WO2018000593A1 - 螺旋桨、动力套装及无人飞行器 - Google Patents

螺旋桨、动力套装及无人飞行器 Download PDF

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Publication number
WO2018000593A1
WO2018000593A1 PCT/CN2016/099525 CN2016099525W WO2018000593A1 WO 2018000593 A1 WO2018000593 A1 WO 2018000593A1 CN 2016099525 W CN2016099525 W CN 2016099525W WO 2018000593 A1 WO2018000593 A1 WO 2018000593A1
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Prior art keywords
propeller
blade
center
rotation
distance
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Ceased
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PCT/CN2016/099525
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English (en)
French (fr)
Inventor
刘峰
邓涛
江彬
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SZ DJI Technology Co Ltd
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SZ DJI Technology Co Ltd
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Publication of WO2018000593A1 publication Critical patent/WO2018000593A1/zh
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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
    • B64C11/16—Blades
    • B64C11/18—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
    • B64C27/467—Aerodynamic features

Definitions

  • the present invention relates to a propeller, a power kit having the propeller, and an aircraft having the power kit.
  • the propeller on the unmanned aerial vehicle is a key component of the unmanned aerial vehicle, and the propeller is used to convert the rotation of the motor or the engine intermediate shaft of the UAV into a propulsive force to provide flight power to the unmanned aerial vehicle.
  • the prior art propellers have low working efficiency due to the contour and structure constraints, and cannot meet the expected driving force requirements at work.
  • a propeller comprising a blade on a pitch of 60% of a radius of revolution of the propeller on the blade, the blade having an angle of attack of 16.89 ⁇ 1.5 degrees;
  • the distance from the center of rotation of the propeller on the blade is 73.33% of the radius of gyration of the propeller, the angle of attack of the blade is 15 ⁇ 1.5 degrees;
  • the pitch of the propeller is from the propeller
  • the distance from the center of revolution is 86.67% of the radius of gyration of the propeller, and the angle of attack of the blade is 13.78 ⁇ 1.5 degrees.
  • the distance from the center of rotation of the propeller on the blade is 46.67% of the radius of gyration of the propeller, and the angle of attack of the blade is 19.86 ⁇ 1.5 degrees;
  • the distance from the center of rotation of the propeller on the blade is 98.67% of the radius of gyration of the propeller, and the angle of attack of the blade is 12.54 ⁇ 1.5 degrees.
  • the rotary diameter of the propeller is 150 mm, and the angle of attack of the blade is 19.86 ⁇ 1.5 degrees at a distance of 35 mm from the center of rotation of the propeller;
  • the angle of attack of the blade is 15 ⁇ 1.5 degrees
  • the blade has an angle of attack of 12.54 ⁇ 1.5 degrees.
  • the distance from the center of rotation of the propeller on the blade is 60% of the radius of gyration of the propeller, and the chord length of the blade is 12.88 ⁇ 3 mm;
  • the distance from the center of rotation of the propeller on the blade is 73.33% of the radius of gyration of the propeller, the chord length of the blade is 11.8 ⁇ 3 mm;
  • the distance from the center of rotation of the propeller on the blade is 86.67% of the radius of gyration of the propeller, and the chord length of the blade is 10.76 ⁇ 3 mm.
  • the distance from the center of rotation of the propeller on the blade is 46.37% of the radius of gyration of the propeller, and the chord length of the blade is 14.17 ⁇ 3 mm;
  • the distance from the center of rotation of the propeller on the blade is 98.67% of the radius of gyration of the propeller, and the chord length of the blade is 9.76 ⁇ 3 mm.
  • the diameter of the rotation of the propeller is 150 ⁇ 20 mm.
  • the structure of the front surface of the blade is the same as the structure of the reverse surface of the blade, so that when the propeller rotates clockwise or counterclockwise, the driving force in the corresponding direction can be generated.
  • the orthographic projection contour of the blade is a symmetrical structure.
  • the paddle includes a leaf surface and a leaf back disposed away from each other, and a first side edge connecting one side of the leaf back and the leaf surface, and another connecting the leaf back and the leaf surface a second side edge of one side; a side of the blade having the leaf surface is the front surface, and a side of the blade having the leaf back is the reverse side.
  • cross-sectional profile of the leaf surface and the cross-sectional profile of the blade back are both curved;
  • the first side edge and the second side edge are disposed symmetrically about a centerline of the blade.
  • first side edge comprises a curved outwardly convex first arching portion; the second side edge comprises a curved outwardly projecting second arching portion.
  • first arching portion and the second arching portion are both close to the rotation of the propeller Center setting
  • the first arching portion and the second arching portion are symmetrically disposed about a center line of the blade.
  • the propeller is a folding paddle, the propeller further includes a paddle, the number of the blades is at least two, and each of the blades is rotatably coupled to the paddle;
  • the propeller includes a hub that is fixedly coupled to the blade, the number of the blades being at least two.
  • the pitch of the propeller is 48 mm ⁇ 5 mm.
  • a power kit for an unmanned aerial vehicle comprising at least one propeller of any of the above; and at least one drive member that drives rotation of the propeller.
  • the driving member is a motor
  • the propeller is connected to the motor
  • the motor has a KV value of 2300 rpm / (minute ⁇ volt).
  • An unmanned aerial vehicle comprising a fuselage, a plurality of arms, and a plurality of power sets as described above, the plurality of arms being coupled to the body, the plurality of power sets being respectively mounted on the plurality of On the arm.
  • the propeller provided by the invention reduces the air resistance, improves the efficiency, and has a relatively large driving force through the design of the angle of attack on different parts of the blade.
  • FIG. 1 is a schematic structural view of a propeller provided by an embodiment of the present invention.
  • Figure 2 is a front elevational view of the propeller of Figure 1.
  • Figure 3 is a side view of the propeller of Figure 1.
  • FIG. 4 is a side elevational view of another perspective view of the propeller of FIG. 1.
  • FIG. 5 is a schematic illustration of the paddle of the propeller of Figure 2.
  • Figure 6 is a cross-sectional view of the A-A section of the blade of Figure 5.
  • Figure 7 is a cross-sectional view of the B-B section of the blade of Figure 5.
  • Figure 8 is a cross-sectional view of the C-C section of the paddle of Figure 5.
  • Figure 9 is a cross-sectional view of the D-D section of the blade of Figure 5.
  • Figure 10 is a cross-sectional view of the E-E section of the paddle of Figure 5.
  • a component when referred to as being "fixed” to another component, it can be directly on the other component or the component can be present.
  • a component When a component is considered to "connect” another component, it can be directly connected to another component or possibly a central component.
  • a component When a component is considered to be “set to” another component, it can be placed directly on another component or possibly with a centered component.
  • Embodiments of the present invention provide a propeller that includes a paddle.
  • the distance from the center of rotation of the propeller on the blade is 60% of the radius of gyration of the propeller, the angle of attack of the blade is 16.89 ⁇ 1.5 degrees; the propeller is spaced from the propeller
  • the distance of the center of rotation is 73.33% of the radius of gyration of the propeller, the angle of attack of the blade is 15 ⁇ 1.5 degrees; the distance from the center of rotation of the propeller on the blade is the propeller At 86.67% of the radius of gyration, the angle of attack of the blade is 13.78 ⁇ 1.5 degrees.
  • the embodiment of the present invention further provides a power package of an unmanned aerial vehicle, the power package includes a propeller and a motor, the propeller is connected to the motor, and the motor is used to drive the propeller to rotate, the KV of the motor
  • the value is 2300 rpm / (minute ⁇ volt).
  • the propeller includes a blade on which the distance from the center of rotation of the propeller is 60% of the radius of gyration of the propeller, and the angle of attack of the blade is 16.89 ⁇ 1.5 degrees;
  • the distance from the center of rotation of the propeller on the blade is 73.33% of the radius of gyration of the propeller, the angle of attack of the blade is 15 ⁇ 1.5 degrees;
  • the center of rotation of the propeller is on the blade
  • the distance is 86.67% of the radius of gyration of the propeller, and the angle of attack of the blade is 13.78 ⁇ 1.5 degrees.
  • the propeller can provide a large driving force.
  • An embodiment of the present invention further provides an unmanned aerial vehicle including a fuselage, a plurality of arms, and a plurality of power sets, wherein the plurality of arms are connected to the body, and the plurality of power sets are respectively installed in the On multiple arms.
  • the power pack includes a propeller and a motor, the propeller being coupled to the motor for driving the propeller to rotate, the motor having a KV value of 2300 rpm / (minute volt).
  • the propeller includes a blade on which the distance from the center of rotation of the propeller is 60% of the radius of gyration of the propeller, and the angle of attack of the blade is 16.89 ⁇ 1.5 degrees;
  • the distance from the center of rotation of the propeller on the blade is the radius of gyration of the propeller At 73.33%, the angle of attack of the blade is 15 ⁇ 1.5 degrees; the distance from the center of rotation of the propeller on the blade is 86.67% of the radius of gyration of the propeller, the blade
  • the angle of attack is 13.78 ⁇ 1.5 degrees.
  • An unmanned aerial vehicle includes a fuselage, an arm, a propeller, and a driving member for driving the rotation of the propeller, and the arm is coupled to the fuselage.
  • the propeller may be a folding paddle.
  • the number of the propellers may be selected according to actual needs, and may be one, two or more.
  • the driving component is a motor, and the KV value of the motor is 2300 rpm / (minute ⁇ volt); it can be understood that in other embodiments, the KV value of the motor can be selected according to actual flight requirements.
  • the drive member may be in other forms such as an engine or the like.
  • the propeller may be a positive paddle or a reverse paddle.
  • the so-called positive paddle refers to a propeller that rotates counterclockwise to generate lift from the tail of the driving part such as the motor to the direction of the motor head; the so-called reverse paddle refers to the clockwise rotation from the tail of the motor to the direction of the motor head to generate lift.
  • the structure of the positive paddle is mirror symmetrical with the structure of the reverse paddle, so the structure of the propeller is only exemplified by a positive paddle.
  • the plurality of arms are plural, and the propeller and the driving member are all plural, and each driving member drives one of the propellers to rotate to form a power set. At least one set of the power kit is provided on each arm.
  • the power pack may also include a drive member and a plurality of (e.g., two) propellers.
  • FIG. 1 to FIG. 3 shows a schematic structural view of a propeller 100 according to an embodiment of the present invention.
  • the propeller 100 includes a paddle 101 and two blades 200 disposed on both sides of the paddle 101, and the two blades 200 are disposed symmetrically about a center of the paddle 101.
  • the two blades 200 and the paddle 101 are rotated to form a paddle.
  • the center of the paddle 101 substantially coincides with the center of the paddle.
  • the propeller 100 may be a straight paddle, and the propeller 100 may include a hub and The two blades 200 are fixedly connected to the hub.
  • the propeller 100 is a fixed propeller, and the two blades 200 are fixedly coupled to the paddle 101. It can be understood that in other embodiments, the propeller 100 can be a foldable paddle, and the paddle 200 is rotatably coupled to the paddle 101. Alternatively, in some embodiments, the paddle 200 is integrally formed with the paddle 101, or, in some embodiments, the paddle 200 is removably mounted to the paddle by a connector. 101 is not limited to the description in the embodiment of the present invention.
  • the number of blades 200 in each of the propellers 100 may be other numbers, such as three, four, etc., depending on actual needs.
  • the number of the blades 200 is three, and the three blades 200 are evenly spaced in the circumferential direction with respect to the center of the paddle.
  • the paddle has a diameter of 150 ⁇ 20 mm.
  • the diameter of the paddle may be 130 mm, 140 mm, 150 mm, 160 mm, 170 mm, or the diameter of the paddle may be any value within a range of values defined by any two of the above values.
  • the paddle has a diameter of 150 mm.
  • the "center of the paddle” and the “paddle center” mentioned above and below should be understood as “ “Slewing center of the propeller”, similarly, “diameter of the paddle” and “paddle disk diameter” mentioned above and below should be understood as “the diameter of the propeller", “radius of the paddle” and “paddle plate” The radius “should be understood as “the radius of gyration of the propeller”.
  • the paddle 101 can be used to connect with a rotating shaft of a drive member of the UAV to enable the drive member to drive the propeller 100 to rotate.
  • a reinforcing spacer may be embedded in the paddle 101, and the reinforcing piece may be made of a lightweight high-strength material such as aluminum alloy to increase the strength of the propeller 100.
  • the paddle 101 is substantially cylindrical. Two of the blades 200 are disposed in a central symmetry on both sides of the paddle 101, and each of the blades 200 is screwed to the paddle 101.
  • the pitch of the propeller is 48 mm ⁇ 5 mm, and the pitch is a distance that the propeller 100 rotates one revolution, theoretically rising in the axial direction.
  • the pitch of the propeller may be 43 mm, 44 mm, 45 mm, 46 mm, 47 mm, 48 mm, 49 mm, 50 mm, 51 mm, 52 mm, 53 mm, or the pitch may be Any value within the range of values defined by any two of the above values.
  • the pitch is 48 mm.
  • the blade 200 includes a blade face 10 and a blade back 20 disposed away from each other, and a first side edge 30 connecting the blade back 20 and a side of the blade face 10, connecting the blade back 20 and the The second side edge 40 of the other side of the foliage 10.
  • the cross-sectional profile of the foliage 10 and the cross-sectional profile of the blade back 20 are both curved (see Figures 6-10).
  • the leaf surface 10 and the leaf back 20 are curved surfaces, and the curvatures of the contours of the leaf surface 10 and the leaf back 20 are equal at the same cross section.
  • the first side edge 30 includes a curved, outwardly projecting first arched portion 31.
  • the first arching portion 31 is smoothly transitionally connected to other portions of the first side edge 30.
  • the first arching portion 31 is disposed adjacent to the paddle 101.
  • the second side edge 40 includes a curved, outwardly projecting second bulge 41 that is smoothly transitionally connected to other portions of the second side edge 40.
  • the second arching portion 41 is disposed adjacent to the paddle 101. The distance between the second arched portion 41 and the paddle 101 and the distance between the first arched portion 31 and the paddle 101 are substantially the same.
  • the projection profile of the blade 200 is substantially symmetrical along the length direction of the blade 200.
  • the first side edge 30 and the second side edge 40 are substantially symmetrically disposed about a center line of the blade 200, and the first arching portion 31 and the second arching portion 41 are substantially related to the paddle
  • the center line of the blade 200 is symmetrically arranged, which enables the propeller 100 to be mounted on the driving member of the UAV, whether it is clockwise or counterclockwise, and can generate a driving force in a corresponding direction, which is beneficial to The UAV quickly changes the direction of flight.
  • the propeller 100 described above is exemplified by a positive paddle.
  • the propeller 100 rotates clockwise to provide an upward lifting urging force for the unmanned aerial vehicle.
  • the unmanned aerial vehicle employing the propeller 100 can quickly raise or lower the altitude, quickly change the flight direction such as forward, backward, left turn, right turn, and the like, and the unmanned aerial vehicle is more suitable for 3D violent flight.
  • one side having the blade surface 10 is set to the front side, and the side having the blade back surface 20 is set to the reverse side due to the propeller 100 has the above symmetrical structure, so that the shape, contour and structure of the front side and the back side are the same. Therefore, regardless of whether the propeller 100 is rotated clockwise or counterclockwise, the driving force in the corresponding direction can be generated, which is beneficial to the The UAV quickly changes the direction of flight.
  • the blade 200 has no sharp twist, the stress is small, the structural strength is high, the fracture is not easy, and the reliability is high.
  • One end of the blade 200 away from the paddle 101 is the thinnest portion of the paddle 200, which is advantageous for reducing air resistance. That is, the thickness of one end of the blade 200 away from the center of the paddle is less than the thickness of other portions of the paddle 200.
  • the length of the blade 200 is 75 ⁇ 10 mm.
  • the length of the blade 200 may be any value between 65 mm and 85 mm, such as 65 mm, 70 mm, 75 mm, 80 mm, 85 mm, or the length of the blade 200 may be any of the above two Any value within the range of values defined by the values.
  • the blade 200 has a length of 75 mm.
  • the angle of attack referred to herein refers to the angle between the chord of the blade 200 and the velocity of the incoming flow.
  • the distance from the center O of the paddle on the blade 200 is 46.67% of the blade radius, and the angle of attack ⁇ 1 of the blade 200 is 19.86 ⁇ 1.5. degree.
  • the angle of attack ⁇ 1 of the blade 200 herein may be 18.36 degrees, 18.86 degrees, 19.36 degrees, 19.86 degrees, 20.36 degrees, 20.86 degrees, 21.36 degrees, or the angle of attack ⁇ 1 of the blade 200 herein. Any value within the numerical range defined by any two of the above numerical values may be used. In the present embodiment, the angle of attack ⁇ 1 is 19.86 degrees.
  • chord length L1 of the blade 200 is 14.17 ⁇ 3 mm.
  • the chord length L1 of the blade 200 herein may be 11.17 mm, 12.17 mm, 13.17 mm, 14.17 mm, 15.17 mm, 16.17 mm, 17.17 mm, or the chord length L1 of the blade 200 herein.
  • the distance from the center O of the paddle on the blade 200 is 60% of the blade radius, and the angle of attack ⁇ 2 of the blade 200 is 16.89 ⁇ 1.5. degree.
  • the angle of attack ⁇ 12 of the blade 200 herein may be 15.39 degrees, 15.89 degrees, 16.39 degrees, 16.89 degrees, 17.39 degrees, 17.89 degrees, 18.39 degrees, or the angle of attack ⁇ 2 of the blade 200 herein. Any value within the numerical range defined by any two of the above numerical values may be used.
  • the angle of attack ⁇ 2 is 16.89 degrees.
  • the distance from the center O of the paddle on the paddle 200 is 60% of the paddle radius, and the chord length L2 of the paddle 200 is 12.88 ⁇ 3 mm.
  • chord length L2 of the blade 200 may be 9.88 mm, 10.88 mm, 11.88 mm, 12.88 mm, 13.88 mm, 14.88 mm, 15.88 mm, or, specifically, the chord length L2 of the blade 200 herein may be Any value within the numerical range defined by any two of the above numerical values, in the present embodiment, the chord length L2 is 12.88 mm.
  • the distance from the center O of the paddle on the blade 200 is 73.33% of the blade radius, and the angle of attack ⁇ 3 of the blade 200 is 15 ⁇ 1.5. degree.
  • the angle of attack ⁇ 3 of the blade 200 herein may be 13.5 degrees, 14 degrees, 14.5 degrees, 15 degrees, 15.5 degrees, 16 degrees 16.5 degrees, or the angle of attack ⁇ 3 of the blade 200 may be In any value within the numerical range defined by any two of the above numerical values, in the present embodiment, the angle of attack ⁇ 3 is 15 degrees.
  • the distance from the center O of the paddle on the paddle 200 is 73.33% of the paddle radius, and the chord length L3 of the paddle 200 is 11.8 ⁇ 3 mm.
  • chord length L3 of the blade 200 herein may be 8.8 mm, 9.8 mm, 10.8 mm, 11.8 mm, 12.8 mm, 13.8 mm, 14.8 mm, or the chord length L3 of the blade 200 herein. Any value within the numerical range defined by any two of the above numerical values may be used. In the present embodiment, the chord length L3 is 11.8 mm.
  • the distance from the center O of the paddle on the paddle 200 is 86.67% of the paddle radius, and the angle of attack ⁇ 4 of the paddle 200 is 13.78 ⁇ 1.5. degree.
  • the angle of attack ⁇ 4 of the blade 200 herein may be 12.28 degrees, 12.78 degrees, 13.28 degrees, 13.78 degrees, 14.28 degrees, 14.78 degrees, 15.28 degrees, or, here, the angle of attack ⁇ 4 of the blade 200. Any value within the numerical range defined by any two of the above numerical values may be used. In the present embodiment, the angle of attack ⁇ 4 is 13.78 degrees.
  • the distance from the center O of the paddle on the paddle 200 is 86.67% of the paddle radius, and the chord length L4 of the paddle 200 is 10.78 ⁇ 3 mm.
  • chord length L4 of the blade 200 herein may be 7.78 mm, 8.78 mm, 9.78 mm, 10.78 mm, 11.78 mm, 12.78 mm, 13.78 mm, or the chord length L4 of the blade 200 herein. Any value within the range of values defined by any two of the above values may be used. In the present embodiment, the chord length L4 is 10.78 mm.
  • the distance from the center O of the paddle on the paddle 200 is 98.67% of the paddle radius, and the angle of attack ⁇ 5 of the paddle 200 is 12.54 ⁇ 1.5. degree.
  • the angle of attack ⁇ 5 of the blade 200 herein may be 11.04 degrees, 11.54 degrees, 12.04 degrees, 12.54 degrees, 13.04 degrees, 13.54 degrees, 14.04 degrees, or the angle of attack ⁇ 5 of the blade 200 herein. Any value within a range of values defined by any two of the above numerical values, in the present embodiment, The angle of attack ⁇ 5 is 12.54 degrees.
  • the distance from the center O of the paddle on the paddle 200 is 98.67% of the paddle radius, and the chord length L5 of the paddle 200 is 9.76 ⁇ 3 mm.
  • chord length L5 of the blade 200 herein may be 6.76 mm, 7.76 mm, 8.76 mm, 9.76 mm, 10.76 mm, 11.76 mm, 12.76 mm, or the chord length L5 of the blade 200 herein. Any value within the numerical range defined by any two of the above numerical values may be used. In the present embodiment, the chord length L5 is 9.76 mm.
  • the paddle has a diameter of 150 mm.
  • the angle of attack ⁇ 1 of the blade 200 is 19.86 degrees, and the chord length L1 of the blade 200 is 14.17 mm; at the distance from the paddle 45 mm at the center, the angle of attack ⁇ 2 of the blade 200 is 16.89 degrees, the chord length L2 of the blade 200 is 12.88 mm; at 55 mm from the center of the paddle, the blade 200
  • the angle of attack ⁇ 3 is 15 degrees
  • the chord length L3 of the blade 200 is 11.8 mm
  • the angle of attack ⁇ 4 of the blade 200 is 13.78 degrees at a distance of 65 mm from the center of the paddle, the blade 200
  • the chord length L4 is 10.76 mm; at an angle of 74 mm from the center of the paddle, the blade angle 200 of the blade 200 is 12.54 degrees, and the chord length L5 of the blade 200 is 9.76 mm.
  • Table 1 shows the driving force values of the propellers provided by the present embodiment at different rotational speeds.
  • the propeller provided by the embodiment can provide a large pulling force, thereby saving power consumption, increasing the cruising distance of the UAV and improving the efficiency.
  • the propeller provided by the invention reduces the air resistance, improves the efficiency, increases the cruising range of the aircraft and improves the flight performance of the aircraft through the design of the angle of attack on different parts of the blade.
  • the blades of the propeller have a symmetrical structure, and the shapes, contours and structures of the front and back sides are the same, so that the propeller can generate phases regardless of whether the propeller rotates clockwise or counterclockwise.
  • the driving force of the direction is favorable for the UAV to quickly change the flight direction.

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Abstract

本发明提供一种螺旋桨(100)，其包括桨叶(200)，其中，在所述桨叶(200)上距所述螺旋桨(100)的回转中心的距离为所述螺旋桨(100)的回转半径的60％处，所述桨叶(200)的攻角为16.89±1.5度；在所述桨叶(200)上距所述螺旋桨(100)的回转中心的距离为所述螺旋桨(100)的回转半径的73.33％处，所述桨叶(200)的攻角为15±1.5度；在所述桨叶(200)上距所述螺旋桨(100)的回转中心的距离为所述螺旋桨(100)的回转半径的86.67％处，所述桨叶(200)的攻角为13.78±1.5度。本发明还提供一种采用上述螺旋桨(100)的动力套装和无人飞行器。

Description

螺旋桨、动力套装及无人飞行器 技术领域
本发明涉及一种螺旋桨、具有所述螺旋桨的动力套装及具有所述动力套装的飞行器。
背景技术
无人飞行器上的螺旋桨为无人飞行器的关键元件，所述螺旋桨用于将所述无人飞行器的电机或者发动机中转轴的转动转化为推动力，从而为所述无人飞行器提供飞行的动力。现有技术中的螺旋桨由于外形轮廓和结构的限制，其工作效率较低，在工作时无法满足预期的推动力的需求。
发明内容
有鉴于此，有必要提供一种具有较高效率的螺旋桨，还有必要提供一种采用所述螺旋桨的动力套装和无人飞行器。
一种螺旋桨，其包括桨叶，在所述桨叶上距所述螺旋桨的回转中心的距离为所述螺旋桨的回转半径的60％处，所述桨叶的攻角为16.89±1.5度；在所述桨叶上距所述螺旋桨的回转中心的距离为所述螺旋桨的回转半径的73.33％处，所述桨叶的攻角为15±1.5度；在所述桨叶上距所述螺旋桨的回转中心的距离为所述螺旋桨的回转半径的86.67％处，所述桨叶的攻角为13.78±1.5度。
进一步地，在所述桨叶上距所述螺旋桨的回转中心的距离为所述螺旋桨的回转半径的46.67％处，所述桨叶的攻角为19.86±1.5度；
或/及，在所述桨叶上距所述螺旋桨的回转中心的距离为所述螺旋桨的回转半径的98.67％处，所述桨叶的攻角为12.54±1.5度。
进一步地，所述螺旋桨的回转直径为150毫米，在距离所述螺旋桨的回转中心35毫米处，所述桨叶的攻角为19.86±1.5度；
或/及，在距离所述螺旋桨的回转中心45毫米处，所述桨叶的攻角为16.89±1.5度；
或/及，在距离所述螺旋桨的回转中心55毫米处，所述桨叶的攻角为 15±1.5度；
或/及，在距离所述螺旋桨的回转中心65毫米处，所述桨叶的攻角为13.78±1.5度；
或/及，在距离所述螺旋桨的回转中心74毫米处，所述桨叶的攻角为12.54±1.5度。
进一步地，在所述桨叶上距所述螺旋桨的回转中心的距离为所述螺旋桨的回转半径的60％处，所述桨叶的弦长为12.88±3毫米；
或/及，在所述桨叶上距所述螺旋桨的回转中心的距离为所述螺旋桨的回转半径的73.33％处，所述桨叶的弦长为11.8±3毫米；
或/及，在所述桨叶上距所述螺旋桨的回转中心的距离为所述螺旋桨的回转半径的86.67％处，所述桨叶的弦长为10.76±3毫米。
进一步地，在所述桨叶上距所述螺旋桨的回转中心的距离为所述螺旋桨的回转半径的46.37％处，所述桨叶的弦长为14.17±3毫米；
或/及，在所述桨叶上距所述螺旋桨的回转中心的距离为所述螺旋桨的回转半径的98.67％处，所述桨叶的弦长为9.76±3毫米。
进一步地，所述螺旋桨的回转的直径为150±20毫米。
进一步地，所述桨叶的正面的结构与所述桨叶的反面的结构相同，使所述螺旋桨在顺时针或逆时针转动时，均能够产生相应方向的推动力。
进一步地，对所述螺旋桨进行沿所述螺旋桨的转动轴线方向的正投影时，所述桨叶的正投影轮廓为对称结构。
进一步地，所述桨叶包括相互背离设置的叶面及叶背，以及连接所述叶背及所述叶面的一侧的第一侧缘、连接所述叶背及所述叶面的另一侧的第二侧缘；所述桨叶具有所述叶面的一侧为所述正面，所述桨叶具有所述叶背的一侧为所述反面。
进一步地，所述叶面的横截面轮廓及所述叶背的横截面轮廓均弯曲；
或/及，对所述螺旋桨进行沿所述螺旋桨的转动轴线方向的正投影时，所述第一侧缘及所述第二侧缘大致关于所述桨叶的中心线对称设置。
进一步地，所述第一侧缘包括曲面状的向外凸出的第一拱起部；所述第二侧缘包括曲面状的向外凸出的第二拱起部。
进一步地，所述第一拱起部及所述第二拱起部均靠近所述螺旋桨的回转 中心设置；
或/及，对所述螺旋桨进行沿所述螺旋桨的转动轴线方向的正投影时，所述第一拱起部及所述第二拱起部关于所述桨叶的中心线对称设置。
进一步地，所述螺旋桨为折叠桨，所述螺旋桨还包括桨座，所述桨叶的数量为至少两个，每个所述桨叶能够转动地连接于所述桨座上；
或者，所述螺旋桨包括与所述桨叶固定连接的桨毂，所述桨叶的数量为至少两个。
进一步地，所述螺旋桨的螺距为48mm±5毫米。
一种无人飞行器的动力套装，所述动力套装包括上述任一项所述的至少一个螺旋桨；以及驱动所述螺旋桨转动的至少一个驱动件。
进一步地，所述驱动件为电机，所述螺旋桨连接于所述电机上，所述电机的KV值为2300转/(分钟·伏特)。
一种无人飞行器，其包括机身、多个机臂及如上所述的多个动力套装，所述多个机臂与所述机身连接，所述多个动力套装分别安装在所述多个机臂上。
本发明提供的螺旋桨通过对桨叶的不同部位的攻角的设计，减少了空气阻力，提高了效率，且推动力相对较大。
附图说明
图1是本发明实施方式提供的螺旋桨的结构示意图。
图2是图1中的螺旋桨的主视图。
图3是图1中的螺旋桨的侧视图。
图4是图1中的螺旋桨的另一视角的侧视图。
图5是图2中的螺旋桨的桨叶的示意图。
图6是图5中的桨叶的A-A剖面的剖视图。
图7是图5中的桨叶的B-B剖面的剖视图。
图8是图5中的桨叶的C-C剖面的剖视图。
图9是图5中的桨叶的D-D剖面的剖视图。
图10是图5中的桨叶的E-E剖面的剖视图。
主要元件符号说明
螺旋桨                        100
桨座                          101
桨叶                          200
叶面                          10
叶背                          20
第一侧缘                      30
第一拱起部                    31
第二侧缘                      40
第二拱起部                    41
如下具体实施方式将结合上述附图进一步说明本发明。
具体实施方式
下面将结合本发明实施例中的附图，对本发明实施例中的技术方案进行清楚、完整地描述，显然，所描述的实施例仅仅是本发明一部分实施例，而不是全部的实施例。基于本发明中的实施例，本领域普通技术人员在没有做出创造性劳动前提下所获得的所有其他实施例，都属于本发明保护的范围。
需要说明的是，当组件被称为“固定于”另一个组件，它可以直接在另一个组件上或者也可以存在居中的组件。当一个组件被认为是“连接”另一个组件，它可以是直接连接到另一个组件或者可能同时存在居中组件。当一个组件被认为是“设置于”另一个组件，它可以是直接设置在另一个组件上或者可能同时存在居中组件。
除非另有定义，本文所使用的所有的技术和科学术语与属于本发明的技术领域的技术人员通常理解的含义相同。本文中在本发明的说明书中所使用的术语只是为了描述具体的实施例的目的，不是旨在于限制本发明。本文所使用的术语“及/或”包括一个或多个相关的所列项目的任意的和所有的组 合。
在实现本发明的过程中，发明人发现了如下问题：
(1)螺旋桨的效率与螺旋桨的攻角和弦长有关，为此，发明人在螺旋桨的形状及结构方面做出了重点改进。
(2)特别地，螺旋桨的效率受到螺旋桨中部(60％～90％区域)的攻角以及弦长影响，为此，发明人在螺旋桨的中部重点做出改进。
(3)螺旋桨的形状及结构直接影响到其在旋转时产生的推动力方向以及推动力大小，为此，发明人在此方面做出了一些改进。
本发明实施例提供一种螺旋桨，其包括桨叶。在所述桨叶上距所述螺旋桨的回转中心的距离为所述螺旋桨的回转半径的60％处，所述桨叶的攻角为16.89±1.5度；在所述桨叶上距所述螺旋桨的回转中心的距离为所述螺旋桨的回转半径的73.33％处，所述桨叶的攻角为15±1.5度；在所述桨叶上距所述螺旋桨的回转中心的距离为所述螺旋桨的回转半径的86.67％处，所述桨叶的攻角为13.78±1.5度。
本发明实施例还提供一种无人飞行器的动力套装，所述动力套装包括螺旋桨以及电机，所述螺旋桨连接于所述电机上，所述电机用于驱动所述螺旋桨转动，所述电机的KV值为2300转/(分钟·伏特)。所述螺旋桨包括桨叶，在所述桨叶上距所述螺旋桨的回转中心的距离为所述螺旋桨的回转半径的60％处，所述桨叶的攻角为16.89±1.5度；在所述桨叶上距所述螺旋桨的回转中心的距离为所述螺旋桨的回转半径的73.33％处，所述桨叶的攻角为15±1.5度；在所述桨叶上距所述螺旋桨的回转中心的距离为所述螺旋桨的回转半径的86.67％处，所述桨叶的攻角为13.78±1.5度。所述螺旋桨可提供较大的推动力。
本发明实施例还提供一种无人飞行器，其包括机身、多个机臂以及多个动力套装，所述多个机臂与所述机身连接，所述多个动力套装分别安装在所述多个机臂上。所述动力套装包括螺旋桨以及电机，所述螺旋桨连接于所述电机上，所述电机用于驱动所述螺旋桨转动，所述电机的KV值为2300转/(分钟·伏特)。所述螺旋桨包括桨叶，在所述桨叶上距所述螺旋桨的回转中心的距离为所述螺旋桨的回转半径的60％处，所述桨叶的攻角为16.89±1.5度；在所述桨叶上距所述螺旋桨的回转中心的距离为所述螺旋桨的回转半径 的73.33％处，所述桨叶的攻角为15±1.5度；在所述桨叶上距所述螺旋桨的回转中心的距离为所述螺旋桨的回转半径的86.67％处，所述桨叶的攻角为13.78±1.5度。
下面结合附图，对本发明的一些实施方式作详细说明。在不冲突的情况下，下述的实施例及实施例中的特征可以相互组合。
本发明一实施方式提供的无人飞行器，其包括机身、机臂、螺旋桨及用于驱动所述螺旋桨转动的驱动件，所述机臂与所述机身相连接。可以理解，在一些实施方式中，所述螺旋桨可以为折叠桨。所述螺旋桨的数量可以根据实际需要选择，可以为一个、两个或者多个。本实施方式中，所述驱动件为电机，所述电机的KV值为2300转/(分钟·伏特)；可以理解，在其他实施方式中，所述电机的KV值可以根据实际的飞行需要选取；所述驱动件可以为其他形式，如发动机等。
所述螺旋桨可以是正桨或者反桨。所谓正桨，指从驱动件如电机的尾部向电机头部方向看，逆时针旋转以产生升力的螺旋桨；所谓反桨，指从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阐述所述螺旋桨的结构。
具体在本实施方式中，所述机臂为多个，所述螺旋桨及所述驱动件均为多个，并且每一个驱动件驱动一个所述螺旋桨转动，构成一套动力套装。每个机臂上设有至少一套所述动力套装。
可以理解，所述动力套装也可包括一个驱动件和多个(如两个)螺旋桨。
另外，本发明实施方式的描述中出现的上、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，而不应所述认为具有限制性。
请同时参阅图1至图3，图中示出了本发明实施方式提供的螺旋桨100的结构示意图。所述螺旋桨100包括桨座101及设置于所述桨座101的两侧的两个桨叶200，两个所述桨叶200关于所述桨座101的中心呈中心对称设置。两个所述桨叶200及所述桨座101旋转起来形成一桨盘。在本实施方式中，所述桨座101的中心与所述桨盘的中心基本重合。当然，在其他实施方式中，所述螺旋桨100可以为直桨，所述螺旋桨100可以包括桨毂及与所述 桨毂固定连接的两个桨叶200。
在本实施方式中，所述螺旋桨100为固定式螺旋桨，两个所述桨叶200均固定地连接于所述桨座101上。可以理解，在其他的实施方式中，所述螺旋桨100可以为可折叠桨，所述桨叶200可转动地连接于所述桨座101上。或者，在一些实施方式中，所述桨叶200与所述桨座101为一体成型结构，或者，在一些实施方式中，所述桨叶200通过连接件可拆卸地装设于所述桨座101上，并不局限于本发明实施例中所描述。
同样可以理解的是，根据实际需要，每个所述螺旋桨100中所述桨叶200的数量可以为其他数量，如三个、四个等等。具体地如，在另一个实施方式中，所述桨叶200的数量为三个，三个所述桨叶200相对所述桨盘的中心在圆周方向上间隔均匀分布。
在本实施方式中，所述桨盘的直径为150±20毫米。具体地，所述桨盘的直径可以为130毫米、140毫米、150毫米、160毫米、170毫米，或者，所述桨盘的直径可以为上述任意两个数值所界定的数值范围内的任意值。优选地，所述桨盘的直径为150毫米。由于所述桨盘是由所述桨叶200及所述桨座101旋转而形成的效果，上文以及下文中所提到的“桨盘的中心”和“桨盘中心”，应当理解为“螺旋桨的回转中心”，类似地，上文以及下文中所提到的“桨盘的直径”和“桨盘直径”应当理解为“螺旋桨的回转直径”，“桨盘的半径”和“桨盘半径”应当理解为“螺旋桨的回转半径”。
所述桨座101可以用于与所述无人飞行器的驱动件的转轴相连接，以使所述驱动件能够驱动所述螺旋桨100转动。所述桨座101内可以嵌设有加强垫片，所述加强片可以采用铝合金等轻质高强度材料制成，以提高所述螺旋桨100的强度。
请同时参阅图4，在本实施方式中，所述桨座101大致呈圆柱状。两个所述桨叶200呈中心对称状设置在所述桨座101的两侧，且每个所述桨叶200与所述桨座101通过螺纹连接。在本实施方式中，所述螺旋桨的螺距为48mm±5毫米，所述螺距为螺旋桨100旋转一周，理论上沿轴向上升的距离。具体地，所述螺旋桨的螺距可以为43毫米、44毫米、45毫米、46毫米、47毫米、48毫米、49毫米、50毫米、51毫米、52毫米、53毫米，或者，所述螺距可以为上述任意两个数值所界定的数值范围内的任意值。优选地，所 述螺距为48毫米。
所述桨叶200包括相互背离设置的叶面10和叶背20，以及连接所述叶背20及所述叶面10的一侧的第一侧缘30、连接所述叶背20及所述叶面10的另一侧的第二侧缘40。所述叶面10的横截面轮廓及所述叶背20的横截面轮廓均弯曲(请参阅图6至图10)。当所述螺旋桨100装设在所述无人机的驱动件上时，所述叶面10朝向所述驱动件，也即，所述叶面10朝下设置；且所述叶背20背离所述驱动件，也即，所述叶背20朝上设置。在本实施方式中，所述叶面10及所述叶背20均为曲面，且在同一截面处，叶面10和叶背20的轮廓的曲率相等。所述第一侧缘30包括曲面状的向外凸出的第一拱起部31。所述第一拱起部31与所述第一侧缘30的其他部分平滑过渡连接。在本实施方式中，所述第一拱起部31邻近所述桨座101设置。所述第二侧缘40包括曲面状的向外凸出的第二拱起部41，所述第二拱起部41与所述第二侧缘40的其他部分平滑过渡连接。在本实施方式中，所述第二拱起部41邻近所述桨座101设置。所述第二拱起部41与所述桨座101之间的距离和所述第一拱起部31与所述桨座101之间的距离大致相同。
在本实施方式中，当对所述螺旋桨100沿其转动轴线方向进行正投影时(请参阅图2)，所述桨叶200的投影轮廓沿所述桨叶200的长度方向大致为对称结构，所述第一侧缘30及所述第二侧缘40大致关于所述桨叶200的中心线对称设置，所述第一拱起部31及所述第二拱起部41大致关于所述桨叶200的中心线对称设置，这就使得所述螺旋桨100装设于所述无人飞行器的驱动件上后，无论是顺时针转动或逆时针转动，都能够产生相应方向的推动力，有利于所述无人飞行器快速变换飞行方向。具体而言，上述的螺旋桨100以正桨为例，从驱动件尾部向头部方向看，所述螺旋桨100顺时针旋转以便为所述无人飞行器提供向上提升的推动力，当所述螺旋桨100逆时针旋转时，其能够为所述无人飞行器提供向下降落或降低飞行高度的推动力。因此，采用所述螺旋桨100的无人飞行器能够快速地提升或拉低高度、快速地变换飞行方向如前进、后退、左转、右转等等，所述无人飞行器更适应于3D暴力飞行。
综上所述，对于上述的螺旋桨100的桨叶200，将其具有所述叶面10的一侧设为正面，将其具有所述叶背20的一侧设为反面，由于所述螺旋桨 100具有上述的对称结构，使所述正面与反面的形状、轮廓及结构均相同，因此，无论所述螺旋桨100是顺时针转动或逆时针转动，都能够产生相应方向的推动力，有利于所述无人飞行器快速变换飞行方向。
另外，在本发明实施方式中，所述桨叶200上无急剧扭转之处，应力较小，结构强度较高，不易折断，可靠性高。所述桨叶200远离所述桨座101的一端为所述桨叶200最薄的部分，有利于减小空气阻力。即，所述桨叶200远离所述桨盘的中心的一端的厚度小于所述桨叶200其他部分的厚度。
本实施方式中，所述桨叶200的长度为75±10毫米。所述桨叶200的长度可以为65毫米至85毫米之间的任意值，例如65毫米、70毫米、75毫米、80毫米、85毫米，或者，所述桨叶200的长度可以为上述任意两个数值所界定的数值范围内的任意值。优选地，所述桨叶200的长度为75毫米。
本文中所指的攻角，是指所述桨叶200的翼弦与来流速度之间的夹角。
请同时参阅图5及图6，在所述桨叶200上距所述桨盘的中心O的距离为所述桨盘半径的46.67％处，所述桨叶200的攻角α1为19.86±1.5度。具体地，此处所述桨叶200的攻角α1可以为18.36度、18.86度、19.36度、19.86度、20.36度、20.86度、21.36度，或者，此处所述桨叶200的攻角α1可以为上述任意两个数值所界定的数值范围内的任意值，在本实施方式中，所述攻角α1为19.86度。在所述桨叶200上距所述桨盘的中心O的距离为所述桨盘半径的46.67％处，所述桨叶200的弦长L1为14.17±3毫米。具体地，此处所述桨叶200的弦长L1可以为11.17毫米、12.17毫米、13.17毫米、14.17毫米、15.17毫米、16.17毫米、17.17毫米，或者，此处所述桨叶200的弦长L1可以为上述任意两个数值所界定的数值范围内的数值，在本实施方式中，所述弦长L1为14.17毫米。
请同时参阅图5及图7，在所述桨叶200上距所述桨盘的中心O的距离为所述桨盘半径的60％处，所述桨叶200的攻角α2为16.89±1.5度。具体地，此处所述桨叶200的攻角α12可以为15.39度、15.89度、16.39度、16.89度、17.39度、17.89度、18.39度，或者，此处所述桨叶200的攻角α2可以为上述任意两个数值所界定的数值范围内的任意值，在本实施方式中，所述攻角α2为16.89度。在所述桨叶200上距所述桨盘的中心O的距离为所述桨盘半径的60％处，所述桨叶200的弦长L2为12.88±3毫米。具体地，此 处所述桨叶200的弦长L2可以为9.88毫米、10.88毫米、11.88毫米、12.88毫米、13.88毫米、14.88毫米、15.88毫米，或者，具体地，此处所述桨叶200的弦长L2可以为上述任意两个数值所界定的数值范围内的任意值，在本实施方式中，所述弦长L2为12.88毫米。
请同时参阅图5及图8，在所述桨叶200上距所述桨盘的中心O的距离为所述桨盘半径的73.33％处，所述桨叶200的攻角α3为15±1.5度。体地，此处所述桨叶200的攻角α3可以为13.5度、14度、14.5度、15度、15.5度、16度16.5度，或者，此处所述桨叶200的攻角α3可以为上述任意两个数值所界定的数值范围内的任意值，在本实施方式中，所述攻角α3为15度。在所述桨叶200上距所述桨盘的中心O的距离为所述桨盘半径的73.33％处，所述桨叶200的弦长L3为11.8±3毫米。具体地，此处所述桨叶200的弦长L3可以为8.8毫米、9.8毫米、10.8毫米、11.8毫米、12.8毫米、13.8毫米、14.8毫米，或者，此处所述桨叶200的弦长L3可以为上述任意两个数值所界定的数值范围内的任意值，在本实施方式中，所述弦长L3为11.8毫米。
请同时参阅图5及图9，在所述桨叶200上距所述桨盘的中心O的距离为所述桨盘半径的86.67％处，所述桨叶200的攻角α4为13.78±1.5度。具体地，此处所述桨叶200的攻角α4可以为12.28度、12.78度、13.28度、13.78度、14.28度、14.78度、15.28度，或者，此处所述桨叶200的攻角α4可以为上述任意两个数值所界定的数值范围内的任意值，在本实施方式中，所述攻角α4为13.78度。在所述桨叶200上距所述桨盘的中心O的距离为所述桨盘半径的86.67％处，所述桨叶200的弦长L4为10.78±3毫米。具体地，此处所述桨叶200的弦长L4可以为7.78毫米、8.78毫米、9.78毫米、10.78毫米、11.78毫米、12.78毫米、13.78毫米，或者，此处所述桨叶200的弦长L4可以为上述任意两个数值所界定的数值范围内的任意值，在本实施方式中，所述弦长L4为10.78毫米。
请同时参阅图5及图10，在所述桨叶200上距所述桨盘的中心O的距离为所述桨盘半径的98.67％处，所述桨叶200的攻角α5为12.54±1.5度。具体地，此处所述桨叶200的攻角α5可以为11.04度、11.54度、12.04度、12.54度、13.04度、13.54度、14.04度，或者，此处所述桨叶200的攻角α5可以为上述任意两个数值所界定的数值范围内的任意值，在本实施方式中， 所述攻角α5为12.54度。在所述桨叶200上距所述桨盘的中心O的距离为所述桨盘半径的98.67％处，所述桨叶200的弦长L5为9.76±3毫米。具体地，此处所述桨叶200的弦长L5可以为6.76毫米、7.76毫米、8.76毫米、9.76毫米、10.76毫米、11.76毫米、12.76毫米，或者，此处所述桨叶200的弦长L5可以为上述任意两个数值所界定的数值范围内的任意值，在本实施方式中，所述弦长L5为9.76毫米。
请再次参阅图5至图10，在本实施方式中，所述桨盘的直径为150毫米。在所述桨叶200上距离所述桨盘的中心35毫米处，所述桨叶200的攻角α1为19.86度，所述桨叶200的弦长L1为14.17毫米；在距离所述桨盘的中心45毫米处，所述桨叶200的攻角α2为16.89度，所述桨叶200的弦长L2为12.88毫米；在距离所述桨盘的中心55毫米处，所述桨叶200的攻角α3为15度，所述桨叶200的弦长L3为11.8毫米；在距离所述桨盘的中心65毫米处，所述桨叶200的攻角α4为13.78度，所述桨叶200的弦长L4为10.76毫米；在距离所述桨盘的中心74毫米处，所述桨叶200的攻角α5为12.54度，所述桨叶200的弦长L5为9.76毫米。
请参阅表1，表1所示为本实施方式提供的螺旋桨在不同的转速下的推动力值。
表1螺旋桨转速-推动力值
项次 转速(转/分) 推动力(克)
1 8790 102
2 11653 176
3 13979 250
4 16760 350
5 18500(最大) 472
由表中可以看出，本实施方式提供的螺旋桨能够提供较大的拉力，从而节省电量消耗，增加了无人飞行器的续航距离，提高了效率。
本发明提供的螺旋桨通过对桨叶的不同部位的攻角的设计，减少了空气阻力，提高了效率，增加了飞行器的续航距离并提高了飞行器的飞行性能。同时，所述螺旋桨的桨叶具有对称结构，其正面与反面的形状、轮廓及结构均相同，因此，无论所述螺旋桨是顺时针转动或逆时针转动，都能够产生相 应方向的推动力，有利于所述无人飞行器快速变换飞行方向。
另外，本技术领域的普通技术人员应当认识到，以上的实施方式仅是用来说明本发明，而并非用作为对本发明的限定，只要在本发明的实质精神范围之内，对以上实施例所作的适当改变和变化都落在本发明要求保护的范围之内。

Claims (17)

  1. 一种螺旋桨，其包括桨叶，其特征在于：在所述桨叶上距所述螺旋桨的回转中心的距离为所述螺旋桨的回转半径的60％处，所述桨叶的攻角为16.89±1.5度；在所述桨叶上距所述螺旋桨的回转中心的距离为所述螺旋桨的回转半径的73.33％处，所述桨叶的攻角为15±1.5度；在所述桨叶上距所述螺旋桨的回转中心的距离为所述螺旋桨的回转半径的86.67％处，所述桨叶的攻角为13.78±1.5度。
  2. 如权利要求1所述的螺旋桨，其特征在于：在所述桨叶上距所述螺旋桨的回转中心的距离为所述螺旋桨的回转半径的46.67％处，所述桨叶的攻角为19.86±1.5度；
    或/及，在所述桨叶上距所述螺旋桨的回转中心的距离为所述螺旋桨的回转半径的98.67％处，所述桨叶的攻角为12.54±1.5度。
  3. 如权利要求1所述的螺旋桨，其特征在于：所述螺旋桨的回转直径为150毫米，在距离所述螺旋桨的回转中心35毫米处，所述桨叶的攻角为19.86±1.5度；
    或/及，在距离所述螺旋桨的回转中心45毫米处，所述桨叶的攻角为16.89±1.5度；
    或/及，在距离所述螺旋桨的回转中心55毫米处，所述桨叶的攻角为15±1.5度；
    或/及，在距离所述螺旋桨的回转中心65毫米处，所述桨叶的攻角为13.78±1.5度；
    或/及，在距离所述螺旋桨的回转中心74毫米处，所述桨叶的攻角为12.54±1.5度。
  4. 如权利要求1所述的螺旋桨，其特征在于：在所述桨叶上距所述螺旋桨的回转中心的距离为所述螺旋桨的回转半径的60％处，所述桨叶的弦长为12.88±3毫米；
    或/及，在所述桨叶上距所述螺旋桨的回转中心的距离为所述螺旋桨的回转半径的73.33％处，所述桨叶的弦长为11.8±3毫米；
    或/及，在所述桨叶上距所述螺旋桨的回转中心的距离为所述螺旋桨的回 转半径的86.67％处，所述桨叶的弦长为10.76±3毫米。
  5. 如权利要求4所述的螺旋桨，其特征在于：在所述桨叶上距所述螺旋桨的回转中心的距离为所述螺旋桨的回转半径的46.37％处，所述桨叶的弦长为14.17±3毫米；
    或/及，在所述桨叶上距所述螺旋桨的回转中心的距离为所述螺旋桨的回转半径的98.67％处，所述桨叶的弦长为9.76±3毫米。
  6. 如权利要求1所述的螺旋桨，其特征在于：所述螺旋桨的回转的直径为150±20毫米。
  7. 如权利要求1所述的螺旋桨，其特征在于：所述桨叶的正面的结构与所述桨叶的反面的结构相同，使所述螺旋桨在顺时针或逆时针转动时，均能够产生相应方向的推动力。
  8. 如权利要求1所述的螺旋桨，其特征在于：对所述螺旋桨进行沿所述螺旋桨的转动轴线方向的正投影时，所述桨叶的正投影轮廓为对称结构。
  9. 如权利要求8所述的螺旋桨，其特征在于：所述桨叶包括相互背离设置的叶面及叶背，以及连接所述叶背及所述叶面的一侧的第一侧缘、连接所述叶背及所述叶面的另一侧的第二侧缘；所述桨叶具有所述叶面的一侧为所述正面，所述桨叶具有所述叶背的一侧为所述反面。
  10. 如权利要求9所述的螺旋桨，其特征在于：所述叶面的横截面轮廓及所述叶背的横截面轮廓均弯曲；
    或/及，对所述螺旋桨进行沿所述螺旋桨的转动轴线方向的正投影时，所述第一侧缘及所述第二侧缘大致关于所述桨叶的中心线对称设置。
  11. 如权利要求9所述的螺旋桨，其特征在于：所述第一侧缘包括曲面状的向外凸出的第一拱起部；所述第二侧缘包括曲面状的向外凸出的第二拱起部。
  12. 如权利要求11所述的螺旋桨，其特征在于：所述第一拱起部及所述第二拱起部均靠近所述螺旋桨的回转中心设置；
    或/及，对所述螺旋桨进行沿所述螺旋桨的转动轴线方向的正投影时，所述第一拱起部及所述第二拱起部关于所述桨叶的中心线对称设置。
  13. 如权利要求1所述的螺旋桨，其特征在于：所述螺旋桨为折叠桨，所述螺旋桨还包括桨座，所述桨叶的数量为至少两个，每个所述桨叶能够转 动地连接于所述桨座上；
    或者，所述螺旋桨包括与所述桨叶固定连接的桨毂，所述桨叶的数量为至少两个。
  14. 如权利要求1所述的螺旋桨，其特征在于：所述螺旋桨的螺距为48mm±5毫米。
  15. 一种无人飞行器的动力套装，其特征在于：所述动力套装包括权利要求1-14中任一项所述的至少一个螺旋桨及驱动所述螺旋桨转动的驱动件。
  16. 如权利要求15所述的动力套装，其特征在于：所述驱动件为电机，所述螺旋桨连接于所述电机上，所述电机的KV值为2300转/(分钟.伏特)。
  17. 一种无人飞行器，其包括机身、多个机臂及权利要求15或16所述的多个动力套装，所述多个机臂与所述机身连接，所述多个动力套装分别安装在所述多个机臂上。
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