WO2017148135A1 - Hélice, ensemble d'alimentation et aéronef - Google Patents

Hélice, ensemble d'alimentation et aéronef Download PDF

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Publication number
WO2017148135A1
WO2017148135A1 PCT/CN2016/099694 CN2016099694W WO2017148135A1 WO 2017148135 A1 WO2017148135 A1 WO 2017148135A1 CN 2016099694 W CN2016099694 W CN 2016099694W WO 2017148135 A1 WO2017148135 A1 WO 2017148135A1
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WO
WIPO (PCT)
Prior art keywords
propeller
blade
paddle
center
angle
Prior art date
Application number
PCT/CN2016/099694
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English (en)
Chinese (zh)
Inventor
刘峰
邓涛
江彬
Original Assignee
深圳市大疆创新科技有限公司
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by 深圳市大疆创新科技有限公司 filed Critical 深圳市大疆创新科技有限公司
Publication of WO2017148135A1 publication Critical patent/WO2017148135A1/fr

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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 propeller structure technology, and more particularly to a propeller, a power assembly, and an aircraft.
  • the propeller on the aircraft is used to convert the rotational force of the drive motor or the engine's intermediate shaft into the thrust or lift of the air, causing the aircraft to rise and change the heading.
  • the shape of the propeller is mostly rectangular, and the resistance to the air during the rotation is large, resulting in poor force conversion efficiency, thereby reducing the flight speed of the aircraft, shortening the sailing distance, and seriously affecting the aircraft. Flight performance.
  • the object of the present invention is to provide a propeller, a power assembly and an aircraft, which can effectively reduce the resistance of the propeller during rotation to improve the force conversion efficiency.
  • the present invention provides the following technical solutions:
  • a propeller in a first aspect, is provided, the propeller including a blade, and the blade is rotated to form a paddle, wherein the blade has a chord length of 13.8 at a distance of 40% from the center of the paddle Mm ⁇ 5 mm, the angle of attack is 17.1 ° ⁇ 2.5 °; at a distance of 60% from the center of the paddle, the blade has a chord length of 11.9 mm ⁇ 5 mm and an angle of attack of 14.3 ° ⁇ 2.5 °; The center of the paddle is 80% apart, the blade has a chord length of 10.3 mm ⁇ 5 mm, and the angle of attack is 12.4 ° ⁇ 2.5 °.
  • a further improvement of the above propeller is at a distance of 20% from the center of the paddle, the blade having a chord length of 14.4 mm ⁇ 5 mm and an angle of attack of 19.7 ° ⁇ 2.5 °.
  • a further improvement of the above propeller is at a distance of 100% from the center of the paddle, the blade having a chord length of 9.1 mm ⁇ 5 mm and an angle of attack of 10.7 ° ⁇ 2.5 °.
  • the diameter of the propeller is 150 mm; at a distance of 30 mm from the center of the paddle, the blade has a chord length of 13.8 mm and an angle of attack of 17.1°; The center of the paddle is at a distance of 45 mm, the blade has a chord length of 11.9 mm and an angle of attack of 14.3°; at a distance of 60 mm from the center of the paddle, the blade has a chord length of 10.3 mm and an angle of attack. It is 12.4°.
  • the diameter of the propeller is 150 mm; at a distance of 15 mm from the center of the paddle, the blade has a chord length of 14.4 mm and an angle of attack of 19.7.
  • a further improvement of the above propeller is at a distance of 75 mm from the center of the paddle, the blade having a chord length of 9.1 mm and an angle of attack of 10.7.
  • the blade having a leaf back, a leaf surface, a first side edge connecting the leaf back and one side of the leaf surface, and a second side edge connecting the leaf back and the other side of the leaf surface;
  • the leaf back and the leaf surface are curved surfaces.
  • the first side edge of the blade near one end of the center of the paddle has a curved first arch.
  • a further improvement of the above propeller comprising a plurality of blades, the propeller further comprising a paddle, the plurality of blades being evenly disposed along a circumference of the paddle, the paddle of the propeller being a hollow structure.
  • a further improvement of the above propeller including a first connecting portion connecting the blades, a second connecting portion for connecting the driving members, and a first interval between the first connecting portion and the second connecting portion Three connections.
  • the thickness of the blade gradually decreases from an end of the blade near the center of the paddle to an end of the blade away from the center of the paddle.
  • the pitch of the propeller is 40 mm.
  • a power assembly in a second aspect, includes a drive member and a propeller as described above, the propeller being coupled to the drive member by a hub.
  • the drive member is a motor having a KV value of 2200 to 2400 rpm / (minute volt).
  • an aircraft including a fuselage, further comprising at least one power assembly as described above, the power assembly being coupled to the fuselage.
  • the aircraft includes a plurality of power components that rotate in different directions.
  • the embodiment of the invention can reduce the resistance of the propeller during the rotation process, improve the force conversion efficiency, and improve the flight speed of the aircraft. Increase the sailing distance and improve flight performance under certain power conditions.
  • FIG. 1 is a schematic structural view of a propeller according to an embodiment of the present invention.
  • Figure 2 is a schematic view showing the structure of the propeller of Figure 1 under another viewing angle
  • Figure 3 is a front elevational view of the propeller of Figure 1;
  • Figure 4 is a right side view of the propeller of Figure 1;
  • Figure 5 is a left side view of the propeller of Figure 1;
  • Figure 6 is a plan view of the propeller of Figure 1;
  • Figure 7 is a bottom plan view of the propeller of Figure 1;
  • FIG. 8 is a schematic diagram of dividing a different cross section on a blade in a propeller according to an embodiment of the present invention.
  • Figure 9 is a schematic structural view of the cross section of the propeller A-A of Figure 8.
  • Figure 10 is a schematic structural view of the cross section of the propeller B-B of Figure 8.
  • Figure 11 is a schematic structural view of a cross section of the propeller C-C of Figure 8.
  • Figure 12 is a schematic structural view of the cross section of the propeller D-D of Figure 8.
  • Figure 13 is a schematic view showing the structure of the cross section of the propeller E-E of Figure 8.
  • 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 at least one of the features, either explicitly or implicitly.
  • FIG. 1 is a schematic structural view of a propeller provided in the present embodiment
  • FIG. 2 is a schematic structural view of the propeller in FIG. 1 at another viewing angle
  • FIG. 3 is a front view of the propeller in FIG. 1
  • FIG. 4 is a right side view of the propeller in FIG.
  • Figure 5 is a left side view of the propeller of Figure 1
  • Figure 6 is a top view of the propeller of Figure 1
  • Figure 7 is a bottom view of the propeller of Figure 1.
  • the propeller provided in this embodiment may be a positive propeller or a reverse propeller.
  • the positive paddle refers to a propeller that rotates clockwise to generate lift from the perspective of the aircraft
  • the reverse paddle refers to a propeller that generates counter-rotation by counterclockwise rotation from the perspective of the aircraft.
  • the structure of the positive paddle and the structure of the reverse paddle are mirror-symmetric. This embodiment is only described by taking the structure of the positive paddle as an example. Those skilled in the art can expand the structure provided by the embodiment to obtain the structure of the reverse paddle.
  • the propeller provided in this embodiment can be applied to a biaxial aircraft, a quadcopter or an eight-axis aircraft, and the like.
  • Two, three or more blades can be connected to the propeller hub.
  • the paddle drives the paddle to rotate to form a paddle.
  • the hub and the blade may be of a unitary structure, or may be a split type propeller formed by separately mounting the blade on the hub.
  • the present embodiment will be described in detail by taking a propeller having an integrated structure in which two blades are mounted on the hub, and those skilled in the art can extend the propeller to include according to the technical solution provided by the embodiment.
  • the propeller includes a hub 2 and a blade 1 attached to the hub 2.
  • the hub 2 is used for connecting with the driving member on the aircraft, and the driving member drives the hub 2 to rotate, thereby driving the blade 1 connected to the hub 2 to rotate.
  • the number of the blades 1 is two, which are respectively connected to the hub 2, and the center of the paddle formed by the rotation is center-symmetrical.
  • the hub 2 in the propeller provided in this embodiment is a hollow structure.
  • the hollow structure is a hollow along the axial direction of the paddle 2.
  • the hub 2 may include a first connection portion 21, a second connection portion 23, and a third connection portion 25.
  • the first connecting portion 21 is connected to the blade 1
  • the second connecting portion 23 is connected to the driving member
  • the third connecting portion 25 is disposed between the first connecting portion 21 and the second connecting portion 23 for connecting the first connection.
  • the third connecting portion 25 may be two, three or three Above, the interval is provided between the first connecting portion 21 and the second connecting portion 23.
  • the plurality of third connecting portions 25 described above may be evenly disposed between the first connecting portion 21 and the second connecting portion 23.
  • three evenly spaced third connecting portions 25 are provided between the first connecting portion 21 and the second connecting portion 23.
  • the hollow structure of the above-mentioned hub can also be other hollow structures in the prior art.
  • the propeller of this embodiment since the hub 2 is a hollow structure, the weight of the propeller can be reduced, and the flight performance of the propeller can be improved.
  • the propeller using the hub 2 and the blade 1 as a unitary structure can greatly improve the flight performance.
  • the third connecting portion 25 disposed between the first connecting portion 21 and the second connecting portion 23 can not only improve the structural strength of the propeller, but also further improve the stability of the propeller during flight, thereby improving the flight performance of the propeller. .
  • the connection position of the third connecting portion 25 and the first connecting portion 21 and the second connecting portion 23 can be smoothly transitioned, thereby reducing the stress at the connection position and improving the reliability of the hub 2. .
  • the blade 1 in the propeller provided in the present embodiment includes a blade back 13, a blade surface 11, a first side edge 15 connecting the blade back 13 and the side of the blade surface 11, and a connection.
  • the leaf back 13 is the one side of the blade 1 during the flight of the aircraft; the leaf surface 11 is the side of the blade 1 facing downward (or facing the ground) during the flight.
  • the leaf back 13 and the leaf surface 11 are curved surfaces, and the tendency to bend is that when the blade 1 is in a horizontal state as a whole, the first side edge 15 is located at a position lower than the second side. The position of the edge 17 is low.
  • the surface of the blade 1 is a smooth transition and there is no sharp twist, it has a small stress, and the strength is high and is not easily broken, and has high reliability.
  • the first side edge 15 has a curved bulge 151 which is smoothly transitioned to the remainder of the first side edge 15.
  • the arched portion 151 of the upper blade 1 faces the right side
  • the lower blade 1 faces the left side; and, in the longitudinal direction of the entire blade 1, the arched portion 151 is located close to the blade 1 Position with one end of the center of the paddle.
  • the blade 1 tapers from one end near the center of the paddle to one end away from the center of the paddle.
  • the end of the blade 1 away from the center of the paddle is the thinnest portion of the blade 1, it is advantageous to reduce the air resistance, thereby providing the flight performance of the propeller.
  • FIG. 8 is a schematic view showing a different cross section of a propeller in a propeller according to an embodiment of the present invention
  • FIG. 9 is a schematic structural view of a cross section of the propeller A-A in FIG. 8
  • FIG. 10 is a cross section of the propeller B-B in FIG.
  • FIG. 11 is a schematic structural view of a cross section of a propeller C-C in FIG. 8
  • FIG. 12 is a structural schematic view of a cross section of the propeller D-D in FIG. 8
  • FIG. 13 is a structural schematic view of a cross section of the propeller E-E in FIG.
  • the size of the present embodiment is improved at the five sections of the blade 1, wherein the improvements in the dimensions of the B-B section, the C-C section and the D-D section have an optimum effect:
  • the chord length L2 of the blade 1 shown in FIG. 10 is 13.8 mm ⁇ as shown in FIG. 5 mm
  • the angle of attack ⁇ 2 is 17.1 ° ⁇ 2.5 °.
  • the chord length refers to the distance between the leftmost end point of the first side edge 15 on the cross section and the rightmost end point of the second side edge 17 on the cross section at the cross section
  • the angle of attack is The first side edge 15 is located at an angle between the line connecting the leftmost end point of the section and the rightmost end point of the second side edge 17 and the horizontal direction, or the angle of attack can also be understood as a paddle.
  • the CC section of the center of the paddle is H3, and the chord length L3 of the blade 1 shown in Fig. 11 is 11.9 mm ⁇ 5 mm.
  • the angle ⁇ 3 is 14.3 ° ⁇ 2.5 °.
  • the DD section of the paddle center is H4
  • the chord length L4 of the blade 1 shown in Fig. 12 is 10.3 mm ⁇ 5 mm.
  • the angle ⁇ 4 is 12.4° ⁇ 2.5°.
  • the resistance of the propeller during the rotation process can be reduced, the force conversion efficiency can be improved, and the flight speed of the aircraft can be improved, and the power is supplied under certain electric conditions. Increase the sailing distance and improve flight performance.
  • chord length and the attack angle of the A-A section and the E-E section of the blade 1 are respectively improved, and the resistance of the propeller during the rotation can be further reduced.
  • the AA section of the paddle center is H1
  • the chord length L1 of the blade 1 shown in Fig. 9 is 14.4 mm ⁇ 5 mm.
  • the angle ⁇ 1 is 19.7° ⁇ 2.5°.
  • the EE section of the paddle center is H5
  • the chord length L5 of the blade 1 shown in Fig. 13 is 9.1 mm ⁇ 5 mm.
  • the angle ⁇ 5 is 10.7 ° ⁇ 2.5 °.
  • the present embodiment provides a specific propeller having a diameter of 150 mm and a distance of 30 mm from the center of the paddle.
  • the chord length of the blade 1 is specifically 13.8 mm and the angle of attack is 17.1.
  • the blade 1 has a chord length of 11.9 mm and an angle of attack of 14.3.
  • the blade 1 has a chord length of 10.3 mm and an angle of attack of 12.4°.
  • the blade 1 has a chord length of 14.4 mm and an angle of attack of 19.7.
  • the blade 1 has a chord length of 9.1 mm and an angle of attack of 10.7. It can be understood that since the positions of the section A-A and the section E-E may be slightly changed, the angle of attack and the chord length at the section A-A and the section E-E may be correspondingly changed accordingly.
  • the pitch of the propeller may be 40 mm, that is, the blade 1 is rotated one revolution, and the theoretical rising distance is 40 mm.
  • the above-mentioned propeller provided by the present embodiment can be basically obtained by comparing with the prior art propeller.
  • the rotation speed of the propeller provided by the embodiment is higher under the same pulling force, that is, With a smaller pulling force, it has a higher rotational speed, which improves the dynamic response speed of the propeller blades, increases the life time and the maximum flight distance, and thus improves the flight performance of the aircraft.
  • the existing propeller can provide a pulling force of 495 g
  • the propeller of the present embodiment can provide a pulling force of 538 g, which is far superior to the existing propeller.
  • the present embodiment also provides a power assembly including a drive member and a propeller as provided above, the propeller being coupled to the drive member via a second attachment portion 23 of the hub.
  • the driving component may specifically be a motor, and the KV value of the motor is 2200 rpm/(min ⁇ volt), 2400 rpm/(minute ⁇ volt) Or any value between the two, for example, 2300 rpm / (minute volts).
  • the embodiment further provides an aircraft comprising a fuselage and at least one of the above power components, the power component being coupled to the fuselage.
  • the aircraft adopts the above power component, and by setting the chord length and the angle of attack of the three sections in the blade 1, the resistance of the propeller during the rotation can be reduced, the force conversion efficiency is improved, and the flight speed of the aircraft is improved, at a certain
  • the power supply condition is extended to extend the navigation distance and improve flight performance.
  • the aircraft includes a plurality of power components, and the plurality of power components rotate in different directions.

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  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Toys (AREA)
  • Wind Motors (AREA)

Abstract

L'invention concerne une hélice, un ensemble d'alimentation et un aéronef, l'hélice comprenant un moyeu (2) et des pales (1) reliées au moyeu (2). À la distance de 40 % depuis un centre de disque d'hélice, la longueur de corde des pales (1) est 13,8 mm ± 5 mm et l'angle d'attaque est 17,1° ± 2,5°. À la distance de 60 % depuis le centre de disque d'hélice, la longueur de corde des pales (1) est 11,9 mm ± 5 mm et l'angle d'attaque est 14,3° ± 2,5°. À la distance de 80 % depuis le centre de disque d'hélice, la longueur de corde des pales (1) est 10,3 mm ± 5 mm et l'angle d'attaque est 12,4° ± 2,5°. L'hélice, l'ensemble d'alimentation et l'aéronef réduisent efficacement la résistance de l'hélice pendant la rotation et améliorent l'efficacité de conversion de force.
PCT/CN2016/099694 2016-02-29 2016-09-22 Hélice, ensemble d'alimentation et aéronef WO2017148135A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
CN201620153117.8 2016-02-29
CN201620153117.8U CN205469778U (zh) 2016-02-29 2016-02-29 螺旋桨、动力组件及飞行器

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WO2017148135A1 true WO2017148135A1 (fr) 2017-09-08

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Families Citing this family (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN205469778U (zh) * 2016-02-29 2016-08-17 深圳市大疆创新科技有限公司 螺旋桨、动力组件及飞行器
CN205837193U (zh) * 2016-07-28 2016-12-28 深圳市大疆创新科技有限公司 螺旋桨、动力套装及无人飞行器
CN206141830U (zh) * 2016-10-28 2017-05-03 深圳市大疆创新科技有限公司 螺旋桨、动力套装及无人飞行器
CN206394872U (zh) * 2016-11-30 2017-08-11 深圳市大疆创新科技有限公司 螺旋桨、动力组件及飞行器
CN106741858B (zh) * 2016-12-06 2023-10-03 丰翼科技(深圳)有限公司 螺旋桨翼片
CN206691356U (zh) * 2017-02-28 2017-12-01 深圳市大疆创新科技有限公司 螺旋桨、动力组件及飞行器
CN206954494U (zh) * 2017-06-30 2018-02-02 深圳市大疆创新科技有限公司 螺旋桨、动力组件及飞行器
CN206926806U (zh) * 2017-07-25 2018-01-26 深圳市大疆创新科技有限公司 螺旋桨、动力组件及飞行器
CN207072430U (zh) * 2017-07-28 2018-03-06 深圳市大疆创新科技有限公司 螺旋桨、动力组件及飞行器
CN207403925U (zh) * 2017-08-11 2018-05-25 深圳市大疆创新科技有限公司 螺旋桨、动力组件及飞行器
WO2019119379A1 (fr) * 2017-12-21 2019-06-27 深圳市大疆创新科技有限公司 Hélice, assemblage motorisé et aéronef sans pilote
CN109969391A (zh) * 2017-12-28 2019-07-05 辽宁壮龙无人机科技有限公司 无人机及其螺旋桨
CN112977816B (zh) * 2021-05-17 2021-08-06 北京三快在线科技有限公司 旋翼飞行器的桨叶及旋翼飞行器

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CN102963522A (zh) * 2012-10-31 2013-03-13 中国航天空气动力技术研究院 临近空间螺旋桨
CN203374428U (zh) * 2013-06-14 2014-01-01 中国科学院工程热物理研究所 一族大厚度钝尾缘风力机翼型
CN203593160U (zh) * 2013-12-13 2014-05-14 吉林大学 一种机翼结构
CN105253295A (zh) * 2015-10-30 2016-01-20 深圳市道通智能航空技术有限公司 一种螺旋桨及飞行器
CN205469778U (zh) * 2016-02-29 2016-08-17 深圳市大疆创新科技有限公司 螺旋桨、动力组件及飞行器

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Publication number Priority date Publication date Assignee Title
JP2002220089A (ja) * 2001-01-23 2002-08-06 Hitachi Zosen Corp 船舶の推進効率向上用ダクト
CN102963522A (zh) * 2012-10-31 2013-03-13 中国航天空气动力技术研究院 临近空间螺旋桨
CN203374428U (zh) * 2013-06-14 2014-01-01 中国科学院工程热物理研究所 一族大厚度钝尾缘风力机翼型
CN203593160U (zh) * 2013-12-13 2014-05-14 吉林大学 一种机翼结构
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CN205469778U (zh) * 2016-02-29 2016-08-17 深圳市大疆创新科技有限公司 螺旋桨、动力组件及飞行器

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