WO2017128742A1 - Hélice, élément fournisseur de puissance et aéronef - Google Patents

Hélice, élément fournisseur de puissance et aéronef Download PDF

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Publication number
WO2017128742A1
WO2017128742A1 PCT/CN2016/099698 CN2016099698W WO2017128742A1 WO 2017128742 A1 WO2017128742 A1 WO 2017128742A1 CN 2016099698 W CN2016099698 W CN 2016099698W WO 2017128742 A1 WO2017128742 A1 WO 2017128742A1
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WO
WIPO (PCT)
Prior art keywords
paddle
blade
propeller
center
distance
Prior art date
Application number
PCT/CN2016/099698
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English (en)
Chinese (zh)
Inventor
陶冶
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 WO2017128742A1 publication Critical patent/WO2017128742A1/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
    • 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 invention belongs to the technical field of propellers, and in particular to a propeller, a power component 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 propeller of the prior art finds that the shape of the blade of the prior art propeller has a large flight resistance and low efficiency, resulting in a small flying speed of the aircraft and a short following distance, which seriously affects the aircraft. Flight performance.
  • the invention provides a propeller, a power component and an aircraft to solve the technical problem of high resistance and low efficiency of the propeller in the prior art.
  • An embodiment of the present invention provides a propeller, including: a paddle and a blade connected to the paddle;
  • the blade has an angle of attack of 13° ⁇ 2.5° at a second threshold value from a center of the paddle formed by the propeller, and a chord length of 33.75 mm ⁇ 2.5 mm, the second threshold being the center of the paddle to 44.44% of the distance from the end of the blade;
  • the blade has an angle of attack of 10.8° ⁇ 2.5° at a third threshold from the center of the paddle and a chord length of 26.32 mm ⁇ 2.5 mm, the third threshold being the center of the paddle to the paddle 62.96% of the distance from the end of the leaf;
  • the blade has an angle of attack of 8.8° ⁇ 2.5° at a fourth threshold from the center of the paddle and a chord length of 21.08 mm ⁇ 2.5 mm, the fourth threshold being the center of the paddle to the paddle
  • the distance at the end of the leaf is 81.48%.
  • propeller as described above, the propeller forming a paddle diameter of 540 mm ⁇ 54 mm;
  • the blade has an angle of attack of 13° and a chord length of 33.75 mm at a distance of 120 mm from the center of the paddle;
  • the blade has an angle of attack of 10.8° and a chord length of 26.32 mm at a distance of 170 mm from the center of the paddle;
  • the blade At an angle of 220 mm from the center of the paddle, the blade has an angle of attack of 8.8° and a chord length of 21.08 mm.
  • a propeller as described above, wherein the blade has an angle of attack of 18.3° ⁇ 2.5° at a first threshold from the center of the paddle and a chord length of 46.63 mm ⁇ 2.5 mm, the first threshold being the paddle
  • the distance from the center of the disk to the end of the blade was 25.93%.
  • the propeller has a paddle diameter of 540 mm ⁇ 54 mm; at a distance of 70 mm from the center of the paddle, the blade has an angle of attack of 18.3° and a chord length of 46.63 mm.
  • a propeller as described above, wherein the blade has an angle of attack of 7° ⁇ 2.5° at a fifth threshold from the center of the paddle and a chord length of 17.47 mm ⁇ 2.5 mm, the fifth threshold being the paddle 100% of the distance from the center of the disk to the end of the blade.
  • the propeller as described above has a paddle diameter of 540 mm ⁇ 54 mm; the blade has an angle of attack of 7° and a chord length of 17.47 mm at a distance of 270 mm from the center of the paddle.
  • the propeller as described above has a length of 247 mm ⁇ 24.7 mm.
  • the propeller as described above gradually decreases in thickness of the blade 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 number of the blades is at least two, and at least two of the blades are evenly distributed along the circumference of the paddle.
  • the propeller has a pitch of 70 mm as described above.
  • the blade is provided with a connecting hole having a diameter of 6 mm.
  • the distance between the connecting hole of the paddle and the center of the paddle is 23 mm.
  • the blade comprising an upwardly facing leaf back, a downwardly facing leaf surface, connected to the a first side edge between the leaf back and one side of the leaf surface, and a second side edge connected between the leaf back and the other side of the leaf surface, the first side edge being located Below the second side edge.
  • the first side edge comprising a curved outwardly convex first arch
  • the second side edge comprising a curved outwardly projecting second arch
  • the first arching portion and the second arching portion are both adjacent to an end of the blade connected to the paddle.
  • An embodiment of the present invention further provides a power assembly including a driving member and the propeller according to any one of the above, wherein the propeller is coupled to the driving member through a paddle.
  • the drive member is a motor having a KV value of 130 rpm / (minute volt).
  • An embodiment of the present invention further provides an aircraft comprising a body and the power assembly of any of the above, the power component being coupled to the body.
  • the propeller, the power component and the aircraft provided by the invention can reduce the resistance of the propeller during the rotation process by setting the chord length and the attack angle of the above three sections in the blade, and improve the flight speed of the aircraft, at a certain power.
  • the conditional supply extends the sailing distance and improves flight performance.
  • FIG. 1 is a front view of a blade in a propeller according to a first embodiment of the present invention
  • Figure 2 is a right side view of the blade of Figure 1;
  • Figure 3 is a left side view of the blade of Figure 1;
  • Figure 4 is a bottom plan view of the blade of Figure 1;
  • Figure 5 is a plan view of the blade of Figure 1;
  • Figure 6 is a perspective view of the blade of Figure 1;
  • Figure 7 is a schematic cross-sectional view of the blade of Figure 1 taken along line A-A;
  • Figure 8 is a schematic cross-sectional view of the blade of Figure 1 taken along line B-B;
  • Figure 9 is a schematic cross-sectional view of the blade of Figure 1 taken along line C-C;
  • Figure 10 is a schematic cross-sectional view of the blade of Figure 1 taken along line D-D;
  • Figure 11 is a cross-sectional view of the blade of Figure 1 taken along line E-E;
  • FIG. 12 is a schematic structural diagram of an aircraft according to Embodiment 3 of the present invention.
  • 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 attached 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 aircraft
  • the so-called reverse propeller refers to the aircraft from the overhead view. From the perspective, the propeller that rotates counterclockwise to generate lift.
  • 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 paddle and the paddle may be integrally formed, or may be connected by other means, such as screwing, or welding, or connecting through other connecting members.
  • the number of blades may be one or more, and a plurality of blades may be circumferentially along the paddle Evenly distributed, a plurality of blades may be integrally formed or independent of each other, and the present invention is not limited thereto.
  • FIG. 1 is a front elevational view of a blade in a propeller according to a first embodiment of the present invention.
  • Figure 2 is a right side view of the blade of Figure 1.
  • Figure 3 is a left side elevational view of the blade of Figure 1.
  • Figure 4 is a bottom plan view of the blade of Figure 1.
  • Figure 5 is a plan view of the blade of Figure 1.
  • Figure 6 is a perspective view of the blade of Figure 1.
  • the blade of the propeller in this embodiment may include an upward leaf back 2, a downward facing leaf surface 3 , a first one connected to the leaf back 2 and the leaf surface 3 .
  • the leaf back 2 is the one side of the blade during the flight of the aircraft; the leaf surface 3 is the side of the blade with the blade facing downward during the flight. Both the leaf back 2 and the leaf surface 3 are curved surfaces, and the tendency to bend is that the first side edge 4 is located lower than the position where the second side edge 5 is located when the blade is entirely horizontal.
  • the first side edge 4 may comprise a curved, outwardly projecting first arching portion 6, the first arching portion 6 being in a smooth transitional connection with the remainder of the first side edge 4.
  • the first arch portion 6 is closer to one end of the blade connected to the paddle than the one end of the paddle away from the paddle in the longitudinal direction of the entire blade.
  • the first arching portion 6 not only arches towards one side of the blade, but can also be arched downwards, ie in the direction of the blade surface 3, and is smoothly transitioned to the blade surface 3.
  • the second side edge 5 may comprise a curved, outwardly projecting second arching portion 7, the second arching portion 7 being in a smooth transitional connection with the remainder of the second side edge 5.
  • the second arch portion 7 is closer to one end of the blade connected to the paddle than the end of the paddle away from the paddle in the lengthwise direction of the entire blade.
  • the degree of protrusion of the second arching portion 7 may be smaller than the degree of protrusion of the first arching portion 6.
  • the apex of the first arching portion 6 and the apex of the second arching portion 7 are located substantially on the same cross section of the blade.
  • the surface of the blade is a smooth transition, there is no sharp twist, so it has less stress, and the strength is higher and not easy to break, and has high reliability.
  • the circular shape 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.
  • the thickness of the blade may be gradually reduced, away from the center of the paddle in the blade 1 of The end is the thinnest part of the blade, which helps to reduce air resistance.
  • Figure 7 is a schematic cross-sectional view of the blade of Figure 1 taken along line A-A.
  • Figure 8 is a schematic cross-sectional view of the blade of Figure 1 taken along line B-B.
  • Figure 9 is a schematic cross-sectional view of the blade of Figure 1 taken along line C-C.
  • Figure 10 is a schematic cross-sectional view of the blade of Figure 1 taken along line D-D.
  • Figure 11 is a cross-sectional view of the blade of Figure 1 taken along line E-E.
  • the present embodiment can improve the dimensions of the five sections of the blade to improve the flight performance of the aircraft.
  • the improvement of the dimensions at the B-B line, the C-C line, and the D-D line is most important.
  • the angle of attack of the paddle A2 is 13° ⁇ 2.5°
  • chord length D2 is 33.75 mm ⁇ 2.5 mm
  • the second threshold is 44.44% of the distance from the center 1 of the paddle to the end of the blade.
  • the chord length is the length of the section where the blade is projected in the horizontal direction
  • the angle of attack is the angle between the chord and the direction in which the gas flows.
  • the angle of attack A3 of the blade is 10.8 ° ⁇ 2.5. °
  • the chord length D3 is 26.32 mm ⁇ 2.5 mm
  • the third threshold is 62.96% of the distance from the center 1 of the paddle to the end of the blade.
  • the angle of attack A4 of the blade is 8.8 ° ⁇ 2.5. °
  • the chord length D4 is 21.08 mm ⁇ 2.5 mm
  • the fourth threshold is 81.48% of the distance from the center 1 of the paddle to the end of the blade.
  • the resistance of the propeller during the rotation process can be reduced, the flight speed of the aircraft can be improved, and the sailing distance can be extended under a certain power condition supply, thereby improving Flight performance.
  • the angle of attack and the chord length at the A-A line and the E-E line in the blade can be improved, and the resistance of the propeller during the rotation can be further reduced.
  • the A1 angle of attack of the blade may be 18.3 ° ⁇ 2.5 °
  • the chord length D1 may be 46.63 mm ⁇ 2.5 mm
  • the first threshold being 25.93% of the distance from the center 1 of the paddle to the end of the blade.
  • a fifth threshold from the center 1 of the paddle that is, the distance from the center of the paddle 1 in FIG. 1 is L5.
  • the blade may have an angle of attack of 7° ⁇ 2.5° and a chord length of 17.47 mm ⁇ 2.5 mm, and the fifth threshold is 1 to the center of the paddle. 100% of the distance at the end of the blade.
  • the embodiment provides a specific propeller.
  • the diameter of the paddle formed by the propeller is 540 mm ⁇ 54 mm, and the distance from the center 1 of the paddle to the end of the paddle is half of the diameter of the paddle, that is, the paddle
  • the distance from the center 1 to the end of the blade is 270 mm ⁇ 27 mm.
  • the blade has an angle of attack of 13 and a chord length of 33.75 mm.
  • the blade has an angle of attack of 10.8° and a chord length of 26.32 mm.
  • the blade has an angle of attack of 8.8° and a chord length of 21.08 mm.
  • the blade has an angle of attack of 18.3° and a chord length of 46.63 mm.
  • the blade has an angle of attack of 7 and a chord length of 17.47 mm.
  • the length of the blade may be 247 mm ⁇ 24.7 mm.
  • the blade is provided with a connecting hole 8, the diameter of the connecting hole 8 is 6 mm ⁇ 0.6 mm, and the distance L6 of the connecting hole 8 from the center 1 of the paddle may be 23 mm ⁇ 2.3 mm.
  • the paddle can be connected to the paddle through the connecting hole 8, and the structure is simple and convenient to implement.
  • the pitch of the blade may be 70 mm, that is, the blade rotates one revolution, and the theoretical rising distance is 70 mm.
  • the propeller provided in this embodiment has a great improvement in performance compared with the propeller in the prior art.
  • Table 1 is a comparison table of the tension and power of the propeller provided in the present embodiment and the propeller of the prior art. Referring to Table 1, the power of the propeller provided by this embodiment is lower under the same pulling force, that is, under the same power conditions, the propeller provided in this embodiment has more advantages than the propeller of the prior art. Large pulling force saves power loss and increases battery life.
  • a second embodiment of the present invention provides a power assembly including a driving member and a propeller according to any of the above embodiments, wherein the propeller is coupled to the driving member through a paddle.
  • the driving member can drive the paddle to rotate, thereby driving 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 motor has a KV value of 130 rpm/(minute ⁇ volt).
  • 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 the power assembly of any of the above embodiments, the power component being coupled to the fuselage.
  • FIG. 12 is a schematic structural diagram of an aircraft according to Embodiment 3 of the present invention.
  • the power assembly includes a propeller 9 and a drive member 10.
  • the number of the power components in the aircraft may be one or more, which is not limited in this embodiment.
  • the aircraft provided in this embodiment adopts the above power component, and by setting the chord length and the angle of attack of the three sections in the blade, the resistance of the propeller 9 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.
  • the units described as separate components may or may not be physically separated, and the components displayed as the unit may or may not be physical units, that is, may be located in one place, or It can also be distributed to multiple network elements. Some or all of the units may be selected according to actual needs to achieve the purpose of the solution of the embodiment.
  • each functional unit in each embodiment of the present invention may be integrated into one processing unit, or each unit may exist physically separately, or two or more units may be integrated into one unit.

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

Abstract

L'invention concerne une hélice (9), un élément fournisseur de puissance et un aéronef, l'hélice (9) comprenant un moyeu et une pale reliée au moyeu. À la distance de l'ordre d'une deuxième valeur seuil à partir du centre (1) du cercle balayé par l'hélice, la pale a un angle d'attaque de 13° ± 2,5° et une longueur de corde de 33,75 mm ± 2,5 mm, la deuxième valeur seuil équivalant à 44,44 % de la distance entre le centre (1) du cercle balayé par l'hélice et l'extrémité arrière de la pale ; à la distance de l'ordre d'une troisième valeur seuil à partir du centre (1) du cercle balayé par l'hélice, la pale a un angle d'attaque de 10,8° ± 2,5° et une longueur de corde de 26,32 mm ± 2,5 mm, la troisième valeur seuil équivalant à 62,96 % de la distance entre le centre (1) du cercle balayé par l'hélice et l'extrémité arrière de la pale ; et à la distance de l'ordre d'une quatrième valeur seuil à partir du centre (1) du cercle balayé par l'hélice, la pale a un angle d'attaque de 8,8° ± 2,5° et une longueur de corde de 21,08 mm ± 2,5 mm, la quatrième valeur seuil équivalant à 81,48 % de la distance entre le centre (1) du cercle balayé par l'hélice et l'extrémité arrière de la pale. L'hélice (9), l'élément fournisseur de puissance et l'aéronef de la présente invention réduisent la résistance de l'hélice (9) pendant sa rotation, améliorant ainsi les performances de vol.
PCT/CN2016/099698 2016-01-27 2016-09-22 Hélice, élément fournisseur de puissance et aéronef WO2017128742A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
CN201620080797.5 2016-01-27
CN201620080797.5U CN205345320U (zh) 2016-01-27 2016-01-27 螺旋桨、动力组件及飞行器

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Families Citing this family (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
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
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
CN205891216U (zh) * 2016-08-04 2017-01-18 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
WO2018045575A1 (fr) * 2016-09-09 2018-03-15 深圳市大疆创新科技有限公司 Ensemble hélice, système de puissance et véhicule aérien
CN206068155U (zh) * 2016-09-27 2017-04-05 深圳市大疆创新科技有限公司 桨叶、螺旋桨、动力套装及无人飞行器
CN206202682U (zh) * 2016-09-27 2017-05-31 深圳市大疆创新科技有限公司 桨叶、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
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
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
CN108945396A (zh) * 2018-03-30 2018-12-07 中山市朗宇模型有限公司 螺旋桨
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

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US1471590A (en) * 1922-10-02 1923-10-23 Samuel W Carter Propeller
US5209643A (en) * 1991-03-27 1993-05-11 The Cessna Aircraft Company Tapered propeller blade design
US5433586A (en) * 1991-03-27 1995-07-18 Cessna Aircraft Company Tapered propeller blade design
US5879131A (en) * 1994-04-25 1999-03-09 Arlton; Paul E. Main rotor system for model helicopters
CN103587684A (zh) * 2013-10-24 2014-02-19 中国科学院长春光学精密机械与物理研究所 一种低雷诺数下的二维翼型及采用该翼型的旋翼
CN203996873U (zh) * 2014-07-30 2014-12-10 深圳市大疆创新科技有限公司 飞行器及其螺旋桨
CN105235893A (zh) * 2015-10-27 2016-01-13 深圳市道通智能航空技术有限公司 一种螺旋桨及飞行器
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

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1471590A (en) * 1922-10-02 1923-10-23 Samuel W Carter Propeller
US5209643A (en) * 1991-03-27 1993-05-11 The Cessna Aircraft Company Tapered propeller blade design
US5433586A (en) * 1991-03-27 1995-07-18 Cessna Aircraft Company Tapered propeller blade design
US5879131A (en) * 1994-04-25 1999-03-09 Arlton; Paul E. Main rotor system for model helicopters
CN103587684A (zh) * 2013-10-24 2014-02-19 中国科学院长春光学精密机械与物理研究所 一种低雷诺数下的二维翼型及采用该翼型的旋翼
CN203996873U (zh) * 2014-07-30 2014-12-10 深圳市大疆创新科技有限公司 飞行器及其螺旋桨
CN105235893A (zh) * 2015-10-27 2016-01-13 深圳市道通智能航空技术有限公司 一种螺旋桨及飞行器
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

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