WO2017148134A1 - 螺旋桨、动力组件及飞行器 - Google Patents

螺旋桨、动力组件及飞行器 Download PDF

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Publication number
WO2017148134A1
WO2017148134A1 PCT/CN2016/099690 CN2016099690W WO2017148134A1 WO 2017148134 A1 WO2017148134 A1 WO 2017148134A1 CN 2016099690 W CN2016099690 W CN 2016099690W WO 2017148134 A1 WO2017148134 A1 WO 2017148134A1
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Prior art keywords
propeller
paddle
blade
center
attack
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Ceased
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PCT/CN2016/099690
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English (en)
French (fr)
Inventor
刘峰
邓涛
江彬
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SZ DJI Technology Co Ltd
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SZ DJI Technology Co Ltd
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Publication of WO2017148134A1 publication Critical patent/WO2017148134A1/zh
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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 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 at least 50% of the radius of the paddle with an angle of attack of 14.4° ⁇ 2.5° and a chord length of 16 mm ⁇ 5 mm;
  • the blade has an angle of attack of 12.8 ° ⁇ 2.5 ° at a distance of 66.7% of the paddle radius from the center of the paddle formed by the propeller, and a chord length of 13.7 mm ⁇ 5 mm;
  • the blade has an angle of attack of 12° ⁇ 2.5° at a distance of 83.3% of the paddle radius from the center of the paddle formed by the propeller, and a chord length of 11.3 mm ⁇ 5 mm.
  • propeller as described above, the propeller forming a paddle having a diameter of 180 mm;
  • the blade has an angle of attack of 14.4° at a distance of 45 mm from the center of the paddle formed by the propeller, and a chord length of 16 mm;
  • the blade has an angle of attack of 12.8° at a distance of 60 mm from the center of the paddle formed by the propeller, and a chord length of 13.7 mm;
  • the blade has an angle of attack of 12° at a distance of 75 mm from the center of the paddle formed by the propeller, and a chord length of 11.3 mm.
  • the blade has an angle of attack of 15.3 ° ⁇ 2.5 ° at a distance of 33.3% of the paddle radius from the center of the paddle formed by the propeller, and a chord length of 18.1 mm ⁇ 5 mm.
  • propeller as described above, the propeller forming a paddle having a diameter of 180 mm;
  • the blade has an angle of attack of 15.3° at a distance of 30 mm from the center of the paddle formed by the propeller, and a chord length of 18.1 mm.
  • the blade has an angle of attack of 11.4° ⁇ 2.5° at a distance of 100% of the paddle disk from the center of the paddle formed by the propeller, and a chord length of 9.2 mm ⁇ 5 mm.
  • propeller as described above, the propeller forming a paddle having a diameter of 180 mm;
  • the blade has an angle of attack of 11.4° at a distance of 90 mm from the center of the paddle formed by the propeller, and a chord length of 9 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.
  • the propeller as described above includes at least two blades, the propeller further including a paddle connecting the blades, 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 25 mm.
  • Another aspect of the present invention provides a power assembly including a drive member and the above a propeller that is coupled to the drive member by a paddle.
  • the driving member is a motor having a KV value of 1800 to 2400 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 component and the aircraft provided by the invention have an angle of attack of 14.4° ⁇ 2.5° and a chord length of 16 mm because the blade is at a distance of 50% of the blade radius from the center of the paddle formed by the propeller. ⁇ 5 mm; the blade has an angle of attack of 12.8 ° ⁇ 2.5 ° at a distance of 66.7% of the paddle radius from the center of the paddle formed by the propeller, and a chord length of 13.7 mm ⁇ 5 mm;
  • the center of the paddle formed by the propeller is at an angle of attack of 83.3% of the paddle radius of 12° ⁇ 2.5° and the chord length is 11.3 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 right side view of the propeller of Figure 1;
  • Figure 5 is a bottom plan view of the propeller of Figure 1;
  • Figure 6 is a plan view of the propeller shown in Figure 1;
  • Figure 7 is a schematic cross-sectional view of the propeller of Figure 2 taken along line A-A;
  • Figure 8 is a schematic cross-sectional view of the propeller of Figure 2 taken along line B-B;
  • Figure 9 is a schematic cross-sectional view of the propeller of Figure 2 taken along line C-C;
  • Figure 10 is a schematic cross-sectional view of the propeller of Figure 2 taken along line D-D;
  • Figure 11 is a 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 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 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 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 shown in FIG. 1
  • FIG. 7 is a cross-sectional view of the blade in FIG. Schematic diagram of the middle blade along the BB line
  • Fig. 9 is a schematic cross-sectional view of the blade along line CC in Fig. 1
  • Fig. 10 is a schematic cross-sectional view of the blade along line DD in Fig. 1
  • Fig. 11 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 blade 1 is at a distance of 50% of the blade radius at the center of the paddle formed with 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 14.4° ⁇ 2.5°
  • the chord length D2 is 16 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 66.7% 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 12.8 ° ⁇ 2.5 °, and the chord length D3 is 13.7 mm ⁇ 5 mm.
  • the paddle 1 is at a distance of 83.3% 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 12° ⁇ 2.5° for A4 and 11.3 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 blade 1 is at the center of the paddle formed from the propeller, which is a paddle half.
  • 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 11.4 ° ⁇ 2.5 °, and the chord length is 9.2 mm ⁇ 5 mm.
  • the embodiment provides a specific propeller.
  • the diameter of the paddle formed by the propeller is 180 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 90 mm.
  • the blade 1 is at an angle of 45 mm (i.e., 50% of 90 mm) at an angle of 45 mm from the center of the paddle formed by the propeller, and has a chord length of 16 mm; the blade 1 is formed with the propeller.
  • the center of the paddle is 60mm (ie, 66.7% of 90mm) with an angle of attack of 12.8° and a chord length of 13.7mm; the blade 1 is at a distance of 75mm from the center of the paddle formed by the propeller (ie 83.3 of 90mm) %) has an angle of attack of 12° and a chord length of 11.3 mm.
  • the blade 1 has an angle of attack of 15.3° and a chord length of 18.1 mm.
  • the blade 1 has an angle of attack of 11.4 and a chord length of 9.2 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 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, thus reducing the power loss and increasing Increase 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
  • Figure 4 is a right side view of the blade of Figure 1
  • Figure 5 is a bottom view of the blade of Figure 1
  • Figure 6 is a plan view of the blade of Figure 1.
  • the blade of the propeller in this embodiment may include an upwardly facing leaf back 3, a downwardly facing leaf surface 2, and a side connected to the leaf back 3 and the leaf surface 2 a first side edge 4 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 being located below the second side edge 5; the leaf back 3 and the leaf surface 2 Both are 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 second outwardly projecting second arch 501, thereby Further increasing the pulling force of the blade 1, the second arching portion 501 and the remaining portion of the second side edge 5 are in a smooth transitional 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 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.
  • 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 1800 to 2400 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 1800 to 2400 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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Abstract

本发明提供了一种螺旋桨、动力组件及飞行器，其中，螺旋桨包括桨座(6)和连接在桨座(6)上的桨叶(1)；桨叶(1)在与螺旋桨形成的桨盘的中心相距为桨盘半径的50％处的攻角为14.4°±2.5°，弦长为16mm±5mm；桨叶(1)在与螺旋桨形成的桨盘的中心相距为桨盘半径的66.7％处的攻角为12.8°±2.5°，弦长为13.7mm±5mm；桨叶(1)在与螺旋桨形成的桨盘的中心相距为桨盘半径的83.3％处的攻角为12°±2.5°，弦长为11.3mm±5mm。本发明提供的螺旋桨、动力组件及飞行器，通过优化螺旋桨的结构，可降低螺旋桨转动的阻力，以进一步减小飞行器的飞行阻力、提高飞行器的飞行速度和飞行效率，提高飞行器的飞行性能。

Description

螺旋桨、动力组件及飞行器 技术领域
本发明涉及螺旋桨结构技术，尤其涉及一种螺旋桨、动力组件及飞行器。
背景技术
飞行器上的螺旋桨，作为飞行器的重要关键器件，其用于将电机或发动机中转轴的转动转化为推力或升力。
现有技术中的螺旋桨，其桨叶外形形状大多呈矩形，导致其飞行时阻力大、效率低，导致飞行器的飞行速度小、续航距离短，严重影响了飞行器的飞行性能。
发明内容
本发明提供一种螺旋桨、动力组件及飞行器，用以解决现有技术中的上述缺陷，以优化螺旋桨的结构，提高飞行器的飞行性能。
本发明一方面提供一种螺旋桨，包括桨叶，所述桨叶旋转形成桨盘；
所述桨叶在与所述螺相距为桨盘半径的50％处的攻角为14.4°±2.5°，弦长为16mm±5mm；
所述桨叶在与所述螺旋桨形成的桨盘的中心相距为桨盘半径的66.7％处的攻角为12.8°±2.5°，弦长为13.7mm±5mm；
所述桨叶在与所述螺旋桨形成的桨盘的中心相距为桨盘半径的83.3％处的攻角为12°±2.5°，弦长为11.3mm±5mm。
如上所述的螺旋桨，所述螺旋桨形成的桨盘直径为180mm；
所述桨叶在与所述螺旋桨形成的桨盘的中心相距为45mm处的攻角为14.4°，弦长为16mm；
所述桨叶在与所述螺旋桨形成的桨盘的中心相距为60mm处的攻角为12.8°，弦长为13.7mm；
所述桨叶在与所述螺旋桨形成的桨盘的中心相距为75mm处的攻角为12°，弦长为11.3mm。
如上所述的螺旋桨，
所述桨叶在与所述螺旋桨形成的桨盘的中心相距为桨盘半径的33.3％处的攻角为15.3°±2.5°，弦长为18.1mm±5mm。
如上所述的螺旋桨，所述螺旋桨形成的桨盘直径为180mm；
所述桨叶在与所述螺旋桨形成的桨盘的中心相距为30mm处的攻角为15.3°，弦长为18.1mm。
如上所述的螺旋桨，
所述桨叶在与所述螺旋桨形成的桨盘的中心相距为桨盘半径的100％处的攻角为11.4°±2.5°，弦长为9.2mm±5mm。
如上所述的螺旋桨，所述螺旋桨形成的桨盘直径为180mm；
所述桨叶在与所述螺旋桨形成的桨盘的中心相距为90mm处的攻角为11.4°，弦长为9mm。
如上所述的螺旋桨，所述桨叶的数量为两个，两个桨叶关于桨盘的中心呈中心对称。
如上所述的螺旋桨，从所述桨叶靠近所述桨盘中心的一端至所述桨叶远离所述桨盘中心的一端，所述桨叶的厚度逐渐减小。
如上所述的螺旋桨，所述桨叶包括朝上的叶面、朝下的叶背，以及连接于所述叶背及所述叶面的一侧之间的第一侧缘、以及连接于所述叶背及所述叶面的另一侧之间的第二侧缘，所述第一侧缘位于所述第二侧缘下方；所述叶背以及所述叶面均为曲面。
如上所述的螺旋桨，包括至少两个桨叶，所述螺旋桨还包括连接所述桨叶的桨座，所述至少两个桨叶沿所述桨座周向均匀分布。
如上所述的螺旋桨，所述第一侧缘包括一个曲面状的向外凸出的第一拱起部，所述第二侧缘包括一个曲面状的向外凸出的第二拱起部；所述第一拱起部及所述第二拱起部均靠近所述桨叶与所述桨座相连的一端；且所述第一拱起部的凸出程度大于所述第二拱起部的凸出程度。
如上所述的螺旋桨的螺距为25mm。
本发明另一方面还提供一种动力组件，包括驱动件和如上任一项所述的 螺旋桨，所述螺旋桨通过桨座与所述驱动件连接。
如上所述的动力组件，所述驱动件为电机，所述电机的KV值为1800～2400转/(分钟·伏特)。
本发明又一方面提供一种飞行器，包括机身，还包括至少一个如上所述的动力组件，所述动力组件与所述机身连接。
所述飞行器包括多个所述动力组件，且所述多个动力组件的转向不同。
本发明提供的螺旋桨、动力组件及飞行器，由于所述桨叶在与所述螺旋桨形成的桨盘的中心相距为桨盘半径的50％处的攻角为14.4°±2.5°，弦长为16mm±5mm；所述桨叶在与所述螺旋桨形成的桨盘的中心相距为桨盘半径的66.7％处的攻角为12.8°±2.5°，弦长为13.7mm±5mm；所述桨叶在与所述螺旋桨形成的桨盘的中心相距为桨盘半径的83.3％处的攻角为12°±2.5°，弦长为11.3mm±5mm。因此能够降低螺旋桨在转动过程中的阻力，减小飞行器飞行过程中的飞行阻力，提高飞行效率，增加续航距离，提高飞行器的飞行性能。
附图说明
图1为本发明实施例一提供的螺旋桨的立体图；
图2为图1所示螺旋桨的主视图；
图3为图1所示螺旋桨的左视图；
图4为图1所示螺旋桨的右视图；
图5为图1所示螺旋桨的仰视图；
图6为图1所示螺旋桨的俯视图；
图7为图2中螺旋桨沿A-A线的剖面示意图；
图8为图2中螺旋桨沿B-B线的剖面示意图；
图9为图2中螺旋桨沿C-C线的剖面示意图；
图10为图2中螺旋桨沿D-D线的剖面示意图；
图11为图2中螺旋桨沿E-E线的剖面示意图。
附图标记：
1-桨叶；      2-叶面；      3-叶背
4-第一侧缘；  5-第二侧缘；  6-桨座；
401-第一拱起部；  501-第二拱起部。
具体实施方式
为使本发明实施例的目的、技术方案和优点更加清楚，下面将结合本发明实施例中的附图，对本发明实施例中的技术方案进行清楚、完整地描述，显然，所描述的实施例是本发明一部分实施例，而不是全部的实施例。基于本发明中的实施例，本领域普通技术人员在没有作出创造性劳动前提下所获得的所有其他实施例，都属于本发明保护的范围。
需要说明的是，当组件被称为“固定于”另一个组件，它可以直接在另一个组件上或者也可以存在居中的组件。当一个组件被认为是“连接”另一个组件，它可以是直接连接到另一个组件或者可能同时存在居中组件。
除非另有定义，本文所使用的所有的技术和科学术语与属于本发明的技术领域的技术人员通常理解的含义相同。本文中在本发明的说明书中所使用的术语只是为了描述具体的实施例的目的，不是旨在于限制本发明。本文所使用的术语“及/或”包括一个或多个相关的所列项目的任意的和所有的组合。
实施例一
本发明实施例一提供一种螺旋桨。本实施例中的螺旋桨，可以应用于飞行器，螺旋桨可以包括：桨座和连接在桨座上的桨叶。本实施例提供的螺旋桨中，桨叶与桨座可以为一体成型结构，或者也可以通过其它方式实现相互连接，例如可通过焊接的形式固定，又或者可以通过可拆卸的连接件固定连接，例如螺接固定，或通过其它连接件实现连接等。在此，本实施例不作具体限定。
在本实施例中，螺旋桨可以是正桨或反桨，所谓正桨，指的是从俯视飞行器的角度看(或者，从驱动件如电机尾部向电机头部方向看)，顺时针旋转而产生升力的螺旋桨；所谓反桨，指的是从俯视飞行器的角度看(指从电机尾部向电机头部方向看)，逆时针旋转而产生升力的螺旋桨。正桨的结构与反桨的结构之间为镜面对称，本实施例中仅以正桨的结构为例对螺旋桨的结构进行说明，本领域技术人员可以根据本实施例所提供的方式进行扩展而得到反桨的结构。
图1为本发明实施例一提供的螺旋桨中桨叶的立体图；图2为图1所示桨叶的主视图；图7为图1中桨叶沿A-A线的剖面示意图；图8为图1中桨叶沿B-B线的剖面示意图；图9为图1中桨叶沿C-C线的剖面示意图；图10为图1中桨叶沿D-D线的剖面示意图；图11为图1中桨叶沿E-E线的剖面示意图。本实施例对桨叶的五个截面处的尺寸进行改进，其中，对B-B截面、C-C截面和D-D截面处的尺寸所进行的改进最为重要。
本实施例所提供的螺旋桨的桨座带动桨叶旋转时，在旋转过程中所形成的圆，称为桨盘，该圆的中心称为桨盘的中心，该圆的直径称为桨盘的直径。对于分体式的桨叶1而言，桨盘的半径可以大于桨叶1的长度。桨叶1的数量可以为两个，或者两个以上，在本实施例中，优选的，桨叶1的数量为两个，两个桨叶1关于桨盘的中心可以呈中心对称，由此，可提高螺旋桨的平衡性。对于一体式的螺旋桨，桨盘的半径即为螺旋桨的半径。
如图2和图8所示，桨叶1在与螺旋桨形成的桨盘的中心相距为桨盘半径的50％处，即：如图2所示的距离桨盘中心L2的B-B截面处，该处桨叶1的攻角A2为14.4°±2.5°，弦长D2为16mm±5mm。其中，弦长为桨叶1在该处的截面在水平方向上投影的长度，攻角为弦翼与气体来流方向的夹角。
如图2和图9所示，桨叶1在与螺旋桨形成的桨盘的中心相距为桨盘半径的66.7％处，即：如图2所示的距离桨盘中心L3的C-C截面处，该处桨叶1的攻角A3为12.8°±2.5°，弦长D3为13.7mm±5mm。
如图2和图10所示，桨叶1在与螺旋桨形成的桨盘的中心相距为桨盘半径的83.3％处，即：如图2所示的距离桨盘中心L4的D-D截面处，该处桨叶1的攻角为A4为12°±2.5°，弦长D4为11.3mm±5mm。
本实施例通过对桨叶1中上述三个截面的弦长和攻角的设定，由上述参数限定出具备特定形状的桨叶，具备该种桨叶的螺旋桨在转动过程中的阻力较小，飞行器的飞行速度和飞行效率高，并且在一定的电力条件供给下增加续航距离，提高飞行器的飞行性能。
在上述技术方案的基础上，还可以对桨叶1中A-A截面和E-E截面的攻角和弦长进行优化，以进一步降低螺旋桨在转动过程中的空气阻力。
如图2和图7所示，桨叶1在与螺旋桨形成的桨盘的中心相距为桨盘半 径的33.3％处，即：如图2所示的距离桨盘中心L1的A-A截面处，该处桨叶1的攻角为15.3°±2.5°，弦长为18.1mm±5mm。
如图2和图11所示，桨叶1在与螺旋桨形成的桨盘的中心相距为桨盘半径的100％处，即：如图2所示的距离桨盘中心L5的E-E截面处，该处桨叶1的攻角为11.4°±2.5°，弦长为9.2mm±5mm。
当然，本领域技术人员可以理解的是，上述A-A截面、B-B截面、C-C截面、D-D截面和E-E截面的位置可略微变动。
对于上述技术方案，本实施例提供一种具体的螺旋桨，该螺旋桨所形成的桨盘直径为180mm，桨盘中心到桨叶1末端的距离为桨盘直径的一半，即桨盘中心到桨叶1末端的距离为90mm。
以桨盘直径180mm为例，桨叶1在与螺旋桨形成的桨盘的中心相距为45mm处(即90mm的50％)的攻角为14.4°，弦长为16mm；桨叶1在与螺旋桨形成的桨盘的中心相距为60mm处(即90mm的66.7％)的攻角为12.8°，弦长为13.7mm；桨叶1在与螺旋桨形成的桨盘的中心相距为75mm处(即90mm的83.3％)的攻角为12°，弦长为11.3mm。
进一步的，在与桨盘中心距离30mm(即90mm的33.3％)处，桨叶1的攻角为15.3°，弦长为18.1mm。在与桨盘中心距离90mm(即90mm的100％)处，桨叶1的攻角为11.4°，弦长为9.2mm。
可以理解的是，因A-A截面、B-B截面、C-C截面、D-D截面和E-E截面的位置可略微变动，故相应地，在A-A截面、B-B截面、C-C截面、D-D截面和E-E截面处所得的攻角和弦长值可相应改变。
上述各截面的弦长和攻角的设定均可以桨盘的尺寸来进行设定。桨座6可以呈圆筒状，并且，在圆筒状的桨座6中心可以安装驱动件，桨叶1可以呈长条状，桨叶1与桨座6可以一体成型或者通过连接件连接，并沿桨座的径向延伸。具体的，驱动件可以为电机，电机的转轴与桨座6的中心固定连接，用以直接传递扭矩，驱动件可以带动桨座6转动，而桨座6则带动桨叶1转动，进而产生推力或升力。
本实施例所提供的上述螺旋桨，通过与现有技术中的螺旋桨进行对比测试，参照表一可知，在相同的拉力下，本实施例所提供的螺旋桨的功率更低，也即：在较小的功率条件下，具有更大的拉力，从而降低电量损耗，增 加续航距离。特别的，本实施例提供的螺旋桨在密度降低的高海拔区域或者低海拔地区起飞重量较大的极端情况下，其可以显著提高拉力，保证足够动力同时延长续航时间，提高飞行性能。
表一  本实施例所提供的螺旋桨与现有技术的对比参数
Figure PCTCN2016099690-appb-000001
图3为图1所示桨叶的左视图；图4为图1所示桨叶的右视图；图5为图1所示桨叶的仰视图；图6为图1所示桨叶的俯视图。如图1至图6所示，本实施例中的螺旋桨的桨叶，可以包括朝上的叶背3、朝下的叶面2，以及连接于叶背3及叶面2的一侧之间的第一侧缘4、以及连接于叶背3及叶面2的另一侧之间的第二侧缘5，第一侧缘4位于第二侧缘5下方；叶背3以及叶面2均为曲面。
其中，叶背3为飞行器在飞行过程中，桨叶1朝上的一面；叶面2为飞行器在飞行过程中，桨叶1朝下的一面。如图5所示，叶背3和叶面2均为曲面，且弯曲的趋势为：当桨叶1整体处于水平状态时，第一侧缘4所处的位置比第二侧缘5所处的位置低，因此可减小空气的阻力，提高桨叶1的拉力。
第一侧缘4可以包括曲面状的向外凸出的第一拱起部401，由此可进一步提高桨叶1的拉力，第一拱起部401与第一侧缘4的其余部分为平滑过渡连接。在整个桨叶1的长度方向上，相对于桨叶1远离桨座6的一端，第一拱起部401更靠近桨叶1与桨座6相连的一端。第一拱起部401不仅朝桨叶1的一侧拱起，同时还可以向下拱起，即朝向叶面2所在的方向拱起，并且可与叶面2形成平滑过渡连接。
第二侧缘5可以包括一个曲面状的向外凸出的第二拱起部501，由此可 进一步提高桨叶1的拉力，第二拱起部501与第二侧缘5的其余部分为平滑过渡连接。在整个桨叶1的长度方向上，相对于桨叶1远离桨座6的一端，第二拱起部501更靠近桨叶1与桨座6相连的一端。
在本实施例中，第一拱起部401的凸出程度可以大于第二拱起部501的凸出程度。第一拱起部401的顶点与第二拱起部501的顶点可以大致位于桨叶1的同一个横截面上。并且，桨叶1的表面各个位置处均为平滑过渡，无急剧扭转之处，因此具有较小的应力，且强度较高不易折断，整个螺旋桨具有较高的可靠性。
本实施例所提供的螺旋桨在旋转过程中所形成的圆，称为桨盘，该圆的中心称为桨盘的中心，该圆的直径称为桨盘的直径。对于分体式的桨叶1而言，桨盘的半径可以大于桨叶1的长度。
从桨叶1靠近桨盘中心的一端至桨叶1远离桨盘中心的一端，桨叶1的厚度可以逐渐减小。由此，桨叶1中离桨盘中心最远处的端部为桨叶1中最薄的部分，因而有利于降低飞行时的空气阻力，提高飞行效率。
实施例二
本发明实施例二提供一种动力组件，包括驱动件和上述实施例所述的螺旋桨，所述螺旋桨通过桨座与所述驱动件连接。
桨座与驱动件连接后，驱动件可以带动桨座转动，进而桨座带动桨叶转动。而桨叶的数量可以根据实际需要来设置。其中，驱动件具体可以为电机，电机的KV值为1800～2400转/(分钟·伏特)，其中，KV值用于衡量电机转速对电压增加的敏感度，本实施例中的电机的电压每增加1伏，电机每分钟转速就提高1800～2400转。
本实施例提供的动力组件，通过对桨叶中的三个截面弦长和攻角的设定，能够降低螺旋桨在转动过程中的阻力，提高飞行器的飞行速度，在一定的电力条件供给下延长航行距离，提高飞行性能。
实施例三
本发明实施例三提供一种飞行器。本实施例中的飞行器，可以包括机身以及至少一个如上述实施例二所述的动力组件，所述动力组件与所述机身连接。飞行器中动力组件的个数可以为一个，也可以为多个，本实施例的飞行器包括多个动力组件，且所述多个动力组件的转向不同。
本实施例提供的飞行器，采用了上述动力组件，通过对桨叶中的至少三个截面弦长和攻角的设定，能够降低螺旋桨在转动过程中的阻力，提高飞行器的飞行速度，在一定的电力条件供给下延长航行距离，提高飞行性能。
最后应说明的是：以上实施例仅用以说明本发明的技术方案，而非对其限制；尽管参照前述实施例对本发明进行了详细的说明，本领域的普通技术人员应当理解：其依然可以对前述各实施例所记载的技术方案进行修改，或者对其中部分技术特征进行等同替换；而这些修改或者替换，并不使相应技术方案的本质脱离本发明各实施例技术方案的精神和范围。

Claims (16)

  1. 一种螺旋桨，包括桨叶，其特征在于，所述桨叶旋转形成桨盘；
    所述桨叶在与所述螺旋桨形成的桨盘的中心相距为桨盘半径的50％处的攻角为14.4°±2.5°，弦长为16mm±5mm；
    所述桨叶在与所述螺旋桨形成的桨盘的中心相距为桨盘半径的66.7％处的攻角为12.8°±2.5°，弦长为13.7mm±5mm；
    所述桨叶在与所述螺旋桨形成的桨盘的中心相距为桨盘半径的83.3％处的攻角为12°±2.5°，弦长为11.3mm±5mm。
  2. 根据权利要求1所述的螺旋桨，其特征在于，所述螺旋桨形成的桨盘直径为180mm；
    所述桨叶在与所述螺旋桨形成的桨盘的中心相距为45mm处的攻角为14.4°，弦长为16mm；
    所述桨叶在与所述螺旋桨形成的桨盘的中心相距为60mm处的攻角为12.8°，弦长为13.7mm；
    所述桨叶在与所述螺旋桨形成的桨盘的中心相距为75mm处的攻角为12°，弦长为11.3mm。
  3. 根据权利要求1所述的螺旋桨，其特征在于，
    所述桨叶在与所述螺旋桨形成的桨盘的中心相距为桨盘半径的33.3％处的攻角为15.3°±2.5°，弦长为18.1mm±5mm。
  4. 根据权利要求3所述的螺旋桨，其特征在于，所述螺旋桨形成的桨盘直径为180mm；
    所述桨叶在与所述螺旋桨形成的桨盘的中心相距为30mm处的攻角为15.3°，弦长为18.1mm。
  5. 根据权利要求1所述的螺旋桨，其特征在于，
    所述桨叶在与所述螺旋桨形成的桨盘的中心相距为桨盘半径的100％处的攻角为11.4°±2.5°，弦长为9.2mm±5mm。
  6. 根据权利要求5所述的螺旋桨，其特征在于，所述螺旋桨形成的桨盘直径为180mm；
    所述桨叶在与所述螺旋桨形成的桨盘的中心相距为90mm处的攻角为11.4°，弦长为9mm。
  7. 根据权利要求1所述的螺旋桨，其特征在于，所述桨叶的数量为两个，两个桨叶关于桨盘的中心呈中心对称。
  8. 根据权利要求1所述的螺旋桨，其特征在于，从所述桨叶靠近所述桨盘中心的一端至所述桨叶远离所述桨盘中心的一端，所述桨叶的厚度逐渐减小。
  9. 根据权利要求1～8任一项所述的螺旋桨，其特征在于，所述桨叶包括朝上的叶面、朝下的叶背，以及连接于所述叶背及所述叶面的一侧之间的第一侧缘、以及连接于所述叶背及所述叶面的另一侧之间的第二侧缘，所述第一侧缘位于所述第二侧缘下方；所述叶背以及所述叶面均为曲面。
  10. 根据权利要求9所述的螺旋桨，其特征在于，所述螺旋桨包括至少两个桨叶，所述螺旋桨还包括连接所述桨叶的桨座，所述至少两个桨叶沿所述桨座周向均匀分布。
  11. 根据权利要求10所述的螺旋桨，其特征在于，所述第一侧缘包括一个曲面状的向外凸出的第一拱起部，所述第二侧缘包括一个曲面状的向外凸出的第二拱起部；所述第一拱起部及所述第二拱起部均靠近所述桨叶与所述桨座相连的一端；且所述第一拱起部的凸出程度大于所述第二拱起部的凸出程度。
  12. 根据权利要求1～8任一项所述的螺旋桨，其特征在于，所述螺旋桨的螺距为25mm。
  13. 一种动力组件，其特征在于，包括驱动件和如权利要求1～11任一项所述的螺旋桨，所述螺旋桨通过桨座与所述驱动件连接。
  14. 根据权利要求13所述的动力组件，其特征在于，所述驱动件为电机，所述电机的KV值为1800～2400转/(分钟·伏特)。
  15. 一种飞行器，包括机身，其特征在于，还包括至少一个如权利要求13或14所述的动力组件，所述动力组件与所述机身连接。
  16. 根据权利要求15所述的飞行器，其特征在于，所述飞行器包括多个所述动力组件，且所述多个动力组件的转向不同。
PCT/CN2016/099690 2016-02-29 2016-09-22 螺旋桨、动力组件及飞行器 Ceased WO2017148134A1 (zh)

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