WO2018098873A1 - 螺旋桨、动力组件及飞行器 - Google Patents

螺旋桨、动力组件及飞行器 Download PDF

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Publication number
WO2018098873A1
WO2018098873A1 PCT/CN2016/111919 CN2016111919W WO2018098873A1 WO 2018098873 A1 WO2018098873 A1 WO 2018098873A1 CN 2016111919 W CN2016111919 W CN 2016111919W WO 2018098873 A1 WO2018098873 A1 WO 2018098873A1
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WIPO (PCT)
Prior art keywords
paddle
propeller
blade
center
degrees
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Ceased
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PCT/CN2016/111919
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English (en)
French (fr)
Inventor
刘峰
陈鹏
邓涛
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SZ DJI Technology Co Ltd
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SZ DJI Technology Co Ltd
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Publication date
Application filed by SZ DJI Technology Co Ltd filed Critical SZ DJI Technology Co Ltd
Priority to CN201680088410.3A priority Critical patent/CN109562827A/zh
Publication of WO2018098873A1 publication Critical patent/WO2018098873A1/zh
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

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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
    • B64C11/20—Constructional features
    • 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
    • B64C27/467—Aerodynamic features

Definitions

  • the present invention relates to the field of aircraft technology, and more particularly to a propeller, a power assembly having the propeller, and an aircraft having the power assembly.
  • the aircraft is a rapidly developing flying device that has the advantages of flexibility, quick response, unmanned flight, and low operational requirements.
  • the scope of use of aircraft has been expanded to three major fields of military, scientific research and civil use, specifically in power, communications, meteorology, agriculture, oceanography, exploration, photography, disaster prevention and mitigation, crop yield estimation, anti-drug smuggling, border patrol, law and order. Perform various tasks in areas such as counter-terrorism.
  • the propellers of the existing aircrafts are mostly rectangular in shape, and the resistance is large and the efficiency is low, which results in a small flying speed of the aircraft and a short following distance, which seriously affects the flight performance of the aircraft.
  • Embodiments of the present invention aim to solve at least one of the technical problems existing in the prior art. To this end, embodiments of the present invention need to provide a propeller, a power assembly, and an aircraft.
  • the present invention provides a propeller that includes a paddle that rotates to form a paddle.
  • the center of the paddle is 43.86% of the radius of the paddle, and the angle of attack of the paddle is (20.27 ⁇ 2.5) degrees;
  • the center of the paddle is 61.40% of the paddle radius, and the blade has an angle of attack of (14.82 ⁇ 2.5) degrees;
  • the center of the paddle is 78.95% of the paddle radius, and the blade has an angle of attack of (11.75 ⁇ 2.5) degrees.
  • chord length of the blade is (14.13 ⁇ 5) mm at a distance of 43.86% of the paddle center from the center of the paddle;
  • the center of the paddle is 61.40% of the paddle radius, and the chord length of the blade is (12.67 ⁇ 5) mm; and/or
  • the center of the paddle is 78.95% of the paddle radius, and the chord length of the blade is (10.90 ⁇ 5) mm.
  • the blade has an angle of attack of (8.04 ⁇ 2.5) degrees from the center of the paddle at 96.49% of the paddle radius.
  • the paddle has a diameter in the range of (114 ⁇ 30) mm.
  • chord length of the paddle is (9.10 ⁇ 5) mm from the center of the paddle at 96.49% of the paddle radius.
  • the paddle includes a first face, a second face opposite the first face, a first side edge connecting the second face and a side of the first face, and a connection
  • the second side and the second side edge of the other side of the first surface are both curved by the first surface and the second surface.
  • the first face includes a convex first arch; the first side edge includes a curved outwardly projecting second arch; the second side edge includes a curved surface a third arched portion that protrudes outward.
  • the first bulge, the second bulge, and the third bulge are all near the center of the paddle.
  • the number of blades is two, two of the blade phases Centrally symmetric about the center of the paddle;
  • the thickness of one end of the blade away from the center of the paddle is less than the thickness of other portions of the paddle.
  • the propeller is a folding paddle and the propeller includes a hub that is rotationally or fixedly coupled to the blade, the number of blades being at least two.
  • the present invention provides a propeller, the propeller being a folding paddle, the propeller comprising a hub and at least two blades connected to the hub;
  • the paddle formed by the blade has a diameter of (114 ⁇ 30) mm;
  • the blade At an angle of 43.86% of the paddle radius from the center of the paddle, the blade has an angle of attack of (20.27 ⁇ 2.5) degrees and the blade has a chord length of (14.13 ⁇ 5) mm;
  • the center of the paddle is 61.40% of the radius of the paddle, the angle of attack of the paddle is (14.82 ⁇ 2.5) degrees, the chord length of the paddle is (12.67 ⁇ 5) mm;
  • the center of the paddle is 78.95% of the radius of the paddle, the angle of attack of the blade is (11.75 ⁇ 2.5) degrees, the chord length of the blade is (10.90 ⁇ 5) mm; at the distance from the center of the paddle At 96.49% of the paddle radius, the blade has an angle of attack of (8.04 ⁇ 2.5) degrees and the blade has a chord length of (9.10 ⁇ 5) mm.
  • the present invention provides a power assembly comprising the propeller of any of the above;
  • a driving member for driving the propeller to rotate.
  • the drive member is a motor having a KV value of 2100 KV.
  • the present invention provides an aircraft comprising a fuselage, at least one arm, and at least one power assembly according to any of the above embodiments, the arm being coupled to the body, the power components being respectively mounted on the machine On the arm.
  • the aircraft has a plurality of arms and power components, and the plurality of power components are respectively mounted on the plurality of the arms and rotated in different directions.
  • the propeller, the power component and the aircraft of the embodiment of the invention can reduce the resistance, improve the efficiency, increase the endurance time and the maximum flight distance, and improve the dynamic response speed of the blade by optimizing the angle of attack of different parts of the blade, thereby improving the flight of the aircraft. performance.
  • FIG. 1 is a perspective view of a blade of some embodiments of the present invention.
  • Figure 2 is a plan view of the blade of Figure 1;
  • Figure 3 is another plan view of the blade of Figure 1;
  • Figure 4 is a schematic cross-sectional view of the blade of Figure 2 taken along line IV-IV;
  • Figure 5 is a schematic cross-sectional view of the blade of Figure 2 taken along line V-V;
  • Figure 6 is a schematic cross-sectional view of the blade of Figure 2 taken along line VI-VI;
  • Figure 7 is a schematic cross-sectional view of the blade of Figure 2 taken along line VII-VII;
  • Figure 8 is a perspective view of an aircraft according to an embodiment of the present invention.
  • Figure 9 is an enlarged perspective view of the power assembly of the embodiment of the present invention.
  • Fig. 10 is a schematic perspective view showing the propeller in a folded state of the aircraft according to the embodiment of the present invention.
  • first and second are used for descriptive purposes only and are not to be construed as indicating or implying a relative importance or implicitly indicating the number of technical features indicated.
  • features defining “first” or “second” may include one or more of the described features either explicitly or implicitly.
  • the meaning of "a plurality” is two or more unless specifically and specifically defined otherwise.
  • installation is to be understood broadly, and may be, for example, a fixed connection, a detachable connection, or an integral connection; they may be mechanically connected, or may be electrically connected or may be in communication with each other. It can be directly connected or indirectly connected through an intermediate medium, which can be the internal communication of two elements or the interaction of two elements.
  • intermediate medium can be the internal communication of two elements or the interaction of two elements.
  • the first feature "on” or “under” the second feature may include direct contact of the first and second features, and may also include first and second features, unless otherwise specifically defined and defined. It is not in direct contact but through additional features between them.
  • the first feature "above”, “above” and “above” the second feature includes the first feature directly above and above the second feature, or merely indicating that the first feature level is higher than the second feature.
  • the first feature “below”, “below” and “below” the second feature includes the first feature directly below and below the second feature, or merely the first feature level being less than the second feature.
  • a propeller 100 package hub 20 and two blades 10 fixedly disposed on two sides of the hub 20 are provided.
  • the two blades 10 are centered on the center of the hub 20 . symmetry.
  • the two blades 10 are rotated to form a paddle.
  • the center of the hub 20 substantially coincides with the center O of the pad (as shown in FIG. 2).
  • the number of blades 10 may be any other number, such as three, four, five, six, etc.
  • the number of blades 10 is three, three
  • the paddles 10 are evenly distributed at intervals of 120 degrees in the circumferential direction with respect to the center O of the paddles; when the number of the blades 10 is four, the four blades 10 are uniformly distributed 90 degrees apart from the center O of the paddles in the circumferential direction; The distribution of the blade 10, the six blades 10 and the other blades 10 is the same.
  • the paddle 10 is rotatably coupled to the hub 20.
  • the propeller 100 is a folding paddle.
  • the propeller 100 can be a positive paddle or a reverse paddle.
  • the so-called positive paddle refers to a propeller 100 that rotates clockwise to generate lift from the tail of the driving member 101, for example, the motor toward the head of the motor; the so-called reverse paddle refers to the direction of the motor head from the tail of the driving member 101, for example, the motor,
  • the propeller 100 is rotated counterclockwise to produce lift.
  • the size parameters of the positive and negative propellers are exactly the same, and the structure of the positive and negative propellers is mirror symmetrical.
  • each blade 10 includes a first face 12 , a second face 14 opposite the first face 12 , and a second face 14 and the other side of the first face 12 .
  • the first face 12 and the second face 14 are both curved surfaces.
  • the first face 12 includes a convex first arch 122 that is smoothly transitioned to other portions of the first face 12.
  • the first arching portion 122 is adjacent to the blade 10 and One end of the hub 20 is connected, that is, the first arch 122 is adjacent to the center O of the paddle.
  • the first side edge 16 includes a curved, outwardly projecting second bulge 162.
  • the second arch 162 is smoothly transitioned to the other portions of the first side edge 16.
  • the second arching portion 162 is adjacent to one end of the blade 10 that is connected to the hub 20, that is, the first arching portion 122 is adjacent to the center O of the paddle.
  • the second side edge 18 includes a curved, outwardly projecting third bulge 182.
  • the third arched portion 182 is smoothly transitioned with the other portions of the second side edge 18.
  • the third arching portion 182 is adjacent to one end of the blade 10 that is connected to the hub 20, that is, the first arching portion 122 is adjacent to the center O of the paddle.
  • the thickness of the end of the blade 10 away from the center O of the paddle is smaller than the thickness of other portions of the blade 10, which is advantageous for reducing resistance and high structural strength. Not easy to break, high reliability.
  • the diameter of the paddle of the present embodiment is (114 ⁇ 30) mm.
  • the diameter of the paddle may be 84 mm, 87 mm, 95 mm, 107 mm, 118 mm, 132 mm, 144 mm, or within a numerical range defined by any of the above two values. The value.
  • the paddle has a diameter of 114 mm.
  • the paddle 10 and the hub 20 may be integrally formed or connected to each other by a connecting member.
  • the angle of attack referred to herein refers to the angle between the chord of the blade 10 and the velocity of the incoming flow.
  • the distance O from the center O of the paddle is 43.86% of the paddle radius (i.e., at IV-IV), the angle of attack ⁇ 1 of the blade 10 is (20.27 ⁇ 2.5) degrees, and the chord of the blade 10
  • the length L1 is (14.13 ⁇ 5) mm.
  • the angle of attack ⁇ 1 of the blade 10 may be 17.77 degrees, 19.55 degrees, 20.69 degrees, 20.77 degrees, 22.77 degrees, or a value within a range of values defined by any of the above two values;
  • the chord length L1 of the blade 10 may Values in the range of values defined by 9.13 mm, 11.23 mm, 13.22 mm, 14.76 mm, 15.67 mm, 16.95, 19.13 mm, or any of the above two values.
  • the present embodiment is the angle of attack ⁇ 1 20.27 degrees, the chord length L1 is 14.1mm.
  • the center O of the paddle is 61.40% of the paddle radius (i.e., at VV)
  • the angle of attack ⁇ 2 of the blade 10 is (14.82 ⁇ 2.5) degrees
  • the chord length L2 of the blade 10 It is (12.67 ⁇ 5) mm.
  • the angle of attack ⁇ 2 of the blade 10 may be 12.32 degrees, 13.03 degrees, 13.64 degrees, 14.50 degrees, 15.84 degrees, 16.23 degrees, 17.32 degrees, or a value within a range of values defined by any of the above two values;
  • the chord length L2 of 10 may be 7.67 mm, 8.35 mm, 10.62 mm, 12.44 mm, 14.62 mm, 16.32 mm, 17.67 mm, or a value within a range of values defined by any of the above two values.
  • the angle of attack ⁇ 2 is 14.82 degrees
  • the chord length L2 is 12.67 mm.
  • the distance O from the center O of the paddle is 78.95% of the paddle radius (ie VI-VI).
  • the angle of attack ⁇ 3 of the blade 10 is (11.75 ⁇ 2.5) degrees, and the chord length of the blade is L3. It is (10.90 ⁇ 5) mm.
  • the angle of attack ⁇ of the blade 3 10 may be 9.25 degrees, 10.02 degrees, 10.50 degrees, the value of the numerical range of 11.22 degrees, 12.71 degrees, 13.26 degrees, 14.25 degrees, or any two values as defined above; and blade
  • the chord length L3 of 10 may be 5.9 mm, 6.95 mm, 7.20 mm, 9.70 mm, 10.60 mm, 13.75 mm, 15.90 mm, or a value within a range of values defined by any of the above two values.
  • the angle of attack ⁇ 3 is 11.75 degrees
  • the chord length L3 is 10.90 mm.
  • the center of the paddle O is 96.49% of the paddle radius (i.e., at VII-VII), and the angle of attack ⁇ 4 of the blade 10 is (8.04 ⁇ 2.5) degrees, the string of the blade 10
  • the length L4 is (9.10 ⁇ 5) mm.
  • the angle of attack ⁇ 4 of the blade 10 may be 5.54 degrees, 6.5 degrees, 6.98 degrees, 7.41 degrees, 8.72 degrees, 9.56 degrees, 10.54 degrees, or a value within a range of values defined by any of the above two values;
  • the chord length L4 of 10 may be 4.10 mm, 6.45 mm, 8.24 mm, 9.75 mm, 11.66 mm, 12.97 mm, 14.50 mm, or a value within a range of values defined by any of the above two values.
  • the angle of attack ⁇ 4 is 8.04 degrees
  • the chord length L4 is 9.10 mm.
  • the diameter of the paddle is 114 mm.
  • the angle of attack ⁇ 1 of the blade is 20.27 degrees
  • the chord length L1 of the blade is 14.13 mm
  • the angle of attack ⁇ of the blade 2 is 14.82 degrees
  • the blade chord length L2 is 11.75 degrees
  • the The chord length L3 of the leaf is 10.90 mm
  • the blade has an angle of attack ⁇ 4 of 8.04 degrees and the blade has a chord length L4 of 9.10 mm.
  • Table 1 is a comparison of the test results of the propeller 100 and the existing propeller 100 according to the embodiment of the present invention. It can be seen from Table 1 that when the tensile force is 25g, 45g, 90g, 120g, 150g and 185g, The power of the propeller 100 of the embodiment of the invention is less than the power of the existing propeller 100, that is, the propeller 100 provided by the embodiment of the present invention provides a larger power at the same power than the existing propeller 100. The pulling force thus indicates that the propeller 100 provided by the embodiment of the present invention effectively reduces the resistance. This can improve efficiency and help increase battery life and maximum flight distance.
  • the propeller 100 provided by the embodiment of the present invention can reduce the air resistance, improve the efficiency, increase the endurance time and the maximum flight distance, and improve the dynamic response speed of the blade 10 by optimizing the angle of attack of different parts of the blade 10, thereby improving the aircraft 200. Flight performance.
  • the power assembly 110 includes a driving member 101 and the propeller 100 of any of the above embodiments.
  • the driving member 101 is used to drive the rotation of the propeller 100.
  • the drive member 101 is a motor having a KV value of 2100 KV.
  • the number of the propellers 100 can be selected according to actual needs, and can be one, two or more. Each drive motor drives a propeller 100 to rotate.
  • An aircraft 200 provided by an embodiment of the present invention includes a fuselage 120, at least one arm 130, and at least one of the above-described power components 110.
  • the arm 130 is coupled to the body 120, and the power assembly 110 is mounted to the arm 130, respectively.
  • the plurality of power components 110 are respectively mounted on the plurality of arms 130 and rotate in different directions.
  • the power assembly 110 and the aircraft 200 provided by the embodiments of the present invention can reduce the air resistance, improve the efficiency, increase the endurance time and the maximum flight distance, and improve the dynamics of the blade 10 by optimizing the angle of attack of different parts of the blade 10 of the propeller 100.
  • the speed is responsive to improve the flight performance of the aircraft 200.
  • first and second are used for descriptive purposes only and are not to be construed as indicating or implying a relative importance or implicitly indicating the number of technical features indicated.
  • features defining “first” and “second” may include at least one feature, either explicitly or implicitly.
  • the meaning of "a plurality” is at least two, such as two, three, etc., unless specifically defined otherwise.

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  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
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Abstract

一种螺旋桨（100）、动力组件（110）及飞行器（200）。螺旋桨（100）包括桨叶（10），桨叶（10）旋转形成桨盘；距离所述桨盘中心为所述桨盘半径的43.86％处，所述桨叶（10）的攻角为（20.27±2.5）度；距离所述桨盘中心为所述桨盘半径的61.40％处，所述桨叶（10）的攻角为（14.82±2.5）度；距离所述桨盘中心为所述桨盘半径的78.95％处，所述桨叶（10）的攻角为（11.75±2.5）度。上述螺旋桨（100）、动力组件（110）及飞行器（200），通过优化设计桨叶（10）的不同部位的攻角实现了减少空气阻力，提高效率，增加续航时间和最大飞行距离，提高桨叶动态响应速度，从而提高飞行器的飞行性能。

Description

螺旋桨、动力组件及飞行器 技术领域
本发明涉及飞行器技术领域，尤其是涉及一种螺旋桨、具有所述螺旋桨的动力组件以及具有所述动力组件的飞行器。
背景技术
飞行器是一种处在迅速发展中的飞行装置，其具有机动灵活、反应快速、无人飞行、操作要求低的优点。目前，飞行器的使用范围已经扩宽到军事、科研、民用三大领域，具体可在电力、通信、气象、农业、海洋、勘探、摄影、防灾减灾、农作物估产、缉毒缉私、边境巡逻、治安反恐等领域执行各项任务。现有的飞行器的螺旋桨，其外形形状大多呈矩形，其阻力大、效率低，导致飞行器的飞行速度小、继航距离短，严重影响了飞行器的飞行性能。
实用新型内容
本发明的实施方式旨在至少解决现有技术中存在的技术问题之一。为此，本发明的实施方式需要提供一种螺旋桨、动力组件及飞行器。
本发明提供一种螺旋桨，所述螺旋桨包括桨叶，所述桨叶旋转形成桨盘。
距离所述桨盘中心为所述桨盘半径的43.86％处，所述桨叶的攻角为(20.27±2.5)度；
距离所述桨盘中心为所述桨盘半径的61.40％处，所述桨叶的攻角为(14.82±2.5)度；
距离所述桨盘中心为所述桨盘半径的78.95％处，所述桨叶的攻角为(11.75±2.5)度。
在某些实施方式中，距离所述桨盘中心为所述桨盘半径的43.86％处，所述桨叶的弦长为(14.13±5)mm；及/或
距离所述桨盘中心为所述桨盘半径的61.40％处，所述桨叶的弦长为(12.67±5)mm；及/或
距离所述桨盘中心为所述桨盘半径的78.95％处，所述叶的弦长为(10.90±5)mm。
在某些实施方式中，距离所述桨盘中心为所述桨盘半径的96.49％处，所述桨叶的攻角为(8.04±2.5)度。
在某些实施方式中，所述桨盘的直径范围为(114±30)mm。
在某些实施方式中，距离所述桨盘中心为所述桨盘半径的96.49％处，所述桨叶的弦长为(9.10±5)mm。
在某些实施方式中，所述桨叶包括第一面、与所述第一面相背的第二面、连接所述第二面及所述第一面的一侧的第一侧缘及连接所述第二面及所述第一面另一侧的第二侧缘，所述第一面与所述第二均弯曲。
在某些实施方式中，所述第一面包括凸出的第一拱起部；所述第一侧缘包括曲面状的向外突出的第二拱起部；所述第二侧缘包括曲面状的向外突出的第三拱起部。
在某些实施方式中，所述第一拱起部、所述第二拱起部及所述第三拱起部均靠近所述桨盘的中心。
在某些实施方式中，所述桨叶的数量为两个，两个所述桨叶相 对于所述桨盘的中心呈中心对称；
或/及，所述桨叶远离所述桨盘的中心的一端的厚度小于所述桨叶的其它部分的厚度。
在某些实施方式中，所述螺旋桨为折叠桨，并且所述螺旋桨包括与所述桨叶转动连接或固定连接的桨毂，所述桨叶的数量为至少两个。
本发明提供一种螺旋桨，所述螺旋桨为折叠桨，所述螺旋桨包括桨毂及与所述桨毂连接的至少两个桨叶；
所述桨叶形成的桨盘的直径为(114±30)mm；
在距离所述桨盘中心为所述桨盘半径的43.86％处，所述桨叶的攻角为(20.27±2.5)度，所述桨叶的弦长为(14.13±5)mm；在距离所述桨盘中心为所述桨盘半径的61.40％处，所述桨叶的攻角为(14.82±2.5)度，所述桨叶的弦长为(12.67±5)mm；在距离所述桨盘中心为所述桨盘半径的78.95％处，所述桨叶的攻角为(11.75±2.5)度，所述叶的弦长为(10.90±5)mm；在距离所述桨盘中心为所述桨盘半径的96.49％处，所述桨叶的攻角为(8.04±2.5)度，所述桨叶的弦长为(9.10±5)mm。
本发明提供一种动力组件，所述动力组件包括上述任一项所述的螺旋桨；以及
驱动件，所述驱动件用于驱动所述螺旋桨转动。
在某些实施方式中，所述驱动件为电机，所述电机的KV值为2100KV。
本发明提供一种飞行器，包括机身、至少一个机臂及至少一个上任意一实施方式所述的动力组件，所述机臂与所述机身连接，所述动力组件分别安装在所述机臂上。
在某些实施方式中，所述飞行器的机臂和动力组件均为多个，所述多个动力组件分别安装在多个所述机臂上，并依照不同方向转动。
本发明实施方式的螺旋桨、动力组件及飞行器，通过优化设计桨叶不同部位的攻角实现了减少阻力，提高效率，增加续航时间和最大飞行距离，提高桨叶动态响应速度，从而提高飞行器的飞行性能。
本发明的实施方式的附加方面和优点将在下面的描述中部分给出，部分将从下面的描述中变得明显，或通过本发明的实施方式的实践了解到。
附图说明
本发明的实施方式的上述和/或附加的方面和优点从结合下面附图对实施方式的描述中将变得明显和容易理解，其中：
图1是本发明某些实施方式的桨叶的立体示意图；
图2是图1中桨叶的一平面示意图；
图3是图1中桨叶的另一平面示意图；
图4是图2中桨叶沿线IV-IV处的截面示意图；
图5是图2中桨叶沿线V-V处的截面示意图；
图6是图2中桨叶沿线VI-VI处的截面示意图；
图7是图2中桨叶沿线VII-VII处的截面示意图；
图8是本发明实施方式的飞行器的立体示意图；
图9是图8中本发明实施方式的动力组件的放大立体示意图；
图10是本发明实施方式的飞行器的螺旋桨折叠状态时的立体示意图。
主要元件符号说明：
飞行器200，动力组件110，螺旋桨100，桨叶10，第一面12，第一拱起部122，第二面14，第一侧缘16，第二拱起部162，第二侧缘18，第三拱起部182，桨毂20，驱动件101，机身120，机臂130。
具体实施方式
下面详细描述本发明的实施方式，所述实施方式的示例在附图中示出，其中自始至终相同或类似的标号表示相同或类似的元件或具有相同或类似功能的元件。下面通过参考附图描述的实施方式是示例性的，仅用于解释本发明，而不能理解为对本发明的限制。
在本发明的描述中，需要理解的是，术语“中心”、“纵向”、“横向”、“长度”、“宽度”、“厚度”、“上”、“下”、“前”、“后”、“左”、“右”、“竖直”、“水平”、“顶”、“底”、“内”、“外”、“顺时针”、“逆时针”等指示的方位或位置关系为基于附图所示的方位或位置关系，仅是为了便于描述本发明和简化描述，而不是指示或暗示所指的装置或元件必须具有特定的方位、以特定的方位构造和操作，因此不能理解为对本发明的限制。此外，术语“第一”、“第二”仅用于描述目的，而不能理解为指示或暗示相对重要性或者隐含指明所指示的技术特征的数量。由此，限定有“第一”、“第二”的特征可以明示或者隐含地包括一个或者更多个所述特征。在本发明的描述中，“多个”的含义是两个或两个以上，除非另有明确具体的限定。
在本发明的描述中，需要说明的是，除非另有明确的规定和限定， 术语“安装”、“相连”、“连接”应做广义理解，例如，可以是固定连接，也可以是可拆卸连接，或一体地连接；可以是机械连接，也可以是电连接或可以相互通讯；可以是直接相连，也可以通过中间媒介间接相连，可以是两个元件内部的连通或两个元件的相互作用关系。对于本领域的普通技术人员而言，可以根据具体情况理解上述术语在本发明中的具体含义。
在本发明中，除非另有明确的规定和限定，第一特征在第二特征之“上”或之“下”可以包括第一和第二特征直接接触，也可以包括第一和第二特征不是直接接触而是通过它们之间的另外的特征接触。而且，第一特征在第二特征“之上”、“上方”和“上面”包括第一特征在第二特征正上方和斜上方，或仅仅表示第一特征水平高度高于第二特征。第一特征在第二特征“之下”、“下方”和“下面”包括第一特征在第二特征正下方和斜下方，或仅仅表示第一特征水平高度小于第二特征。
下文的公开提供了许多不同的实施方式或例子用来实现本发明的不同结构。为了简化本发明的公开，下文中对特定例子的部件和设置进行描述。当然，它们仅仅为示例，并且目的不在于限制本发明。此外，本发明可以在不同例子中重复参考数字和/或参考字母，这种重复是为了简化和清楚的目的，其本身不指示所讨论各种实施方式和/或设置之间的关系。此外，本发明提供了的各种特定的工艺和材料的例子，但是本领域普通技术人员可以意识到其他工艺的应用和/或其他材料的使用。
请参阅图1、图8及图9本发明实施方式提供的螺旋桨100包桨毂20及固定设置在桨毂20两侧的两个桨叶10，两个桨叶10关于桨毂20中心呈中心对称。两个桨叶10旋转起来形成一桨盘，本实施方式中，桨毂20中心与桨盘中心O(如图2所示)基本重合。当然，根据实际需要，桨叶10的数量可以为其他任意数量，例如三个、四个、五个、六个等等；如在其他实施方式中，桨叶10的数量为三个，三个桨叶10相对桨盘中心O在圆周方向上间隔120度均匀分布；桨叶10的数量为四个时，四个桨叶10相对桨盘中心O在圆周方向上间隔90度均匀分布；五个桨叶10、六个桨叶10及其他桨叶10的分布情况则依此类推。在其他实施方式中，桨叶10与桨毂20可转动连接。
请结合图10，本实施方式中，螺旋桨100为折叠桨。螺旋桨100可以是正桨或者反桨。所谓正桨，指从驱动件101例如电机的尾部向电机头部方向看，顺时针旋转以产生升力的螺旋桨100；所谓反桨，指从驱动件101例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100。正桨与反桨的尺寸参数完全一致，正桨与反桨的结构之间镜像对称。
请参阅图1～图4及图9，每个桨叶10包括第一面12、与第一面12相背的第二面14、连接第二面14及第一面12的另一侧的第一侧缘16及连接第二面14及第一面12的第一侧的第二侧缘18。
在一个实施方式中，第一面12与第二面14均为曲面。第一面12包括凸出的第一拱起部122，第一拱起部122与第一面12的其他部分平滑的过渡连接。本实施方式中，第一拱起部122靠近桨叶10与 桨毂20相连接的一端，即第一拱起部122靠近桨盘中心O。第一侧缘16包括曲面状的向外突出的第二拱起部162。第二拱起部162与第一侧缘16的其他部分平滑的过渡连接。本实施方式中，第二拱起部162靠近桨叶10与桨毂20相连接的一端，即第一拱起部122靠近桨盘中心O。第二侧缘18包括曲面状的向外突出的第三拱起部182。第三拱起部182与第二侧缘18的其他部分平滑的过渡连接。本实施方式中，第三拱起部182靠近桨叶10与桨毂20相连接的一端，即第一拱起部122靠近桨盘中心O。
在某些实施方式中，桨叶10上无急剧扭转之处，桨叶10远离桨盘中心O的一端的厚度小于桨叶10的其它部分的厚度，有利于减小阻力，结构强度较高，不易折断，可靠性高。
本实施方式的桨盘直径为(114±30)mm，具体地，桨盘的直径可以为84mm、87mm、95mm、107mm、118mm、132mm、144mm，或者任意上述两个数值所界定的数值范围内的数值。优选地，桨盘的直径为114mm。桨叶10与桨毂20可以一体成型或者通过连接件相互连接。
本文中所指的攻角，是指桨叶10的翼弦与来流速度之间的夹角。
请参阅图2及图4，距离桨盘中心O为桨盘半径的43.86％处(即IV-IV处)，桨叶10的攻角α1为(20.27±2.5)度，桨叶10的弦长L1为(14.13±5)mm。当然，桨叶10的攻角α1可以为17.77度、19.55度、20.69度、20.77度、22.77度，或者任意上述两个数值所界定的数值范围内的数值；桨叶10的弦长L1可以为9.13mm、11.23mm、13.22mm、14.76mm、15.67mm、16.95、19.13mm，或者任意上述两个数 值所界定的数值范围内的数值。本实施方式中攻角α1为20.27度，弦长L1为14.1mm。
请参阅图2及图5，距离桨盘中心O为桨盘半径的61.40％处(即V-V处)，桨叶10的攻角α2为(14.82±2.5)度，桨叶10的弦长L2为(12.67±5)mm。当然，桨叶10的攻角α2可以为12.32度、13.03度、13.64度、14.50度、15.84度、16.23度、17.32度，或者任意上述两个数值所界定的数值范围内的数值；桨叶10的弦长L2可以为7.67mm、8.35mm、10.62mm、12.44mm、14.62mm、16.32mm、17.67mm，或者任意上述两个数值所界定的数值范围内的数值。本实施方式中攻角α2为14.82度，弦长L2为12.67mm。
请参阅图2及图6，距离桨盘中心O为桨盘半径的78.95％处(即VI-VI处)，桨叶10的攻角α3为(11.75±2.5)度，叶的弦长L3为(10.90±5)mm。当然，桨叶10的攻角α3可以为9.25度、10.02度、10.50度、11.22度、12.71度、13.26度、14.25度，或者任意上述两个数值所界定的数值范围内的数值；桨叶10的弦长L3可以为5.9mm、6.95mm、7.20mm、9.70mm、10.60mm、13.75mm、15.90mm，或者任意上述两个数值所界定的数值范围内的数值。本实施方式中攻角α3为11.75度，弦长L3为10.90mm。
请参阅图2及图7，距离桨盘中心O为桨盘半径的96.49％处(即VII-VII处)，桨叶10的攻角α4为(8.04±2.5)度，桨叶10的弦长L4为(9.10±5)mm。当然，桨叶10的攻角α4可以为5.54度、6.5度、6.98度、7.41度、8.72度、9.56度、10.54度，或者任意 上述两个数值所界定的数值范围内的数值；桨叶10的弦长L4可以为4.10mm、6.45mm、8.24mm、9.75mm、11.66mm、12.97mm、14.50mm，或者任意上述两个数值所界定的数值范围内的数值。本实施方式中攻角α4为8.04度，弦长L4为9.10mm。
请参阅图4～图7并结合图2，本实施方式中，桨盘的直径为114mm。在距离所述桨盘中心O的25mm处，所述桨叶的攻角α1为20.27度，所述桨叶的弦长L1为14.13mm；在距离所述桨盘中心O的35mm处，所述桨叶的攻角α2为14.82度，所述桨叶的弦长L2为12.67mm；在距离所述桨盘中心O的45mm处，所述桨叶的攻角α3为11.75度，所述叶的弦长L3为10.90mm；在距离所述桨盘中心O的55mm处，所述桨叶的攻角α4为8.04度，所述桨叶的弦长L4为9.10mm。
请参阅表1，为本发明实施方式的螺旋桨100与现有的螺旋桨100的测试结果的比对，由表1可以看出，在拉力为25g、45g、90g、120g、150g及185g时，本发明实施方式的螺旋桨100的功率均小于现有的螺旋桨100的功率，也就是说，相较于现有的螺旋桨100，本发明实施方式所提供的螺旋桨100在同等的功率下提供了更大的拉力，由此表明本发明实施方式所提供的螺旋桨100有效的减少了阻力。如此能够提高效率，有利于增加续航时间和最大飞行距离。
表1
Figure PCTCN2016111919-appb-000001
Figure PCTCN2016111919-appb-000002
本发明实施方式所提供的螺旋桨100通过优化设计桨叶10的不同部位的攻角实现了减少空气阻力，提高效率，增加续航时间和最大飞行距离，提高桨叶10动态响应速度，从而提高飞行器200的飞行性能。
请参阅图8及图9，本发明实施方式提供的动力组件110包括驱动件101及上述任一实施方式的螺旋桨100。驱动件101用于驱动螺旋桨100转动。在某些实施方式中，驱动件101为电机，电机的KV值为2100KV。螺旋桨100的数量可以根据实际需要选择，可以为一个、两个或者多个。每个驱动电机驱动一个螺旋桨100转动。
本发明实施方式提供的飞行器200，包括机身120、至少一个机臂130及至少一个上述的动力组件110。机臂130与机身120连接，动力组件110分别安装在机臂130上。飞行器200的机臂130和动力组件110均为多个，多个动力组件110分别安装在多个机臂130上，并依照不同方向转动。
本发明实施方式所提供的动力组件110及飞行器200通过优化设计螺旋桨100的桨叶10的不同部位的攻角实现了减少空气阻力，提高效率，增加续航时间和最大飞行距离，提高桨叶10动态响应速度，从而提高飞行器200的飞行性能。
在本说明书的描述中，参考术语“某些实施方式”、“一个实施方式”、“一些实施方式”、“示意性实施方式”、“示例”、“具体示例”、 或“一些示例”等的描述意指结合实施方式或示例描述的具体特征、结构、材料或者特点包含于本发明的至少一个实施方式或示例中。在本说明书中，对上述术语的示意性表述不一定指的是相同的实施方式或示例。而且，描述的具体特征、结构、材料或者特点可以在任何的一个或多个实施方式或示例中以合适的方式结合。
此外，术语“第一”、“第二”仅用于描述目的，而不能理解为指示或暗示相对重要性或者隐含指明所指示的技术特征的数量。由此，限定有“第一”、“第二”的特征可以明示或者隐含地包括至少一个特征。在本发明的描述中，“多个”的含义是至少两个，例如两个，三个等，除非另有明确具体的限定。
尽管上面已经示出和描述了本发明的实施方式，可以理解的是，上述实施方式是示例性的，不能理解为对本发明的限制，本领域的普通技术人员在本发明的范围内可以对上述实施方式进行变化、修改、替换和变型，本发明的范围由权利要求及其等同物限定。

Claims (15)

  1. 一种螺旋桨，包括桨叶，所述桨叶旋转形成桨盘，其特征在于：
    距离所述桨盘中心为所述桨盘半径的43.86％处，所述桨叶的攻角为(20.27±2.5)度；
    距离所述桨盘中心为所述桨盘半径的61.40％处，所述桨叶的攻角为(14.82±2.5)度；及
    距离所述桨盘中心为所述桨盘半径的78.95％处，所述桨叶的攻角为(11.75±2.5)度。
  2. 如权利要求1所述的螺旋桨，其特征在于，距离所述桨盘中心为所述桨盘半径的43.86％处，所述桨叶的弦长为(14.13±5)mm；及/或
    距离所述桨盘中心为所述桨盘半径的61.40％处，所述桨叶的弦长为(12.67±5)mm；及/或
    距离所述桨盘中心为所述桨盘半径的78.95％处，所述叶的弦长为(10.90±5)mm。
  3. 如权利要求1所述的螺旋桨，其特征在于，距离所述桨盘中心为所述桨盘半径的96.49％处，所述桨叶的攻角为(8.04±2.5)度。
  4. 如权利要求1或3所述的螺旋桨，其特征在于，所述桨盘的直径范围为(114±30)mm。
  5. 如权利要求3所述的螺旋桨，其特征在于，距离所述桨盘中心为所述桨盘半径的96.49％处，所述桨叶的弦长为(9.10±5)mm。
  6. 如权利要求1所述的螺旋桨，其特征在于，所述桨叶包括第一面、与所述第一面相背的第二面、连接所述第二面及所述第一面的一侧的第一侧缘及连接所述第二面及所述第一面的另一侧的第二侧缘，所述第一面与所述第二面均弯曲。
  7. 如权利要求6所述的螺旋桨，其特征在于，所述第一面包括凸出的第一拱起部；所述第一侧缘包括曲面状的向外突出的第二拱起部；所述第二侧缘包括曲面状的向外突出的第三拱起部。
  8. 如权利要求7所述的螺旋桨，其特征在于，所述第一拱起部、所述第二拱起部及所述第三拱起部均靠近所述桨盘的中心。
  9. 如权利要求1所述的螺旋桨，其特征在于，所述桨叶的数量为两个，两个所述桨叶相对于所述桨盘的中心呈中心对称；
    或/及，所述桨叶远离所述桨盘的中心的一端的厚度小于所述桨叶的其它部分的厚度。
  10. 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，并且所述螺旋桨包括与所述桨叶转动连接或固定连接的桨毂，所述桨叶的数量为至少两个。
  11. 一种螺旋桨，其特征在于，所述螺旋桨为折叠桨，所述螺旋桨包括桨毂及与所述桨毂连接的至少两个桨叶；
    所述桨叶形成的桨盘的直径为(114±5)mm；
    在距离所述桨盘中心为所述桨盘半径的43.86％处，所述桨叶的攻角为(20.27±2.5)度，所述桨叶的弦长为(14.13±5)mm；在距离所述桨盘中心为所述桨盘半径的61.40％处，所述桨叶的攻角为(14.82±2.5)度，所述桨叶的弦长为(12.67±5)mm；在距离所述桨盘中心为所述桨盘半径的78.95％处，所述桨叶的攻角为(11.75±2.5)度，所述叶的弦长为(10.90±5)mm；在距离 所述桨盘中心为所述桨盘半径的96.49％处，所述桨叶的攻角为(8.04±2.5)度，所述桨叶的弦长为(9.10±5)mm。
  12. 一种动力组件，其特征在于，所述动力组件包括如权利要求1-11任一项所述的螺旋桨；以及
    驱动件，所述驱动件用于驱动所述螺旋桨转动。
  13. 如权利要求12所述的动力组件，其特征在于，所述驱动件为电机，所述电机的KV值为2100KV。
  14. 一种飞行器，其特征在于，包括机身、至少一个机臂及至少一个如权利要求12或13所述的动力组件，所述机臂与所述机身连接，所述动力组件分别安装在所述机臂上。
  15. 如权利要求14所述的飞行器，其特征在于，所述飞行器的机臂和动力组件均为多个，所述多个动力组件分别安装在多个所述机臂上，并依照不同方向转动。
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