, the swept portion
  • the front edge extends obliquely toward the trailing edge.
  • the paddle forms a bend at the position of the tip, the leading edge extending obliquely from the bend to the side where the suction face is located.
  • leading edge is convexly formed with a curved leading edge bulge near the paddle; or/and
  • the trailing edge is convexly formed with a curved trailing edge arch portion near the paddle.
  • the propeller further includes a hub, the blades being at least two, at least two of the blades being coupled to the hub and being centrally symmetric about a center of the hub.
  • the center of the back bend from the hub is 90.9% of the radius of the propeller.
  • 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 blade at 45.5% of the radius of the propeller from the center of the hub, the blade has an angle of attack of 19.78° ⁇ 2.5° and the blade has a chord length of 26.58 mm. ⁇ 5mm.
  • the diameter of the propeller is 220 mm ⁇ 22 mm;
  • the blade At an angle of 50 mm from the center of the hub, the blade has an angle of attack of 19.78° and the blade has a chord length of 26.58 mm.
  • the angle of attack of the blade is 17.83° ⁇ 2.5° at a distance of 54.6% of the radius of the propeller from the center of the hub, and the chord length of the blade is 24.75 mm ⁇ 5mm.
  • the diameter of the propeller is 220 mm ⁇ 22 mm;
  • the blade At an angle of 60 mm from the center of the hub, the blade has an angle of attack of 17.83° and the blade has a chord length of 24.75 mm.
  • the angle of attack of the blade is 16.42° ⁇ 2.5° at a distance of 63.6% of the radius of the propeller from the center of the hub, and the chord length of the blade is 22.65 mm ⁇ 5mm.
  • the diameter of the propeller is 220 mm ⁇ 22 mm;
  • the blade At an angle of 70 mm from the center of the hub, the blade has an angle of attack of 16.42° and the blade has a chord length of 22.65 mm.
  • the angle of attack of the blade is 14.97° ⁇ 2.5° at a distance of 72.7% of the radius of the propeller from the center of the hub, and the chord length of the blade is 20.07 mm ⁇ 5mm.
  • the diameter of the propeller is 220 mm ⁇ 22 mm;
  • the blade At an angle of 80 mm from the center of the hub, the blade has an angle of attack of 14.97° and the blade has a chord length of 20.07 mm.
  • the pitch of the paddle is 4.8 ⁇ 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 300 to 800 rpm / (minute volts).
  • An aircraft according to an embodiment of the present invention includes a power body and a power assembly according to any of the above embodiments, the power assembly being coupled to the body.
  • the aircraft includes a plurality of power components that rotate in different directions.
  • the aircraft is a multi-rotor aircraft.
  • the leading edge of the propeller blade provided by the present invention extends obliquely from the side of the paddle toward the side of the pressure surface, and is inclined obliquely toward the side of the suction surface near the tip of the blade, and the swept portion is rearward from the leading edge.
  • the blade extends, and the propeller, power assembly and aircraft using the blade can reduce the air resistance, increase the pulling force and efficiency, increase the flight distance of the aircraft and improve the flight performance of the aircraft, and reduce the blade work.
  • the noise generated during the time makes the aircraft quieter when hovering and improves the user experience.
  • FIG. 1 is a perspective view of a propeller according to an embodiment of the present invention.
  • Figure 2 is a perspective view of another perspective view of the propeller of Figure 1.
  • Figure 3 is a plan view of the propeller of Figure 1.
  • Figure 4 is a plan view of the propeller of Figure 1.
  • Figure 5 is a plan view of the propeller of Figure 1.
  • Figure 6 is a parametric diagram of the swept portion of the propeller of Figure 1 extending obliquely from the leading edge to the trailing edge.
  • FIG. 7 is a parametric diagram in which the leading edge of the propeller of FIG. 1 extends obliquely from the corner of the retraction toward the side where the suction surface is located.
  • Figure 8 is a cross-sectional view of the A-A section of the propeller of Figure 5 at a distance of 30 mm from the center of the hub.
  • Figure 9 is a cross-sectional view of the B-B section of the propeller of Figure 5 at a distance of 40 mm from the center of the hub.
  • Figure 10 is a cross-sectional view of the C-C section of the propeller of Figure 5 at a distance of 50 mm from the center of the hub.
  • Figure 11 is a cross-sectional view of the D-D section of the propeller of Figure 5 at a distance of 60 mm from the center of the hub.
  • Figure 12 is a cross-sectional view of the E-E section of the propeller of Figure 5 at a distance of 70 mm from the center of the hub.
  • Figure 13 is a cross-sectional view of the F-F section of the propeller of Figure 5 at a distance of 80 mm from the center of the hub.
  • Figure 14 is a cross-sectional view of the G-G section of the propeller of Figure 5 at a distance of 90 mm from the center of the hub.
  • Figure 15 is a cross-sectional view of the H-H section of the propeller of Figure 5 at a distance of 100 mm from the center of the hub.
  • Figure 16 is a cross-sectional view of the I-I section of the propeller of Figure 5 at a distance of 110 mm from the center of the hub.
  • Figure 17 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.
  • 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.”
  • Embodiments of the present invention provide a propeller, which may be a positive propeller or a reverse propeller.
  • the so-called positive paddle refers to a propeller that rotates clockwise to generate lift from the tail of the motor, such as the tail of the motor.
  • the so-called reverse paddle refers to the propeller that rotates counterclockwise to generate lift from the tail of the motor to the direction of the motor head.
  • the structure of the positive paddle is mirror symmetrical with the structure of the reverse paddle, so the structure of the propeller will be described below by taking only the positive paddle as an example.
  • the terms of the upper and lower orientations appearing in this embodiment are based on the conventional operating posture of the propeller and the aircraft after the propeller is mounted on the aircraft, and should not be considered as limiting.
  • the present invention provides a propeller 100.
  • the propeller 100 includes a paddle 20.
  • the blade 20 includes a pressure surface 21, a suction surface 22, a trailing edge 23, a leading edge 24, a paddle 25, a tip 26, and a swept portion 261.
  • the paddle tip 26 faces away from the blade root 25.
  • the suction surface 22 is opposite to the pressure surface 21.
  • the leading edge 24 is connected to one side of the pressure surface 21 and the suction surface 22, and the trailing edge 23 is connected to the other side of the pressure surface 21 and the suction surface 22.
  • the swept portion 261 is formed at the tip end 26.
  • the leading edge 24 extends obliquely from the side of the paddle root 25 toward the side where the pressure surface 21 is located, and is inclined obliquely toward the side where the suction surface 22 is located at a portion close to the blade tip 26.
  • the swept portion 261 extends obliquely from the leading edge 24 to the trailing edge 23.
  • the pressure surface 21 is a surface facing the ground of the blade 20 during normal flight of the aircraft
  • the suction surface 22 is a surface facing the sky of the blade 20 when the aircraft is normally flying.
  • the leading edge 24 of the propeller 100 of the present invention extends obliquely from the paddle root 25 toward the side where the pressure surface 21 is located, and is inclined obliquely toward the side where the suction surface 22 is located near the blade tip 26, and the swept portion 261 From the leading edge 24 to the trailing edge 23, the propeller 100 using the blade 20 can reduce the air resistance, increase the pulling force and efficiency, increase the flight distance of the aircraft and improve the flight performance of the aircraft, and reduce the paddle.
  • the noise generated by the blade 20 during operation makes the aircraft quieter when hovering, improving the user experience.
  • the paddle 20 optionally forms a back bend 262 at the position of the blade tip 26, and the leading edge 24 is located at the return bend 262 along the direction of the suction face 22 One side of the slope extends.
  • the position of the return bend 262 is indicated by MM.
  • the propeller 100 further includes a hub 10 having at least two blades 20, and at least two blades 20 are coupled to the hub 10 and are centrally symmetric about the center of the hub 10. Thereby, the balance of the propeller 100 can be improved.
  • the return bend 262 is 90.9% of the center of the hub 10 that is the radius of the propeller 100. Thus, the bend back 262 is away from the center of the hub 10, enhancing the overall aesthetics of the blade 20.
  • leading edge 24 is convexly formed with a curved leading edge arching portion 241 near the paddle 25; or/and the trailing edge 23 is convexly formed with a curved surface near the paddle 25 The trailing edge arched portion 231.
  • leading edge 24 is convexly formed with a curved leading edge arching portion 241 near the paddle 25; or the trailing edge 23 is convexly formed with a curved trailing edge arching portion 231 near the paddle 25.
  • leading edge 24 is convexly formed with a curved leading edge bulging portion 241 near the paddle 25
  • the trailing edge 23 is convexly formed with a curved trailing edge bulging portion 231 near the paddle root 25, In order to further increase the pulling force of the blade 20.
  • the hub 10 may have a cylindrical shape, or the cross section of the hub 10 may have an elliptical shape, a rhombus shape or the like.
  • the center of the hub 10 is provided with a connecting hole for arranging on the output end of the motor.
  • the blade 20 may be in the form of a strip, the blade 20 being coupled to the hub 10 and extending in the radial direction of the hub 10.
  • the blade 20 has a central axis JJ passing through the center of the hub 10, the leading edge 24 has a leading edge tangent KK parallel to the central axis JJ, and the trailing edge 23 has parallel
  • the tangent to the trailing edge of the center axis JJ is LL.
  • the swept portion 261 is located between the leading edge tangent K-K and the trailing edge tangent L-L. Thereby, the swept portion 261 can reduce the turbulence and the downwashing flow generated by the blade 20, thereby reducing the turbulence and the downwashing airflow hitting the outer casing of the aircraft, reducing the air resistance of the propeller 100, and improving the maneuverability of the aircraft. To make the aircraft more stable while further reducing the overall noise of the aircraft.
  • the suction surface 22 and the pressure surface 21 are curved surfaces.
  • the suction surface 22 and the pressure surface 21 are curved aerodynamic shapes, which can avoid turbulence generated by various parts of the blade 20 and the downwashing airflow directly impacting the outer casing of the aircraft, thereby reducing the overall noise of the aircraft.
  • the swept portion 261 extends obliquely from the leading edge 24 toward the trailing edge 23.
  • the abscissa Blade Radius represents the distance from the center of the hub 10 at a certain position (such as MM) of the blade 20 in the spanwise direction.
  • 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, and the end point is the free end 261 of the blade tip 26, at which time the distance of the blade 20 from the center of the hub 10 is 110 mm.
  • the Sweep Length (mm) (the swept distance, the degree of inclination of the swept portion 261) indicates the distance of the point at 1/2 of the chord length of the blade 20 with respect to the center axis J-J. Since the angle of attack ⁇ of the embodiment is less than 25 degrees, the point at 1/2 of the chord length of the blade 20 is smaller than the point at 1/2 of the blade 20 of the top view in FIG. 5, so The distance of the point at 1/2 of the blade 20 of the top view in FIG. 1 with respect to the central axis JJ represents the Sweep Length. Among them, the positive value of the Sweep Length (mm) is swept back, and the negative value is swept forward.
  • the swept portion 261 begins to extend obliquely from the leading edge 24 toward the trailing edge 23.
  • the swept portion 261 regularly extends obliquely from the leading edge 24 to the trailing edge 23, which can reduce turbulence and downwashing due to interaction of the plurality of blades 20, and reduce the hitting
  • the turbulence and downwashing airflow to the outer casing of the aircraft reduces the air resistance experienced by the blade 20, improves the maneuverability of the aircraft, and makes the aircraft more stable. At the same time, the turbulence and the downwashing airflow are further reduced to impact the outer casing of the aircraft. noise.
  • the leading edge 24 extends obliquely from the return bend 262 along the side where the suction surface 22 is located.
  • the abscissa Blade Radius represents the distance from the center of the hub 10 at a certain position (such as MM) of the blade 20 in the spanwise direction.
  • 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, and the end point is the free end 261 of the blade tip 26, at which time the distance of the blade 20 from the center of the hub 10 is 110 mm.
  • the ordinate Anhedral Length (mm) (the distance of the upper reverse, the degree of inclination of the leading edge 24) represents the distance of the point at 1/2 of the chord length of the blade 20 with respect to the horizontal reference line passing through the center of the hub 10.
  • the positive value of the ordinate Anhedral Length (mm) is the upper and the reverse, and the negative value is the lower.
  • the leading edge 24 begins to extend obliquely along the side where the suction surface 22 is located, that is, the blade 20 is spaced from the hub 10.
  • the leading edge 24 extends from the bendback 262 to an extent that extends obliquely toward the side on which the suction surface 22 is located.
  • the leading edge 24 is regularly inclined from the corner of the curved portion 262 along the side where the suction surface 22 is located, which can reduce the turbulence caused by the interaction of the plurality of blades 20.
  • the lifting point of the blade 20 can be rated, so that the aircraft can automatically correct the flight attitude, increase the inertial stability of the aircraft, and make the aircraft fly. The time is more stable, and at the same time, the noise generated by the turbulence and the downwashing airflow impinging on the outer casing of the aircraft is further reduced.
  • the angle of attack ⁇ 1 of the blade 20 is 21.64° ⁇ 2.5°.
  • the chord length L1 of the blade 20 is 27.53 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 19.14° or 21.64° or 24.14°, or any one of 19.64°, 20.14°, 20.64°, 21.14°, 22.14°, 22.64°, 23.14°, 23.64°, and the like.
  • chord length L1 of the blade 20 may be 22.53 mm or 27.53 mm or 32.53 mm, or 23.53 mm, 24.53 mm, 25.53 mm, 26.53 mm, 28.53 mm, 29.53 mm, 30.53 mm. Any one of 31.53 mm or the like or a value between any of the above.
  • the angle of attack ⁇ 2 of the blade 20 is 20.43° ⁇ 2.5°.
  • the chord length L2 of the blade 20 is 27.78 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 ⁇ 2 of the blade 20 may be 17.93° or 20.43° or 22.93°, or any one of 18.43°, 18.93°, 19.43°, 19.93°, 20.93°, 21.43°, 21.93°, 22.43°, and the like.
  • chord length L2 of the blade 20 may be 22.78 mm or 27.78 mm or 32.78 mm, or 23.78 mm, 24.78 mm, 25.78 mm, 26.78 mm, 28.78 mm, 29.78 mm, 30.78 mm. Any one of 31.78 mm or the like or a value between any of the above.
  • D3 is at a distance of 45.5% of the radius of the propeller 100 from the center of the hub 10, and the angle of attack ⁇ 3 of the blade 20 is 19.78° ⁇ 2.5°.
  • the chord length L3 of the blade 20 is 26.58 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 ⁇ 3 of the blade 20 may be 17.28° or 19.78° or 22.28°, or any one of 17.78°, 18.28°, 18.78°, 19.28°, 20.28°, 20.78°, 21.28°, 21.78°, and the like.
  • chord length L3 of the blade 20 may be 21.58 mm or 26.58 mm or 31.58 mm, or 22.58 mm, 23.58 mm, 24.58 mm, 25.58 mm, 27.58 mm, 28.58 mm, 29.58 mm. Any one of 30.58 mm or the like or a value between any of the above.
  • D4 is 54.6% of the radius of the propeller 100 from the center of the hub 10, and the angle of attack ⁇ 4 of the blade 20 is 17.83° ⁇ 2.5°.
  • the chord length L4 of the blade 20 is 24.75 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 ⁇ 4 of the blade 20 may be 15.33° or 17.83° or 20.33°, or any one of 15.83°, 16.33°, 16.83°, 17.33°, 18.33°, 18.83°, 19.33°, 19.83°, and the like.
  • chord length L4 of the blade 20 may be 19.75 mm or 24.75 mm or 29.75 mm, or 20.75 mm, 21.75 mm, 22.75 mm, 23.75 mm, 25.75 mm, 26.75 mm, 27.75 mm. Any one of 28.75 mm or the like or a value between any two of the above.
  • the angle of attack ⁇ 5 of the blade 20 is 16.42° ⁇ 2.5°.
  • the chord length L5 of the blade 20 is 22.65 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 ⁇ 5 of the blade 20 may be 13.92° or 16.42° or 18.92°, or any one of 14.42°, 14.92°, 15.42°, 15.92°, 16.92°, 17.42°, 17.92°, 18.42°, and the like.
  • chord length L5 of the blade 20 may be 17.65 mm or 22.65 mm or 27.65 mm, or 18.65 mm, 19.65 mm, 20.65 mm, 21.65 mm, 23.65 mm, 24.65 mm, 25.65 mm. Any one of 26.65 mm or the like or a value between any two of the above.
  • D6 at the center of the hub 10 is 72.7% of the radius of the propeller 100
  • the angle of attack ⁇ 6 of the blade 20 is 14.97° ⁇ 2.5°.
  • the chord length L6 of the blade 20 is 20.07 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 ⁇ 6 of the blade 20 may be 12.47° or 14.97° or 17.47°, or any one of 12.97°, 13.47°, 13.97°, 14.47°, 15.47°, 15.97°, 16.47°, 16.97°, and the like.
  • chord length L6 of the blade 20 may be 15.07 mm or 20.07 mm or 25.07 mm, or 16.07 mm, 17.07 mm, 18.07 mm, 19.07 mm, 21.07 mm, 22.07 mm, 23.07 mm. Any one of 24.07 mm or the like or a value between any two of the above.
  • D7 at the center of the hub 10 is 81.8% of the radius of the propeller 100
  • the angle of attack ⁇ 7 of the blade 20 is 13.17° ⁇ 2.5°.
  • the chord length L7 of the blade 20 is 16.64 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 10.67° or 13.17° or 15.67°, or any one of 11.17°, 11.67°, 12.17°, 12.67°, 13.67°, 14.17°, 14.67°, 15.17°, and the like.
  • chord length L7 of the blade 20 may be 11.64 mm or 16.64 mm or 21.64 mm, or 12.64 mm, 13.64 mm, 14.64 mm, 15.64 mm, 17.64 mm, 18.64 mm, Any one of 19.64 mm, 20.64 mm, etc., or a value between any of the above.
  • the angle of attack ⁇ 8 of the blade 20 is 10.68° ⁇ 2.5°.
  • the chord length L8 of the blade 20 is 11.15 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 ⁇ 8 of the blade 20 may be 8.18° or 10.68° or 13.18°, or any one of 8.68°, 9.18°, 9.68°, 10.18°, 11.18°, 11.68°, 12.18°, 12.68°, and the like.
  • chord length L8 of the blade 20 may be 6.15 mm or 11.15 mm or 16.15 mm, or 7.15 mm, 8.15 mm, 9.15 mm, 10.15 mm, 12.15 mm, 13.15 mm, 14.15 mm. Any one of 15.15 mm or the like or a value between any of the above.
  • the angle of attack ⁇ 9 of the blade 20 is 6.63° ⁇ 2.5°.
  • the chord length L9 of the blade 20 is 3.92 mm ⁇ 2 mm to further reduce the air resistance of the propeller 100, increase the pulling force and efficiency, and reduce noise.
  • the angle of attack ⁇ 9 of the blade 20 may be 4.13° or 6.63° or 9.13°, or any one of 4.63°, 5.13°, 5.63°, 6.13°, 7.13°, 7.63°, 8.13°, 8.63°, and the like.
  • chord length L9 of the blade 20 may be 1.92 mm or 3.92 mm or 5.92 mm, or 2.42 mm, 2.92 mm, 3.42 mm, 4.42 mm, 4.92 mm, 5.42 mm, or the like. Any one or a value between any two of the above.
  • the angle of attack ⁇ refers to the angle between the chord of the blade 20 and the incoming flow velocity
  • the chord length L refers to the length of the cross section of the blade 20.
  • the diameter of the propeller 100 is 220 mm ⁇ 22 mm.
  • the angle of attack ⁇ 1 of the blade 20 is 21.64°, and the chord length L1 of the blade 20 is 27.53 mm.
  • the diameter of the propeller 100 may be 198 mm or 220 mm or 242 mm, or any one of 200 mm, 205 mm, 210 mm, 215 mm, 225 mm, 230 mm, 235 mm, 240 mm, or the like, or a value between any two of the above.
  • the diameter of the propeller 100 is 220 mm ⁇ 22 mm.
  • the angle of attack ⁇ 2 of the blade 20 is 20.43°
  • the chord length L2 of the blade 20 is 27.78 mm.
  • the diameter of the propeller 100 may be 198 mm or 220 mm or 242 mm, or any one of 200 mm, 205 mm, 210 mm, 215 mm, 225 mm, 230 mm, 235 mm, 240 mm, or the like, or a value between any two of the above.
  • the diameter of the propeller 100 is 220 mm ⁇ 22 mm.
  • the angle of attack ⁇ 3 of the blade 20 is 19.78°, and the chord length L3 of the blade 20 is 26.58 mm.
  • the diameter of the propeller 100 may be 198 mm or 220 mm or 242 mm, or any one of 200 mm, 205 mm, 210 mm, 215 mm, 225 mm, 230 mm, 235 mm, 240 mm, or the like, or a value between any two of the above.
  • the diameter of the propeller 100 is 220 mm ⁇ 22 mm.
  • the angle of attack ⁇ 4 of the blade 20 is 17.83°
  • the chord length L4 of the blade 20 is 24.75 mm.
  • the diameter of the propeller 100 may be 198 mm or 220 mm or 242 mm, or any one of 200 mm, 205 mm, 210 mm, 215 mm, 225 mm, 230 mm, 235 mm, 240 mm, or the like, or a value between any two of the above.
  • the diameter of the propeller 100 is 220 mm ⁇ 22 mm.
  • the angle of attack ⁇ 5 of the blade 20 is 16.42°, and the chord length L5 of the blade 20 is 22.65 mm.
  • the diameter of the propeller 100 may be 198 mm or 220 mm or 242 mm, or any one of 200 mm, 205 mm, 210 mm, 215 mm, 225 mm, 230 mm, 235 mm, 240 mm, or the like, or a value between any two of the above.
  • the diameter of the propeller 100 is 220 mm ⁇ 22 mm.
  • the angle of attack ⁇ 6 of the blade 20 is 14.97°, and the chord length L6 of the blade 20 is 20.07 mm.
  • the diameter of the propeller 100 may be 198 mm or 220 mm or 242 mm, or any one of 200 mm, 205 mm, 210 mm, 215 mm, 225 mm, 230 mm, 235 mm, 240 mm, or the like, or a value between any two of the above.
  • the diameter of the propeller 100 is 220 mm ⁇ 22 mm.
  • the angle of attack ⁇ 7 of the blade 20 is 13.17°
  • the chord length L7 of the blade 20 is 16.64 mm.
  • the diameter of the propeller 100 may be 198 mm or 220 mm or 242 mm, or any one of 200 mm, 205 mm, 210 mm, 215 mm, 225 mm, 230 mm, 235 mm, 240 mm, or the like, or a value between any two of the above.
  • the diameter of the propeller 100 is 220 mm ⁇ 22 mm.
  • the angle of attack ⁇ 8 of the blade 20 is 10.68°
  • the chord length L8 of the blade 20 is 11.15 mm.
  • the diameter of the propeller 100 may be 198 mm or 220 mm or 242 mm, or any one of 200 mm, 205 mm, 210 mm, 215 mm, 225 mm, 230 mm, 235 mm, 240 mm, or the like, or a value between any two of the above.
  • the diameter of the propeller 100 is 220 mm ⁇ 22 mm.
  • the angle of attack ⁇ 9 of the blade 20 is 6.63°, and the chord length L9 of the blade 20 is 3.92 mm.
  • the diameter of the propeller 100 may be 198 mm or 220 mm or 242 mm, or any one of 200 mm, 205 mm, 210 mm, 215 mm, 225 mm, 230 mm, 235 mm, 240 mm, or the like, or a value between any two of the above.
  • the pitch of the blade 20 is optionally 4.8 ⁇ 0.5 inches. Thereby, 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 4.3 inches or 4.8 inches or 5.3 inches, or any one of 4.4 inches, 4.5 inches, 4.6 inches, 4.7 inches, 4.9 inches, 5.0 inches, 5.1 inches, 5.2 inches, etc. The value between any two.
  • the comparison between the propeller 100 provided by this embodiment and the test results of the existing propeller As can be seen from Table 3, 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, 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 the noise power. In addition, as can be seen from the frequency response curve (Frequency (Hz)-Loudness (dB-A)) in FIG. 17, the loudness of the propeller 100 provided in this embodiment is lower than that under the condition of most of the same frequency. Propeller.
  • Hz Frequency
  • dB-A Low-Loudness
  • 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 propeller 100 employing the blade 20 of the above-described embodiment of the present invention can reduce air resistance, increase tension and efficiency, increase the range of the aircraft, and improve the flight performance of the aircraft.
  • the overall noise generated by the propeller 100 using the blade 20 is lower than that of the existing propeller.
  • the propeller 100 provided in this embodiment can effectively reduce the noise power.
  • 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.
  • 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.
  • the propeller 100 provided in this embodiment can effectively reduce the noise power.
  • Embodiments of the present invention also provide a power assembly including a drive member and a propeller 100 of any of the embodiments of the present invention, the propeller 100 being coupled to the drive member via the hub 10.
  • the specific structure of the propeller 100 is similar to the foregoing embodiment, and details are not described herein again. That is, the description of the propeller 100 in the above embodiments and embodiments is equally applicable to the power assembly provided by the embodiment of the present invention.
  • the leading edge 24 of the propeller 100 blade 20 extends obliquely from the paddle root 25 toward the side where the pressure surface 21 is located and toward the suction tip 22 at a portion adjacent to the blade tip 26.
  • the side is reversed and the swept portion 261 extends obliquely from the leading edge 24 to the trailing edge 23.
  • the power assembly using the propeller 100 can reduce the air resistance, increase the pulling force and efficiency, increase the flight distance of the aircraft and improve the flight performance of the aircraft, and also reduce the noise generated by the blade 20 during operation, so that the aircraft Quiet when hovering, improving the user experience.
  • the driving member is a motor
  • the KV value of the motor is 300 to 800 rpm / (minute ⁇ volt).
  • Embodiments of the present invention also provide an aircraft comprising a fuselage and a power assembly of any of the embodiments of the present invention, the power assembly being coupled to the fuselage.
  • the specific structure of the power component is similar to the foregoing embodiment, and details are not described herein again. That is, the description of the propeller 100 in the above embodiments and embodiments is equally applicable to the aircraft provided by the embodiment of the present invention.
  • the aircraft includes a plurality of power components, and the plurality of power components have different rotation directions.
  • the aircraft is a multi-rotor aircraft.
  • the leading edge 24 of the blade 20 of the propeller 100 extends obliquely from the paddle root 25 toward the side where the pressure surface 21 is located, and the portion adjacent to the blade tip 26 toward the suction surface 22 The side is reversed and the swept portion 261 extends obliquely from the leading edge 24 to the trailing edge 23.
  • the aircraft using the propeller 100 can reduce air resistance, increase pulling force and efficiency, increase the range of the aircraft and improve the flight performance of the aircraft.
  • the noise generated by the blade 20 during operation is also reduced, which makes the aircraft quieter when hovering and improves the user experience.

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Abstract

A propeller (100), comprising blades (20). Each blade (20) comprises a blade root (25), a blade tip (26) facing away from the blade root (25), a pressure face (21), a suction face (22) opposite to the pressure face (21), a leading edge (24) connected to one side of the pressure face (21) and one side of the suction face (22), a rear edge (23) connected to the other side of the pressure face (21) and the other side of the suction face (22), and a sweepback part (261) formed at the blade tip (26). The leading edge (24) extends from the blade root (25) obliquely toward the side of the pressure face (21) in the span direction and is inclined reversely toward the side of the suction face (22) at a portion near the blade tip (26), and the sweepback part (261) extends obliquely from the leading edge (24) toward the rear edge (23). Further disclosed are a power assembly and an aircraft. The propeller (100) using the blades (20), the power assembly and the aircraft can reduce air resistance, increase pulling force and efficiency, increase the aircraft's cruising distance and improve the flight performance of the aircraft, and can also reduce the noise generated by the blades during operation, enabling the aircraft to be more quiet during hovering, improving user experience.

Description

螺旋桨、动力组件及飞行器Propellers, power components and aircraft 技术领域Technical field
本发明涉及飞行器领域，特别涉及螺旋桨、动力组件及飞行器。The present invention relates 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.
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叶。The propeller of the embodiment of the invention includes a paddle.
所述桨叶包括桨根、背离所述桨根的桨尖、压力面、与所述压力面相背的吸力面、连接于所述压力面和所述吸力面一侧边的前缘、连接于所述压力面和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 paddle root, a blade tip facing away from the blade root, a pressure surface, a suction surface opposite to the pressure surface, a leading edge connected to the pressure surface and a side of the suction surface, and connected to a pressure surface and a trailing edge of the other side of the suction surface, and a swept portion formed at the tip of the blade;
所述前缘自所述桨根沿展向朝所述压力面所在的一侧倾斜延伸并在靠近所述桨尖的部分朝所述吸力面所在的一侧反转倾斜，所述后掠部自所述前缘向所述后缘倾斜延伸。The leading edge extends obliquely from the side of the paddle toward the side where the pressure face is located, and is inclined obliquely toward a side of the suction face at a portion close to the tip end, the swept portion The front edge extends obliquely 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沿展向向所述吸力面所在的一侧倾斜延伸。In some embodiments, the paddle forms a bend at the position of the tip, the leading edge extending obliquely from the bend to the side where the suction face is located.
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；或/和In some embodiments, the leading edge is convexly formed with a curved leading edge bulge near the paddle; or/and
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。The trailing edge is convexly formed with a curved trailing edge arch portion near the paddle.
在某些实施方式中，所述螺旋桨还包括桨毂，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 propeller further includes a hub, the blades being at least two, at least two of the blades being coupled to the hub and being centrally symmetric about a center of the hub.
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螺旋桨的半径的90.9％。In certain embodiments, the center of the back bend from the hub is 90.9% of the radius of the propeller.
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，在距离所述桨毂的中心为所述螺旋桨的半径的45.5％处，所述桨叶的攻角为19.78°±2.5°，所述桨叶的弦长为26.58mm±5mm。In certain embodiments, at 45.5% of the radius of the propeller from the center of the hub, the blade has an angle of attack of 19.78° ± 2.5° and the blade has a chord length of 26.58 mm. ±5mm.
在某些实施方式中，所述螺旋桨的直径为220mm±22mm；In some embodiments, the diameter of the propeller is 220 mm ± 22 mm;
在距离所述桨毂的中心50mm处，所述桨叶的攻角为19.78°，所述桨叶的弦长为26.58mm。At an angle of 50 mm from the center of the hub, the blade has an angle of attack of 19.78° and the blade has a chord length of 26.58 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54.6％处，所述桨叶的攻角为17.83°±2.5°，所述桨叶的弦长为24.75mm±5mm。In certain embodiments, the angle of attack of the blade is 17.83° ± 2.5° at a distance of 54.6% of the radius of the propeller from the center of the hub, and the chord length of the blade is 24.75 mm ±5mm.
在某些实施方式中，所述螺旋桨的直径为220mm±22mm；In some embodiments, the diameter of the propeller is 220 mm ± 22 mm;
在距离所述桨毂的中心60mm处，所述桨叶的攻角为17.83°，所述桨叶的弦长为24.75mm。At an angle of 60 mm from the center of the hub, the blade has an angle of attack of 17.83° and the blade has a chord length of 24.75 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63.6％处，所述桨叶的攻角为16.42°±2.5°，所述桨叶的弦长为22.65mm±5mm。In certain embodiments, the angle of attack of the blade is 16.42° ± 2.5° at a distance of 63.6% of the radius of the propeller from the center of the hub, and the chord length of the blade is 22.65 mm ±5mm.
在某些实施方式中，所述螺旋桨的直径为220mm±22mm；In some embodiments, the diameter of the propeller is 220 mm ± 22 mm;
在距离所述桨毂的中心70mm处，所述桨叶的攻角为16.42°，所述桨叶的弦长为22.65mm。At an angle of 70 mm from the center of the hub, the blade has an angle of attack of 16.42° and the blade has a chord length of 22.65 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72.7％处，所述桨叶的攻角为14.97°±2.5°，所述桨叶的弦长为20.07mm±5mm。In certain embodiments, the angle of attack of the blade is 14.97° ± 2.5° at a distance of 72.7% of the radius of the propeller from the center of the hub, and the chord length of the blade is 20.07 mm ±5mm.
在某些实施方式中，所述螺旋桨的直径为220mm±22mm；In some embodiments, the diameter of the propeller is 220 mm ± 22 mm;
在距离所述桨毂的中心80mm处，所述桨叶的攻角为14.97°，所述桨叶的弦长为20.07mm。At an angle of 80 mm from the center of the hub, the blade has an angle of attack of 14.97° and the blade has a chord length of 20.07 mm.
在某些实施方式中，所述桨叶的螺距为4.8±0.5英寸。In certain embodiments, the pitch of the paddle is 4.8 ± 0.5 inches.
本发明实施方式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300至800转/(分钟·伏特)。In certain embodiments, the drive member is a motor having a KV value of 300 to 800 rpm / (minute volts).
本发明实施方式的飞行器包括机身和上述任意一项实施方式所述的动力组件，所述动力组件与所述机身连接。An aircraft according to an embodiment of the present invention includes a power body and a power assembly according to any of the above embodiments, the power assembly being coupled to the body.
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.
本发明提供的螺旋桨桨叶的前缘自桨根沿展向朝压力面所在的一侧倾斜延伸并在靠近桨尖的部分朝吸力面所在的一侧反转倾斜，后掠部自前缘向后缘倾斜延伸，采用该桨叶的螺旋桨、动力组件及飞行器能够在减少空气阻力，提高拉力和效率，增加了飞行器的继航距离并提高了飞行器的飞行性能的同时，还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 leading edge of the propeller blade provided by the present invention extends obliquely from the side of the paddle toward the side of the pressure surface, and is inclined obliquely toward the side of the suction surface near the tip of the blade, and the swept portion is rearward from the leading edge. The blade extends, and the propeller, power assembly and aircraft using the blade can reduce the air resistance, increase the pulling force and efficiency, increase the flight distance of the aircraft and improve the flight performance of the aircraft, and reduce the blade work. The noise generated during the time makes the aircraft quieter when hovering and improves the 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螺旋桨的立体图。1 is a perspective view of a propeller according to an embodiment of the present invention.
图2是图1中螺旋桨的另一视角的立体图。Figure 2 is a perspective view of another perspective view of the propeller of Figure 1.
图3是图1中螺旋桨的平面示意图。Figure 3 is a plan view of the propeller of Figure 1.
图4是图1中螺旋桨的平面示意图。Figure 4 is a plan view of the propeller of Figure 1.
图5是图1中螺旋桨的平面示意图。Figure 5 is a plan view of the propeller of Figure 1.
图6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 6 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7是图1中螺旋桨的前缘自回弯处沿展向向吸力面所在的一侧倾斜延伸的参数图。7 is a parametric diagram in which the leading edge of the propeller of FIG. 1 extends obliquely from the corner of the retraction toward the side where the suction surface is located.
图8是图5中螺旋桨距离桨毂的中心30mm处的A-A剖面的剖视图。Figure 8 is a cross-sectional view of the A-A section of the propeller of Figure 5 at a distance of 30 mm from the center of the hub.
图9是图5中螺旋桨中距离桨毂的中心40mm处的B-B剖面的剖视图。Figure 9 is a cross-sectional view of the B-B section of the propeller of Figure 5 at a distance of 40 mm from the center of the hub.
图10是图5中螺旋桨中距离桨毂的中心50mm处的C-C剖面的剖视图。Figure 10 is a cross-sectional view of the C-C section of the propeller of Figure 5 at a distance of 50 mm from the center of the hub.
图11是图5中螺旋桨中距离桨毂的中心60mm处的D-D剖面的剖视图。Figure 11 is a cross-sectional view of the D-D section of the propeller of Figure 5 at a distance of 60 mm from the center of the hub.
图12是图5中螺旋桨中距离桨毂的中心70mm处的E-E剖面的剖视图。Figure 12 is a cross-sectional view of the E-E section of the propeller of Figure 5 at a distance of 70 mm from the center of the hub.
图13是图5中螺旋桨中距离桨毂的中心80mm处的F-F剖面的剖视图。Figure 13 is a cross-sectional view of the F-F section of the propeller of Figure 5 at a distance of 80 mm from the center of the hub.
图14是图5中螺旋桨中距离桨毂的中心90mm处的G-G剖面的剖视图。Figure 14 is a cross-sectional view of the G-G section of the propeller of Figure 5 at a distance of 90 mm from the center of the hub.
图15是图5中螺旋桨中距离桨毂的中心100mm处的H-H剖面的剖视图。Figure 15 is a cross-sectional view of the H-H section of the propeller of Figure 5 at a distance of 100 mm from the center of the hub.
图16是图5中螺旋桨中距离桨毂的中心110mm处的I-I剖面的剖视图。Figure 16 is a cross-sectional view of the I-I section of the propeller of Figure 5 at a distance of 110 mm from the center of the hub.
图17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。Figure 17 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.
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."
本发明实施例提供一种螺旋桨，可以是正桨或者是反桨。所谓正桨，指从驱动件如电机尾部向电机头部方向看，顺时针旋转以产生升力的螺旋桨；所谓反桨，指从电机尾部向电机头部方向看，逆时针旋转以产生升力的螺旋桨。所述正桨的结构与所述反桨的结构之间镜像对称，故下文仅以正桨为例说明所述螺旋桨的结构。Embodiments of the present invention provide a propeller, which may be a positive propeller or a reverse propeller. The so-called positive paddle refers to a propeller that rotates clockwise to generate lift from the tail of the motor, such as the tail of the motor. The so-called reverse paddle refers to the propeller that rotates counterclockwise to generate lift from the tail of the motor to the direction of the motor head. . The structure of the positive paddle is mirror symmetrical with the structure of the reverse paddle, so the structure of the propeller will be described below by taking only the positive paddle as an example.
另外，本实施例中出现的上、下等方位用语是以所述螺旋桨安装于所述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。In addition, the terms of the upper and lower orientations appearing in this embodiment are based on the conventional operating posture of the propeller and the aircraft after the propeller is mounted on the aircraft, and should not be considered as limiting.
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.
请一并参阅图1及图2，本发明提供一种螺旋桨100。螺旋桨100包括桨叶20。Referring to FIG. 1 and FIG. 2 together, the present invention provides a propeller 100. The propeller 100 includes a paddle 20.
桨叶20包括压力面21、吸力面22、后缘23、前缘24、桨根25、桨尖26、及后掠部261。桨尖26背离桨根25。吸力面22与压力面21相背。前缘24连接于压力面21和吸力面22的一侧边，后缘23连接于压力面21和吸力面22的另一侧边。后掠部261形成于桨尖26。前缘24自桨根25沿展向朝压力面21所在的一侧倾斜延伸并在靠近桨尖26的部分朝吸力面22所在的一侧反转倾斜。后掠部261自前缘24向后缘23倾斜延伸。其中，压力面21为飞行器正常飞行时桨叶20的朝向地面的表面，吸力面22为飞行器正常飞行时桨叶20的朝向天空的表面。The blade 20 includes a pressure surface 21, a suction surface 22, a trailing edge 23, a leading edge 24, a paddle 25, a tip 26, and a swept portion 261. The paddle tip 26 faces away from the blade root 25. The suction surface 22 is opposite to the pressure surface 21. The leading edge 24 is connected to one side of the pressure surface 21 and the suction surface 22, and the trailing edge 23 is connected to the other side of the pressure surface 21 and the suction surface 22. The swept portion 261 is formed at the tip end 26. The leading edge 24 extends obliquely from the side of the paddle root 25 toward the side where the pressure surface 21 is located, and is inclined obliquely toward the side where the suction surface 22 is located at a portion close to the blade tip 26. The swept portion 261 extends obliquely from the leading edge 24 to the trailing edge 23. Wherein, the pressure surface 21 is a surface facing the ground of the blade 20 during normal flight of the aircraft, and the suction surface 22 is a surface facing the sky of the blade 20 when the aircraft is normally flying.
本发明的螺旋桨100的前缘24自桨根25沿展向朝压力面21所在的一侧倾斜延伸并在靠近桨尖26的部分朝吸力面22所在的一侧反转倾斜，后掠部261自前缘24向后缘23倾斜延伸，采用该桨叶20的螺旋桨100能够在减少空气阻力，提高拉力和效率， 增加了飞行器的继航距离并提高了飞行器的飞行性能的同时，还减少了桨叶20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 leading edge 24 of the propeller 100 of the present invention extends obliquely from the paddle root 25 toward the side where the pressure surface 21 is located, and is inclined obliquely toward the side where the suction surface 22 is located near the blade tip 26, and the swept portion 261 From the leading edge 24 to the trailing edge 23, the propeller 100 using the blade 20 can reduce the air resistance, increase the pulling force and efficiency, increase the flight distance of the aircraft and improve the flight performance of the aircraft, and reduce the paddle. The noise generated by the blade 20 during operation makes the aircraft quieter when hovering, improving the user experience.
请一并参阅图1至图4，本实施例中，可选地，桨叶20在桨尖26的位置形成回弯处262，前缘24自回弯处262沿展向向吸力面22所在的一侧倾斜延伸。回弯处262的位置用MM表示。Referring to FIG. 1 to FIG. 4 together, in the embodiment, the paddle 20 optionally forms a back bend 262 at the position of the blade tip 26, and the leading edge 24 is located at the return bend 262 along the direction of the suction face 22 One side of the slope extends. The position of the return bend 262 is indicated by MM.
本实施例中，螺旋桨100还包括桨毂10，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。回弯处262距离桨毂10的中心为螺旋桨100的半径的90.9％。由此，回弯处262远离桨毂10的中心，提升桨叶20的整体美观。In the present embodiment, the propeller 100 further includes a hub 10 having at least two blades 20, and at least two blades 20 are coupled to the hub 10 and are centrally symmetric about the center of the hub 10. Thereby, the balance of the propeller 100 can be improved. The return bend 262 is 90.9% of the center of the hub 10 that is the radius of the propeller 100. Thus, the bend back 262 is away from the center of the hub 10, enhancing the overall aesthetics of the blade 20.
本实施例中，可选地，前缘24外凸形成有靠近桨根25的呈曲面状的前缘拱起部241；或/和，后缘23外凸形成有靠近桨根25的呈曲面状的后缘拱起部231。In this embodiment, optionally, the leading edge 24 is convexly formed with a curved leading edge arching portion 241 near the paddle 25; or/and the trailing edge 23 is convexly formed with a curved surface near the paddle 25 The trailing edge arched portion 231.
具体地，前缘24外凸形成有靠近桨根25的呈曲面状的前缘拱起部241；或者，后缘23外凸形成有靠近桨根25的呈曲面状的后缘拱起部231；或者，前缘24外凸形成有靠近桨根25的呈曲面状的前缘拱起部241，且后缘23外凸形成有靠近桨根25的呈曲面状的后缘拱起部231，以起到进一步提高桨叶20的拉力的效果。Specifically, the leading edge 24 is convexly formed with a curved leading edge arching portion 241 near the paddle 25; or the trailing edge 23 is convexly formed with a curved trailing edge arching portion 231 near the paddle 25. Or, the leading edge 24 is convexly formed with a curved leading edge bulging portion 241 near the paddle 25, and the trailing edge 23 is convexly formed with a curved trailing edge bulging portion 231 near the paddle root 25, In order to further increase the pulling force of the blade 20.
其中，桨毂10可以为圆筒状，或桨毂10的截面可以为椭圆形、菱形等形状。桨毂10中心设有连接孔，连接孔用于套设在电机的输出端上。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。The hub 10 may have a cylindrical shape, or the cross section of the hub 10 may have an elliptical shape, a rhombus shape or the like. The center of the hub 10 is provided with a connecting hole for arranging on the output end of the motor. The blade 20 may be in the form of a strip, the blade 20 being coupled to the hub 10 and extending in the radial direction of the hub 10.
请参阅图5，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J-J，前缘24具有平行于中轴线J-J的前缘切线K-K，后缘23具有平行于中轴线J-J的后缘切线L-L。后掠部261位于前缘切线K-K与后缘切线L-L之间。由此，后掠部261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外壳上的湍流及下洗气流，在减小螺旋桨100的空气阻力，提高飞行器的可操纵性，使飞行器更加平稳的同时进一步减小飞行器整体的噪音。Referring to FIG. 5, in the present embodiment, optionally, the blade 20 has a central axis JJ passing through the center of the hub 10, the leading edge 24 has a leading edge tangent KK parallel to the central axis JJ, and the trailing edge 23 has parallel The tangent to the trailing edge of the center axis JJ is LL. The swept portion 261 is located between the leading edge tangent K-K and the trailing edge tangent L-L. Thereby, the swept portion 261 can reduce the turbulence and the downwashing flow generated by the blade 20, thereby reducing the turbulence and the downwashing airflow hitting the outer casing of the aircraft, reducing the air resistance of the propeller 100, and improving the maneuverability of the aircraft. To make the aircraft more stable while further reducing the overall noise of the aircraft.
本实施例中，可选地，吸力面22和压力面21均为曲面。吸力面22和压力面21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外壳，从而减小飞行器整体的噪音。In this embodiment, optionally, the suction surface 22 and the pressure surface 21 are curved surfaces. The suction surface 22 and the pressure surface 21 are curved aerodynamic shapes, which can avoid turbulence generated by various parts of the blade 20 and the downwashing airflow directly impacting the outer casing of the aircraft, thereby reducing the overall noise of the aircraft.
请一并参阅表1及图5-6，本实施例中，后掠部261自前缘24向后缘23倾斜延伸。具体地，横坐标Blade Radius(mm)表示沿展向方向上桨叶20的某一位置(比如MM处)距离桨毂10中心的距离。起始点为桨毂10中心，此时桨叶20距离桨毂10的中心的距离为0mm，终点为桨尖26的自由端261，此时桨叶20距离桨毂10的中心的距离为110mm。纵坐标Sweep Length(mm)(后掠的距离，后掠部261的倾斜程度)表示桨叶 20的截面弦长的1/2处的点相对中轴线J-J的距离。由于实施例的攻角α均小于25度，桨叶20的截面弦长的1/2处的点与图5中的俯视视角的桨叶20的1/2处的点差别较小，故用图1中的俯视视角的桨叶20的1/2处的点相对中轴线J-J的距离来表示Sweep Length。其中，纵坐标Sweep Length(mm)的正值为后掠，负值为前掠。Referring to Table 1 and FIG. 5-6 together, in the present embodiment, the swept portion 261 extends obliquely from the leading edge 24 toward the trailing edge 23. Specifically, the abscissa Blade Radius (mm) represents the distance from the center of the hub 10 at a certain position (such as MM) of the blade 20 in the spanwise direction. 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, and the end point is the free end 261 of the blade tip 26, at which time the distance of the blade 20 from the center of the hub 10 is 110 mm. The Sweep Length (mm) (the swept distance, the degree of inclination of the swept portion 261) indicates the distance of the point at 1/2 of the chord length of the blade 20 with respect to the center axis J-J. Since the angle of attack α of the embodiment is less than 25 degrees, the point at 1/2 of the chord length of the blade 20 is smaller than the point at 1/2 of the blade 20 of the top view in FIG. 5, so The distance of the point at 1/2 of the blade 20 of the top view in FIG. 1 with respect to the central axis JJ represents the Sweep Length. Among them, the positive value of the Sweep Length (mm) is swept back, and the negative value is swept forward.
表1Table 1
Figure PCTCN2017118671-appb-000001
Figure PCTCN2017118671-appb-000001
由表1可知，在桨叶20距离桨毂10的中心的距离为90.75mm时，后掠部261开始自前缘24向后缘23倾斜延伸。在多个桨叶20同时工作时，后掠部261有规律地自前缘24向后缘23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，并减少打到飞行器外壳上的湍流及下洗气流，减小桨叶20受到的空气阻力，提高飞行器的可操纵性，使飞行器更加平稳，同时，进一步减小了由于湍流及下洗气流冲击飞行器外壳产生的噪音。As can be seen from Table 1, when the distance of the blade 20 from the center of the hub 10 is 90.75 mm, the swept portion 261 begins to extend obliquely from the leading edge 24 toward the trailing edge 23. When the plurality of blades 20 are simultaneously operated, the swept portion 261 regularly extends obliquely from the leading edge 24 to the trailing edge 23, which can reduce turbulence and downwashing due to interaction of the plurality of blades 20, and reduce the hitting The turbulence and downwashing airflow to the outer casing of the aircraft reduces the air resistance experienced by the blade 20, improves the maneuverability of the aircraft, and makes the aircraft more stable. At the same time, the turbulence and the downwashing airflow are further reduced to impact the outer casing of the aircraft. noise.
请一并参阅图5、图7及表2，本实施例中，前缘24自回弯处262沿展向向吸力面22所在的一侧倾斜延伸。具体地，横坐标Blade Radius(mm)表示沿展向方向上桨叶20的某一位置(比如MM处)距离桨毂10中心的距离。起始点为桨毂10中心，此时桨叶20距离桨毂10的中心的距离为0mm，终点为桨尖26的自由端261，此时桨叶20距离桨毂10的中心的距离为110mm。纵坐标Anhedral Length(mm)(上反的距离，前缘24的倾斜程度)表示桨叶20的截面弦长的1/2处的点相对穿过桨毂10的中心的水平参考线的距离。其中，纵坐标Anhedral Length(mm)的正值为上反，负值为下反。Referring to FIG. 5, FIG. 7 and Table 2 together, in the present embodiment, the leading edge 24 extends obliquely from the return bend 262 along the side where the suction surface 22 is located. Specifically, the abscissa Blade Radius (mm) represents the distance from the center of the hub 10 at a certain position (such as MM) of the blade 20 in the spanwise direction. 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, and the end point is the free end 261 of the blade tip 26, at which time the distance of the blade 20 from the center of the hub 10 is 110 mm. The ordinate Anhedral Length (mm) (the distance of the upper reverse, the degree of inclination of the leading edge 24) represents the distance of the point at 1/2 of the chord length of the blade 20 with respect to the horizontal reference line passing through the center of the hub 10. 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2Table 2
Figure PCTCN2017118671-appb-000002
Figure PCTCN2017118671-appb-000002
Figure PCTCN2017118671-appb-000003
Figure PCTCN2017118671-appb-000003
由表2可知，在桨叶20距离桨毂10的中心的距离为90.75mm时，前缘24开始沿展向向吸力面22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90.75mm时上反。前缘24自回弯处262沿展向向吸力面22所在的一侧倾斜延伸的程度加大。在多个桨叶20同时工作时，前缘24有规律地自回弯处262沿展向向吸力面22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，并减少打到飞行器外壳上的湍流及下洗气流，另外，还能够额定桨叶20的升力点，使飞行器能自动修正飞行姿态，增加了飞行器的惯性稳定性，使飞行器飞行时更加平稳，同时，进一步减小了由于湍流及下洗气流冲击飞行器外壳产生的噪音。As can be seen from Table 2, when the distance between the blade 20 and the center of the hub 10 is 90.75 mm, the leading edge 24 begins to extend obliquely along the side where the suction surface 22 is located, that is, the blade 20 is spaced from the hub 10. When the distance of the center is 90.75mm, it is reversed. The leading edge 24 extends from the bendback 262 to an extent that extends obliquely toward the side on which the suction surface 22 is located. When the plurality of blades 20 are simultaneously operated, the leading edge 24 is regularly inclined from the corner of the curved portion 262 along the side where the suction surface 22 is located, which can reduce the turbulence caused by the interaction of the plurality of blades 20. And the under-washing airflow, and reduce the turbulence and the downwashing airflow hitting the outer casing of the aircraft. In addition, the lifting point of the blade 20 can be rated, so that the aircraft can automatically correct the flight attitude, increase the inertial stability of the aircraft, and make the aircraft fly. The time is more stable, and at the same time, the noise generated by the turbulence and the downwashing airflow impinging on the outer casing of the aircraft is further reduced.
请一并参阅图5及图8，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27.2％处D1，桨叶20的攻角α1为21.64°±2.5°，桨叶20的弦长L1为27.53mm±5mm，以进一步减少螺旋桨100的空气阻力，提高拉力和效率，减小噪音。其中，桨叶20的攻角α1可以为19.14°或21.64°或24.14°，或者是19.64°、20.14°、20.64°、21.14°、22.14°、22.64°、23.14°、23.64°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22.53mm或27.53mm或32.53mm，或者是23.53mm、24.53mm、25.53mm、26.53mm、28.53mm、29.53mm、30.53mm、31.53mm等中的任意一个或上述任意二者之间的数值。Referring to FIG. 5 and FIG. 8 together, in the embodiment, optionally, at an angle of 27.2% of the radius of the propeller 100 from the center of the hub 10, the angle of attack α1 of the blade 20 is 21.64°±2.5°. The chord length L1 of the blade 20 is 27.53 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 19.14° or 21.64° or 24.14°, or any one of 19.64°, 20.14°, 20.64°, 21.14°, 22.14°, 22.64°, 23.14°, 23.64°, and the like. Or the value between any two of the above, the chord length L1 of the blade 20 may be 22.53 mm or 27.53 mm or 32.53 mm, or 23.53 mm, 24.53 mm, 25.53 mm, 26.53 mm, 28.53 mm, 29.53 mm, 30.53 mm. Any one of 31.53 mm or the like or a value between any of the above.
请一并参阅图5及图9，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36.3％处D2，桨叶20的攻角α2为20.43°±2.5°，桨叶20的弦长L2为27.78mm±5mm，以进一步减少螺旋桨100的空气阻力，提高拉力和效率，减小噪音。其中，桨叶20的攻角α2可以为17.93°或20.43°或22.93°，或者是18.43°、18.93°、19.43°、19.93°、20.93°、21.43°、21.93°、22.43°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22.78mm或27.78mm或32.78mm，或者是23.78mm、24.78mm、25.78mm、26.78mm、28.78mm、29.78mm、30.78mm、31.78mm等中的任意一个或上述任意二者之间的数值。Referring to FIG. 5 and FIG. 9 together, in the embodiment, optionally, at an angle D3 from the center of the hub 10 which is 36.3% of the radius of the propeller 100, the angle of attack α2 of the blade 20 is 20.43°±2.5°. The chord length L2 of the blade 20 is 27.78 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 α2 of the blade 20 may be 17.93° or 20.43° or 22.93°, or any one of 18.43°, 18.93°, 19.43°, 19.93°, 20.93°, 21.43°, 21.93°, 22.43°, and the like. Or the value between any two of the above, the chord length L2 of the blade 20 may be 22.78 mm or 27.78 mm or 32.78 mm, or 23.78 mm, 24.78 mm, 25.78 mm, 26.78 mm, 28.78 mm, 29.78 mm, 30.78 mm. Any one of 31.78 mm or the like or a value between any of the above.
请一并参阅图5及图10，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45.5％处D3，桨叶20的攻角α3为19.78°±2.5°，桨叶20的弦长L3 为26.58mm±5mm，以进一步减少螺旋桨100的空气阻力，提高拉力和效率，减小噪音。其中，桨叶20的攻角α3可以为17.28°或19.78°或22.28°，或者是17.78°、18.28°、18.78°、19.28°、20.28°、20.78°、21.28°、21.78°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L3可以为21.58mm或26.58mm或31.58mm，或者是22.58mm、23.58mm、24.58mm、25.58mm、27.58mm、28.58mm、29.58mm、30.58mm等中的任意一个或上述任意二者之间的数值。Referring to FIG. 5 and FIG. 10 together, in the embodiment, optionally, D3 is at a distance of 45.5% of the radius of the propeller 100 from the center of the hub 10, and the angle of attack α3 of the blade 20 is 19.78°±2.5°. The chord length L3 of the blade 20 is 26.58 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 α3 of the blade 20 may be 17.28° or 19.78° or 22.28°, or any one of 17.78°, 18.28°, 18.78°, 19.28°, 20.28°, 20.78°, 21.28°, 21.78°, and the like. Or the value between any two of the above, the chord length L3 of the blade 20 may be 21.58 mm or 26.58 mm or 31.58 mm, or 22.58 mm, 23.58 mm, 24.58 mm, 25.58 mm, 27.58 mm, 28.58 mm, 29.58 mm. Any one of 30.58 mm or the like or a value between any of the above.
请一并参阅图5及图11，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54.6％处D4，桨叶20的攻角α4为17.83°±2.5°，桨叶20的弦长L4为24.75mm±5mm，以进一步减少螺旋桨100的空气阻力，提高拉力和效率，减小噪音。其中，桨叶20的攻角α4可以为15.33°或17.83°或20.33°，或者是15.83°、16.33°、16.83°、17.33°、18.33°、18.83°、19.33°、19.83°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19.75mm或24.75mm或29.75mm，或者是20.75mm、21.75mm、22.75mm、23.75mm、25.75mm、26.75mm、27.75mm、28.75mm等中的任意一个或上述任意二者之间的数值。Referring to FIG. 5 and FIG. 11 together, in the embodiment, optionally, D4 is 54.6% of the radius of the propeller 100 from the center of the hub 10, and the angle of attack α4 of the blade 20 is 17.83°±2.5°. The chord length L4 of the blade 20 is 24.75 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 α4 of the blade 20 may be 15.33° or 17.83° or 20.33°, or any one of 15.83°, 16.33°, 16.83°, 17.33°, 18.33°, 18.83°, 19.33°, 19.83°, and the like. Or the value between any two of the above, the chord length L4 of the blade 20 may be 19.75 mm or 24.75 mm or 29.75 mm, or 20.75 mm, 21.75 mm, 22.75 mm, 23.75 mm, 25.75 mm, 26.75 mm, 27.75 mm. Any one of 28.75 mm or the like or a value between any two of the above.
请一并参阅图5及图12，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63.6％处D5，桨叶20的攻角α5为16.42°±2.5°，桨叶20的弦长L5为22.65mm±5mm，以进一步减少螺旋桨100的空气阻力，提高拉力和效率，减小噪音。其中，桨叶20的攻角α5可以为13.92°或16.42°或18.92°，或者是14.42°、14.92°、15.42°、15.92°、16.92°、17.42°、17.92°、18.42°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17.65mm或22.65mm或27.65mm，或者是18.65mm、19.65mm、20.65mm、21.65mm、23.65mm、24.65mm、25.65mm、26.65mm等中的任意一个或上述任意二者之间的数值。Referring to FIG. 5 and FIG. 12 together, in the embodiment, optionally, at the center of the hub 10, which is 63.6% of the radius of the propeller 100, the angle of attack α5 of the blade 20 is 16.42°±2.5°. The chord length L5 of the blade 20 is 22.65 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 α5 of the blade 20 may be 13.92° or 16.42° or 18.92°, or any one of 14.42°, 14.92°, 15.42°, 15.92°, 16.92°, 17.42°, 17.92°, 18.42°, and the like. Or the value between any two of the above, the chord length L5 of the blade 20 may be 17.65 mm or 22.65 mm or 27.65 mm, or 18.65 mm, 19.65 mm, 20.65 mm, 21.65 mm, 23.65 mm, 24.65 mm, 25.65 mm. Any one of 26.65 mm or the like or a value between any two of the above.
请一并参阅图5及图13，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72.7％处D6，桨叶20的攻角α6为14.97°±2.5°，桨叶20的弦长L6为20.07mm±5mm，以进一步减少螺旋桨100的空气阻力，提高拉力和效率，减小噪音。其中，桨叶20的攻角α6可以为12.47°或14.97°或17.47°，或者是12.97°、13.47°、13.97°、14.47°、15.47°、15.97°、16.47°、16.97°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15.07mm或20.07mm或25.07mm，或者是16.07mm、17.07mm、18.07mm、19.07mm、21.07mm、22.07mm、23.07mm、24.07mm等中的任意一个或上述任意二者之间的数值。Referring to FIG. 5 and FIG. 13 together, in the embodiment, optionally, D6 at the center of the hub 10 is 72.7% of the radius of the propeller 100, and the angle of attack α6 of the blade 20 is 14.97°±2.5°. The chord length L6 of the blade 20 is 20.07 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 α6 of the blade 20 may be 12.47° or 14.97° or 17.47°, or any one of 12.97°, 13.47°, 13.97°, 14.47°, 15.47°, 15.97°, 16.47°, 16.97°, and the like. Or the value between any two of the above, the chord length L6 of the blade 20 may be 15.07 mm or 20.07 mm or 25.07 mm, or 16.07 mm, 17.07 mm, 18.07 mm, 19.07 mm, 21.07 mm, 22.07 mm, 23.07 mm. Any one of 24.07 mm or the like or a value between any two of the above.
请一并参阅图5及图14，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81.8％处D7，桨叶20的攻角α7为13.17°±2.5°，桨叶20的弦长L7 为16.64mm±5mm，以进一步减少螺旋桨100的空气阻力，提高拉力和效率，减小噪音。其中，桨叶20的攻角α7可以为10.67°或13.17°或15.67°，或者是11.17°、11.67°、12.17°、12.67°、13.67°、14.17°、14.67°、15.17°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L7可以为11.64mm或16.64mm或21.64mm，或者是12.64mm、13.64mm、14.64mm、15.64mm、17.64mm、18.64mm、19.64mm、20.64mm等中的任意一个或上述任意二者之间的数值。Referring to FIG. 5 and FIG. 14 together, in the embodiment, optionally, D7 at the center of the hub 10 is 81.8% of the radius of the propeller 100, and the angle of attack α7 of the blade 20 is 13.17°±2.5°. The chord length L7 of the blade 20 is 16.64 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 10.67° or 13.17° or 15.67°, or any one of 11.17°, 11.67°, 12.17°, 12.67°, 13.67°, 14.17°, 14.67°, 15.17°, and the like. Or any value between any two of the above, the chord length L7 of the blade 20 may be 11.64 mm or 16.64 mm or 21.64 mm, or 12.64 mm, 13.64 mm, 14.64 mm, 15.64 mm, 17.64 mm, 18.64 mm, Any one of 19.64 mm, 20.64 mm, etc., or a value between any of the above.
请一并参阅图5及图15，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90.9％处D8，桨叶20的攻角α8为10.68°±2.5°，桨叶20的弦长L8为11.15mm±5mm，以进一步减少螺旋桨100的空气阻力，提高拉力和效率，减小噪音。其中，桨叶20的攻角α8可以为8.18°或10.68°或13.18°，或者是8.68°、9.18°、9.68°、10.18°、11.18°、11.68°、12.18°、12.68°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6.15mm或11.15mm或16.15mm，或者是7.15mm、8.15mm、9.15mm、10.15mm、12.15mm、13.15mm、14.15mm、15.15mm等中的任意一个或上述任意二者之间的数值。Referring to FIG. 5 and FIG. 15 together, in the embodiment, optionally, at the center of the hub 10, which is 90.9% of the radius of the propeller 100, the angle of attack α8 of the blade 20 is 10.68°±2.5°. The chord length L8 of the blade 20 is 11.15 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 8.18° or 10.68° or 13.18°, or any one of 8.68°, 9.18°, 9.68°, 10.18°, 11.18°, 11.68°, 12.18°, 12.68°, and the like. Or the value between any two of the above, the chord length L8 of the blade 20 may be 6.15 mm or 11.15 mm or 16.15 mm, or 7.15 mm, 8.15 mm, 9.15 mm, 10.15 mm, 12.15 mm, 13.15 mm, 14.15 mm. Any one of 15.15 mm or the like or a value between any of the above.
请一并参阅图5及图16，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6.63°±2.5°，桨叶20的弦长L9为3.92mm±2mm，以进一步减少螺旋桨100的空气阻力，提高拉力和效率，减小噪音。其中，桨叶20的攻角α9可以为4.13°或6.63°或9.13°，或者是4.63°、5.13°、5.63°、6.13°、7.13°、7.63°、8.13°、8.63°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1.92mm或3.92mm或5.92mm，或者是2.42mm、2.92mm、3.42mm、4.42mm、4.92mm、5.42mm等中的任意一个或上述任意二者之间的数值。Referring to FIG. 5 and FIG. 16 together, in the embodiment, optionally, at 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 6.63°±2.5°. The chord length L9 of the blade 20 is 3.92 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 4.13° or 6.63° or 9.13°, or any one of 4.63°, 5.13°, 5.63°, 6.13°, 7.13°, 7.63°, 8.13°, 8.63°, and the like. Or the value between any two of the above, the chord length L9 of the blade 20 may be 1.92 mm or 3.92 mm or 5.92 mm, or 2.42 mm, 2.92 mm, 3.42 mm, 4.42 mm, 4.92 mm, 5.42 mm, or the like. Any one or a value between any two of the above.
其中，攻角α是指桨叶20的翼弦与来流速度之间的夹角，弦长L是指桨叶20横截面的长度。Wherein, the angle of attack α refers to the angle between the chord of the blade 20 and the incoming flow velocity, and the chord length L refers to the length of the cross section of the blade 20.
请再次一并参阅图5及图8，本实施例中，可选地，螺旋桨100的直径为220mm±22mm。在距离桨毂10的中心30mm处D1，桨叶20的攻角α1为21.64°，桨叶20的弦长L1为27.53mm。其中，螺旋桨100的直径可以为198mm或220mm或242mm，或者是200mm、205mm、210mm、215mm、225mm、230mm、235mm、240mm等中的任意一个或上述任意二者之间的数值。Please refer to FIG. 5 and FIG. 8 again. In this embodiment, optionally, the diameter of the propeller 100 is 220 mm±22 mm. At an angle D1 of 30 mm from the center of the hub 10, the angle of attack α1 of the blade 20 is 21.64°, and the chord length L1 of the blade 20 is 27.53 mm. The diameter of the propeller 100 may be 198 mm or 220 mm or 242 mm, or any one of 200 mm, 205 mm, 210 mm, 215 mm, 225 mm, 230 mm, 235 mm, 240 mm, or the like, or a value between any two of the above.
请再次一并参阅图5及图9，本实施例中，可选地，螺旋桨100的直径为220mm±22mm。在距离桨毂10的中心40mm处D2，桨叶20的攻角α2为20.43°，桨叶20的弦长L2为27.78mm。其中，螺旋桨100的直径可以为198mm或220mm或242mm， 或者是200mm、205mm、210mm、215mm、225mm、230mm、235mm、240mm等中的任意一个或上述任意二者之间的数值。Please refer to FIG. 5 and FIG. 9 again. In this embodiment, optionally, the diameter of the propeller 100 is 220 mm±22 mm. At an angle D2 40 mm from the center of the hub 10, the angle of attack α2 of the blade 20 is 20.43°, and the chord length L2 of the blade 20 is 27.78 mm. The diameter of the propeller 100 may be 198 mm or 220 mm or 242 mm, or any one of 200 mm, 205 mm, 210 mm, 215 mm, 225 mm, 230 mm, 235 mm, 240 mm, or the like, or a value between any two of the above.
请再次一并参阅图5及图10，本实施例中，可选地，螺旋桨100的直径为220mm±22mm。在距离桨毂10的中心50mm处D3，桨叶20的攻角α3为19.78°，桨叶20的弦长L3为26.58mm。其中，螺旋桨100的直径可以为198mm或220mm或242mm，或者是200mm、205mm、210mm、215mm、225mm、230mm、235mm、240mm等中的任意一个或上述任意二者之间的数值。Please refer to FIG. 5 and FIG. 10 again. In this embodiment, optionally, the diameter of the propeller 100 is 220 mm±22 mm. At an angle D3 of 50 mm from the center of the hub 10, the angle of attack α3 of the blade 20 is 19.78°, and the chord length L3 of the blade 20 is 26.58 mm. The diameter of the propeller 100 may be 198 mm or 220 mm or 242 mm, or any one of 200 mm, 205 mm, 210 mm, 215 mm, 225 mm, 230 mm, 235 mm, 240 mm, or the like, or a value between any two of the above.
请再一并参阅图5及图11，本实施例中，可选地，螺旋桨100的直径为220mm±22mm。在距离桨毂10的中心60mm处D4，桨叶20的攻角α4为17.83°，桨叶20的弦长L4为24.75mm。其中，螺旋桨100的直径可以为198mm或220mm或242mm，或者是200mm、205mm、210mm、215mm、225mm、230mm、235mm、240mm等中的任意一个或上述任意二者之间的数值。Referring to FIG. 5 and FIG. 11 together, in the embodiment, optionally, the diameter of the propeller 100 is 220 mm±22 mm. At an angle of 40 mm from the center of the hub 10, the angle of attack α4 of the blade 20 is 17.83°, and the chord length L4 of the blade 20 is 24.75 mm. The diameter of the propeller 100 may be 198 mm or 220 mm or 242 mm, or any one of 200 mm, 205 mm, 210 mm, 215 mm, 225 mm, 230 mm, 235 mm, 240 mm, or the like, or a value between any two of the above.
再次一并参阅图5及图12，本实施例中，可选地，螺旋桨100的直径为220mm±22mm。在距离桨毂10的中心70mm处D5，桨叶20的攻角α5为16.42°，桨叶20的弦长L5为22.65mm。由此，可进一步减少螺旋桨100的空气阻力，提高拉力和效率，减小噪音。其中，螺旋桨100的直径可以为198mm或220mm或242mm，或者是200mm、205mm、210mm、215mm、225mm、230mm、235mm、240mm等中的任意一个或上述任意二者之间的数值。Referring again to FIG. 5 and FIG. 12, in the present embodiment, optionally, the diameter of the propeller 100 is 220 mm ± 22 mm. At an angle D5 of 70 mm from the center of the hub 10, the angle of attack α5 of the blade 20 is 16.42°, and the chord length L5 of the blade 20 is 22.65 mm. Thereby, the air resistance of the propeller 100 can be further reduced, the pulling force and efficiency can be improved, and noise can be reduced. The diameter of the propeller 100 may be 198 mm or 220 mm or 242 mm, or any one of 200 mm, 205 mm, 210 mm, 215 mm, 225 mm, 230 mm, 235 mm, 240 mm, or the like, or a value between any two of the above.
请再次一并参阅图5及图13，本实施例中，可选地，螺旋桨100的直径为220mm±22mm。在距离桨毂10的中心80mm处D6，桨叶20的攻角α6为14.97°，桨叶20的弦长L6为20.07mm。由此，可进一步减少螺旋桨100的空气阻力，提高拉力和效率，减小噪音。其中，螺旋桨100的直径可以为198mm或220mm或242mm，或者是200mm、205mm、210mm、215mm、225mm、230mm、235mm、240mm等中的任意一个或上述任意二者之间的数值。Please refer to FIG. 5 and FIG. 13 again. In this embodiment, optionally, the diameter of the propeller 100 is 220 mm±22 mm. At an angle of 80 mm from the center of the hub 10, the angle of attack α6 of the blade 20 is 14.97°, and the chord length L6 of the blade 20 is 20.07 mm. Thereby, the air resistance of the propeller 100 can be further reduced, the pulling force and efficiency can be improved, and noise can be reduced. The diameter of the propeller 100 may be 198 mm or 220 mm or 242 mm, or any one of 200 mm, 205 mm, 210 mm, 215 mm, 225 mm, 230 mm, 235 mm, 240 mm, or the like, or a value between any two of the above.
请再次一并参阅图5及图14，本实施例中，可选地，螺旋桨100的直径为220mm±22mm。在距离桨毂10的中心90mm处D7，桨叶20的攻角α7为13.17°，桨叶20的弦长L7为16.64mm。其中，螺旋桨100的直径可以为198mm或220mm或242mm，或者是200mm、205mm、210mm、215mm、225mm、230mm、235mm、240mm等中的任意一个或上述任意二者之间的数值。Please refer to FIG. 5 and FIG. 14 again. In this embodiment, optionally, the diameter of the propeller 100 is 220 mm±22 mm. At an angle of 90 mm from the center of the hub 10, the angle of attack α7 of the blade 20 is 13.17°, and the chord length L7 of the blade 20 is 16.64 mm. The diameter of the propeller 100 may be 198 mm or 220 mm or 242 mm, or any one of 200 mm, 205 mm, 210 mm, 215 mm, 225 mm, 230 mm, 235 mm, 240 mm, or the like, or a value between any two of the above.
请再次一并参阅图5及图15，本实施例中，可选地，螺旋桨100的直径为220mm±22mm。在距离桨毂10的中心100mm处D8，桨叶20的攻角α8为10.68°，桨叶20的弦长L8为11.15mm。其中，螺旋桨100的直径可以为198mm或220mm或242mm， 或者是200mm、205mm、210mm、215mm、225mm、230mm、235mm、240mm等中的任意一个或上述任意二者之间的数值。Please refer to FIG. 5 and FIG. 15 again. In this embodiment, optionally, the diameter of the propeller 100 is 220 mm±22 mm. At an angle D8 of 100 mm from the center of the hub 10, the angle of attack α8 of the blade 20 is 10.68°, and the chord length L8 of the blade 20 is 11.15 mm. The diameter of the propeller 100 may be 198 mm or 220 mm or 242 mm, or any one of 200 mm, 205 mm, 210 mm, 215 mm, 225 mm, 230 mm, 235 mm, 240 mm, or the like, or a value between any two of the above.
请再次一并参阅图5及图16，本实施例中，可选地，螺旋桨100的直径为220mm±22mm。在距离桨毂10的中心110mm处D9，桨叶20的攻角α9为6.63°，桨叶20的弦长L9为3.92mm。由此，可进一步减少螺旋桨100的空气阻力，提高拉力和效率，减小噪音。其中，螺旋桨100的直径可以为198mm或220mm或242mm，或者是200mm、205mm、210mm、215mm、225mm、230mm、235mm、240mm等中的任意一个或上述任意二者之间的数值。Please refer to FIG. 5 and FIG. 16 again. In this embodiment, optionally, the diameter of the propeller 100 is 220 mm±22 mm. At an angle 110 mm from the center of the hub 10, the angle of attack α9 of the blade 20 is 6.63°, and the chord length L9 of the blade 20 is 3.92 mm. Thereby, the air resistance of the propeller 100 can be further reduced, the pulling force and efficiency can be improved, and noise can be reduced. The diameter of the propeller 100 may be 198 mm or 220 mm or 242 mm, or any one of 200 mm, 205 mm, 210 mm, 215 mm, 225 mm, 230 mm, 235 mm, 240 mm, or the like, or a value between any two of the above.
请再一并参阅图1及图5，本实施例中，可选地，桨叶20的螺距为4.8±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4.3英寸或4.8英寸或5.3英寸，或者是4.4英寸、4.5英寸、4.6英寸、4.7英寸、4.9英寸、5.0英寸、5.1英寸、5.2英寸等中的任意一个或上述任意二者之间的数值。Referring to FIG. 1 and FIG. 5 together, in the embodiment, the pitch of the blade 20 is optionally 4.8±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 4.3 inches or 4.8 inches or 5.3 inches, or any one of 4.4 inches, 4.5 inches, 4.6 inches, 4.7 inches, 4.9 inches, 5.0 inches, 5.1 inches, 5.2 inches, etc. The value between any two.
请参阅表3及图17，本实施例提供的螺旋桨100与现有的螺旋桨的测试结果的比对。由表3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能有效减小噪音功率。另外，由图17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 3 and FIG. 17, the comparison between the propeller 100 provided by this embodiment and the test results of the existing propeller. As can be seen from Table 3, 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, 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 the noise power. In addition, as can be seen from the frequency response curve (Frequency (Hz)-Loudness (dB-A)) in FIG. 17, 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3table 3
Figure PCTCN2017118671-appb-000004
Figure PCTCN2017118671-appb-000004
由于反桨的结构与正桨的结构之间镜像对称，对反桨的结构不再赘述。Since the structure of the reverse paddle is mirror symmetrical with the structure of the positive paddle, the structure of the reverse paddle will not be described again.
综上，采用本发明上述实施例的桨叶20的螺旋桨100能够减少空气阻力，提高拉力和效率，增加了飞行器的继航距离并提高了飞行器的飞行性能。同时，相对市面上已有的螺旋桨，在相同的悬停工况声学性能测试条件下，采用该桨叶20的螺旋桨100产生的噪音的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 小噪音功率。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能有效减小噪音功率。In summary, the propeller 100 employing the blade 20 of the above-described embodiment of the present invention can reduce air resistance, increase tension and efficiency, increase the range of the aircraft, and improve the flight performance of the aircraft. At the same time, compared with the existing propellers on the market, under the same hovering performance acoustic performance test conditions, the overall noise generated by the propeller 100 using the blade 20 is lower than that of the existing propeller. Thus, the propeller 100 provided in this embodiment can effectively reduce the noise power. 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 the noise power.
本发明实施例还提供一种动力组件，包括驱动件和本发明任意实施例的螺旋桨100，螺旋桨100通过桨毂10与驱动件连接。其中，螺旋桨100的具体结构与前述实施例类似，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。Embodiments of the present invention also provide a power assembly including a drive member and a propeller 100 of any of the embodiments of the present invention, the propeller 100 being coupled to the drive member via the hub 10. The specific structure of the propeller 100 is similar to the foregoing embodiment, and details are not described herein again. That is, the description of the propeller 100 in the above embodiments and embodiments is equally applicable to the power assembly provided by the embodiment of the present invention.
在本发明的动力组件中，螺旋桨100桨叶20的的前缘24自桨根25沿展向朝压力面21所在的一侧倾斜延伸并在靠近桨尖26的部分朝吸力面22所在的一侧反转倾斜，后掠部261自前缘24向后缘23倾斜延伸。采用该螺旋桨100的动力组件能够在减少空气阻力，提高拉力和效率，增加了飞行器的继航距离并提高了飞行器的飞行性能的同时，还减少了桨叶20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。In the power assembly of the present invention, the leading edge 24 of the propeller 100 blade 20 extends obliquely from the paddle root 25 toward the side where the pressure surface 21 is located and toward the suction tip 22 at a portion adjacent to the blade tip 26. The side is reversed and the swept portion 261 extends obliquely from the leading edge 24 to the trailing edge 23. The power assembly using the propeller 100 can reduce the air resistance, increase the pulling force and efficiency, increase the flight distance of the aircraft and improve the flight performance of the aircraft, and also reduce the noise generated by the blade 20 during operation, so that the aircraft Quiet when hovering, improving the user experience.
本实施例中，可选地，驱动件为电机，电机的KV值为300至800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 is a motor, and the KV value of the motor is 300 to 800 rpm / (minute·volt). Thereby, the dynamic performance of the power unit can be ensured.
本发明实施例还提供一种飞行器，包括机身和本发明任意实施例的动力组件，动力组件与机身连接。其中动力组件的具体结构与前述实施例类似，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。Embodiments of the present invention also provide an aircraft comprising a fuselage and a power assembly of any of the embodiments of the present invention, the power assembly being coupled to the fuselage. The specific structure of the power component is similar to the foregoing embodiment, and details are not described herein again. That is, the description of the propeller 100 in the above embodiments and embodiments is equally applicable to the aircraft provided by the embodiment of the present invention.
本实施例中，可选地，飞行器包括多个动力组件，多个动力组件的转动方向不同。In this embodiment, optionally, the aircraft includes a plurality of power components, and the plurality of power components have different rotation directions.
本实施例中，可选地，飞行器为多旋翼飞行器。In this embodiment, optionally, the aircraft is a multi-rotor aircraft.
在本发明的飞行器中，由于螺旋桨100的桨叶20的前缘24自桨根25沿展向朝压力面21所在的一侧倾斜延伸并在靠近桨尖26的部分朝吸力面22所在的一侧反转倾斜，后掠部261自前缘24向后缘23倾斜延伸，采用该螺旋桨100的飞行器能够在减少空气阻力，提高拉力和效率，增加了飞行器的继航距离并提高了飞行器的飞行性能的同时，还减少了桨叶20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。In the aircraft of the present invention, since the leading edge 24 of the blade 20 of the propeller 100 extends obliquely from the paddle root 25 toward the side where the pressure surface 21 is located, and the portion adjacent to the blade tip 26 toward the suction surface 22 The side is reversed and the swept portion 261 extends obliquely from the leading edge 24 to the trailing edge 23. The aircraft using the propeller 100 can reduce air resistance, increase pulling force and efficiency, increase the range of the aircraft and improve the flight performance of the aircraft. At the same time, the noise generated by the blade 20 during operation is also reduced, which makes the aircraft quieter when hovering and improves 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 (21)

  1. 一种螺旋桨，所述螺旋桨包括桨叶，其特征在于：A propeller comprising a paddle characterized by:
    所述桨叶包括桨根、背离所述桨根的桨尖、压力面、与所述压力面相背的吸力面、连接于所述压力面和所述吸力面一侧边的前缘、连接于所述压力面和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 paddle root, a blade tip facing away from the blade root, a pressure surface, a suction surface opposite to the pressure surface, a leading edge connected to the pressure surface and a side of the suction surface, and connected to a pressure surface and a trailing edge of the other side of the suction surface, and a swept portion formed at the tip of the blade;
    所述前缘自所述桨根沿展向朝所述压力面所在的一侧倾斜延伸并在靠近所述桨尖的部分朝所述吸力面所在的一侧反转倾斜，所述后掠部自所述前缘向所述后缘倾斜延伸。The leading edge extends obliquely from the side of the paddle toward the side where the pressure face is located, and is inclined obliquely toward a side of the suction face at a portion close to the tip end, the swept portion The front edge extends obliquely toward the trailing edge.
  2. 根据权利要求1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沿展向向所述吸力面所在的一侧倾斜延伸。The propeller according to claim 1, wherein said blade forms a back bend at a position of said tip, said leading edge being oriented from said return bend toward said suction side The side is inclined to extend.
  3. 根据权利要求2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；或/和The propeller according to claim 2, wherein said leading edge is convexly formed with a curved leading edge arch portion near said paddle; or/and
    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。The trailing edge is convexly formed with a curved trailing edge arch portion near the paddle.
  4. 根据权利要求2所述的螺旋桨，其特征在于，所述螺旋桨还包括桨毂，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。The propeller according to claim 2, wherein said propeller further comprises a hub, said blades being at least two, at least two of said blades being coupled to said hub and associated with said hub The center is center-symmetrical.
  5. 根据权利要求4所述的螺旋桨，其特征在于，所述回弯处距离所述桨毂的中心为所述螺旋桨的半径的90.9％。The propeller according to claim 4, wherein the center of the back bend from the hub is 90.9% of the radius of the propeller.
  6. 根据权利要求1所述的螺旋桨，其特征在于，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。The propeller of claim 1 wherein said blade has a central axis passing through a center of said hub, said leading edge having a leading edge tangent parallel to said central axis, said trailing edge A trailing edge tangent parallel to the central axis, the swept portion being between the leading edge tangent and the trailing edge tangent.
  7. 根据权利要求1所述的螺旋桨，其特征在于，所述吸力面和所述压力面均为曲面。The propeller according to claim 1, wherein the suction surface and the pressure surface are both curved surfaces.
  8. 根据权利要求1-7任一项所述的螺旋桨，其特征在于，在距离所述桨毂的中心 为所述螺旋桨的半径的45.5％处，所述桨叶的攻角为19.78°±2.5°，所述桨叶的弦长为26.58mm±5mm。A propeller according to any one of claims 1 to 7, wherein the blade has an angle of attack of 19.78° ± 2.5° at a distance of 45.5% of the radius of the propeller from the center of the hub. The chord length of the blade is 26.58 mm ± 5 mm.
  9. 根据权利要求8所述的螺旋桨，其特征在于：A propeller according to claim 8 wherein:
    所述螺旋桨的直径为220mm±22mm；The diameter of the propeller is 220 mm ± 22 mm;
    在距离所述桨毂的中心50mm处，所述桨叶的攻角为19.78°，所述桨叶的弦长为26.58mm。At an angle of 50 mm from the center of the hub, the blade has an angle of attack of 19.78° and the blade has a chord length of 26.58 mm.
  10. 根据权利要求1-7任意一项所述的螺旋桨，其特征在于，在距离所述桨毂的中心为所述螺旋桨的半径的54.6％处，所述桨叶的攻角为17.83°±2.5°，所述桨叶的弦长为24.75mm±5mm。A propeller according to any one of claims 1 to 7, wherein the blade has an angle of attack of 17.83 ° ± 2.5 ° at a distance of 54.6% of the radius of the propeller from the center of the hub. The chord length of the blade is 24.75 mm ± 5 mm.
  11. 根据权利要求10所述的螺旋桨，其特征在于：A propeller according to claim 10, wherein:
    所述螺旋桨的直径为220mm±22mm；The diameter of the propeller is 220 mm ± 22 mm;
    在距离所述桨毂的中心60mm处，所述桨叶的攻角为17.83°，所述桨叶的弦长为24.75mm。At an angle of 60 mm from the center of the hub, the blade has an angle of attack of 17.83° and the blade has a chord length of 24.75 mm.
  12. 根据权利要求1-7任意一项所述的螺旋桨，其特征在于，在距离所述桨毂的中心为所述螺旋桨的半径的63.6％处，所述桨叶的攻角为16.42°±2.5°，所述桨叶的弦长为22.65mm±5mm。A propeller according to any one of claims 1 to 7, wherein the blade has an angle of attack of 16.42 ° ± 2.5 ° at a distance of 63.6% of the radius of the propeller from the center of the hub. The chord length of the blade is 22.65 mm ± 5 mm.
  13. 根据权利要求12所述的螺旋桨，其特征在于：A propeller according to claim 12, wherein:
    所述螺旋桨的直径为220mm±22mm；The diameter of the propeller is 220 mm ± 22 mm;
    在距离所述桨毂的中心70mm处，所述桨叶的攻角为16.42°，所述桨叶的弦长为22.65mm。At an angle of 70 mm from the center of the hub, the blade has an angle of attack of 16.42° and the blade has a chord length of 22.65 mm.
  14. 根据权利要求1-7任意一项所述的螺旋桨，其特征在于，在距离所述桨毂的中心为所述螺旋桨的半径的72.7％处，所述桨叶的攻角为14.97°±2.5°，所述桨叶的弦长为20.07mm±5mm。A propeller according to any one of claims 1 to 7, wherein the blade has an angle of attack of 14.97 ° ± 2.5 ° at 72.7% of the radius of the propeller from the center of the hub. The chord length of the blade is 20.07 mm ± 5 mm.
  15. 根据权利要求14所述的螺旋桨，其特征在于：A propeller according to claim 14 wherein:
    所述螺旋桨的直径为220mm±22mm；The diameter of the propeller is 220 mm ± 22 mm;
    在距离所述桨毂的中心80mm处，所述桨叶的攻角为14.97°，所述桨叶的弦长为20.07mm。At an angle of 80 mm from the center of the hub, the blade has an angle of attack of 14.97° and the blade has a chord length of 20.07 mm.
  16. 根据权利要求1-7中任一所述的螺旋桨，其特征在于，所述桨叶的螺距为4.8±0.5英寸。A propeller according to any one of claims 1-7, wherein the pitch of the blade is 4.8 ± 0.5 inches.
  17. 一种动力组件，包括驱动件和权利要求1-16中任意一项所述的螺旋桨，其特征在于，所述螺旋桨通过所述桨毂与所述驱动件连接。A power assembly comprising a drive member and a propeller according to any of claims 1-16, wherein the propeller is coupled to the drive member via the hub.
  18. 根据权利要求17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300至800转/(分钟·伏特)。The power pack according to claim 17, wherein said driving member is a motor having a KV value of 300 to 800 rpm / (minute volt).
  19. 一种飞行器，其特征在于，包括机身和权利要求17或18所述的动力组件，所述动力组件与所述机身连接。An aircraft characterized by comprising a fuselage and the power assembly of claim 17 or 18, the power assembly being coupled to the fuselage.
  20. 根据权利要求19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。The aircraft of claim 19 wherein said aircraft includes a plurality of power assemblies, said plurality of power assemblies having different directions of rotation.
  21. 根据权利要求19所述的飞行器，其特征在于，所述飞行器为多旋翼飞行器。The aircraft of claim 19 wherein said aircraft is a multi-rotor aircraft.
PCT/CN2017/118671 2017-12-26 2017-12-26 Propeller, power assembly and aircraft WO2019127028A1 (en)

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