WO2019119379A1 - Hélice, assemblage motorisé et aéronef sans pilote - Google Patents

Hélice, assemblage motorisé et aéronef sans pilote Download PDF

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Publication number
WO2019119379A1
WO2019119379A1 PCT/CN2017/117851 CN2017117851W WO2019119379A1 WO 2019119379 A1 WO2019119379 A1 WO 2019119379A1 CN 2017117851 W CN2017117851 W CN 2017117851W WO 2019119379 A1 WO2019119379 A1 WO 2019119379A1
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WO
WIPO (PCT)
Prior art keywords
paddle
blade
center
angle
distance
Prior art date
Application number
PCT/CN2017/117851
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English (en)
Chinese (zh)
Inventor
刘翊涵
宋浩
陈鹏
黄宏升
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 CN201780029485.9A priority Critical patent/CN109153449A/zh
Priority to PCT/CN2017/117851 priority patent/WO2019119379A1/fr
Publication of WO2019119379A1 publication Critical patent/WO2019119379A1/fr

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Classifications

    • 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
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/32—Rotors
    • B64C27/46—Blades
    • B64C27/473—Constructional features

Definitions

  • the invention relates to a propeller, a power component and an unmanned aerial vehicle, and belongs to the technical field of unmanned aerial vehicles.
  • the propeller is an important component of the rotary wing unmanned aerial vehicle, which is used to convert the rotation of the output shaft of the motor or the engine into thrust or lift to realize the take-off, turn, hover, and the like of the unmanned aerial vehicle.
  • the propeller generally includes a hub and a paddle that is coupled to the output shaft of the motor via a transmission component.
  • the hub connected to the output shaft also rotates, thereby driving the blades fixed on the hub to rotate to form a paddle, thereby driving air flow near the blade to generate a rotor-type unmanned The lift or thrust of the aircraft.
  • the diameter of the paddle is relatively small, as the rotation speed of the propeller increases, the gas flowing through the blade gradually transitions from a laminar flow state to a vortex state, which causes a sharp drop in the performance of the propeller.
  • embodiments of the present invention provide a propeller, a power assembly, and an unmanned aerial vehicle.
  • a propeller comprising a blade, the blade rotating to form a paddle; the blade comprising a blade root and a blade tip facing away from the blade root; the blade having a suction surface a pressure surface, a leading edge connecting one side of the suction side and the pressure side, and a trailing edge connecting the suction side and the other side of the pressure side; the paddle is 50% to 80% of the center of the paddle A lower recess extending to the leading edge and the trailing edge is formed in the range.
  • a power assembly comprising: a drive member, and a propeller;
  • the propeller includes: a blade and a hub, the blade rotating to form a paddle;
  • the hub and the drive The output shaft of the piece is connected;
  • the paddle includes a paddle root and a blade tip facing away from the paddle;
  • the paddle has a suction surface, a pressure surface, a leading edge connecting the suction side and the pressure side, and a connection suction force a trailing edge of the other side of the face and the pressure face;
  • the paddle is formed with a lower recess extending to the leading edge and the trailing edge in a range from 50% to 80% from the center of the paddle.
  • an unmanned aerial vehicle comprising: a frame, an arm, and a power assembly; one end of the arm is coupled to the frame, and the other end of the arm is used for mounting
  • the power assembly includes: a drive member, and a propeller; the propeller includes a paddle and a hub, the blade rotates to form a paddle; the hub is coupled to an output shaft of the drive member;
  • the blade includes a blade root and a blade tip facing away from the blade root; the blade has a suction surface, a pressure surface, a leading edge connecting the suction surface and the pressure side, and a connection suction surface and a pressure surface a trailing edge of the side; the blade is formed with a lower recess extending to the leading edge and the trailing edge in a range from 50% to 80% from the center of the paddle.
  • the resistance when air flows through the blade can be reduced, so that When the rotation speed of the propeller is increased, the possibility of eddy current generated by the air flowing through the propeller is reduced, thereby improving the flight efficiency of the UAV and increasing the cruising distance.
  • 1a-1e are schematic structural views of a propeller according to an embodiment of the present invention at different viewing angles;
  • Figure 1f is a cross-sectional view taken along line E-E of Figure 1c;
  • Figure 2 is a left side view of the propeller of Figure 1;
  • Figure 3 is a bottom plan view of the propeller of Figure 1;
  • Figure 4 is a plan view of the propeller of Figure 1;
  • Figure 5 is a cross-sectional view taken along line A-A of Figure 4.
  • Figure 6 is a cross-sectional view taken along line B-B of Figure 4.
  • Figure 7 is a cross-sectional view taken along line C-C of Figure 4.
  • Figure 8 is a cross-sectional view taken along line D-D of Figure 4.
  • Figure 9 is a cross-sectional view taken along line H-H of Figure 4.
  • Figure 10 is a cross-sectional view taken along line I-I of Figure 4.
  • Figure 11 is a cross-sectional view taken along line J-J of Figure 4.
  • Figure 12 is a cross-sectional view taken along line K-K of Figure 4.
  • Figure 13 is a cross-sectional view taken along line L-L of Figure 4.
  • Figure 14 is a cross-sectional view taken along line M-M of Figure 4.
  • Figure 15 is a schematic structural view of a hub according to an embodiment of the present invention.
  • FIG. 16 is a schematic structural diagram of an unmanned aerial vehicle according to an embodiment of the present invention.
  • the propeller in the following embodiment is suitable for a rotary rotor type drone having a small diameter, such as a single-shaft or multi-axis drone.
  • FIG. 1a-1e are schematic views showing the structure of a propeller at different viewing angles according to an embodiment of the present invention
  • FIG. 1f is a cross-sectional view taken along line EE of FIG. 1c
  • FIG. 2 is a left side view of the propeller of FIG. 1
  • FIG. 3 is a propeller of FIG. 4 is a top view of the propeller of FIG. 1.
  • the propeller provided in this embodiment includes a blade 100 that is rotated by a power component such as a motor or an engine.
  • the paddle 100 includes a paddle root 101 for attachment to the hub and a paddle tip 102 that faces away from the paddle root 101.
  • the blade 100 rotates about a center of rotation to form a paddle to disturb the airflow to generate lift or thrust to propel the UAV movement, such as an airship or a rotary wing drone.
  • the paddle diameter of the propeller provided in this embodiment is less than 150 mm, and the blade 100 can be manufactured by any material in the prior art, including but not limited to steel, aluminum alloy, plastic, carbon fiber and the like. At the time of manufacture, various prior art processing techniques including molding, stamping, forging, and the like can also be employed.
  • the blade 100 further has a suction surface 103 and a pressure surface 104, a leading edge 105 connecting the suction surface 103 and the pressure surface 104, and a trailing edge 106 connecting the suction surface 103 and the other side of the pressure surface 104.
  • the pressure surface 104 is the side of the unmanned aerial vehicle with the blade 100 facing upward during flight; the suction surface 103 is the side of the unmanned aerial vehicle with the blade 100 facing downward (or facing the ground) during flight.
  • the paddle 100 is formed with a recessed portion 107 in the range of 50% to 80% from the center of the paddle plate (four lines in the figure indicate the approximate position of the recessed portion 107 on the blade, wherein
  • the outer side that is, the two line segments near the paddle root 101 and the tip 102 indicate the position of the upper edge of the lower recess 107
  • the two line segments on the inner side indicate the position of the lower edge of the lower recess 107.
  • the above illustration is not a specific limitation of the lower recess 107, and the front side of the lower recess 107 extends to the leading edge 105 and the rear side extends to the trailing edge 106.
  • the lower surface of the lower recess 107 is lower than the other portions of the paddle surface, that is, the lower recess 107 is further downward with respect to the other portions of the blade 100 as seen in the cross-sectional view shown in FIG. 1f. Prominent, so that the airflow can be better guided to reduce fluid resistance.
  • the blade 100 can be placed on a support table, and a groove is formed on the support table, and the groove corresponds to the position where the blade needs to form the lower recess 107, and then punched. Then, the lower concave portion 107 whose lower surface is lower than the other portions of the suction surface 103 can be formed.
  • the lower recess 107 smoothly transitions with other portions of the blade 100 to enable the gas flowing through the blade 100 to conform to the surface of the blade 100, preventing it from being closer to the trailing edge 106.
  • the distance is separated to increase the aerodynamic performance of the blade 100.
  • the thickness of the paddle 100 is optionally tapered from the paddle root 101 to the tip 102 so that the end of the blade 100 away from the center of the paddle is the thinnest portion of the blade 100 to reduce air resistance. Improve the flight performance of the propeller.
  • the leading edge 105 is optionally provided with a curved bulge that is smoothly transitioned to the remainder of the leading edge 105.
  • FIG. 3 shows that the bulging portion of the blade 100 is disposed near the paddle 101, and the bulging portion of the blade 100 located above is directed toward the left side, and the bulging portion of the blade 100 located downward is oriented.
  • the propeller of the present embodiment can form a lower recess 107 extending to the trailing edge 106 in the range of 50% to 80% of the blade 100 from the center of the paddle, thereby reducing the resistance of the air as it flows through the surface of the paddle 100, so that when When the rotation speed of the blade 100 is increased, the possibility that the surface airflow of the blade 100 enters the eddy current state can be reduced, so as to improve the working efficiency of the propeller and increase the cruising distance.
  • Figure 5 is a cross-sectional view taken along the line BB in Figure 4;
  • Figure 6 is a cross-sectional view taken along the line BB in Figure 4;
  • Figure 7 is a cross-sectional view taken along line CC in Figure 4;
  • Figure 8 is a cross-sectional view taken along line DD in Figure 4;
  • Fig. 10 is a cross-sectional view taken along the line XX in Fig. 4;
  • Fig. 12 is a cross-sectional view taken along line KK in Fig. 4;
  • Fig. 13 is a cross-sectional view taken along line LL in Fig. 4;
  • the present embodiment provides an example of the improvement of the size of the blade 100 suitable for the rotary wing type unmanned aerial vehicle, but can be applied to other persons directly or after a simple change according to the following description. On the unmanned aerial vehicle.
  • the dimensions at ten sections in the blade 100 of the rotary wing type unmanned aerial vehicle are improved, wherein the improvements in the dimensions at the HH section, the II section, the JJ section, and the KK section are improved.
  • the HH section of the paddle center is H5
  • the chord length L5 of the blade 100 shown in Fig. 9 is 8 mm ⁇ 5 mm
  • the angle of attack 55 is 15.29 ° ⁇ 2.5 °.
  • the chord length means that at the cross section, the leading edge 105 is located at the leftmost end of the section and the trailing edge 106 is located at the rightmost end of the section in the horizontal direction, and the angle of attack is the leading edge 105.
  • the angle between the leftmost end point of the section and the trailing edge 106 between the rightmost end point of the section is horizontal to the angle, or the angle of attack is also understood to be the chord and gas of the blade 100.
  • the angle of the incoming flow direction is also understood to be the chord and gas of the blade 100.
  • the II section of the paddle center is H6, and the chord length L6 of the blade 100 shown in Fig. 10 is 6.70 mm ⁇ 5 mm.
  • the angle ⁇ 6 is 14.38° ⁇ 2.5°.
  • the JJ section of the paddle center is H7
  • the chord length L7 of the blade 100 shown in Fig. 11 is 5.57 mm ⁇ 5 mm.
  • the angle ⁇ 7 is 12.39° ⁇ 2.5°.
  • the KK section of the paddle center is H8, and the chord length L8 of the blade 100 shown in Fig. 12 is 4.97 mm ⁇ 5 mm.
  • the angle ⁇ 8 is 9.55° ⁇ 2.5°.
  • the resistance when the air flows through the blade 100 can be reduced, so that when the rotation speed of the propeller is increased, the air flowing through the propeller does not generate. Eddy current, which improves the flight efficiency of the UAV and increases the cruising range.
  • chord length and the attack angle of the AA section, the BB section, the CC section, the DD section, the LL section, and the MM section in the blade 100 are respectively improved, which can further reduce the flow of air through the blade 100. Resistance to improve the flight efficiency of the UAV and increase the cruising range.
  • the AA section of the paddle center is H1
  • the chord length L1 of the blade 100 shown in Fig. 5 is 6.19 mm ⁇ 5 mm.
  • the angle ⁇ 1 is 18.36° ⁇ 2.5°.
  • the chord length L2 of the blade 100 shown in Fig. 6 is 9.30 mm ⁇ 5 mm.
  • the angle ⁇ 2 is 18.33 ° ⁇ 2.5 °.
  • the CC section of the paddle center is H3
  • the chord length L3 of the blade 100 shown in Fig. 7 is 9.90 mm ⁇ 5 mm.
  • the angle ⁇ 3 is 18.31 ° ⁇ 2.5 °.
  • the DD section of the paddle center is H4
  • the chord length L4 of the blade 100 shown in Fig. 8 is 9.16 mm ⁇ 5 mm.
  • the angle ⁇ 4 is 18.05° ⁇ 2.5°.
  • the LL section of the paddle center is H9
  • the chord length L9 of the blade 100 shown in Fig. 13 is 4.47 mm ⁇ 5 mm.
  • the angle ⁇ 9 is 7.68 ° ⁇ 2.5 °.
  • the MM section of the paddle center is H10
  • the chord length L10 of the blade 100 shown in Fig. 14 is 4.18 mm ⁇ 5 mm.
  • the angle ⁇ 10 is 6.49 ° ⁇ 2.5 °.
  • section A-A, section B-B, section C-C, section D-D, section L-L, and section M-M are not limited to the above-described scheme, and may be slightly changed.
  • the present embodiment provides a specific propeller having a radius of 38 ⁇ 3.8 mm, that is, the diameter H of the paddle is 76 ⁇ 7.6 mm.
  • the chord length of the blade 100 is specifically 8 mm and the angle of attack is 15.29.
  • the blade 100 has a chord length of 6.70 mm and an angle of attack of 14.38.
  • the blade 100 has a chord length of 5.57 mm and an angle of attack of 12.39.
  • the blade 100 has a chord length of 4.97 mm and an angle of attack of 9.55.
  • the blade 100 has a chord length of 6.19 mm and an angle of attack of 18.36.
  • the blade 100 has a chord length of 9.30 mm and an angle of attack of 18.33.
  • the blade 100 has a chord length of 9.90 mm and an angle of attack of 18.31.
  • the blade 100 has a chord length of 9.16 mm and an angle of attack of 18.05.
  • the blade 100 has a chord length of 4.47 mm and an angle of attack of 7.68.
  • the blade 100 has a chord length of 4.18 mm and an angle of attack of 6.49. It can be understood that the positions of the section AA, the section BB, the section CC, the section DD, the section LL, and the section MM may slightly vary, and accordingly, at section AA, section BB, section CC, section DD, section LL, and section MM The angle of attack and the length of the chord can also be changed accordingly.
  • the pitch of the propeller may be 44 mm, that is, the blade 100 is rotated one revolution, and the theoretical rising distance is 44 mm.
  • the above-mentioned propeller provided by this embodiment is compared with the propeller of the prior art, and when the propeller needs to generate the pulling force of 20g, 30g and 40g, the propeller of the present embodiment needs to provide the on-axis power which can be reduced by 14.9%. 14.3% and 12.7%.
  • a propeller prototype manufactured according to the present embodiment has been tested, and when it provides tensile forces of 20g, 30g, 40g, and 43g, respectively, it is only necessary to provide on-axis power of 1.53W, 3.75W, and 4.12W, respectively.
  • Some propellers provide the same pull but require 2.50W, 3.35W, and 5.10W of on-axis power, respectively.
  • two, three or more blades 100 can be coupled to the hub 200 of the propeller.
  • the paddle drives the paddle 100 to rotate to form a paddle.
  • the hub 200 and the blade 100 may be a unitary structure, or may be a split type propeller formed by separately mounting the blade 100 on the hub 200.
  • a mounting hole may be formed in the paddle 101 of the blade 100. The blade 100 is thus mounted to the hub 200 through the mounting holes.
  • FIG. 15 shows a schematic structural view of a hub.
  • the hub 200 may include a first connecting portion 201, a second connecting portion 202, and a third connecting portion 203.
  • the first connecting portion 201 is connected to the blade 100, for example, through a mounting hole opened in the blade root 101 of the blade 100 to fix the blade 100 to the first connecting portion 201.
  • the second connecting portion 202 is connected to the driving member.
  • the second connecting portion 202 is sleeved on the output shaft of the motor or the engine to drive the blade 100 to rotate by the motor or the engine driving hub to form a paddle, thereby generating lift or thrust.
  • the third connecting portion 203 is disposed between the first connecting portion 201 and the second connecting portion 202 for connecting the first connecting portion 201 and the second connecting portion 202.
  • the third connecting portions 203 may be two, three or more, and are disposed between the first connecting portion 201 and the second connecting portion 202 at intervals.
  • the plurality of third connecting portions 203 may be evenly disposed between the first connecting portion 201 and the second connecting portion 202.
  • three evenly spaced third connecting portions 203 may be provided between the first connecting portion 201 and the second connecting portion 202.
  • the first connecting portion 201 and the second connecting portion 202 are connected together by the third connecting portion 203, so that the weight of the propeller can be reduced and the flight performance of the propeller can be improved.
  • the flight performance can be greatly improved.
  • the third connecting portion 203 disposed between the first connecting portion 201 and the second connecting portion 202 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 of the propeller. performance.
  • the connection position of the third connecting portion 203 and the first connecting portion 201 and the second connecting portion 202 can be smoothly transitioned, thereby reducing the stress at the connection position and improving the reliability of the hub 200. .
  • the propeller may be a self-tightening paddle having a coupling hole formed therein for connection with an output shaft of the motor.
  • the self-tightening paddle means that the hub 200 of the propeller is formed with a self-locking mechanism matched with the fuselage, when the connecting hole of the hub 200 is sleeved on the output shaft of the motor and the unmanned aerial vehicle is started.
  • the self-locking mechanism provided by the fuselage and the hub 200 locks the propeller on the fuselage to avoid flying blades or bombers.
  • a groove is formed in the hub 200, and a pawl driven by a cam mechanism is disposed on the body, so that when the UAV is started, the pawl is driven to rotate along the axial direction of the hub 200 by the rotation of the cam mechanism.
  • Exercise to lock the hub 200 For another example, a disk-shaped structure controlled by an electromagnet is mounted on the body, and the disk-shaped structure is movable in the axial direction of the hub 200, thereby pressing the hub between the disk-shaped structure and the body to realize the paddle. The hub 200 is locked.
  • the propeller may also be a folding paddle such that the volume of the entire UAV can be reduced by folding a plurality of blades 100 and arms into or parallel to the fuselage. This facilitates transportation and storage.
  • the propellers described above may be positive or negative.
  • the positive paddle refers to a propeller that rotates clockwise to generate lift from the perspective of overlooking the unmanned aerial vehicle
  • the reverse paddle refers to a propeller that generates counter-rotation by counterclockwise rotation from the perspective of the unmanned aerial vehicle.
  • the structure of the positive paddle and the structure of the reverse paddle are mirror symmetrical.
  • the present embodiment also provides a power assembly including a drive member and a propeller as provided above, the propeller being coupled to the output shaft of the drive member via a hub.
  • the driving member may specifically be a motor, such as a hollow cup motor.
  • the power assembly of the present embodiment can reduce the flow of air through the surface of the blade 100 by forming the lower recess 107 extending to the leading edge 105 and the trailing edge 106 in the range of 50% to 80% of the blade 100 from the center of the paddle.
  • the resistance of the time so that when the rotation speed of the blade 100 is increased, the possibility that the surface airflow of the blade 100 enters the eddy current state can be reduced, so as to improve the working efficiency of the propeller and increase the cruising distance.
  • FIG. 16 is a schematic structural diagram of an unmanned aerial vehicle according to an embodiment of the present invention.
  • the embodiment further provides an unmanned aerial vehicle comprising a frame 10, a machine arm 20, and at least one power component 30.
  • One end of the arm 20 is connected to the frame 10, and the arm 20 is further One end is used to mount the power assembly 30.
  • the unmanned aerial vehicle as described above may be an airship or a rotary wing unmanned aerial vehicle, such as a quadrotor drone.
  • the propeller of the power assembly of the UAV can reduce the air flowing through the surface of the blade 100 by forming a recess 107 extending to the trailing edge 106 in the range of 50% to 80% of the blade 100 from the center of the paddle.
  • the resistance so that when the rotation speed of the blade 100 is increased, the possibility that the surface airflow of the blade 100 enters the eddy current state can be reduced, so as to improve the working efficiency of the propeller and increase the cruising distance.
  • the arm 20 can be attached to or rotatably coupled to the frame 10.
  • the volume occupied by the UAV can be reduced to facilitate storage and transportation.

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

Abstract

La présente invention concerne une hélice qui comprend une pale d'hélice (100). La pale d'hélice tourne pour former un disque d'hélice. La pale d'hélice (100) comprend une portion de base (101) et une portion de pointe (102) espacée de la portion de base (101). La pale d'hélice (100) a un côté aspiration (103), un côté pression (104), un bord avant (105) reliant des premiers côtés du côté aspiration (103) et du côté pression (104) et un bord arrière (106) reliant les autres côtés du côté aspiration (103) et du côté pression (104). Une partie évidée vers le bas (107) est formée dans la pale d'hélice (100) dans une position représentant de 50 % à 80 % de sa longueur prise à partir du centre du disque d'hélice et s'étend entre le bord avant (105) et le bord arrière (106). L'hélice peut réduire la résistance à l'air et augmenter l'efficacité de vol et la distance de vol. L'invention concerne également un assemblage motorisé (30) et un aéronef sans pilote.
PCT/CN2017/117851 2017-12-21 2017-12-21 Hélice, assemblage motorisé et aéronef sans pilote WO2019119379A1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
CN201780029485.9A CN109153449A (zh) 2017-12-21 2017-12-21 螺旋桨、动力组件及无人飞行器
PCT/CN2017/117851 WO2019119379A1 (fr) 2017-12-21 2017-12-21 Hélice, assemblage motorisé et aéronef sans pilote

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PCT/CN2017/117851 WO2019119379A1 (fr) 2017-12-21 2017-12-21 Hélice, assemblage motorisé et aéronef sans pilote

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CN110053765A (zh) * 2019-04-29 2019-07-26 安徽冠廷科技有限公司 桨叶
CN213323651U (zh) * 2020-04-21 2021-06-01 深圳市大疆创新科技有限公司 螺旋桨、动力组件及飞行器
CN113295882B (zh) * 2021-04-13 2022-09-16 四川腾盾科技有限公司 一种直升机空速确定方法
CN115924141B (zh) * 2023-01-06 2023-05-05 南京流湾科技有限公司 一种无人机旋翼机构

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