WO2017070978A1 - Hélice et aéronef - Google Patents

Hélice et aéronef Download PDF

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Publication number
WO2017070978A1
WO2017070978A1 PCT/CN2015/093836 CN2015093836W WO2017070978A1 WO 2017070978 A1 WO2017070978 A1 WO 2017070978A1 CN 2015093836 W CN2015093836 W CN 2015093836W WO 2017070978 A1 WO2017070978 A1 WO 2017070978A1
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WO
WIPO (PCT)
Prior art keywords
blade
length
main body
propeller
root
Prior art date
Application number
PCT/CN2015/093836
Other languages
English (en)
Chinese (zh)
Inventor
李晓亮
梁智颖
Original Assignee
深圳市道通智能航空技术有限公司
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 深圳市道通智能航空技术有限公司 filed Critical 深圳市道通智能航空技术有限公司
Publication of WO2017070978A1 publication Critical patent/WO2017070978A1/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

Definitions

  • the invention relates to the technical field of drones, in particular to a propeller and an aircraft.
  • the propeller is the power component that generates the lift, tension and operating force necessary for the UAV to fly. Increasing the efficiency of the propeller can greatly improve the flight performance of the UAV.
  • the existing propeller has large resistance and low efficiency, resulting in a small flying speed of the unmanned aerial vehicle and a short cruising distance.
  • the present invention is directed to overcoming the deficiencies of the prior art, providing an improved propeller having reduced drag and improved efficiency and an aircraft using the propeller.
  • the present invention provides the following technical solutions:
  • the root portion has a thickness greater than the body portion, and the root portion is provided with a reinforcing chamfer at the junction with the paddle.
  • the length L1 of the root portion is 22%-26% of the length L of the blade
  • the installation inclination angle of the root portion is 11-13°
  • the length L2 of the main body portion is the blade 62%-66% of the length L
  • the length L3 of the blade tip is 10%-12% of the blade length L.
  • the root portion has a length L1 of 25 mm to 35 mm
  • the body portion has a length of 73 mm to 83 mm
  • the body portion has a maximum leaf width of 29 mm to 33 mm.
  • the length of the root portion is 30 mm
  • the length of the main body portion is 78 mm
  • the maximum leaf width of the main body portion is 31 mm
  • the leaf width of the main body portion is 21 mm at a distance of 83 mm from the center of the paddle. .
  • the structural stiffness of the blade tapers in the first direction.
  • the paddle includes upper and lower blade faces, and a first side edge face and a second side edge face respectively connected between the upper and lower blade faces on both sides of the paddle,
  • the upper and lower leaf surfaces and the first side edge surface and the second side edge surface are smooth curved surfaces and smoothly transition between them.
  • the first side edge face includes a first protruding portion that protrudes outward
  • the second side edge face includes a second protruding portion that protrudes outward
  • the second protruding portion The degree of outward convexity is smaller than the first convex portion, and the first convex portion and the second convex portion are located at one end of the main body portion close to the root portion.
  • the present invention provides an aircraft comprising a fuselage, a flight control device disposed to the fuselage, and a propeller as described above, the flight control device for controlling rotation of the propeller.
  • the invention has the beneficial effects that the propeller is arranged in the ARA-D airfoil by the blade, and the length ratio of the root portion, the main body portion and the blade tip portion is set in a certain ratio, so that the whole of the propeller
  • the Reynolds number is the largest, and the air resistance is reduced, which increases the efficiency and thus improves the flying speed and flight distance of the UAV.
  • Figure 1 is a right side elevational view of a first embodiment of a propeller according to an embodiment of the present invention
  • Figure 2 is a front elevational view of the propeller shown in Figure 1;
  • FIG. 3 is a schematic cross-sectional view showing an ARA-D airfoil of a propeller according to an embodiment of the present invention
  • Figure 4 is a cross-sectional view taken along line A-A of Figure 2;
  • Figure 5 is a schematic view showing the structure of the root of the propeller shown in Figure 2;
  • FIG. 6 is a schematic structural view of a second embodiment of a propeller according to an embodiment of the present invention.
  • Fig. 7 is a schematic structural view of an unmanned aerial vehicle according to an embodiment of the present invention.
  • an embodiment of the present invention provides a propeller 100 including a paddle 110 and at least two blades 120 connected to the paddle 110; the airfoil of the blade 120 is ARA-D, paddle
  • the 110 includes a root portion 121, a body portion 122, and a blade tip portion 123 which are sequentially connected.
  • the root portion 121 and the body portion 122 are bounded by a broken line
  • the body portion 122 and the blade tip portion 123 are bounded by a broken line.
  • the paddle has a length L that is the length of the paddle 110 in a first direction from the center of the paddle to the most distal end of the blade tip 123.
  • the length L1 of the root portion 121 is 20% to 30% of the blade length L.
  • the length L1 of the root portion 121 is 20%, 22%, 24%, 26%, 28%, 30%, or the like of the blade length L.
  • the length L1 of the root portion 121 is the length from the center of the paddle to the most distal end of the root portion 121.
  • the mounting inclination angle ⁇ of the root portion 121 is 10-15°.
  • the mounting inclination angle ⁇ of the root portion 121 may be 10°, 11°, 12°, 13°, 14°, 15°; preferably, the mounting inclination angle of the root portion 121 is 12°.
  • the leaf width of the root portion 121 gradually increases in the first direction.
  • the length L2 of the main body portion 122 is 60% to 70% of the blade length L.
  • the length L2 of the main body portion 122 is 60%, 62%, 64%, 66%, 68%, 70%, or the like of the blade length L.
  • the length L2 of the main body portion 122 is the length from the closest end to the farthest end of the main body portion 122 from the center of the paddle, the leaf width of the main body portion 122 is gradually reduced in the first direction, and the minimum leaf width of the main body portion 122 is 55 of its maximum leaf width.
  • %-65% for example, the minimum leaf width of the main body portion 122 is 55%, 57%, 59%, 60%, 61%, 63%, 65%, etc. of the maximum leaf width.
  • the blade width of the body portion 122 varies smoothly along a first direction away from the center of the paddle.
  • the length L3 of the blade tip portion 123 is 8%-15% of the blade length L.
  • the length L3 of the blade tip portion 123 is 8%, 10%, 12%, 14%, 15%, etc. of the blade length L.
  • L L1 + L2 + L3.
  • the length L3 of the blade tip portion 123 is the length of the blade tip portion 123 from the closest end of the blade center to the most distal end thereof, and the blade width of the blade tip portion 123 is gradually reduced in the first direction.
  • the leaf width of the leaf tip portion 123 varies smoothly in the first direction, and the leaf distal end of the leaf tip portion has a width of zero.
  • the propeller 100 is disposed in the ARA-D airfoil by the blade 110, and the length ratio of the root portion 111, the main body portion 112, and the blade tip portion 113 is set in a certain ratio so that the overall Reynolds of the propeller 100 The largest number, less air resistance, increased efficiency, which increased the flight speed and flight distance of the UAV.
  • the root portion 121 has a thickness greater than the main body portion 122 and smoothly transitions from the root portion 121 to the main body portion 122.
  • the joint of the root portion 121 and the paddle 110 is provided with a reinforcing chamfer 130, and the reinforcing chamfer 130 further enhances the strength of the propeller 100. Thereby improving the stability of the propeller 100.
  • the length L1 of the root portion 121 is 22%-26% of the blade length L, for example, the length L1 of the root portion 121 is 22%, 23%, 24%, 25%, 26% of the blade length L; the root portion 121
  • the installation inclination angle ⁇ is 11°-13°, for example, the installation inclination angle ⁇ of the root portion 121 is 11°, 12°, 13°, etc.
  • the length of the main body portion 122 is 62%-66% of the blade length, for example, the main body portion
  • the length of 122 is 62%, 63%, 64%, 65%, 66%, etc. of the length of the blade;
  • the length of the blade tip 123 is 10%-12% of the length of the blade, and the length of the blade tip 123 is the blade. 10%, 11%, 12%, etc. of the length.
  • the length of the root portion 121 is 25 mm to 35 mm, for example, the length of the root portion 121 is 25 mm, 26 mm, 27 mm, 28 mm, 29 mm, 30 mm, 31 mm, 32 mm, 33 mm, 34 mm, 35 mm, etc., preferably, the length of the root portion 121 is 30 mm.
  • the length of the main body portion 122 is 73 mm to 83 mm, for example, the length of the main body portion 122 is 73 mm, 74 mm, 75 mm, 76 mm, 77 mm, 78 mm, 79 mm, 80 mm, 81 mm, 82 mm, 83 mm, etc., preferably, the length of the main body portion 122 is 78 mm; the maximum leaf width of the main body portion 122 is 29 mm - 33 mm, for example, the maximum leaf width of the main body portion 122 is 29 mm, 30 mm, 31 mm, 32 mm, 33 mm, or the like.
  • the leaf width of the body portion is 21 mm at a distance of 83 mm from the center of the paddle.
  • the structural stiffness of the blade 120 tapers in a first direction away from the center of the trowel.
  • the blade 120 includes upper and lower leaf surfaces 124, and a first side edge surface 125 and a second side edge surface 126, which are respectively connected between the upper and lower leaf surfaces 124 on both sides of the blade 120, and the leaf surface 124.
  • the first side edge surface 125 and the second side edge surface 126 are smooth curved surfaces with a smooth transition therebetween.
  • first side edge surface 125 includes a first protruding portion 125a that protrudes outward
  • second side edge 126 includes a second protruding portion 126a that protrudes outward
  • the second protruding portion 126a is convex outward.
  • the extent of the exit is smaller than the first projection 125a, and the first projection 125a and the second projection 126a are both located at one end of the main body portion 122 near the root 121 of the blade 120.
  • an embodiment of the present invention also proposes a second embodiment.
  • an embodiment of the present invention further provides an aircraft including a fuselage 200, a flight control device 300 disposed in the fuselage 200, and a propeller 100 as described above, and the flight control device 300 is configured to control the rotation of the propeller 100.
  • the body 200 includes a main housing 210 and four arms 220 connected to the main housing, and the four arms 220 are distributed in a crisscross pattern.

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  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Toys (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

L'invention concerne une hélice et un aéronef. L'hélice (100) comprend un anneau d'hélice (110) et au moins deux pales d'hélice (120) raccordées à l'anneau d'hélice; le plan de sustentation des pales d'hélice est du type ARA-D; la pale d'hélice est composée d'une emplanture (121), d'un corps principal (122) et d'un bout de pale (123), raccordés en séquence; la longueur L1 de l'emplanture est de 20 %-30 % de la longueur L de la pale d'hélice, l'angle d'inclinaison selon lequel l'emplanture est montée est de 10° à 15°, et la largeur de la pale augmente progressivement le long d'une première direction; la longueur L2 du corps principal est de 60 %-70 % de la longueur L de la pale d'hélice, et la largeur du corps principal diminue progressivement le long de la première direction; la plus petite largeur de pale du corps principal est de 55 %-65 % de sa largeur maximale; la longueur L3 du bout de pale est L3=(L-L1-L2), et la largeur du bout de pale diminue progressivement le long de la première direction. La traînée aérodynamique de l'hélice est réduite et son efficacité est améliorée, ce qui permet d'améliorer la vitesse de vol et la distance de vol de l'aéronef.
PCT/CN2015/093836 2015-10-27 2015-11-05 Hélice et aéronef WO2017070978A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
CN201510706722.3 2015-10-27
CN201510706722.3A CN105235893B (zh) 2015-10-27 2015-10-27 一种螺旋桨及飞行器

Publications (1)

Publication Number Publication Date
WO2017070978A1 true WO2017070978A1 (fr) 2017-05-04

Family

ID=55033809

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/CN2015/093836 WO2017070978A1 (fr) 2015-10-27 2015-11-05 Hélice et aéronef

Country Status (2)

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CN (1) CN105235893B (fr)
WO (1) WO2017070978A1 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN109969389A (zh) * 2017-12-28 2019-07-05 昆山优尼电能运动科技有限公司 一种桨叶连接结构
CN110337404A (zh) * 2018-05-28 2019-10-15 深圳市大疆创新科技有限公司 螺旋桨组件、动力组件及飞行器

Families Citing this family (8)

* 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
CN205524940U (zh) * 2016-02-29 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
CN107434038A (zh) * 2016-05-25 2017-12-05 天津宏宇天翔科技有限公司 一种无人机旋翼
CN106628112A (zh) * 2017-01-16 2017-05-10 顺丰科技有限公司 机翼
CN106938696B (zh) * 2017-02-20 2019-08-13 西安爱生技术集团公司 一种马刀型低噪声螺旋桨桨叶设计方法
CN109071006B (zh) * 2017-12-26 2022-04-08 深圳市大疆创新科技有限公司 螺旋桨、动力组件及飞行器
CN209241318U (zh) * 2018-08-28 2019-08-13 深圳市道通智能航空技术有限公司 螺旋桨、动力组件及无人机
CN110750839A (zh) * 2019-08-26 2020-02-04 深圳市道通智能航空技术有限公司 一种螺旋桨翼型的设计方法及终端设备

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4455003A (en) * 1977-03-23 1984-06-19 Vfw Supercritical air-foil profile
US4773825A (en) * 1985-11-19 1988-09-27 Office National D'etudes Et De Recherche Aerospatiales (Onera) Air propellers in so far as the profile of their blades is concerned
US20120189457A1 (en) * 2011-01-25 2012-07-26 Occhipinti Anthony C Propeller slipstream enhancer
CN202642093U (zh) * 2012-04-10 2013-01-02 深圳市大疆创新科技有限公司 螺旋桨及具有该螺旋桨的飞行器
CN203558202U (zh) * 2013-09-27 2014-04-23 保利科技（珠海）有限公司 螺旋桨及具有该螺旋桨的飞行器
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
CN104583073A (zh) * 2013-05-31 2015-04-29 深圳市大疆创新科技有限公司 自紧固旋翼

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Publication number Priority date Publication date Assignee Title
GB190664A (en) * 1922-02-13 1922-12-28 Robert Leparmentier Improvements in variable pitch screw propellers for aerial machines
CN203486144U (zh) * 2013-09-25 2014-03-19 重庆金泰航空工业有限公司 农用无人飞行器
CN204173156U (zh) * 2014-08-25 2015-02-25 深圳市兴天翼科技有限公司 螺旋桨

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4455003A (en) * 1977-03-23 1984-06-19 Vfw Supercritical air-foil profile
US4773825A (en) * 1985-11-19 1988-09-27 Office National D'etudes Et De Recherche Aerospatiales (Onera) Air propellers in so far as the profile of their blades is concerned
US20120189457A1 (en) * 2011-01-25 2012-07-26 Occhipinti Anthony C Propeller slipstream enhancer
CN202642093U (zh) * 2012-04-10 2013-01-02 深圳市大疆创新科技有限公司 螺旋桨及具有该螺旋桨的飞行器
CN104583073A (zh) * 2013-05-31 2015-04-29 深圳市大疆创新科技有限公司 自紧固旋翼
CN203558202U (zh) * 2013-09-27 2014-04-23 保利科技（珠海）有限公司 螺旋桨及具有该螺旋桨的飞行器
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

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN109969389A (zh) * 2017-12-28 2019-07-05 昆山优尼电能运动科技有限公司 一种桨叶连接结构
CN110337404A (zh) * 2018-05-28 2019-10-15 深圳市大疆创新科技有限公司 螺旋桨组件、动力组件及飞行器

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Publication number Publication date
CN105235893A (zh) 2016-01-13
CN105235893B (zh) 2018-01-16

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