WO2019000560A1 - Hélice, ensemble d'alimentation, et aéronef - Google Patents

Hélice, ensemble d'alimentation, et aéronef Download PDF

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Publication number
WO2019000560A1
WO2019000560A1 PCT/CN2017/095865 CN2017095865W WO2019000560A1 WO 2019000560 A1 WO2019000560 A1 WO 2019000560A1 CN 2017095865 W CN2017095865 W CN 2017095865W WO 2019000560 A1 WO2019000560 A1 WO 2019000560A1
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WO
WIPO (PCT)
Prior art keywords
paddle
propeller
blade
center
attack
Prior art date
Application number
PCT/CN2017/095865
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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 CN201780069690.8A priority Critical patent/CN109923036A/zh
Publication of WO2019000560A1 publication Critical patent/WO2019000560A1/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
    • 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 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-mentioned defects in the prior art to optimize the structure of the propeller and improve the flight performance of the aircraft.
  • An aspect of the invention provides a propeller comprising a paddle that rotates to form a paddle;
  • the blade has an angle of attack of 22.59° ⁇ 2.5° at a distance of 45.8% of the blade radius from the screw, and a chord length of 26.98 mm ⁇ 5 mm;
  • the blade has an angle of attack of 19.57° ⁇ 2.5° at a distance of 62.5% of the paddle radius from the center of the paddle formed by the propeller, and a chord length of 21.91 mm ⁇ 5 mm;
  • the blade has an angle of attack of 16.56° ⁇ 2.5° at a distance of 79.2% of the paddle radius from the center of the paddle formed by the propeller, and a chord length of 17.64 mm ⁇ 5 mm.
  • propeller as described above, the propeller forming a paddle diameter of 240 mm;
  • the blade is at a distance of 55 mm from the center of the paddle formed by the propeller
  • the angle of attack is 22.59° and the chord length is 26.98 mm;
  • the blade has an angle of attack of 19.57° at a distance of 75 mm from the center of the paddle formed by the propeller, and a chord length of 21.91 mm;
  • the blade has an angle of attack of 16.56° at a distance of 95 mm from the center of the paddle formed by the propeller, and a chord length of 17.64 mm.
  • the blade has an angle of attack of 24.74° ⁇ 2.5° at a distance of 29.2% of the paddle radius from the center of the paddle formed by the propeller, and a chord length of 33.58 mm ⁇ 5 mm.
  • propeller as described above, the propeller forming a paddle diameter of 240 mm;
  • the blade has an angle of attack of 24.74° at a distance of 35 mm from the center of the paddle formed by the propeller, and a chord length of 33.58 mm.
  • the blade has an angle of attack of 12.80° ⁇ 2.5° at a distance of 95.8% of the paddle radius from the center of the paddle formed by the propeller, and a chord length of 13.83 mm ⁇ 5 mm.
  • propeller as described above, the propeller forming a paddle diameter of 240 mm;
  • the blade has an angle of attack of 12.80° at a distance of 115 mm from the center of the paddle formed by the propeller, and a chord length of 13.83 mm.
  • the number of the blades is two, and the two blades are center-symmetrical with respect to the center of the paddle.
  • 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 blade comprising an upwardly facing leaf surface, a downwardly facing leaf back, and a first side edge connected between the leaf back and a side of the leaf surface, and a joint a second side edge between the leaf back and the other side of the leaf surface, the first side edge being located below the second side edge; the leaf back and the leaf surface are curved surfaces.
  • a propeller as described above comprising at least two blades, the propeller further comprising A paddle of the paddle is connected, the at least two blades being evenly distributed along the circumference of the paddle.
  • 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 close to an end of the blade connected to the paddle; and the first arching portion protrudes more than the second arching portion The degree of bulging.
  • the pitch of the propeller as described above is 5.5 inches.
  • Another aspect of the present invention also provides a power assembly including a drive member and a propeller according to any of the above, the propeller being coupled to the drive member by a paddle.
  • the driving member is a motor having a KV value of 750 to 850 rpm / (minute volt).
  • Yet another aspect of the present invention provides an aircraft comprising 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 the power components, and the steering of the plurality of power components is different.
  • the propeller, the power assembly and the aircraft provided by the present invention have an angle of attack of 22.59° ⁇ 2.5° at a distance of 45.8% of the paddle radius from the center of the paddle formed by the propeller, and the chord length is 26.98. Mm ⁇ 5 mm;
  • the blade has an angle of attack of 19.57 ° ⁇ 2.5 ° at a distance of 62.5% of the paddle radius from the center of the paddle formed by the propeller, and a chord length of 21.91 mm ⁇ 5 mm;
  • the angle of attack at the center of the paddle formed with the propeller is 79.2% of the paddle radius, which is 16.56° ⁇ 2.5°, and the chord length is 17.64 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 propeller according to a first embodiment of the present invention
  • Figure 2 is a front elevational view of the propeller of Figure 1;
  • Figure 3 is a left side view of the propeller of Figure 1;
  • Figure 4 is a schematic cross-sectional view of the propeller of Figure 2 taken along line A-A;
  • Figure 5 is a schematic cross-sectional view of the propeller of Figure 2 taken along line B-B;
  • Figure 6 is a schematic cross-sectional view of the propeller of Figure 2 taken along line C-C;
  • Figure 7 is a schematic cross-sectional view of the propeller of Figure 2 taken along line D-D;
  • Figure 8 is a schematic cross-sectional view of the propeller 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 in the middle. 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 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, such as a screw connection. Fixed, or connected through other connectors.
  • the embodiment is not specifically limited.
  • the propeller may be a positive propeller or a reverse propeller
  • the so-called positive propeller refers to a view from the perspective of the aircraft (or from the tail of the motor to the direction of the motor head), and rotates clockwise to generate lift.
  • the propeller; the so-called anti-paddle refers to the propeller that produces the lift counterclockwise from the perspective of the aircraft (referring to the direction of the motor head from the rear of the motor).
  • 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.
  • FIG. 1 is a perspective view of a blade in a propeller according to a first embodiment of the present invention
  • FIG. 2 is a front view of the blade of FIG. 1
  • FIG. 4 is a cross-sectional view of the blade of FIG. Schematic diagram of the middle blade along the BB line
  • Fig. 6 is a schematic cross-sectional view of the blade along line CC in Fig. 1
  • Fig. 7 is a schematic cross-sectional view of the blade along line DD in Fig. 1
  • Fig. 8 is the blade along the EE in Fig.
  • This embodiment improves the dimensions of the five sections of the blade, wherein the improvements in the dimensions of the B-B section, the C-C section and the D-D section are of the utmost importance.
  • the circle formed during the rotation is called a paddle
  • the center of the circle is called the center of the paddle
  • the diameter of the circle is called the paddle disk. diameter.
  • the radius of the paddle can be greater than the length of the blade 1 .
  • the number of the blades 1 may be two, or two or more. In the present embodiment, preferably, the number of the blades 1 is two, and the two blades 1 may be centrally symmetrical with respect to the center of the paddle, thereby Can improve the balance of the propeller.
  • the radius of the paddle is the radius of the propeller.
  • the paddle 1 is at a distance of 45.8% of the paddle radius from the center of the paddle formed by the propeller, that is, at a BB cross section from the center L2 of the paddle as shown in FIG.
  • the angle of attack A2 of the blade 1 is 22.59° ⁇ 2.5°
  • the chord length D2 is 26.98 mm ⁇ 5 mm.
  • the chord length is the length of the section of the blade 1 projected in the horizontal direction
  • the angle of attack is the angle between the chord and the direction in which the gas flows.
  • the blade 1 is at a distance of 62.5% 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 19.57° ⁇ 2.5°, and the chord length D3 is 21.91 mm ⁇ 5 mm.
  • the blade 1 is at a distance of 79.2% of the paddle radius at the center of the paddle formed with the propeller, 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 16.56 ° ⁇ 2.5 ° for A4 and 17.64 mm ⁇ 5 mm for the chord length D4.
  • the blade having the specific shape is defined by the above parameters, and the propeller having the blade has less resistance during the rotation.
  • the flight speed and flight efficiency of the aircraft are high, and the cruising distance is increased under certain power conditions to improve 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 29.2% 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. 2.
  • the angle of attack of the blade 1 is 24.74 ° ⁇ 2.5 °, and the chord length is 33.58 mm ⁇ 5 mm.
  • the blade 1 is at a distance of 95.8% of the paddle 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 12.80 ° ⁇ 2.5 °, and the chord length is 13.83 mm ⁇ 5 mm.
  • the present embodiment provides a specific propeller.
  • the diameter of the paddle formed by the propeller is 240 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 between the ends of 1 is 115 mm.
  • the blade 1 has an angle of attack of 55.59° at a distance of 55 mm from the center of the paddle formed by the propeller (ie, 50% of 115 mm), and a chord length of 26.98 mm; the blade 1 is in the propeller
  • the formed paddles have a center-to-center distance of 75 mm (ie, 66.7% of 115 mm) with an angle of attack of 19.57° and a chord length of 21.91 mm; the blade 1 is formed with the propeller
  • the center of the paddles is 95 mm apart (ie, 79.2% of 115 mm) with an angle of attack of 16.56° and a chord length of 17.64 mm.
  • the blade 1 has an angle of attack of 24.74° and a chord length of 33.58 mm.
  • the blade 1 has an angle of attack of 12.80 and a chord length of 13.83 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 paddle 6 may have a cylindrical shape, and a driving member may be installed at the center of the cylindrical paddle 6.
  • the blade 1 may be elongated, and the paddle 1 and the paddle 6 may be integrally formed or connected by a connecting member. And extending along the radial direction of the paddle.
  • the driving component may be a motor, and the rotating shaft of the motor is fixedly connected with the center of the paddle 6 for directly transmitting torque, the driving component can drive the paddle 6 to rotate, and the paddle 6 drives the blade 1 to rotate, thereby generating a thrust. Or lift.
  • the above-mentioned propeller provided by the present embodiment is tested by comparison with the propeller of the prior art.
  • the tensile force provided by the embodiment is greater at the same rotational speed, that is, at a smaller rotational speed. Underneath, it has a larger pulling force, which increases the power of the propeller, reduces the power loss, and increases the cruising distance.
  • the propeller provided by the embodiment can significantly increase the pulling force in the extreme case where the lifting density is high in the high-altitude region with reduced density or the low-altitude region, ensuring sufficient power while prolonging the endurance time and improving flight performance.
  • Figure 3 is a left side view of the blade of Figure 1; as shown in Figures 1 to 3, the blade of the propeller in this embodiment may include an upwardly facing leaf back 3, a downward facing leaf surface 2, and a connection a first side edge 4 between the leaf back 3 and one side of the leaf surface 2, and a second side edge 5 connected between the leaf back 3 and the other side of the leaf surface 2, the first side edge 4 is located at the Below the two side edges 5; the leaf back 3 and the leaf surface 2 are curved surfaces.
  • the leaf back 3 is the side of the blade 1 during the flight
  • the blade 2 is the side of the blade 1 when the aircraft is in flight.
  • the leaf back 3 and the leaf surface 2 are curved surfaces, and the tendency to bend is: when the blade 1 as a whole is in a horizontal state, the first side edge 4 is located at a position closer than the second side edge 5 The position is low, so the resistance of the air can be reduced and the pulling force of the blade 1 can be increased.
  • the first side edge 4 may include a curved outwardly convex first arching portion 401, whereby the pulling force of the blade 1 may be further increased, and the first arching portion 401 and the remaining portion of the first side edge 4 are smoothed Transitional connection.
  • the first arching portion 401 is closer to the end where the blade 1 is connected to the paddle 6 with respect to the longitudinal direction of the blade 1 with respect to the end of the blade 1 away from the paddle 6.
  • the first arch 401 not only arches towards one side of the blade 1 but also arches downwards, ie towards the direction in which the foliage 2 is situated, and can form a smooth transitional connection with the foliage 2 .
  • the second side edge 5 may include a curved, outwardly projecting second arch 501, whereby the pulling force of the blade 1 may be further increased, and the remaining portions of the second arching portion 501 and the second side edge 5 are Smooth transition connection.
  • the second arched portion 501 is closer to the end of the blade 1 connected to the paddle 6 with respect to the longitudinal direction of the blade 1 with respect to the end of the blade 1 away from the paddle 6.
  • the degree of protrusion of the first arching portion 401 may be greater than the degree of protrusion of the second arching portion 501.
  • the apex of the first arching portion 401 and the apex of the second arching portion 501 may be 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 process is called a paddle.
  • 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.
  • 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 750-850 rpm/(minute ⁇ 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 this embodiment is When the voltage is increased by 1 volt, the motor speed is increased by 750 to 850 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 power components in the aircraft may be one or more, and the aircraft of the embodiment includes a plurality of power components, and the steering of the plurality of power components is different.
  • 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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  • Aviation & Aerospace Engineering (AREA)
  • Physics & Mathematics (AREA)
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Abstract

L'invention concerne une hélice, un ensemble d'alimentation, et un aéronef. L'hélice comprend un siège d'hélice (6) et des pales d'hélice (1) reliées au siège d'hélice ; un angle d'incidence de la pale d'hélice (1) au niveau d'une position à 45,8 % du rayon du cercle balayé par l'hélice à partir du centre d'un cercle balayé par l'hélice (6) est égal à 22,59° ± 2,5°, et sa longueur de corde est égale à 26,98 mm ± 5 mm ; l'angle d'incidence de la pale d'hélice (1) au niveau d'une position à 62,5 % du rayon du cercle balayé par l'hélice à partir du centre du cercle balayé par l'hélice (6) est égal à 19,57° ± 2,5°, et sa longueur de corde est égale à 21,91 mm ± 5 mm ; l'angle d'incidence de la pale d'hélice (1) au niveau d'une position à 79,2 % du rayon du cercle balayé par l'hélice à partir du centre du cercle balayé par l'hélice (6) est égal à 16,56° ± 2,5°, et sa longueur de corde est égale à 17,64 mm ± 5 mm. Par rapport à l'hélice, à l'ensemble d'alimentation et à l'aéronef, l'optimisation de la structure de l'hélice permet de réduire la résistance à la rotation de l'hélice, ce qui permet de réduire davantage la résistance au vol de l'aéronef, d'améliorer la vitesse de vol et l'efficacité de vol de l'aéronef, et d'améliorer les caractéristiques de vol de l'aéronef.
PCT/CN2017/095865 2017-06-30 2017-08-03 Hélice, ensemble d'alimentation, et aéronef WO2019000560A1 (fr)

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CN201780069690.8A CN109923036A (zh) 2017-06-30 2017-08-03 螺旋桨、动力组件及飞行器

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CN201720792105.4U CN206954494U (zh) 2017-06-30 2017-06-30 螺旋桨、动力组件及飞行器
CN201720792105.4 2017-06-30

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CN208291465U (zh) * 2018-05-25 2018-12-28 深圳市大疆创新科技有限公司 螺旋桨、动力组件及飞行器
CN113022849B (zh) * 2021-05-28 2024-02-06 北京三快在线科技有限公司 螺旋桨及旋翼飞行器

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CN206954494U (zh) 2018-02-02

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