WO2018018729A1 - 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
WO2018018729A1
WO2018018729A1 PCT/CN2016/099523 CN2016099523W WO2018018729A1 WO 2018018729 A1 WO2018018729 A1 WO 2018018729A1 CN 2016099523 W CN2016099523 W CN 2016099523W WO 2018018729 A1 WO2018018729 A1 WO 2018018729A1
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Prior art keywords
propeller
blade
center
paddle
distance
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PCT/CN2016/099523
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English (en)
French (fr)
Inventor
刘峰
江彬
邓涛
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深圳市大疆创新科技有限公司
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Publication of WO2018018729A1 publication Critical patent/WO2018018729A1/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

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 distance of 43.33% of a radius of revolution of the propeller on the blade, the angle of attack of the blade being 27.4 ⁇ 2.5 degrees;
  • the distance from the center of rotation of the propeller on the blade is 62.59% of the radius of gyration of the propeller, the angle of attack of the blade is 19.2 ⁇ 2.5 degrees;
  • the pitch of the propeller is from the propeller
  • the distance from the center of revolution is 81.85% of the radius of gyration of the propeller, and the angle of attack of the blade is 14.1 ⁇ 2.5 degrees.
  • the distance from the center of rotation of the propeller on the blade is 27.78% of the radius of gyration of the propeller, and the angle of attack of the blade is 29.3 ⁇ 2.5 degrees;
  • the distance from the center of rotation of the propeller on the blade is 98.15% of the radius of gyration of the propeller, and the angle of attack of the blade is 13.2 ⁇ 2.5 degrees.
  • the rotary diameter of the propeller is 540 mm, and the angle of attack of the blade is 29.3 ⁇ 2.5 degrees at a distance of 75 mm from the center of rotation of the propeller;
  • the angle of attack of the blade is 19.2 ⁇ 2.5 degrees;
  • the blade has an angle of attack of 13.2 ⁇ 2.5 degrees.
  • the distance from the center of rotation of the propeller on the blade is 43.33% of the radius of gyration of the propeller, and the chord length of the blade is 36 ⁇ 5 mm;
  • the distance from the center of rotation of the propeller on the blade is 62.59% of the radius of gyration of the propeller, the chord length of the blade is 30.92 ⁇ 5 mm;
  • the distance from the center of rotation of the propeller on the blade is 81.85% of the radius of gyration of the propeller, and the chord length of the blade is 25.2 ⁇ 5 mm.
  • the distance from the center of rotation of the propeller on the blade is 27.78% of the radius of gyration of the propeller, and the chord length of the blade is 41.3 ⁇ 5 mm;
  • the distance from the center of rotation of the propeller on the blade is 98.15% of the radius of gyration of the propeller, and the chord length of the blade is 19.99 ⁇ 5 mm.
  • the diameter of the rotation of the propeller is 540 ⁇ 50 mm.
  • 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 foliage and the cross-sectional profile of the blade back are both curved.
  • first side edge comprises a curved outwardly convex first arching portion; the second side edge comprises a curved outwardly projecting second arching portion.
  • the propeller further includes a paddle, and the blade is provided with a mounting portion, and the mounting portion is connected to the paddle.
  • the mounting portion is provided with a connecting hole for engaging with a fastener, so that the mounting portion can be connected to the paddle by the fastener;
  • the center of the paddle is a center of rotation of the propeller, and the mounting portion is provided with a connecting hole through which the mounting portion can be connected to the paddle, the connecting hole The center is spaced apart from the center of the paddle by a predetermined distance.
  • 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 propeller has a geometric pitch of 9.5 ⁇ 0.5 inches.
  • 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 135 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 view showing the structure of a blade of a propeller according to an embodiment of the present invention.
  • Figure 2 is a front elevational view of the paddle of Figure 1.
  • Figure 3 is a side elevational view of the paddle of Figure 1.
  • FIG. 4 is a side elevational view of another perspective of the paddle of FIG. 1.
  • Figure 5 is a front elevational view of the paddle 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 43.33% of the radius of gyration of the propeller, the angle of attack of the blade is 27.4 ⁇ 2.5 degrees; the propeller is spaced from the propeller
  • the distance of the center of revolution is 62.59% of the radius of gyration of the propeller, the angle of attack of the blade is 19.2 ⁇ 2.5 degrees; the distance from the center of rotation of the propeller on the blade is the propeller
  • the angle of attack of the blade is 14.1 ⁇ 2.5 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 135 rpm / (minute volts).
  • the propeller includes a blade on which the distance from the center of rotation of the propeller is 43.33% of the radius of gyration of the propeller, and the angle of attack of the blade is 27.4 ⁇ 2.5 degrees;
  • the distance from the center of rotation of the propeller on the blade is 62.59% of the radius of gyration of the propeller, the angle of attack of the blade is 19.2 ⁇ 2.5 degrees;
  • the center of rotation of the propeller is on the blade
  • the distance is 81.85% of the radius of gyration of the propeller, and the angle of attack of the blade is 14.1 ⁇ 2.5 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, the motor for driving the propeller to rotate, the motor having a KV value of 135 rpm / (minute volt).
  • the propeller includes a blade on which the distance from the center of rotation of the propeller is 43.33% of the radius of gyration of the propeller, and the angle of attack of the blade is 27.4 ⁇ 2.5 degrees;
  • the distance from the center of rotation of the propeller on the blade is 62.59% of the radius of gyration of the propeller, the angle of attack of the blade is 19.2 ⁇ 2.5 degrees;
  • the center of rotation of the propeller is on the blade
  • the distance is 81.85% of the radius of gyration of the propeller, and the angle of attack of the blade is 14.1 ⁇ 2.5 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 can 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 135 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 a schematic structural view of a blade 200 of a propeller according to an embodiment of the present invention is shown.
  • the propeller includes a paddle (not shown) and two blades 200 disposed on either side of the paddle, the two blades 200 being centrally symmetric about the center of the paddle.
  • the two blades 200 and the paddle are rotated to form a paddle.
  • the center of the paddle substantially coincides with the center of the paddle.
  • the propeller may be a straight paddle, and the propeller may include a hub and two or more blades 200 that are fixedly coupled to the hub.
  • the propeller is a stationary propeller, and the two blades 200 are fixedly coupled to the paddle.
  • one end of the blade 200 is provided with a mounting portion 201
  • the mounting portion 201 is provided with a connecting hole 203 through which the mounting portion 201 passes the paddle Connected to connect the paddle 200 to the paddle.
  • the connecting hole 203 is a threaded hole, and a fastener such as a screw is disposed in the threaded hole, and the mounting portion 201 is connected to the paddle by the fastener.
  • the distance between the center of the connecting hole 203 and the center O of the paddle is approximately 23 mm.
  • the distance between the center of the connecting hole 203 and the center of the paddle can be set according to actual needs, and is not limited to the description of the embodiments of the present invention. Even in some embodiments, the mounting portion 201 and the connecting hole 203 may be omitted.
  • the propeller may be a foldable paddle, the paddle 200 being rotatably coupled to the paddle.
  • the paddle 200 is integrally formed with the paddle or, in some embodiments, the paddle 200 is removably mounted to the paddle by a connector. It is not limited to being described in the embodiment of the present invention.
  • the number of blades 200 in each of the propellers may be other numbers, such as three, four, etc., depending on actual needs. Specifically, as in another embodiment, 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 540 ⁇ 50 mm.
  • the diameter of the paddle may be 490 mm, 510 mm, 540 mm, 570 mm, 590 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 “propeller” "Slewing center”, similarly, “diameter of paddle” and “paddle diameter” mentioned above and below should be understood as “slewing diameter of propeller”, “radius of paddle” and “basin radius” “It should be understood as “the radius of gyration of the propeller”.
  • the paddle 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 to rotate.
  • a reinforcing spacer may be embedded in the paddle, and the reinforcing piece may be made of a lightweight high-strength material such as aluminum alloy to increase the strength of the propeller.
  • the paddle is substantially cylindrical. Two of the blades 200 are disposed in a central symmetry on both sides of the paddle, and the connection between each of the blades 200 and the paddle is threadedly connected.
  • the geometric pitch of the propeller is 9.5 ⁇ 0.5 inches, and the geometric pitch is the distance that the blade advances one revolution when the blade angle of attack is zero.
  • the geometric pitch of the propeller may be 9.0 inches, 9.1 inches, 9.2 inches, 9.3 inches, 9.4 inches, 9.5 inches 9.6 inches, 9.7 inches, 9.8 inches, 9.9 inches, 10.0 inches, or the geometric pitch may be Within the range of values defined by any two of the above values Any value.
  • the geometric pitch is 9.5 inches.
  • 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 foliage 10 faces the drive member, that is, the foliage 10 is disposed downward; and the blade back 20 faces away from the The drive member, that is, the leaf back 20 is disposed upward.
  • the leaf surface 10 and the leaf back 20 are curved surfaces.
  • 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.
  • 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.
  • the blade 200 has no sharp torsion, 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 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 247 ⁇ 25 mm.
  • the length of the blade 200 may be any value between 222 mm and 272 mm, such as 222 mm, 237 mm, 247 mm, 257 mm, 272 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 247 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 27.78% of the blade radius, and the angle of attack ⁇ 1 of the blade 200 is 29.3 ⁇ 2.5. degree.
  • the angle of attack ⁇ 1 of the blade 200 herein may be 26.8 degrees, 27.8 degrees, 28.3 degrees, 29.3 degrees, 30.3 degrees, 30.8 degrees, 31.8 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 29.3 degrees.
  • the distance from the center O of the paddle on the paddle 200 is 27.78% of the paddle radius, and the chord length L1 of the paddle 200 is 41.3 ⁇ 5 mm.
  • the chord length L1 of the blade 200 may be 36.3 mm, 37.3 mm, 39.3 mm, 41.3 mm, 43.3 mm, 45.3 mm, 46.3 mm, or alternatively, the chord length L1 of the blade 200 may be any of the above two values.
  • the numerical value within the defined numerical range, in the present embodiment, the chord length L1 is 41.3 mm.
  • the distance from the center O of the paddle on the paddle 200 is 43.33% of the paddle radius, and the angle of attack ⁇ 2 of the paddle 200 is 27.4 ⁇ 2.5. degree.
  • the angle of attack ⁇ 2 of the blade 200 herein may be 24.9 degrees, 25.9 degrees, 26.4 degrees, 27.4 degrees, 28.4 degrees, 28.9 degrees, 29.9 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. In the present embodiment, the angle of attack ⁇ 2 is 27.4 degrees.
  • chord length L2 of the paddle 200 is 36 ⁇ 5 mm.
  • the chord length L2 of the blade 200 herein may be 31 mm, 32 mm, 34 mm, 36 mm, 38 mm, 39 mm, 41 mm, or, in particular, the blade 200 herein
  • the chord length L2 may be any value within a numerical range defined by any two of the above numerical values. In the present embodiment, the chord length L2 is 36 mm.
  • the distance from the center O of the paddle on the blade 200 is 62.59% of the blade radius, and the angle of attack ⁇ 3 of the blade 200 is 19.2 ⁇ 2.5. degree.
  • the angle of attack ⁇ 3 of the blade 200 herein may be 16.7 degrees, 17.7 degrees, 18.2 degrees, 19.2 degrees, 20.2 degrees, 20.7 degrees, 21.7 degrees, or the angle of attack ⁇ 3 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 ⁇ 3 is 19.2 degrees.
  • chord length L3 of the paddle 200 is 30.92 ⁇ 5 mm.
  • the chord length L3 of the blade 200 herein may be 25.92 mm, 26.92 mm, 28.92 mm, 30.92 mm, 32.92 mm, 33.92 mm, 35.92 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 30.92 mm.
  • the distance from the center O of the paddle on the paddle 200 is 81.85% of the paddle radius, and the angle of attack ⁇ 4 of the paddle 200 is 14.1 ⁇ 2.5. degree.
  • the angle of attack ⁇ 4 of the blade 200 herein may be 11.6 degrees, 12.6 degrees, 13.1 degrees, 14.1 degrees, 15.1 degrees, 15.6 degrees, 16.6 degrees, or the angle of attack ⁇ 4 of the blade 200 herein.
  • the angle of attack ⁇ 4 is 14.1 degrees.
  • the distance from the center O of the paddle on the paddle 200 is 81.85% of the paddle radius, and the chord length L4 of the paddle 200 is 25.2 ⁇ 5 mm.
  • chord length L4 of the blade 200 herein may be 20.2 mm, 21.2 mm, 23.2 mm, 25.2 mm, 27.2 mm, 28.2 mm, 30.2 mm, or the chord length L4 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 L4 is 25.2 mm.
  • the distance from the center O of the paddle on the blade 200 is 98.15% of the paddle radius, and the angle of attack ⁇ 5 of the blade 200 is 13.2 ⁇ 2.5. degree.
  • the angle of attack ⁇ 5 of the blade 200 herein may be 10.7 degrees, 11.7 degrees, 12.2 degrees, 13.2 degrees, 13.7 degrees, 14.7 degrees, 15.7 degrees, or the angle of attack ⁇ 5 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 ⁇ 5 is 13.2 degrees.
  • the distance from the center O of the paddle on the paddle 200 is 98.15% of the paddle radius, and the chord length L5 of the paddle 200 is 19.99 ⁇ 5 mm.
  • chord length L5 of the blade 200 herein may be 14.99 mm, 15.99 mm, 17.99 mm, 19.99 mm, 21.99 mm, 23.99 mm, 24.99 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 19.99 mm.
  • the paddle has a diameter of 540 mm.
  • the angle of attack ⁇ 1 of the blade 200 is 29.3 degrees, the chord length L1 of the blade 200 is 41.3 mm; at the distance from the paddle At a center of 117 mm, the angle of attack ⁇ 2 of the blade 200 is 27.4 degrees, the chord length L2 of the blade 200 is 36 mm; at a distance of 169 mm from the center of the paddle, the blade 200
  • the angle of attack ⁇ 3 is 19.2 degrees
  • the chord length L3 of the blade 200 is 30.92 mm, and the angle of attack ⁇ 4 of the blade 200 is 14.1 degrees at a distance of 221 mm from the center of the paddle, the blade 200
  • the chord length L4 is 25.2 mm; at an angle of 265 mm from the center of the paddle, the blade angle 200 of the blade 200 is 13.2 degrees, and the chord length L5 of the blade 200 is 1
  • 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.

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Abstract

一种螺旋桨、动力组件及飞行器，其包括螺旋桨桨叶(200)，其中，在所述桨叶(200)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43.33％处，所述桨叶(200)的攻角为27.4±2.5度；在所述桨叶(200)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62.59％处，所述桨叶(200)的攻角为19.2±2.5度；在所述桨叶(200)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81.85％处，所述桨叶(200)的攻角为14.1±2.5度。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。

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43.33％处，所述桨叶的攻角为27.4±2.5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62.59％处，所述桨叶的攻角为19.2±2.5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81.85％处，所述桨叶的攻角为14.1±2.5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27.78％处，所述桨叶的攻角为29.3±2.5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98.15％处，所述桨叶的攻角为13.2±2.5度。
进一步地，所述螺旋桨的回转直径为540毫米，在距离所述螺旋桨的回转中心75毫米处，所述桨叶的攻角为29.3±2.5度；
或/及，在距离所述螺旋桨的回转中心117毫米处，所述桨叶的攻角为27.4±2.5度；
或/及，在距离所述螺旋桨的回转中心169毫米处，所述桨叶的攻角为 19.2±2.5度；
或/及，在距离所述螺旋桨的回转中心221毫米处，所述桨叶的攻角为14.1±2.5度；
或/及，在距离所述螺旋桨的回转中心265毫米处，所述桨叶的攻角为13.2±2.5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43.33％处，所述桨叶的弦长为36±5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62.59％处，所述桨叶的弦长为30.92±5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81.85％处，所述桨叶的弦长为25.2±5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27.78％处，所述桨叶的弦长为41.3±5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98.15％处，所述桨叶的弦长为19.99±5毫米。
进一步地，所述螺旋桨的回转的直径为540±50毫米。
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。
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，所述螺旋桨还包括桨座，所述桨叶上设置有安装部，所述安装部与所述桨座连接。
进一步地，所述安装部上设置有连接孔，所述连接孔用于与紧固件相配合，以使所述安装部能够通过所述紧固件连接于所述桨座；
或/及，所述桨座的中心为所述螺旋桨的回转中心，所述安装部上设置有连接孔，所述安装部能够通过所述连接孔与所述桨座相连接，所述连接孔的中心与所述桨座的中心间隔预设距离。
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，所述螺旋桨的几何螺距为9.5±0.5英寸。
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135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桨叶结构示意图。
图2是图1中的桨叶的主视图。
图3是图1中的桨叶的侧视图。
图4是图1中的桨叶的另一视角的侧视图。
图5是图2中的桨叶的正面示意图。
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
桨叶                          200
安装部                        201
连接孔                        203
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(40％～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43.33％处，所述桨叶的攻角为27.4±2.5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62.59％处，所述桨叶的攻角为19.2±2.5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81.85％处，所述桨叶的攻角为14.1±2.5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135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43.33％处，所述桨叶的攻角为27.4±2.5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62.59％处，所述桨叶的攻角为19.2±2.5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81.85％处，所述桨叶的攻角为14.1±2.5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135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43.33％处，所述桨叶的攻角为27.4±2.5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62.59％处，所述桨叶的攻角为19.2±2.5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81.85％处，所述桨叶的攻角为14.1±2.5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135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的桨叶200的结构示意图。所述螺旋桨包括桨座(图中未示出)及设置于所述桨座两侧的两个桨叶200，两个所述桨叶200关于所述桨座的中心呈中心对称设置。两个所述桨叶200及所述桨座旋转起来形成一桨盘。在本实施方式中，所述桨座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，所述螺旋桨可以为直桨，所述螺旋桨可以包括桨毂及与所述桨毂固定连接的两个或多个桨叶200。
在本实施方式中，所述螺旋桨为固定式螺旋桨，两个所述桨叶200均固定地连接于所述桨座上。具体在图示的实施方式中，所述桨叶200的一端设置有安装部201，所述安装部201上设置有连接孔203，所述安装部201通过所述连接孔203与所述桨座相连接，以使所述桨叶200连接于所述桨座上。在本实施方式中，所述连接孔203为螺纹孔，所述螺纹孔内设置有螺钉等紧固件，所述安装部201通过所述紧固件与所述桨座连接。在一实施方式中， 所述连接孔203的中心与所述桨座的中心O之间的距离大致为23毫米。可以理解，在其他一些实施方式中，所述连接孔203的中心与所述桨座的中心之间的距离可以根据实际需要设置，并不局限于本发明实施例所描述。甚至，在一些实施例中，所述安装部201及所述连接孔203均可以省略。
可以理解，在其他的实施方式中，所述螺旋桨可以为可折叠桨，所述桨叶200可转动地连接于所述桨座上。或者，在一些实施方式中，所述桨叶200与所述桨座为一体成型结构，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相对所述桨座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540±50毫米。具体地，所述桨盘的直径可以为490毫米、510毫米、540毫米、570毫米、590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转动。所述桨座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，以提高所述螺旋桨的强度。
请同时参阅图4，在本实施方式中，所述桨座大致呈圆柱状。两个所述桨叶200呈中心对称状设置在所述桨座的两侧，且每个所述桨叶200与所述桨座之间的连接呈螺纹状连接。在本实施方式中，所述螺旋桨的几何螺距为9.5±0.5英寸，所述几何螺距为桨叶剖面迎角为零时，桨叶旋转一周所前进的距离。具体地，所述螺旋桨的几何螺距可以为9.0英寸、9.1英寸、9.2英寸、9.3英寸、9.4英寸、9.5英寸9.6英寸、9.7英寸、9.8英寸、9.9英寸、10.0英寸，或者，所述几何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，所述几何螺距为9.5英寸。
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的横截面轮廓均为弯曲结构(请参阅图6至图10)。当所述螺旋桨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。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邻近所述桨座设置。
在本发明实施方式所提供的螺旋桨中，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247±25毫米。所述桨叶200的长度可以为222毫米至272毫米之间的任意值，例如222毫米、237毫米、247毫米、257毫米、272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247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27.78％处，所述桨叶200的攻角α1为29.3±2.5度。具体地，此处所述桨叶200的攻角α1可以为26.8度、27.8度、28.3度、29.3度、30.3度、30.8度、31.8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29.3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27.78％处，所述桨叶200的弦长L1为41.3±5毫米。具体地，此处所述桨 叶200的弦长L1可以为36.3毫米、37.3毫米、39.3毫米、41.3毫米、43.3毫米、45.3毫米、46.3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41.3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43.33％处，所述桨叶200的攻角α2为27.4±2.5度。具体地，此处所述桨叶200的攻角α2可以为24.9度、25.9度、26.4度、27.4度、28.4度、28.9度、29.9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27.4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43.33％处，所述桨叶200的弦长L2为36±5毫米。具体地，此处所述桨叶200的弦长L2可以为31毫米、32毫米、34毫米、36毫米、38毫米、39毫米、41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36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62.59％处，所述桨叶200的攻角α3为19.2±2.5度。具体地，此处所述桨叶200的攻角α3可以为16.7度、17.7度、18.2度、19.2度、20.2度、20.7度、21.7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19.2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62.59％处，所述桨叶200的弦长L3为30.92±5毫米。具体地，此处所述桨叶200的弦长L3可以为25.92毫米、26.92毫米、28.92毫米、30.92毫米、32.92毫米、33.92毫米、35.92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30.92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81.85％处，所述桨叶200的攻角α4为14.1±2.5度。具体地，此处所述桨叶200的攻角α4可以为11.6度、12.6度、13.1度、14.1度、15.1度、15.6度、16.6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14.1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81.85％处，所述桨叶200的弦长L4为25.2±5毫米。具体地，此处所述桨叶200的弦长L4可以为20.2毫米、21.2毫米、23.2毫米、25.2毫米、27.2毫米、28.2毫米、30.2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25.2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98.15％处，所述桨叶200的攻角α5为13.2±2.5度。具体地，此处所述桨叶200的攻角α5可以为10.7度、11.7度、12.2度、13.2度、13.7度、14.7度、15.7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13.2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98.15％处，所述桨叶200的弦长L5为19.99±5毫米。具体地，此处所述桨叶200的弦长L5可以为14.99毫米、15.99毫米、17.99毫米、19.99毫米、21.99毫米、23.99毫米、24.99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19.99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540毫米。在所述桨叶200上距离所述桨盘的中75毫米处，所述桨叶200的攻角α1为29.3度，所述桨叶200的弦长L1为41.3毫米；在距离所述桨盘的中心117毫米处，所述桨叶200的攻角α2为27.4度，所述桨叶200的弦长L2为36毫米；在距离所述桨盘的中心169毫米处，所述桨叶200的攻角α3为19.2度，所述桨叶200的弦长L3为30.92毫米；在距离所述桨盘的中心221毫米处，所述桨叶200的攻角α4为14.1度，所述桨叶200的弦长L4为25.2毫米；在距离所述桨盘的中心265毫米处，所述桨叶200的攻角α5为13.2度，所述桨叶200的弦长L5为19.99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
Figure PCTCN2016099523-appb-000001
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。
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 (16)

  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43.33％处，所述桨叶的攻角为27.4±2.5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62.59％处，所述桨叶的攻角为19.2±2.5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81.85％处，所述桨叶的攻角为14.1±2.5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27.78％处，所述桨叶的攻角为29.3±2.5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98.15％处，所述桨叶的攻角为13.2±2.5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540毫米，在距离所述螺旋桨的回转中心75毫米处，所述桨叶的攻角为29.3±2.5度；
    或/及，在距离所述螺旋桨的回转中心117毫米处，所述桨叶的攻角为27.4±2.5度；
    或/及，在距离所述螺旋桨的回转中心169毫米处，所述桨叶的攻角为19.2±2.5度；
    或/及，在距离所述螺旋桨的回转中心221毫米处，所述桨叶的攻角为14.1±2.5度；
    或/及，在距离所述螺旋桨的回转中心265毫米处，所述桨叶的攻角为13.2±2.5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43.33％处，所述桨叶的弦长为36±5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62.59％处，所述桨叶的弦长为30.92±5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81.85％处，所述桨叶的弦长为25.2±5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27.78％处，所述桨叶的弦长为41.3±5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98.15％处，所述桨叶的弦长为19.99±5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540±50毫米。
  7. 如权利要求1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。
  8. 如权利要求7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为弯曲结构。
  9. 如权利要求7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。
  10. 如权利要求1所述的螺旋桨，其特征在于：所述螺旋桨还包括桨座，所述桨叶上设置有安装部，所述安装部与所述桨座连接。
  11. 如权利要求10所述的螺旋桨，其特征在于：所述安装部上设置有连接孔，所述连接孔用于与紧固件相配合，以使所述安装部能够通过所述紧固件连接于所述桨座；
    或/及，所述桨座的中心为所述螺旋桨的回转中心，所述安装部上设置有连接孔，所述安装部能够通过所述连接孔与所述桨座相连接，所述连接孔的中心与所述桨座的中心间隔预设距离。
  12. 如权利要求10所述的螺旋桨，其特征在于：所述螺旋桨为折叠桨，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。
  13. 如权利要求1所述的螺旋桨，其特征在于：所述螺旋桨的几何螺距为9.5±0.5英寸。
  14. 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1-11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。
  15. 如权利要求14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135转/(分钟·伏特)。
  16. 一种无人飞行器，其包括机身、多个机臂及权利要求14或15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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