WO2018157426A1 - Hélice, ensemble de puissance et aéronef - Google Patents

Hélice, ensemble de puissance et aéronef Download PDF

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Publication number
WO2018157426A1
WO2018157426A1 PCT/CN2017/078258 CN2017078258W WO2018157426A1 WO 2018157426 A1 WO2018157426 A1 WO 2018157426A1 CN 2017078258 W CN2017078258 W CN 2017078258W WO 2018157426 A1 WO2018157426 A1 WO 2018157426A1
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WO
WIPO (PCT)
Prior art keywords
paddle
propeller
blade
attack
center
Prior art date
Application number
PCT/CN2017/078258
Other languages
English (en)
Chinese (zh)
Inventor
刘峰
陈鹏
邓涛
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
Priority to CN201780052530.2A priority Critical patent/CN109641648A/zh
Publication of WO2018157426A1 publication Critical patent/WO2018157426A1/fr

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Classifications

    • 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
    • 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
    • B64C27/46—Blades
    • B64C27/467—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 rotation of the shaft of the motor or engine into thrust or lift.
  • the shape of the blade of the propeller is mostly rectangular, which results in large resistance and low efficiency during flight, resulting in a small flying speed of the aircraft and a short cruising distance, which seriously affects the flight performance of the aircraft.
  • the invention provides a propeller, a power component and an aircraft to solve the above defects in the prior art, reduce the flight resistance of the propeller, improve the flight efficiency of the propeller, and improve the flight performance of the aircraft.
  • a first aspect of the invention provides a propeller comprising a blade, the blade rotating to form a paddle;
  • the blade is at an angle of attack of 59.32% of the blade radius at the center of the paddle formed by the propeller, and has an angle of attack of 14.05° ⁇ 2.5° and a chord length of 11.94 mm ⁇ 5 mm;
  • the blade has an angle of attack of 11.44° ⁇ 2.5° at a distance of 76.27% of the paddle radius from the center of the paddle formed by the propeller, and a chord length of 10.25 mm ⁇ 5 mm;
  • the blade has an angle of attack of 93.22% of the paddle radius at the center of the paddle formed by the propeller, and has an angle of attack of 9.99° ⁇ 2.5° and a chord length of 8.64 mm ⁇ 5 mm.
  • a second aspect of the present invention provides a power assembly including a driving member and a propeller, wherein the propeller is coupled to the driving member through a paddle;
  • the propeller includes a paddle that rotates to form a paddle
  • the blade is at an angle of attack of 59.32% of the blade radius at the center of the paddle formed by the propeller, and has an angle of attack of 14.05° ⁇ 2.5° and a chord length of 11.94 mm ⁇ 5 mm;
  • the blade has an angle of attack of 11.44° ⁇ 2.5° at a distance of 76.27% of the paddle radius from the center of the paddle formed by the propeller, and a chord length of 10.25 mm ⁇ 5 mm;
  • the blade has an angle of attack of 93.22% of the paddle radius at the center of the paddle formed by the propeller, and has an angle of attack of 9.99° ⁇ 2.5° and a chord length of 8.64 mm ⁇ 5 mm.
  • a third aspect of the invention provides an aircraft comprising a fuselage and at least one power component, the power component being coupled to the fuselage;
  • the power assembly includes: a driving member and a propeller, wherein the propeller is connected to the driving member through a paddle;
  • the propeller includes a paddle that rotates to form a paddle
  • the blade is at an angle of attack of 59.32% of the blade radius at the center of the paddle formed by the propeller, and has an angle of attack of 14.05° ⁇ 2.5° and a chord length of 11.94 mm ⁇ 5 mm;
  • the blade has an angle of attack of 11.44° ⁇ 2.5° at a distance of 76.27% of the paddle radius from the center of the paddle formed by the propeller, and a chord length of 10.25 mm ⁇ 5 mm;
  • the blade has an angle of attack of 93.22% of the paddle radius at the center of the paddle formed by the propeller, and has an angle of attack of 9.99° ⁇ 2.5° and a chord length of 8.64 mm ⁇ 5 mm.
  • the propeller, the power component and the aircraft provided by the invention have an angle of attack of 14.05° ⁇ 2.5° at a distance of 59.32% of the paddle radius of the paddle formed by the propeller, and a chord length of 11.94 mm ⁇ 5 mm;
  • the blade has an angle of attack of 11.44° ⁇ 2.5° at a distance of 76.27% of the paddle radius from the center of the paddle formed by the propeller, and a chord length of 10.25 mm ⁇ 5 mm;
  • the center of the paddle formed by the propeller is 93.22% of the blade radius, the angle of attack is 9.99 ° ⁇ 2.5 °, and the chord length is 8.64 mm ⁇ 5 mm. Therefore, the resistance of the propeller during the rotation process can be reduced, the flight resistance during the flight of the aircraft can be reduced, the flight efficiency can be improved, the cruising range can be increased, and the flight performance of the aircraft can be improved.
  • FIG. 1 is a perspective view of a blade in a propeller according to a first embodiment of the present invention
  • Figure 2 is a front elevational view of the blade of Figure 1;
  • Figure 3 is a left side view of the blade of Figure 1;
  • Figure 4 is a right side view of the blade of Figure 1;
  • Figure 5 is a bottom plan view of the blade of Figure 1;
  • Figure 6 is a plan view of the blade of Figure 1;
  • Figure 7 is a schematic cross-sectional view of the blade of Figure 2 taken along line A-A;
  • Figure 8 is a schematic cross-sectional view of the blade of Figure 2 taken along line B-B;
  • Figure 9 is a schematic cross-sectional view of the blade of Figure 2 taken along line C-C;
  • Figure 10 is a schematic cross-sectional view of the blade of Figure 2 taken along line D-D;
  • Figure 11 is a schematic cross-sectional view of the blade of Figure 2 taken along line E-E.
  • 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. When a component is considered to "connect” another component, it can be directly connected to another component or possibly a central component.
  • Embodiment 1 of the present invention provides a propeller.
  • the propeller in this embodiment can be applied to an aircraft, and the propeller can include: a paddle and a blade connected to the paddle.
  • the propeller may be a positive propeller or a reverse propeller
  • the so-called positive propeller refers to a propeller that rotates clockwise to generate lift from the perspective of the aircraft overlooking
  • the so-called reverse propeller refers to the perspective of the aircraft from above.
  • the structure of the positive paddle is mirror-symmetric with the structure of the reverse paddle.
  • the structure of the propeller is only taken as an example of the structure of the positive paddle, and those skilled in the art can expand according to the manner provided by the embodiment. Get the structure of the reverse paddle.
  • the paddle and the paddle may be integrally formed, or may be connected to each other by other means, for example, by welding, or may be fixedly connected by a detachable connector, for example. Screwed or fixed, or connected by other connectors.
  • the number of the blades may be one or more, and the plurality of blades may be evenly spaced along the circumferential direction of the paddle. In this embodiment, preferably, the number of the blades is at least two, and at least two blades are along the paddle. The circumferential direction is evenly distributed.
  • the plurality of blades may be integrally formed or may be independent of each other, which is not specifically limited in the present invention.
  • FIGS. 1 to 6 are surfaces.
  • the blade of the propeller in this embodiment may include an upwardly facing leaf back 4, a downwardly facing leaf surface 3, and a side connected to the leaf back 4 and the leaf surface 3 a first side edge 5, and a second side edge 6 connected between the leaf back 4 and the other side of the leaf surface 3, the first side edge 5 being located below the second side edge 6; the leaf back 4 and the leaf surface 3 Both are surfaces.
  • the leaf back 4 is the side of the blade 1 during the flight
  • the blade 3 is the side of the blade 1 during the flight.
  • Both the leaf back 4 and the leaf surface 3 are curved surfaces, and the tendency to bend is that when the blade 1 as a whole is in a horizontal state, the first side edge 5 is located lower than the position where the second side edge 6 is located.
  • the first side edge 5 may comprise a curved, outwardly projecting first bulge 501, the first bulging portion 501 being in a smooth transitional connection with the remainder of the first side edge 5.
  • the first arched portion 501 is closer to the end of the blade 1 connected to the paddle than the end of the blade 1 away from the paddle in the longitudinal direction of the entire blade 1.
  • the first arch 501 not only arches towards one side of the blade 1 but also arches downwards, ie in the direction in which the foliage 3 is situated, and can form a smooth transitional connection with the foliage 3.
  • the second side edge 6 may include a curved, outwardly projecting second arch 601, the second arching portion 601 being in a smooth transitional connection with the remainder of the second side edge 6.
  • the second arched portion 601 is closer to the end of the blade 1 connected to the paddle than the end of the blade 1 away from the paddle in the longitudinal direction of the entire blade 1.
  • the degree of protrusion of the first arching portion 501 may be greater than the degree of protrusion of the second arching portion 601.
  • the apex of the first arching portion 501 and the apex of the second arching portion 601 are located substantially on the same cross section of the blade 1.
  • the surface of the blade 1 has a smooth transition at each position, and there is no sharp twist, so it has a small stress, and the strength is high and it is not easy to be broken, and the entire propeller has high reliability.
  • the circle formed by the propeller provided in this embodiment during the rotation is called a paddle, and the center of the circle is called the center of the paddle, and the diameter of the circle is called the diameter of the paddle.
  • the radius of the paddle can be greater than the length of the blade 1 .
  • the thickness of the blade 1 can be gradually reduced from the end of the blade 1 near the center of the paddle to the end of the blade 1 away from the center of the paddle.
  • the end of the blade 1 farthest from the center of the paddle is the thinnest part of the blade 1, which is advantageous for reducing air resistance during flight and improving flight efficiency.
  • Figure 7 is a schematic cross-sectional view of the blade of Figure 2 along line AA;
  • Figure 8 is a schematic cross-sectional view of the blade of Figure 2 along line BB;
  • Figure 9 is a schematic cross-sectional view of the blade of Figure 2 along line CC;
  • Figure 10 is a schematic view of Figure 2 Schematic diagram of the middle blade along the DD line;
  • Fig. 11 is a schematic cross-sectional view of the blade of Fig. 2 along the EE line.
  • the embodiment can improve the dimensions of the five sections of the blade, wherein the dimensions of the B-B section, the C-C section and the D-D section are advanced.
  • the improvement of the line is the most important.
  • the blade 1 is at a distance of 59.32% of the paddle radius at the center of the paddle formed with the propeller, that is, a BB section from the center L2 of the paddle as shown in FIG.
  • the angle of attack A2 of the blade 1 is 14.05° ⁇ 2.5°
  • the chord length D2 is 11.94 mm ⁇ 5 mm; wherein the chord length is the length of the section of the blade 1 projected in the horizontal direction, the angle of attack It is the angle between the chord and the flow direction of the gas.
  • the blade 1 is at a distance of 76.27% of the paddle radius at the center of the paddle formed with the propeller, that is, at a CC section from the center L3 of the paddle as shown in FIG.
  • the angle of attack A3 of the blade 1 is 11.44° ⁇ 2.5°
  • the chord length D3 is 10.25 mm ⁇ 5 mm.
  • the blade 1 is at a center of the paddle formed by the propeller at a distance of 93.22% of the paddle radius, that is, at a DD cross section from the center L4 of the paddle as shown in FIG.
  • the angle of attack of the blade 1 is 9.99° ⁇ 2.5° for A4 and 8.64 mm ⁇ 5 mm for chord length D4.
  • the resistance of the propeller during the rotation can be reduced, the flight speed and flight efficiency of the aircraft can be improved, and the power supply can be increased under certain power conditions.
  • the flight distance improves the flight performance of the aircraft.
  • the angle of attack and the chord length of the A-A section and the E-E section in the blade 1 can also be optimized to further reduce the air resistance of the propeller during the rotation.
  • the paddle 1 is at a distance of 42.37% of the paddle radius at the center of the paddle formed with the propeller, that is, at the AA section of the paddle center L1 as shown in FIG.
  • the angle of attack of the blade 1 is 16.61 ° ⁇ 2.5 °, and the chord length is 13.48 mm ⁇ 5 mm.
  • the blade 1 is at a distance of 100% of the blade radius at the center of the paddle formed with the propeller, that is, at an EE cross section from the center L5 of the paddle as shown in FIG.
  • the angle of attack of the blade 1 is 9.61 ° ⁇ 2.5 °, and the chord length is 8.34 mm ⁇ 5 mm.
  • the embodiment provides a specific propeller.
  • the diameter of the paddle formed by the propeller is 118 mm, and the distance from the center of the paddle to the end of the blade 1 is half of the diameter of the paddle, that is, the center of the paddle to the paddle The distance at the end of 1 is 59 mm.
  • the blade 1 has an angle of attack of 35 mm at the center of the paddle formed by the propeller (ie 59.32% of 59 mm) and a chord length of 11.94 mm; the blade 1 is in the propeller
  • the center of the formed paddle is 45mm (ie, 76.27% of 59mm) with an angle of attack of 11.44° and a chord length of 10.25mm; the blade 1 is 55mm away from the center of the paddle formed by the propeller (ie 59mm) 93.22%) has an angle of attack of 9.99° and a chord length of 8.64 mm.
  • the blade 1 has an angle of attack of 16.61° and a chord length of 13.48 mm.
  • the blade 1 has an angle of attack of 9.61° and a chord length of 8.34 mm.
  • the positions of the AA section, the BB section, the CC section, the DD section, and the EE section may be slightly changed, and accordingly, the angle of attack obtained at the AA section, the BB section, the CC section, the DD section, and the EE section may be obtained.
  • the chord length value can be changed accordingly.
  • the chord length and the angle of attack of each of the above sections can be set by the size of the paddle.
  • the blade 1 may be provided with a connecting hole 2.
  • the paddle 1 can be connected to the paddle through the connecting hole 2, and has a simple structure and is easy to operate.
  • the pitch of the blade 1 may be 30 inches, that is, the blade 1 is rotated one revolution, and the theoretical rising distance is 30 inches.
  • the propeller can also be an integrated paddle, and the length of the entire paddle is 118 mm.
  • the above-mentioned propeller provided by this embodiment is tested by comparison with the propeller of the prior art.
  • the power of the propeller provided by this embodiment is lower under the same pulling force, that is, at a smaller Under the power condition, it has a larger pulling force, thereby reducing the power loss and increasing the cruising distance.
  • Embodiment 2 of the present invention provides a power assembly including a driving member and a propeller according to the above embodiment, wherein the propeller is connected to the driving member through a paddle.
  • the driving member can drive the paddle to rotate, and the paddle drives the blade to rotate.
  • the number of blades can be set according to actual needs.
  • the driving component may specifically be a motor, and the KV value of the motor is 2100 rpm/(min ⁇ volt), wherein the KV value is used to measure the sensitivity of the motor speed to the voltage increase, and the voltage of the motor in the embodiment is increased by 1 Volt, the motor increases by 2100 rpm.
  • the power assembly provided by the embodiment can reduce the resistance of the propeller during the rotation process by setting the chord length and the angle of attack of the three sections in the blade, and improve the flight speed of the aircraft, and is extended under a certain power supply condition. Sailing distance to improve flight performance.
  • Embodiment 3 of the present invention provides an aircraft.
  • the aircraft in this embodiment may include a fuselage and at least one power assembly as described in the second embodiment above, the power assembly being coupled to the fuselage.
  • the number of the power components in the aircraft may be one or more. In this embodiment, the number of power components is plural, and the rotational directions of the plurality of power components are different.
  • the aircraft in this embodiment may include three, four, five, six, eight, etc. power components, and thus may be a corresponding number of rotorcraft.
  • the aircraft provided in this embodiment adopts the above power component, and by setting the chord length and the angle of attack of at least three sections in the blade, the resistance of the propeller during the rotation can be reduced, and the flight speed of the aircraft is improved.
  • the power supply conditions provide extended sailing distance and improved flight performance.

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

Abstract

L'invention concerne une hélice, un ensemble de puissance et un aéronef, l'hélice comprenant un moyeu et une pale (1) reliée au moyeu. La pale (1) a un angle d'attaque de 14,05° ± 2,5° et une longueur de corde de 11,94 mm ± 5 mm à une position où la distance entre la pale (1) et le centre d'un disque d'hélice formé par l'hélice est de 59,32 % du rayon du disque d'hélice ; la pale (1) a un angle d'attaque de 11,44° ± 2,5° et une longueur de corde de 10,25 mm ± 5 mm à une position où la distance entre la pale (1) et le centre du disque d'hélice formé par l'hélice est de 76,27 % du rayon du disque d'hélice ; et la pale (1) a un angle d'attaque de 9,99° ± 2,5° et une longueur de corde de 8,64 mm ± 5 mm à une position où la distance entre la pale (1) et le centre du disque d'hélice formé par l'hélice est de 93,22 % du rayon du disque d'hélice. Une hélice configurée à l'aide des paramètres décrits peut réduire la résistance pendant le processus de rotation de l'hélice, améliorant ainsi les performances de vol de l'aéronef.
PCT/CN2017/078258 2017-02-28 2017-03-27 Hélice, ensemble de puissance et aéronef WO2018157426A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN201780052530.2A CN109641648A (zh) 2017-02-28 2017-03-27 螺旋桨、动力组件及飞行器

Applications Claiming Priority (2)

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CN201720191484.1 2017-02-28
CN201720191484.1U CN206691356U (zh) 2017-02-28 2017-02-28 螺旋桨、动力组件及飞行器

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WO2018157426A1 true WO2018157426A1 (fr) 2018-09-07

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WO (1) WO2018157426A1 (fr)

Families Citing this family (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
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
CN108820187A (zh) * 2018-03-30 2018-11-16 中山市朗宇模型有限公司 螺旋桨、动力组件及飞行器
CN108945396A (zh) * 2018-03-30 2018-12-07 中山市朗宇模型有限公司 螺旋桨
CN108545173A (zh) * 2018-06-25 2018-09-18 北京小米移动软件有限公司 桨叶、螺旋桨及飞行器
CN109229364B (zh) * 2018-10-23 2019-06-11 西北工业大学 应用于高速直升机旋翼反流区的类椭圆翼型
CN109896009B (zh) * 2019-02-20 2024-06-21 丰翼科技(深圳)有限公司 螺旋桨及无人机

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GB2374331A (en) * 2000-12-15 2002-10-16 Robert Andrew Ledingham Aerofoil with protruding aerodynamic surface
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CN205345320U (zh) * 2016-01-27 2016-06-29 深圳市大疆创新科技有限公司 螺旋桨、动力组件及飞行器
CN205524939U (zh) * 2016-01-27 2016-08-31 深圳市大疆创新科技有限公司 螺旋桨、动力组件及飞行器
CN205554565U (zh) * 2016-02-29 2016-09-07 深圳市大疆创新科技有限公司 螺旋桨、动力组件及飞行器
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
GB2374331A (en) * 2000-12-15 2002-10-16 Robert Andrew Ledingham Aerofoil with protruding aerodynamic surface
US20150152733A1 (en) * 2013-12-04 2015-06-04 Sikorsky Aircraft Corporation Boundary layer ingesting blade
CN205589457U (zh) * 2016-02-29 2016-09-21 深圳市大疆创新科技有限公司 螺旋桨、动力组件及飞行器
CN205801500U (zh) * 2016-06-30 2016-12-14 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
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CN206691356U (zh) 2017-12-01

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