WO2018076457A1 - Hélice, série d'alimentation et aéronef sans pilote - Google Patents

Hélice, série d'alimentation et aéronef sans pilote Download PDF

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Publication number
WO2018076457A1
WO2018076457A1 PCT/CN2016/108287 CN2016108287W WO2018076457A1 WO 2018076457 A1 WO2018076457 A1 WO 2018076457A1 CN 2016108287 W CN2016108287 W CN 2016108287W WO 2018076457 A1 WO2018076457 A1 WO 2018076457A1
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WO
WIPO (PCT)
Prior art keywords
propeller
blade
center
degrees
distance
Prior art date
Application number
PCT/CN2016/108287
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English (en)
Chinese (zh)
Inventor
刘峰
邓涛
江彬
Original Assignee
深圳市大疆创新科技有限公司
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
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Priority to CN201680085525.7A priority Critical patent/CN109071004A/zh
Publication of WO2018076457A1 publication Critical patent/WO2018076457A1/fr

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    • 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
    • B64C27/48—Root attachment to rotor head

Definitions

  • the present invention relates to a propeller, a power kit having the propeller, and an aircraft having the power kit.
  • the propeller on the unmanned aerial vehicle is a key component of the unmanned aerial vehicle, and the propeller is used to convert the rotation of the motor or the engine intermediate shaft of the UAV into a propulsive force to provide flight power to the unmanned aerial vehicle.
  • the prior art propellers have low working efficiency due to the contour and structure constraints, and cannot meet the expected driving force requirements at work.
  • a propeller comprising a blade on a pitch of 50% of a radius of revolution of the propeller on the blade, the blade having an angle of attack of 13.68 ⁇ 2.5 degrees;
  • the distance from the center of rotation of the propeller on the blade is 65.79% of the radius of gyration of the propeller, the angle of attack of the blade is 11.11 ⁇ 2.5 degrees; the blade is spaced from the propeller
  • the distance from the center of revolution is 81.58% of the radius of gyration of the propeller, and the angle of attack of the blade is 8.98 ⁇ 2.5 degrees.
  • the distance from the center of rotation of the propeller on the blade is 18.42% of the radius of gyration of the propeller, and the angle of attack of the blade is 20.11 ⁇ 2.5 degrees;
  • the distance from the center of rotation of the propeller on the blade is 97.37% of the radius of gyration of the propeller, and the angle of attack of the blade is 7.57 ⁇ 2.5 degrees.
  • the rotary diameter of the propeller is 380 mm, and the angle of attack of the blade is 20.11 ⁇ 2.5 degrees at a distance of 35 mm from the center of rotation of the propeller;
  • the angle of attack of the blade is 13.68 ⁇ 2.5 degrees;
  • the blade has an angle of attack of 7.57 ⁇ 2.5 degrees.
  • the distance from the center of rotation of the propeller on the blade is 50% of the radius of gyration of the propeller, and the chord length of the blade is 28.28 ⁇ 5 mm;
  • the distance from the center of rotation of the propeller on the blade is 81.58% of the radius of gyration of the propeller, and the chord length of the blade is 19.32 ⁇ 5 mm.
  • the distance from the center of rotation of the propeller on the blade is 18.42% of the radius of gyration of the propeller, and the chord length of the blade is 33.59 ⁇ 5 mm;
  • the distance from the center of rotation of the propeller on the blade is 34.21% of the radius of gyration of the propeller, the chord length of the blade is 33.97 ⁇ 5 mm;
  • the distance from the center of rotation of the propeller on the blade is 81.58% of the radius of gyration of the propeller, and the chord length of the blade is 19.32 ⁇ 5 mm.
  • the diameter of the rotation of the propeller is 380 ⁇ 30 mm.
  • the paddle includes a leaf surface and a leaf back disposed away from each other, and a first side edge connecting one side of the leaf back and the leaf surface, and another connecting the leaf back and the leaf surface The second side edge of one side.
  • cross-sectional profile of the leaf surface and the cross-sectional profile of the blade back are both curved structures.
  • first side edge comprises a curved outwardly convex first arching portion; the second side edge comprises a curved outwardly projecting second arching portion.
  • the propeller includes a paddle, and the paddle is fixedly connected to the blade,
  • the paddle is integrally formed with the paddle.
  • the number of the blades is at least two.
  • the propeller has a geometric pitch of 5 ⁇ 0.5 inches.
  • a power kit for an unmanned aerial vehicle including at least one propeller as described above and a drive member that drives the propeller to rotate.
  • the driving member is a motor
  • the propeller is connected to the motor
  • the motor has a KV value of 460 rpm / (minute volt).
  • An unmanned aerial vehicle comprising a fuselage, a plurality of arms, and a plurality of power sets as described above, the plurality of arms being coupled to the body, the plurality of power sets being respectively mounted on the plurality of On the arm.
  • the propeller provided by the invention reduces the air resistance, improves the efficiency, and has a relatively large driving force through the design of the angle of attack on different parts of the blade.
  • FIG. 1 is a schematic structural view of a propeller according to an embodiment of the present invention.
  • Figure 2 is a plan view of the propeller of Figure 1.
  • Figure 3 is a side view of the propeller of Figure 1.
  • Figure 4 is a front elevational view of the propeller of Figure 2;
  • Figure 5 is a front elevational view of the propeller of Figure 2.
  • Fig. 6 is a cross-sectional view showing the A-A cross section of the propeller of Fig. 5;
  • Fig. 7 is a cross-sectional view showing the B-B section of the propeller of Fig. 5;
  • Figure 8 is a cross-sectional view of the C-C section of the propeller of Figure 5 .
  • Fig. 9 is a cross-sectional view showing the D-D section of the propeller of Fig. 5.
  • Fig. 10 is a cross-sectional view showing the E-E cross section of the propeller of Fig. 5;
  • Figure 11 is a cross-sectional view of the F-F section of the propeller of Figure 5 .
  • 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.
  • a component When a component is considered to "connect” another component, it can be directly connected to another component or possibly a central component.
  • a component When a component is considered to be “set to” another component, it can be placed directly on another component or possibly with a centered component.
  • Embodiments of the present invention provide a propeller that includes a paddle.
  • the distance from the center of rotation of the propeller on the blade is 50% of the radius of gyration of the propeller, the angle of attack of the blade is 13.68 ⁇ 2.5 degrees; the propeller is spaced from the propeller
  • the distance of the center of rotation is 65.79% of the radius of gyration of the propeller, the angle of attack of the blade is 11.11 ⁇ 2.5 degrees; the distance from the center of rotation of the propeller on the blade is the propeller At 81.58% of the radius of gyration, the angle of attack of the blade is 8.98 ⁇ 2.5 degrees.
  • the embodiment of the present invention further provides a power package of an unmanned aerial vehicle, the power package includes a propeller and a motor, the propeller is connected to the motor, and the motor is used to drive the propeller to rotate, the KV of the motor
  • the value is 460 rpm / (minute volts).
  • the propeller includes a blade on which the distance from the center of rotation of the propeller is 50% of the radius of gyration of the propeller, and the angle of attack of the blade is 13.68 ⁇ 2.5 degrees;
  • the distance from the center of rotation of the propeller on the blade is 65.79% of the radius of gyration of the propeller, the angle of attack of the blade is 11.11 ⁇ 2.5 degrees;
  • the center of rotation of the propeller is on the blade
  • the distance is 81.58% of the radius of gyration of the propeller, and the angle of attack of the blade is 8.98 ⁇ 2.5 degrees.
  • the propeller can provide a large driving force.
  • An embodiment of the present invention further provides an unmanned aerial vehicle including a fuselage, a plurality of arms, and a plurality of power sets, wherein the plurality of arms are connected to the body, and the plurality of power sets are respectively installed in the On multiple arms. It can be understood that at least one power package is installed on each arm.
  • the power pack includes a propeller and a motor.
  • the propeller is coupled to the motor for driving the propeller to rotate, the motor having a KV value of 460 rpm / (minute volts).
  • the propeller includes a blade on which the distance from the center of rotation of the propeller is 50% of the radius of gyration of the propeller, and the angle of attack of the blade is 13.68 ⁇ 2.5 degrees;
  • the distance from the center of rotation of the propeller on the blade is 65.79% of the radius of gyration of the propeller, the angle of attack of the blade is 11.11 ⁇ 2.5 degrees;
  • the center of rotation of the propeller is on the blade
  • the distance of the snail At 81.58% of the radius of gyration of the propeller, the angle of attack of the blade is 8.98 ⁇ 2.5 degrees.
  • An unmanned aerial vehicle includes a fuselage, an arm, a propeller, and a driving member for driving the rotation of the propeller, and the arm is coupled to the fuselage.
  • the propeller may be a folding paddle.
  • the number of the propellers may be selected according to actual needs, and may be one, two or more.
  • the driving component is a motor, and the KV value of the motor is 460 rpm / (minute ⁇ volt); it can be understood that in other embodiments, the KV value of the motor can be selected according to actual flight requirements.
  • the drive member may be in other forms such as an engine or the like.
  • the propeller may be a positive paddle or a reverse paddle.
  • the so-called positive paddle refers to a propeller that rotates counterclockwise to generate lift from the tail of the driving part such as the motor to the direction of the motor head; the so-called reverse paddle refers to the clockwise rotation from the tail of the motor to the direction of the motor head to generate lift.
  • the structure of the positive paddle is mirror symmetrical with the structure of the reverse paddle, so the structure of the propeller is only exemplified by a positive paddle.
  • the propeller 100 includes a paddle 101 and two blades 200 respectively disposed on two sides of the paddle 101 .
  • the two blades 200 are centrally symmetrical about the center of the paddle 101.
  • the paddle 101 and the blade 200 of the propeller 100 are integrally formed.
  • the two blades 200 are rotated to form a paddle.
  • the center of the paddle 101 substantially coincides with the center of the paddle.
  • the propeller 100 includes a paddle and two blades that are fixedly coupled to the paddle.
  • the propeller 100 can also be a foldable paddle, and the paddle 200 is rotatably coupled to the paddle.
  • the blade 200 is detachably mounted on the paddle 101 by a connecting member, and is not limited to the present invention.
  • the number of blades 200 in each of the propellers 100 may be other numbers, such as three, four, etc., depending on actual needs.
  • the number of the blades 200 is three, and the three blades 200 are evenly spaced in the circumferential direction with respect to the center of the paddle 101.
  • the paddle has a diameter of 380 ⁇ 30 mm.
  • the diameter of the paddle may be 350 mm, 360 mm, 370 mm, 380 mm, 390 mm, 400 mm, 410 mm, or the diameter of the paddle may be defined by any two of the above values. Any value within the range of values.
  • the paddle has a diameter of 380 mm.
  • the "center of the paddle” and the “paddle center” mentioned above and below should be understood as “propeller” "Slewing center”, similarly, “diameter of paddle” and “paddle diameter” mentioned above and below should be understood as “slewing diameter of propeller”, “radius of paddle” and “basin radius” “It should be understood as “the radius of gyration of the propeller”.
  • the paddle 101 can be used to connect with a rotating shaft of a driving member (not shown) of the UAV to enable the driving member 400 to drive the propeller 100 to rotate.
  • a reinforcing spacer may be embedded in the paddle 101, and the reinforcing sheet may be made of a lightweight high-strength material such as aluminum alloy to increase the strength of the propeller 100.
  • the paddle 101 is substantially cylindrical. Two of the blades 200 are disposed in a central symmetry on both sides of the paddle, and a connection between each of the blades 200 and the paddle is threadedly connected.
  • the geometric pitch of the propeller 100 is 5 ⁇ 0.5 inches, and the geometric pitch is the distance that the blade advances one revolution when the blade angle of attack is zero.
  • the geometric pitch of the propeller 100 can be 4.5 inches, 4.6 inches, 4.7 inches, 4.8 inches, 4.9 inches, 5.0 inches, 5.1 inches, 5.2 inches, 5.3 inches, 5.4 inches, 5.5 inches, or the geometry
  • the pitch can be any value within the range of values defined by any two of the above values.
  • the geometric pitch is 5 inches.
  • the blade 200 includes a blade face 10 and a blade back 20 disposed away from each other, and a first side edge 30 connecting the blade back 20 and a side of the blade face 10, connecting the blade back 20 and the The second side edge 40 of the other side of the foliage 10.
  • the cross-sectional profile of the foliage 10 and the cross-sectional profile of the blade back 20 are both curved (see Figures 7-11).
  • the leaf surface 10 faces the drive member, that is, the leaf surface 10 is disposed downward; and the blade back 20 faces away from the The drive member, that is, the leaf back 20 is disposed upward.
  • the leaf surface 10 and the leaf back 20 are curved surfaces.
  • the first side edge 30 includes a curved, outwardly projecting first arched portion 31.
  • the first arching portion 31 is smoothly transitionally connected to other portions of the first side edge 30.
  • the first arching portion 31 is disposed adjacent to the paddle 101.
  • the second side edge 40 includes a curved, outwardly projecting second bulge 41 that is smoothly transitionally connected to other portions of the second side edge 40.
  • the second arching portion 41 is disposed adjacent to the paddle 101.
  • the blade 200 has no sharp torsion, the stress is small, the structural strength is high, the fracture is not easy, and the reliability is high.
  • One end of the blade 200 away from the paddle is the thinnest portion of the paddle 200, which is advantageous for reducing air resistance. That is, the thickness of one end of the blade 200 away from the center of the paddle is less than the thickness of other portions of the paddle 200.
  • the angle of attack referred to herein refers to the angle between the chord of the blade 200 and the velocity of the incoming flow.
  • the distance from the center O of the paddle on the paddle 200 is 18.42% of the paddle radius, and the angle of attack ⁇ 1 of the paddle 200 is 20.11 ⁇ 2.5. degree.
  • the angle of attack ⁇ 1 of the blade 200 herein may be 17.61 degrees, 18.61 degrees, 19.11 degrees, 20.11 degrees, 21.11 degrees, 21.61 degrees, 22.61 degrees, or the angle of attack ⁇ 1 of the blade 200 herein. Any value within the numerical range defined by any two of the above numerical values may be used. In the present embodiment, the angle of attack ⁇ 1 is 20.11 degrees.
  • chord length L1 of the paddle 200 is 33.59 ⁇ 5 mm.
  • the chord length L1 of the blade 200 may be 28.596 mm, 30.59 mm, 32.59 mm, 33.59 mm, 35.59 mm, 37.59 mm, 38.59 mm, or the chord length L1 of the blade 200 may be any of the above.
  • the numerical value within the range of values defined by the two values, in the present embodiment, the chord length L1 is 33.59 mm.
  • the distance from the center O of the paddle on the blade 200 is 34.21% of the paddle radius, and the angle of attack ⁇ 2 of the blade 200 is 17.57 ⁇ 2.5. degree.
  • the angle of attack ⁇ 2 of the blade 200 herein may be 15.07 degrees, 16.07 degrees, 16.57 degrees, 17.57 degrees, 18.57 degrees, 19.07 degrees, 20.07 degrees, or the angle of attack ⁇ 2 of the blade 200 herein. Any value within the numerical range defined by any two of the above numerical values may be used. In the present embodiment, the angle of attack ⁇ 2 is 17.57 degrees.
  • chord length L2 of the paddle 200 is 33.97 ⁇ 5 mm.
  • the chord length L2 of the blade 200 herein may be 28.97 mm, 30.97 mm, 32.97 mm, 33.97 mm, 35.97 mm, 37.97 mm, 38.97 mm, or, in particular, the blade 200 herein.
  • the chord length L2 may be any value within a range of values defined by any two of the above numerical values. In the present embodiment, the chord length L2 is 33.97 mm.
  • the distance from the center O of the paddle to the paddle 200 is 50% of the blade radius, and the angle of attack ⁇ 3 of the blade 200 is 13.68 ⁇ 2.5. degree.
  • the angle of attack ⁇ 3 of the blade 200 herein may be 11.18 degrees, 12.18 degrees, 12.68 degrees, 13.68 degrees, 14.68 degrees, 15.18 degrees, 16.18 degrees, or the angle of attack ⁇ 3 of the blade 200 herein. Any value within the numerical range defined by any two of the above numerical values may be used.
  • the angle of attack ⁇ 3 is 13.68 degrees.
  • the distance from the center O of the paddle on the paddle 200 is 50% of the paddle radius, and the chord length L3 of the paddle 200 is 28.28 ⁇ 5 mm.
  • chord length L3 of the blade 200 herein may be 23.28 mm, 25.28 mm, 27.28 mm, 28.28 mm, 30.28 mm, 32.28 mm, 33.28 mm, or the chord length L3 of the blade 200 herein. Any value within a range of values defined by any two of the above numerical values, in the present embodiment, The chord length L3 is 28.28 mm.
  • the distance from the center O of the paddle on the blade 200 is 65.79% of the blade radius, and the angle of attack ⁇ 4 of the blade 200 is 11.11 ⁇ 2.5. degree.
  • the angle of attack ⁇ 4 of the blade 200 herein may be 8.61 degrees, 9.61 degrees, 10.11 degrees, 11.11 degrees, 12.11 degrees, 12.61 degrees, 13.61 degrees, or the angle of attack ⁇ 4 of the blade 200 herein. Any value within the numerical range defined by any two of the above numerical values may be used. In the present embodiment, the angle of attack ⁇ 4 is 11.11 degrees.
  • chord length L4 of the paddle 200 is 23.45 ⁇ 5 mm.
  • the chord length L4 of the blade 200 herein may be 18.45 mm, 20.45 mm, 22.45 mm, 23.45 mm, 25.45 mm, 27.45 mm, 28.45 mm, or the chord length L4 of the blade 200 herein. Any value within the range of values defined by any two of the above values may be used. In the present embodiment, the chord length L4 is 23.45 mm.
  • the distance from the center O of the paddle on the paddle 200 is 81.58% of the paddle radius, and the angle of attack ⁇ 5 of the paddle 200 is 8.98 ⁇ 2.5. degree.
  • the angle of attack ⁇ 5 of the blade 200 herein may be 6.48 degrees, 7.48 degrees 7.98 degrees, 8.98 degrees, 9.98 degrees, 10.48 degrees, 11.48 degrees, or the angle of attack ⁇ 5 of the blade 200 may be In any value within the numerical range defined by any two of the above numerical values, in the present embodiment, the angle of attack ⁇ 5 is 8.98 degrees.
  • the distance from the center O of the paddle on the paddle 200 is 81.58% of the paddle radius, and the chord length L5 of the paddle 200 is 19.32 ⁇ 5 mm.
  • chord length L5 of the blade 200 herein may be 14.32 mm, 16.32 mm, 18.32 mm, 19.32 mm, 21.32 mm, 23.32 mm, 24.32 mm, or the chord length L5 of the blade 200 herein. Any value within the range of values defined by any two of the above values may be used. In the present embodiment, the chord length L5 is 19.32 mm.
  • the distance from the center O of the paddle on the paddle 200 is 97.37% of the paddle radius, and the angle of attack ⁇ 6 of the paddle 200 is 7.57 ⁇ 2.5. degree.
  • the angle of attack ⁇ 6 of the blade 200 herein may be 5.07 degrees, 6.07 degrees, 6.57 degrees, 7.57 degrees, 8.57 degrees, 9.07 degrees, 10.07 degrees, or the angle of attack ⁇ 6 of the blade 200 may be In the present embodiment, the angle of attack ⁇ 6 is 7.57 degrees, which is an arbitrary value within a numerical range defined by any two of the above numerical values.
  • the distance from the center O of the paddle on the paddle 200 is 97.37% of the paddle radius, and the chord length L6 of the paddle 200 is 15.46 ⁇ 5 mm.
  • chord length L6 of the blade 200 herein may be 10.46 mm, 12.46 mm, 14.46 mm, 15.46 mm, 17.46 mm, 19.46 mm, 20.46 mm, or the chord length L6 of the blade 200 herein. Any value within the range of values defined by any two of the above values may be used. In the present embodiment, the chord length L6 is 15.46 mm.
  • the paddle has a diameter of 380 mm.
  • the angle of attack ⁇ 1 of the blade 200 is 20.11 degrees, and the chord length L1 of the blade 200 is 33.59 mm;
  • the angle of attack ⁇ 2 of the blade 200 is 17.57 degrees, the chord length L2 of the blade 200 is 33.97 mm, and the blade 200 is attacked 95 mm from the center of the paddle.
  • the angle ⁇ 3 is 13.68 degrees, the chord length L3 of the blade 200 is 28.28 mm; at an angle of 125 mm from the center of the paddle, the angle of attack ⁇ 4 of the blade 200 is 11.11 degrees, the blade 200
  • the chord length L4 is 23.45 mm; at an angle of 155 mm from the center of the paddle, the angle of attack ⁇ 5 of the blade 200 is 8.98 degrees, and the chord length L5 of the blade 200 is 19.32 mm;
  • the angle of attack ⁇ 5 of the blade 200 is 7.57 degrees, and the chord length L6 of the blade 200 is 15.46 mm.
  • Table 1 shows the driving force values of the propellers provided by the present embodiment at different rotational speeds.
  • the propeller provided by the embodiment of the present invention requires less power under the same pulling force, thereby saving power consumption, increasing the cruising distance of the UAV, and improving efficiency.
  • the propeller provided by the invention reduces the air resistance, improves the efficiency, increases the cruising range of the aircraft and improves the flight performance of the aircraft through the design of the angle of attack on different parts of the blade.

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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)
  • Wind Motors (AREA)

Abstract

La présente invention concerne une hélice (100). L'hélice comprend des pales (200). Dans une position sur la pale (200) dans laquelle la distance à partir d'un centre de rotation de l'hélice (100) est de 50 % d'un rayon de rotation de l'hélice (100), l'angle d'attaque de la pale (200) est de 13,68 ± 2,5 degrés ; dans une position sur la pale (200) dans laquelle la distance à partir du centre de rotation de l'hélice (100) est de 65,79 % du rayon de rotation de l'hélice (100), l'angle d'attaque de la pale (200) est de 11,11 ± 2,5 degrés ; et dans une position sur la pale (200) dans laquelle la distance à partir du centre de rotation de l'hélice (100) est de 81,58 % du rayon de rotation de l'hélice (100), l'angle d'attaque de la pale (200) est de 8,98 ± 2,5 degrés. L'invention concerne en outre une série d'alimentation et un aéronef sans pilote utilisant l'hélice mentionnée ci-dessus (100). La conception d'angles d'attaque de différentes pièces de la pale permet de réduire la résistance à l'air, d'améliorer l'efficacité et d'augmenter relativement la propulsion.
PCT/CN2016/108287 2016-10-28 2016-12-01 Hélice, série d'alimentation et aéronef sans pilote WO2018076457A1 (fr)

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CN201680085525.7A CN109071004A (zh) 2016-10-28 2016-12-01 螺旋桨、动力套装及无人飞行器

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CN201621195086.9U CN206141830U (zh) 2016-10-28 2016-10-28 螺旋桨、动力套装及无人飞行器
CN201621195086.9 2016-10-28

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CN206926806U (zh) * 2017-07-25 2018-01-26 深圳市大疆创新科技有限公司 螺旋桨、动力组件及飞行器
CN207106882U (zh) * 2017-07-31 2018-03-16 深圳市大疆创新科技有限公司 桨叶、螺旋桨、动力组件及无人飞行器
WO2019119379A1 (fr) * 2017-12-21 2019-06-27 深圳市大疆创新科技有限公司 Hélice, assemblage motorisé et aéronef sans pilote
CN109969391A (zh) * 2017-12-28 2019-07-05 辽宁壮龙无人机科技有限公司 无人机及其螺旋桨
CN208149614U (zh) * 2018-04-25 2018-11-27 深圳市大疆创新科技有限公司 螺旋桨、动力组件及飞行器
CN114228988A (zh) * 2021-11-26 2022-03-25 南昌三瑞智能科技有限公司 一种大推力高升阻比螺旋桨及该螺旋桨桨叶设计方法

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