WO2020024488A1 - Hélice, ensemble d'alimentation et véhicule aérien sans pilote - Google Patents

Hélice, ensemble d'alimentation et véhicule aérien sans pilote Download PDF

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Publication number
WO2020024488A1
WO2020024488A1 PCT/CN2018/116720 CN2018116720W WO2020024488A1 WO 2020024488 A1 WO2020024488 A1 WO 2020024488A1 CN 2018116720 W CN2018116720 W CN 2018116720W WO 2020024488 A1 WO2020024488 A1 WO 2020024488A1
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WO
WIPO (PCT)
Prior art keywords
blade
propeller
hub
center
chord length
Prior art date
Application number
PCT/CN2018/116720
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English (en)
Chinese (zh)
Inventor
张海浪
孙维
罗东东
Original Assignee
深圳市道通智能航空技术有限公司
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Publication of WO2020024488A1 publication Critical patent/WO2020024488A1/fr

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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/32—Rotors
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/32—Rotors
    • B64C27/46—Blades
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U30/00—Means for producing lift; Empennages; Arrangements thereof
    • B64U30/20—Rotors; Rotor supports
    • B64U30/29—Constructional aspects of rotors or rotor supports; Arrangements thereof
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U50/00—Propulsion; Power supply
    • B64U50/10—Propulsion
    • B64U50/19—Propulsion using electrically powered motors
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U10/00—Type of UAV
    • B64U10/10—Rotorcrafts
    • B64U10/13—Flying platforms
    • B64U10/14—Flying platforms with four distinct rotor axes, e.g. quadcopters
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U2201/00—UAVs characterised by their flight controls
    • B64U2201/20—Remote controls

Definitions

  • the present application relates to the technical field of unmanned aerial vehicle manufacturing, and in particular, to a propeller, a power assembly, and an unmanned aerial vehicle.
  • the propellers on unmanned aerial vehicles are used to convert the rotational energy of the motor output shaft into thrust or lift to achieve the take-off, steering, and hovering of unmanned aerial vehicles.
  • the main source of power, and the aerodynamic efficiency of the propeller directly affects the life of the UAV.
  • the blades of the existing propellers are mostly flat plate-like structures, and the shape of the blades are mostly wide roots and narrow tips, that is, the width of the blade near the hub is larger, and the width of the blade far from the hub is smaller .
  • the existing shape of the blade profile results in low aerodynamic efficiency of the propeller, and high resistance to the flight of the unmanned aerial vehicle, which eventually leads to the problems of low flying speed, short endurance time, and high noise level during the flight of the unmanned aerial vehicle, which seriously affects unmanned aircraft. Flight performance of the aircraft.
  • the present application provides a propeller, a power assembly and an unmanned aerial vehicle, which can improve the endurance time of the propeller and reduce the noise level.
  • the present application provides a propeller including a hub and a blade connected to the hub.
  • the blade includes an upper blade surface, a lower blade surface, a leading edge, and a trailing edge.
  • the leading edge and trailing edge are located on both sides of the blade, the leading edge and the trailing edge connect the upper blade surface and the lower blade surface, the radius of the hub is r, and the radius of the propeller Is R, where:
  • the maximum relative camber of the blade at a position r-30% ⁇ R from the center of the hub is 5% ⁇ 0.3%;
  • the maximum relative camber of the blade is 5.8% ⁇ 0.1%
  • the maximum relative camber of the blade is at a position of 90% ⁇ R to 100% ⁇ R from the center of the hub; 4.8% ⁇ 0.1%;
  • the maximum relative camber of the blade is the ratio of the maximum camber of the airfoil of the blade to the chord length of the blade.
  • the maximum relative camber of the blade is 5% at a position r-30% ⁇ R from the center of the hub;
  • the maximum relative camber of the blade is 4.8%.
  • the position of the maximum camber of the blade is a chord length 38.5% ⁇ 5% from the leading edge;
  • the position of the maximum camber of the blade is a chord length 43.5% ⁇ 0.3% from the leading edge.
  • the maximum camber position of the blade is a chord length 35.5% ⁇ 0.3% from the leading edge.
  • the maximum relative thickness of the blade is 11% ⁇ 0.5%
  • the maximum relative thickness of the blade is 5.1% ⁇ 0.3%;
  • the maximum relative thickness of the paddle at a position 30% ⁇ R to 90% ⁇ R from the center of the hub is 7.1% ⁇ 0.3%;
  • the maximum relative thickness of the blade is the ratio of the maximum thickness of the airfoil of the blade to the chord length of the blade.
  • the position of the maximum thickness of the blade is a chord length 27.5% ⁇ 0.5% from the leading edge;
  • the position of the maximum thickness of the blade is a chord length 18% ⁇ 0.3% from the leading edge;
  • the position of the maximum thickness of the blade is a chord length 30.5% ⁇ 0.3% from the leading edge.
  • the twist angle of the blade is 20 ° ⁇ 0.5 °;
  • the twist angle of the blade is 15 ° ⁇ 0.5 °;
  • the twist angle of the blade is 13 ° ⁇ 0.3 °;
  • the twist angle of the blade is 10.5 ° ⁇ 0.3 °;
  • the twist angle of the blade is 16 ° ⁇ 0.5 °.
  • the twist angle of the blade is 10 ° ⁇ 0.3 °.
  • the ratio of the chord length of the blade to the diameter of the propeller is 8% ⁇ 0.3% at a position r-30% ⁇ R from the center of the hub;
  • the ratio of the chord length of the blade to the diameter of the propeller is 9.5% ⁇ 0.1%;
  • the ratio of the chord length of the blade to the diameter of the propeller is 7.6% ⁇ 0.05%;
  • the ratio of the chord length of the blade to the diameter of the propeller is 6.2% ⁇ 0.05%.
  • the ratio of the chord length of the blade to the diameter of the propeller is 1.9% ⁇ 0.05%.
  • the upper leaf surface, the lower leaf surface, and the leading edge surface are all smooth curved surfaces, and the upper leaf surface, the lower leaf surface, and the leading edge surface are And a smooth transition from the edge surface of the trailing edge.
  • the Reynolds number of the propeller ranges from 10 4 to 5 ⁇ 10 5 .
  • the present application further provides a power assembly, which includes a motor and a propeller as described above, and a hub of the propeller is connected to an output shaft of the motor.
  • an embodiment of the present application further provides an unmanned aerial vehicle, which includes a fuselage, an airframe connected to the airframe, and the above-mentioned power component installed on the airframe.
  • FIG. 2 is a top view of a propeller provided in an embodiment of the present application.
  • FIG. 3 is a front view of the propeller shown in FIG. 2;
  • FIG. 4 is a sectional view of a blade of the propeller shown in FIG. 2;
  • FIG. 5 is a cross-sectional view of the A-A cross section of the propeller shown in FIG. 2;
  • FIG. 6 is a cross-sectional view of a B-B cross section of the propeller shown in FIG. 2;
  • FIG. 7 is a cross-sectional view of the C-C cross section of the propeller shown in FIG. 2;
  • FIG. 8 is a cross-sectional view of the D-D section of the propeller shown in FIG. 2;
  • Fig. 10 is a cross-sectional view taken along the F-F section of the propeller shown in Fig. 2.
  • the propeller provided in the embodiments of the present application is a motor with high aerodynamic efficiency and low noise level.
  • the propeller is mounted on the motor, and can be applied to any application field of mechatronics, especially to various motor-driven applications.
  • On movable objects including but not limited to unmanned aerial vehicles (UAVs), ships, and robots.
  • UAVs unmanned aerial vehicles
  • an unmanned aerial vehicle is taken as an example for description. Applying the propeller provided in the embodiment of the present application to an unmanned aerial vehicle can effectively extend the hovering time of the unmanned aerial vehicle and reduce the noise level of the unmanned aerial vehicle.
  • FIG. 1 is a schematic diagram of an unmanned aerial vehicle according to an embodiment of the present application.
  • the structure of the unmanned aerial vehicle 40 includes a fuselage 41, four arms 42 extending from the fuselage 41 and connected to the fuselage 41, and a power assembly 30 respectively mounted on each of the arms 42. That is, the unmanned aerial vehicle 40 of the present application is a quadrotor unmanned aerial vehicle, and the number of the power components 30 is four.
  • the unmanned aerial vehicle 40 may be any other suitable type of rotary unmanned aerial vehicle, such as a double-rotor unmanned aerial vehicle, a six-rotor unmanned aerial vehicle, and the like. Where the power pack 30 is applied to other types of unmanned aerial vehicles, the number of the power pack 30 may be changed according to actual needs, which is not limited in the embodiment of the present application.
  • the unmanned aerial vehicle 40 may further include a gimbal (not shown), which is connected to the fuselage 41 and is located at the bottom of the fuselage 41.
  • the gimbal is used to carry a high-definition digital camera or other video cameras.
  • the device is used to eliminate the disturbance of the high-definition digital camera or other camera device, and to ensure that the video captured by the camera or other camera device is clear and stable.
  • the arm 42 is fixedly connected to the body 41.
  • the arm 42 is integrally formed with the body 41.
  • the arm 42 may also be connected to the body 41 in a manner that it can be unfolded or folded relative to the body 41.
  • the arm 42 may be connected to the main body 41 through a rotating shaft mechanism, so that the arm 42 can be unfolded or folded relative to the main body 41.
  • the power assembly 30 includes a motor 31 and a propeller 100 driven by the motor 31.
  • the propeller 100 is installed on the output shaft of the motor 31.
  • the propeller 100 is driven by the motor 31 to generate an unmanned aerial vehicle. 40 lift or thrust for flight.
  • the motor 31 may be any suitable type of motor, such as a brushed motor, a brushless motor, a DC motor, a stepper motor, an AC induction motor, and the like.
  • the power assembly 30 of the present application further includes an electronic governor (not shown) disposed in a cavity formed by the fuselage 41 or the arm 42, and the electronic governor is used to generate an electronic governor according to an accelerator controller or an accelerator generator.
  • the throttle signal generates a motor control signal for controlling the rotation speed of the motor to obtain a flying speed or a flying attitude required by the unmanned aerial vehicle.
  • the throttle controller or the throttle generator may be a flight control module of an unmanned aerial vehicle.
  • the flight control module senses the environment around the UAV through various sensors and controls the flight of the UAV.
  • the flight control module may be a processing module (Application Unit), an Application Specific Integrated Circuit (ASIC), or a Field Programmable Gate Array (FPGA).
  • the UAV's flight control module sends a throttle signal to the electric control board.
  • the electric control board receives the throttle signal, generates and sends the signal to the motor for The motor performs motor control signals such as starting and controlling the rotation speed of the motor.
  • FIG. 2 is a top view of a propeller provided in an embodiment of the present application.
  • FIG. 3 is a front view of the propeller in FIG. 2.
  • 4 is a cross-sectional view of a blade of the propeller in FIG. 2.
  • Fig. 5 is a cross-sectional view of the A-A cross section of the propeller in Fig. 2.
  • Fig. 6 is a cross-sectional view taken along the B-B section of the propeller in Fig. 2.
  • Fig. 7 is a cross-sectional view taken along the C-C section of the propeller in Fig. 2.
  • Fig. 8 is a cross-sectional view taken along the D-D section of the propeller in Fig. 2.
  • FIG. 9 is a cross-sectional view of the E-E cross section of the propeller in FIG. 2.
  • Fig. 10 is a cross-sectional view of the F-F cross section of the propeller in Fig. 2.
  • an embodiment of the present application provides a propeller 100 including a hub 10 and at least two blades 20 connected to the hub 10 (the two blades are taken as an example in the figure. Description).
  • the at least two blades 20 are fixedly connected to the hub 10.
  • the at least two blades 20 are integrally formed with the hub 10.
  • the at least two blades 20 may also be connected to the hub 10 in a manner of being unfolded or folded relative to the hub 10.
  • the at least two blades 20 may be connected to the hub 10 through a rotating shaft, respectively, so as to realize the expansion or folding of the at least two blades 20 relative to the hub 10.
  • the hub 10 is used to fixedly connect the propeller 100 to an output shaft of the motor 31.
  • the propeller hub 10 is provided with internal threads, and the output shaft of the motor 31 is provided with external threads corresponding to the internal threads. Through the cooperation of the internal and external threads, The screw connection between the propeller 100 and the motor 31 is realized.
  • the output shaft of the motor 31 can also be locked in the propeller hub 10 by a screw lock, or the output shaft of the motor 31 can be connected to the propeller hub 10 by knurling.
  • a groove may be provided on the motor 31, and a claw portion matching the groove is provided on the propeller 100.
  • the propeller 100 is rotationally connected to the motor 31, and the claw portion on the propeller 100 is connected to the motor 31.
  • the latching of the upper groove realizes the connection between the propeller 100 and the motor 31.
  • the paddle 20 includes an upper blade surface, a lower blade surface, a leading edge 21 and a trailing edge 22, the leading edge 21 and the trailing edge 22 are located on both sides of the paddle 20, and the leading edge 21 and the trailing edge 22 connect the upper and lower leaves. surface.
  • the maximum relative camber of the blade 20 is 5% ⁇ 0.3%, and the maximum relative thickness of the blade 20 is 11% ⁇ 0.5 %. In some embodiments, the maximum relative camber of the blade 20 is 5%, and the maximum relative thickness of the blade 20 is 11%. In some embodiments, the position of the maximum camber of the blade 20 is a chord length of 38.5% ⁇ 0.5% from the leading edge 21. In some embodiments, the position of the maximum thickness of the paddle 20 is a chord length of 27.5% ⁇ 0.5% from the leading edge.
  • the maximum relative camber of the blade 20 is 4.8% ⁇ 0.1%, and the maximum relative thickness of the blade 20 is 5.1 % ⁇ 0.3%. In some embodiments, the maximum relative camber of the blade 20 is 4.8%, and the maximum relative thickness of the blade 20 is 5.1%. In some embodiments, the position of the maximum camber of the blade 20 is a chord length 213.55% ⁇ 0.3% from the leading edge. In some embodiments, the position of the maximum thickness of the blade 20 is a chord length 210.5% ⁇ 0.3% from the leading edge.
  • the maximum relative camber of the blade 20 is the ratio of the maximum camber of the airfoil of the blade 20 to the chord length of the blade 20; the maximum relative thickness of the blade 20 is the maximum thickness of the airfoil of the blade 20 and the blade 20 Chord length ratio.
  • the horizontal distance between the leading edge 21 and the trailing edge 22 of the blade 20 increases from the root of the blade 20 to the blade tip of the blade 20 and then decreases, and the distance between the leading edge 21 and the trailing edge 22 at the blade tip The horizontal distance is smaller than the horizontal distance of the leading edge 21 and the trailing edge 22 at the root of the paddle.
  • the propeller 100 provided in this embodiment can be used to provide flying power for an unmanned aerial vehicle.
  • the airflow velocity above the blade 20 is higher than that of the blade 20.
  • the speed of the airflow below causes a pressure difference between the upper and lower sides of the paddle 20 to cause the UAV to generate upward power.
  • the airfoil distribution of the blades 20 affects the aerodynamic efficiency of the propeller 100 and ultimately affects the flying performance of the unmanned aerial vehicle.
  • the maximum thickness of the blade 20 from the leading edge 21 refers to the distance between the position of the maximum thickness of the blade 20 and the leading edge 21, and the percentage of the distance to the chord length of the blade 20. Because the blades 20 of different structures have different chord lengths, this embodiment chooses this expression to use the chord length of the blades 20 as the limiting standard. When the chord length of the blades 20 changes, the limitation method still has High accuracy.
  • the specific airfoil distribution can be limited by the above numerical range. 5 and FIG. 6, wherein FIG. 5 is a cross-sectional view of the AA cross section of the propeller 100 in FIG. 2, and the AA position is a position point of the radius of the propeller 100 that is 15% from the center of the hub 10, FIG. 6 is a cross-sectional view of the BB cross section of the propeller 100, and the BB position is a position point of the radius of the propeller 100 at a distance of 30% from the center of the hub 10.
  • the maximum relative camber of the blade 20 is 5%, and the maximum relative thickness of the blade 20 is 11%.
  • the position of the maximum camber of the blade 20 is a chord length of 38.5% from the leading edge.
  • the position of the maximum thickness of the blade 20 is a chord length of 27.5% from the leading edge.
  • FIG. 7 is a cross-sectional view of the C-C cross section of the propeller 100 in FIG. 2, and the C-C position is a point of the radius of the propeller 100 that is 50% from the center of the hub 10.
  • FIG. 8 is a cross-sectional view of the D-D section of the propeller 100 in FIG. 2, and the D-D position is a position point of the radius of the propeller 100 which is 75% from the center of the hub 10.
  • FIG. 9 is a cross-sectional view of the E-E cross section of the propeller 100 in FIG.
  • the maximum relative camber of the blade 20 is 5.8%, and the maximum relative thickness of the blade 20 is 7.1%.
  • the position of the maximum camber of the blade 20 is a chord length of 43.5% from the leading edge. In some embodiments, the position of the maximum thickness of the blade 20 is a chord length 18% from the leading edge.
  • FIG. 10 is a cross-sectional view of the F-F- section of the propeller 100 in FIG. 2, and the F-F position is a point from the center of the hub 10 to the radius of the propeller 100.
  • the maximum relative camber of the blade 20 is 4.8%, and the maximum relative thickness of the blade 20 is 5.1%.
  • the position of the maximum camber of the blade 20 is a chord length 35.5% from the leading edge.
  • the position of the maximum thickness of the blade 20 is a chord length 30.5% from the leading edge.
  • chord length of the blade 20 and the diameter of the propeller 100 are at a distance from the center of the hub 10 by a radius of the propeller 100 to 15% of the radius of the propeller 100.
  • the ratio is 7% ⁇ 0.5%.
  • the ratio of the chord length of the blades 20 to the diameter of the propeller 100 is 8% ⁇ 0.3%.
  • the ratio of the chord length of the blade 20 to the diameter of the propeller 100 is 7.6% ⁇ 0.05%.
  • the ratio of the chord length of the blade 20 to the diameter of the propeller 100 is 6.2% ⁇ 0.05%.
  • the ratio of the chord length of the blade 20 to the diameter of the propeller 100 is 1.9% ⁇ 0.05%.
  • FIG. 5 0% to 15% of the radius of the propeller 100 from the center of the hub 10 can be shown in FIG. 5, where the chord length of the blade 20 It can be C1 in the figure.
  • the position from the center of the hub 10 to the radius of the propeller 100 by 30% can be shown in FIG. 6, where the chord length of the blade 20 can be C2 in the figure.
  • the position from the radius of the propeller 100 which is 50% from the center of the hub 10 may be shown in FIG. 7, where the chord length of the blade 20 may be C3 in the figure.
  • FIG. 8 where the chord length of the blade 20 can be C4 in the figure.
  • FIG. 9 The position from the center of the hub 10 to the radius of the propeller 100 can be shown in FIG. 9, where the chord length of the blade 20 can be C5 in the figure.
  • FIG. 10 The position from the center of the hub 10 to the radius of the propeller 100 can be shown in FIG. 10, where the chord length of the blade 20 can be C6 in the figure.
  • the planar shape of the blades 20 of the propeller 100 provided in this embodiment is “saber-shaped”, that is, the trailing edges 22 of the chord lengths of the blades 20 at different positions may be substantially straight.
  • the line of the leading edge 21 is a smooth curve.
  • the horizontal distance between the leading edge 21 and the trailing edge 22 extends from the position of the blade root of the blade 20 to the position of the blade tip, and gradually shows a trend of first increasing and then decreasing, and the blade tip contracting backwards is obviously swept back.
  • the shape, that is, the horizontal distance between the leading edge 21 and the trailing edge 22 at the blade tip position is smaller than the horizontal distance between the leading edge 21 and the trailing edge 22 at the blade root position.
  • the above-mentioned values limit the characteristics of the saber-shaped blade 20 chord length provided in this embodiment, and the front edge 21 at the blade tip position is obviously swept back toward the rear edge 22.
  • Such a setting is beneficial to reduce the propeller 100
  • the flow in the span direction further makes the distribution of the pulling force of the propeller 100 mainly concentrated at the position of the blade tip, thereby improving the aerodynamic efficiency of the propeller 100 and reducing the noise.
  • a thin airfoil is selected for the entire propeller 100, so that the thickness noise of the propeller 100 can be reduced; a small chord length is arranged at the tip of the propeller, which is beneficial to reduce the vortex of the propeller 100 and thus reduce the noise caused by the propeller vortex interference. .
  • the radius of the propeller 100 may be the length shown in R in FIG. 2, that is, the length from the root of the blade 20 to the center of the circle of the hub 10, or may be half of the diameter L of the propeller 100.
  • the maximum thickness of the blade 20 may be the length shown by T in FIG. 4, that is, a series of inscribed circles tangent to the upper and lower arcs are formed inside the airfoil of the blade 20, where the maximum inscribed The diameter of the circle is called the maximum thickness T of the blade.
  • the chord length of the blade 20 may be the length shown in C in FIG. 4, that is, the length of the chord line 23, where the chord line 23 refers to the leading end 21 of the blade 20 at the leftmost end point on the section. The line connecting the trailing edge 22 to the rightmost endpoint on the section.
  • the plurality of paddles 20 are symmetrically disposed at the center of the hub 10.
  • a plurality of blades 20 may be symmetrically disposed on the hub 10 with the center line of the hub 10 as an axis center. In this way, when the hub 10 rotates, the different blades 20 form a relatively uniform lift to drive the unmanned aerial vehicle to fly smoothly.
  • blade root described in this application refers to the part of the blade 20 near the hub 10
  • blade tip refers to the part of the blade 20 that is far from the hub 10.
  • the paddle blade 20 provided in this embodiment may be manufactured by using any material in the prior art, including but not limited to steel, aluminum alloy, plastic material, or carbon fiber. In manufacturing, various existing technologies such as molding, stamping, and forging can also be used.
  • the aerodynamic force generated by the blade root position of the blade 20 generates the maximum torque, so the blade root needs to select an airfoil with a large thickness to resist bending.
  • the relative thickness defined in this embodiment is set at the blade tip. The small thickness airfoil can reduce the thickness noise of the propeller 100 and the blade tip vortex, thereby reducing the influence of the blade tip vortex on the rotation of the propeller 100 and achieving the effect of reducing noise.
  • the maximum camber of the blade 20 may be the length shown in F in FIG. 4, that is, the maximum distance between the middle arc line 24 and the chord line 23.
  • the twist angle of the blade 20 is 16 ° ⁇ 0.5 °.
  • the twist angle of the blade 20 is 20 ° ⁇ 0.5 °.
  • the twist angle of the blade 20 is 13 ° ⁇ 0.3 °.
  • the twist angle of the blade 20 is 10.5 ° ⁇ 0.3 °.
  • the twist angle of the blade 20 is 10 ° ⁇ 0.3 °.
  • the twist angle of the blade 20 is the angle between the chord line 23 of the blade 20 and the horizontal plane. Based on the above description of FIGS. 5 to 10, the distance from the center of the hub 10 to the radius of the propeller 100 from 0% to 15% can be shown in FIG. 5, where the twist angle of the blade 20 can be shown ⁇ 1. The distance from the center of the hub 10 to 30% of the radius of the propeller 100 can be shown in FIG. 6, where the twist angle of the blade 20 can be ⁇ 2 in the figure. The distance from the center of the hub 10 to 50% of the radius of the propeller 100 can be shown in FIG. 7, where the twist angle of the blade 20 can be ⁇ 3 in the figure.
  • the distance from the center of the hub 10 to 85% of the radius of the propeller 100 can be approximated as shown in FIG. 8, where the twist angle of the blade 20 can be ⁇ 4 in the figure.
  • the distance from the center of the hub 10 to 90% of the radius of the propeller 100 can be shown in FIG. 9, where the twist angle of the blade 20 can be ⁇ 5 in the figure.
  • the distance from the center of the hub 10 to 100% of the radius of the propeller 100 can be shown in FIG. 10, where the twist angle of the blade 20 can be ⁇ 6 in the figure.
  • the upper leaf surface, the lower leaf surface, and the edge surface of the leading edge 21 of the blade 20 are smooth curved surfaces, and the upper leaf surface, the lower leaf surface, and the edge surface of the leading edge 21 are smoothly transitioned.
  • the trailing edge 22 of the paddle blade 20 may be formed by comparing the upper blade surface and the lower blade surface with one point, and there may also be a certain distance extension between the upper blade surface and the lower blade surface. ⁇ ⁇ 22 of the paddle 20.
  • the above technical solution is applicable to a propeller having a Reynolds number in a range of 10 4 to 5 ⁇ 10 5 .
  • the propellers provided in the embodiments of the present application by setting specific airfoil distribution, twist angle distribution, and chord length distribution for the propeller blades, can ensure that the blades have better working performance, can effectively improve the aerodynamic efficiency of the propeller, and reduce its Noise level. Further, the application of the propeller to power components and unmanned aerial vehicles can correspondingly improve the efficiency of the power components and unmanned aerial vehicles, which can effectively extend the life of the unmanned aerial vehicle and reduce its noise level, and ultimately improve the unmanned aerial vehicle. Flight performance.
  • An embodiment of the present application further provides a power assembly, which includes a driving member and the propeller 100 in the foregoing embodiment, and a hub 10 of the propeller 100 is connected to the driving member.
  • the driving component in the power assembly may be a motor 31 or an engine
  • the propeller hub 10 of the propeller 100 may be connected to the motor 31 or the output shaft of the engine, thereby outputting the rotational force of the motor 31 or the engine. It is transmitted to the blades through the hub 10, and the blades of the propeller 100 are driven to rotate around the centerline of the hub 10, and the airflow in the air is disturbed to generate lift or thrust, which drives the UAV to move.
  • the power assembly provided in this embodiment includes a motor and a propeller, and by setting specific airfoil distribution, twist angle distribution, and chord length distribution for the propeller blades, it can ensure that the blades have better working performance and can effectively improve the blade performance.
  • the manufactured propeller has aerodynamic efficiency and endurance, and reduces its noise level. Further, the application of the propeller to the power component can correspondingly improve the efficiency of the power component and reduce its noise level, and finally improve the flightability of the unmanned aerial vehicle.
  • An embodiment of the present application further provides an unmanned aerial vehicle 40. It includes a fuselage 41, a boom 42 connected to the fuselage 41, and a power assembly 30 mounted on the boom 42 as described in the above embodiment.
  • the unmanned aerial vehicle 40 provided in this embodiment may be a two-axis unmanned aerial vehicle, a four-axis unmanned aerial vehicle, or an eight-axis unmanned aerial vehicle. This embodiment does not limit the specific types of unmanned aerial vehicles, and is not limited to the above examples.
  • the unmanned aerial vehicle provided in the third embodiment of the present application by setting specific airfoil distribution, torsion angle distribution, and chord length distribution for the propeller blades in its power assembly, can ensure that the blades have better working performance and can effectively improve
  • the propeller is aerodynamic and reduces its noise level.
  • the application of the propeller to power components and unmanned aerial vehicles can correspondingly improve the efficiency of the power components and unmanned aerial vehicles, which can effectively extend the life of the unmanned aerial vehicle and reduce its noise level, and ultimately improve the unmanned aerial vehicle. Flight performance.

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  • Aviation & Aerospace Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

La présente invention concerne une hélice (100), un ensemble d'alimentation (30) et un véhicule aérien sans pilote (40). L'hélice comprend un moyeu (10) et une pluralité de pales (20) reliées au moyeu, les pales se présentant sous la forme d'un ensemble ressemblant à une « forme de sabre », chaque pale comprenant une face de pale supérieure, une face de pale inférieure, un bord d'attaque (21) et un bord de fuite (22), le bord d'attaque et le bord de fuite étant situés sur deux côtés de la pale et le bord d'attaque et le bord de fuite reliant la face de pale supérieure et la face de pale inférieure, de façon à définir la structure des pales à partir de trois aspects comprenant la distribution de profil aérodynamique, la distribution de longueur de corde (C) et l'angle de torsion (α) des pales, assurant que les pales ont une meilleure performance de travail, améliorant efficacement l'efficacité aérodynamique de l'hélice et réduisant le niveau de bruit. L'utilisation de l'hélice pour l'ensemble d'alimentation et le véhicule aérien sans pilote peut améliorer de manière correspondante l'efficacité de l'ensemble d'alimentation et du véhicule aérien sans pilote, ce qui permet d'étendre efficacement la durée de vol du véhicule aérien sans pilote, de réduire son niveau de bruit et d'améliorer les performances de vol du véhicule aérien sans pilote.
PCT/CN2018/116720 2018-08-01 2018-11-21 Hélice, ensemble d'alimentation et véhicule aérien sans pilote WO2020024488A1 (fr)

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Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN210653619U (zh) * 2019-09-05 2020-06-02 深圳市道通智能航空技术有限公司 一种螺旋桨及飞行器
CN110966911B (zh) * 2019-12-19 2021-07-09 中国电子科技集团公司第三十八研究所 一种航空螺旋桨桨叶角测量装置及方法
CN112977815B (zh) * 2021-05-10 2021-08-27 北京三快在线科技有限公司 旋翼飞行器、旋翼飞行器的桨叶及其翼型

Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN203593160U (zh) * 2013-12-13 2014-05-14 吉林大学 一种机翼结构
CN104691739A (zh) * 2015-03-11 2015-06-10 西北工业大学 一种低阻高阻力发散马赫数的高升力层流翼型
CN205524939U (zh) * 2016-01-27 2016-08-31 深圳市大疆创新科技有限公司 螺旋桨、动力组件及飞行器
CN206202665U (zh) * 2016-11-09 2017-05-31 亿航智能设备（广州）有限公司 螺旋桨、动力组件及飞行器
CN106938696A (zh) * 2017-02-20 2017-07-11 西安爱生技术集团公司 一种马刀型低噪声螺旋桨桨叶设计方法
US20170355454A1 (en) * 2016-06-14 2017-12-14 Gopro, Inc. Propeller Blade Beta Twist
CN207565834U (zh) * 2017-10-18 2018-07-03 亿航智能设备（广州）有限公司 螺旋桨和小型多旋翼式无人机
CN207631487U (zh) * 2017-12-21 2018-07-20 深圳市大疆创新科技有限公司 螺旋桨、动力组件及无人飞行器

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN203593160U (zh) * 2013-12-13 2014-05-14 吉林大学 一种机翼结构
CN104691739A (zh) * 2015-03-11 2015-06-10 西北工业大学 一种低阻高阻力发散马赫数的高升力层流翼型
CN205524939U (zh) * 2016-01-27 2016-08-31 深圳市大疆创新科技有限公司 螺旋桨、动力组件及飞行器
US20170355454A1 (en) * 2016-06-14 2017-12-14 Gopro, Inc. Propeller Blade Beta Twist
CN206202665U (zh) * 2016-11-09 2017-05-31 亿航智能设备（广州）有限公司 螺旋桨、动力组件及飞行器
CN106938696A (zh) * 2017-02-20 2017-07-11 西安爱生技术集团公司 一种马刀型低噪声螺旋桨桨叶设计方法
CN207565834U (zh) * 2017-10-18 2018-07-03 亿航智能设备（广州）有限公司 螺旋桨和小型多旋翼式无人机
CN207631487U (zh) * 2017-12-21 2018-07-20 深圳市大疆创新科技有限公司 螺旋桨、动力组件及无人飞行器

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