WO2019000547A1

WO2019000547A1 - Propeller, power device, and aircraft

Info

Publication number: WO2019000547A1
Application number: PCT/CN2017/095237
Authority: WO
Inventors: 刘翊涵; 江彬; 宋浩
Original assignee: 深圳市大疆创新科技有限公司
Priority date: 2017-06-26
Filing date: 2017-07-31
Publication date: 2019-01-03
Also published as: CN206968981U; CN110248870A

Abstract

A propeller, a power device, and an aircraft. The propeller comprises a propeller hub (10) and propeller blades (20) connected to the propeller hub (10); a plurality of wing fences (30) are provided on the surface of the propeller blade (20); the plurality of wing fences (30) are arranged at intervals along the extension direction of the propeller blade (20). According to the propeller of the present invention, by providing the plurality of wing fences at intervals along the extension direction of the propeller blade on the surface of the propeller blade, the air flow which is generated by the propeller blade in the rotating process and moves along the extension direction can be effectively reduced, the flowing speed of a boundary layer on the surface of the propeller blade to the outer wing direction is reduced, the energy of the propeller is prevented from being lost, the pulling force of the propeller in the unit power consumption is improved, and the aircraft is ensured to have enough power; moreover, the duration and distance of flight are prolonged, so that the flight performance of the aircraft is improved.

Description

Propeller, powerplant and aircraft

Technical field

The present invention relates to the field of aircraft, and more particularly to propellers, powerplants, and aircraft.

Background technique

The propeller on the aircraft, as an important key component of the aircraft, is used to convert the rotation of the shaft of the motor or engine into thrust or lift.

The propellers in the prior art are mostly rectangular in shape, and have large resistance and low efficiency, resulting in a small flying speed of the aircraft and a short cruising distance, which seriously affects the flight performance of the aircraft.

During the rotation of a conventional propeller, the medium (air) will produce a speed in the direction of the blade surface (as indicated by the direction of the arrow in Figure 1), which will affect the lift performance of the blade and thus the loss of the propeller. Part of the efficiency.

Summary of the invention

The invention provides a propeller, a power unit and an aircraft.

According to a first aspect of the embodiments of the present invention, there is provided a propeller comprising: a hub and a blade coupled to the hub, the surface of the blade being provided with a plurality of blade cutters, the plurality of blade edges The spanwise directions of the blades are spaced apart.

Further, the blade includes a first surface and a second surface disposed opposite to each other, and the blade is formed on the first surface and the second surface.

Further, the paddle includes opposite first and second surfaces, and the blade is formed on the first surface or the second surface.

Further, the blade is a straight strip structure.

Further, the blade is disposed along a chordwise direction of the blade.

Further, the blade is an arc structure.

Further, the blade comprises an arcuate side edge that is bent in a direction away from the hub.

Further, the blade is convexly formed in a direction away from the surface of the blade.

Further, the blade includes a first surface and a second surface disposed opposite to each other, the blade is formed on the first surface and the second surface; the blade is away from the first A first convex portion is convexly formed in a direction of the surface, and the blade is convexly formed with a second convex portion in a direction away from the second surface.

Further, the blade further includes a first side edge and a second side edge connected between the first surface and the second surface, the first side edge being located below the second side edge .

Further, the first side edge is a windward side, the second side edge is a leeward side, and the second side edge is convexly formed with a protruding portion.

Further, the second side edge is a windward side, the first side edge is a leeward surface, and the first side edge is convexly formed with a convex portion.

Further, the blade further includes a connecting end connected to the hub and an end facing away from the hub, the thickness of the blade being gradually reduced from the connecting end to the end.

Further, the blades are at least two, and the at least two blades are disposed symmetrically with respect to a center of the hub.

According to a second aspect of the embodiments of the present invention, there is provided a power unit including a driving member and a propeller as described above, the propeller being mounted on the driving member.

According to a third aspect of the embodiments of the present invention, there is provided an aircraft comprising an aircraft body and a power unit as described above, the power unit being mounted on the aircraft body.

The technical solution provided by the embodiments of the present invention may include the following beneficial effects: by arranging a plurality of blade cutters along the spanning direction of the blade in the span direction of the blade, the direction along the span of the blade during the rotation process can be effectively reduced. The directional moving airflow reduces the velocity of the boundary layer of the blade surface to the outer wing direction, avoids the loss of the propeller energy, improves the pulling force of the propeller unit power consumption, ensures the aircraft has sufficient power, and prolongs the battery life and battery life. Distance, thereby improving the flight performance of the aircraft.

DRAWINGS

1 is a schematic plan view of a propeller of the prior art.

2 is a schematic plan view of a propeller according to an embodiment of the present invention.

Figure 3 is a perspective view of the propeller shown in Figure 2 at a viewing angle.

Figure 4 is a perspective view of the propeller shown in Figure 2 from another perspective.

Figure 5 is a side elevational view of the propeller of Figure 2 in a viewing angle.

Figure 6 is a side elevational view of the propeller of Figure 2 from another perspective.

7 is a comparison diagram of test results of a propeller and an existing propeller according to an embodiment of the present invention.

Fig. 8 is a schematic view showing the effect of the propeller shown in Fig. 2.

FIG. 9 is a schematic plan view of another propeller according to an embodiment of the present invention.

Fig. 10 is a side view of the propeller shown in Fig. 9.

Fig. 11 is a schematic view showing the effect of the propeller shown in Fig. 9.

Detailed ways

Exemplary embodiments will be described in detail herein, examples of which are illustrated in the accompanying drawings. The following description refers to the same or similar elements in the different figures unless otherwise indicated. The embodiments described in the following exemplary embodiments do not represent all embodiments consistent with the present invention. Instead, they are merely examples of devices and methods consistent with aspects of the invention as detailed in the appended claims.

The terminology used in the present invention is for the purpose of describing particular embodiments, and is not intended to limit the invention. The singular forms "a", "the" and "the" It should also be understood that the term "and/or" as used herein refers to and encompasses any and all possible combinations of one or more of the associated listed items.

It should be understood that the terms "first", "second", and <RTIgt; </ RTI> <RTIgt; </ RTI> <RTIgt; </ RTI> <RTIgt; Similarly, the words "a" or "an" and the like do not denote a quantity limitation, but mean that there is at least one. Unless otherwise indicated, the terms "front", "rear", "lower" and/or "upper" are used for convenience of description and are not limited to one location or one spatial orientation. The word "comprising" or "comprises" or "comprises" or "comprises" or "an" Or an object. The words "connected" or "connected" and the like are not limited to physical or mechanical connections, and may include electrical connections, whether direct or indirect.

Embodiments of the present invention provide a propeller, which may be a positive propeller or a reverse propeller. The so-called positive paddle The moving parts, such as the tail of the motor, are viewed in the direction of the motor head, and rotate clockwise to generate a lift propeller; the so-called reverse paddle refers to a propeller that rotates counterclockwise to generate lift from the tail of the motor toward the direction of the motor head. The structure of the positive paddle is mirror symmetrical with the structure of the reverse paddle, so the structure of the propeller will be described below by taking only the positive paddle as an example.

In addition, the terms of the upper and lower orientations appearing in this embodiment are based on the conventional operating posture of the propeller and the aircraft after the propeller is mounted on the aircraft, and should not be considered as limiting.

The propeller, power unit and aircraft of the present invention will be described in detail below with reference to the accompanying drawings. The features of the embodiments and embodiments described below may be combined with each other without conflict.

Referring to FIG. 2 to FIG. 6 , a propeller provided by an embodiment of the present invention includes: a hub 10 and a blade 20 connected to the hub 10 , and a surface of the blade 20 is provided with a plurality of blade cutters 30 . The plurality of blade cutters 30 are spaced apart along the direction in which the blades 20 are oriented (as indicated by the X direction in FIG. 2). The spanwise direction refers to the direction in which the propeller extends from the end of the blade 20 that is connected to the hub 10 toward the end of the blade 20 and along the blade 20.

In the propeller of the present invention, by providing a plurality of blade cutters 30 on the surface of the blade 20 in the spanwise direction of the blade 20, the airflow in the direction of the span generated by the blade 20 during the rotation can be effectively reduced, and the paddle can be reduced. The velocity of the boundary layer on the surface of the blade 20 (a thin layer of airflow formed by the influence of air viscosity) flows outward in the direction of the wing (ie, the direction of the wing tip), avoiding loss of energy of the propeller and increasing the unit power consumption of the propeller. The pulling force ensures that the aircraft equipped with the propeller of the invention has sufficient power to extend the endurance time and cruising range, thereby improving the flight performance of the aircraft.

Referring to FIG. 7 , it is an alignment diagram of the test results of the propeller and the existing propeller provided in the embodiment, wherein the abscissa indicates the power of the propeller, and the ordinate indicates the propeller in the work. The magnitude of the pulling force, the curve A is the power-pull curve of the propeller provided in this embodiment, and the curve B is the power-pull curve of the existing propeller. It can be seen from the figure that, under the condition of equal power conditions, the propeller of the present invention has a pulling force greater than that of the existing propeller, that is, the propeller provided by the present invention can provide greater pulling force under the same power. Ensure sufficient power while extending battery life and improve aircraft flight performance. In order to more intuitively compare the power-pull relationship between the propeller provided in this embodiment and the existing propeller, the three sets of power-pull numerical relationships represented by the circles in the figure are listed in Table 1 below. 1 It can also be concluded that, in the case of close power conditions, the propeller of the present invention has a pulling force greater than that of the existing propeller.

Table 1

In an embodiment of the invention, the blades 20 are at least two, and the at least two blades 20 are disposed symmetrically with respect to the center of the hub 10. Thereby, the balance of the propeller can be improved. In the present embodiment, the number of the blades 20 is two.

In an alternative embodiment, the blade 20 includes a first surface 210 and a second surface 220 disposed opposite to each other, and the blade 30 is formed on the first surface 210 and the second surface 220 Above, that is, the front and back sides of the blade 20 are provided with the wing cutter 30, so that the upper surface of the blade can reduce the blade rotation during the rotation process by the blade 30 regardless of whether the propeller of the present invention is used as a positive paddle or a reverse paddle. The generated airflow moving in the direction of the exhibition direction, thereby improving the flight performance of the aircraft. In another optional embodiment, the blade 30 is formed on the first surface 210 or the second surface 220, ie The blade 30 is disposed only on one side of the blade 20, so that when the propeller of the present invention is used as a positive paddle, the blade 30 can be disposed on the upper surface of the paddle of the paddle, when the propeller of the present invention is used as a counter paddle, The wing cutter 30 may be disposed on the upper surface of the blade of the reverse paddle, and the upper surface of the blade can also be used to reduce the airflow of the blade moving in the spanwise direction generated by the blade during the rotation, thereby improving the flight performance of the aircraft.

In an optional embodiment, the blade 30 has a straight strip structure. As shown in FIG. 8, the airflow generated by the blade in the direction of the spanwise movement during the rotation can be along the outer edge of the blade 30. Flow out (as indicated by the direction of the arrow in Figure 8), thereby reducing the flow of the blade in the spanwise direction produced during the rotation. Alternatively, the arrangement direction of the blade 30 is inclined with respect to the chord direction of the blade 20 (the Y direction shown in FIG. 2). The chordwise direction refers to a direction perpendicular to the spanwise direction of the blade 20. Preferably, the blade 30 is disposed along the chordwise direction Y of the blade 20, that is, the angle between the arrangement direction of the blade 30 and the chord direction of the blade 20 is 0, which can be maximized. The airflow generated by the blade in the direction of the spanwise movement during the rotation is reduced to a certain extent. Referring to FIG. 9 and FIG. 10, in another optional embodiment, the blade 30 has an arc structure, and as shown in FIG. 11, the airflow generated by the blade in the spanwise direction during the rotation process is shown in FIG. It can be branched along the outer edge of the blade 30 and can also reverse the partial airflow (as indicated by the direction of the arrow in Fig. 8), thereby reducing the movement of the blade in the spanwise direction during the rotation. Airflow. Optionally, the blade 30 includes an arcuate side edge 300 that is bent away from the hub 10 .

In an embodiment of the invention, the blade 30 is convexly formed in a direction away from the surface of the blade 20 to form a convex portion 310 (320), which can move in the direction of the span generated during the rotation of the blade. The air flow further acts as a split to further reduce the airflow generated by the blades during the rotation in the spanwise direction. When the blade 20 is provided on both sides of the blade 20, the blade 30 A first raised portion 310 is formed convexly away from a direction away from the first surface 210 of the blade 20, and the blade 30 is convexly formed in a direction away from the second surface 220 of the blade 20 The raised portion 320. When the blade 30 is disposed only on one side of the blade 20, the blade 30 is convexly formed in a direction away from the upper surface of the blade 20 to form the boss 310 (320).

In an embodiment of the invention, the blade 20 further includes a first side edge 410 and a second side edge 420 connected between the first surface 210 and the second surface 220, the first surface The cross section of the 210 and second surface 220 are both curved, and the first side edge 410 is located below the second side edge 420. Since the cross sections of the first surface 210 and the second surface 220 are both curved, and the first side edge 410 is located below the second side edge 420, the resistance of the air can be reduced, and the pulling force of the blade 20 can be increased. .

Further, the blade 20 further includes a connecting end 230 connected to the hub 10 and a distal end 240 facing away from the hub 10, the blade 20 having a thickness from the connecting end 230 to the end 240 slowing shrieking. Since there is no sharp twist on the blade 20, the stress is relatively uniform, and the stress at the individual position is prevented from being excessively large, the structural strength is high, and it is not easy to be broken, thereby improving the working reliability of the propeller. Additionally, the distal end 240 of the blade 20 away from the hub 10 is the thinnest portion of the blade 20, which is advantageous in reducing air resistance. In this embodiment, the first side edge 410 is a windward side, the second side edge 420 is a leeward side, and the second side edge 420 is convexly formed with a protruding portion 430, thereby further improving the paddle The tension of the leaf 20. Wherein, the protruding portion 430 may be located near the connecting end 230 of the blade 20 to further enhance the pulling force of the blade 20. In another embodiment, the second side edge 420 is a windward side, the first side edge 410 is a leeward surface, and the first side edge 410 is convexly formed with the protrusion 430.

In summary, the propeller of the present invention passes along the surface of the blade 20 along the direction of the blade 20 By arranging a plurality of wing cutters 30, the airflow moving in the spanwise direction generated by the blade 20 during the rotation process can be effectively reduced, and the boundary layer on the surface of the blade 20 can be reduced (the surface of the blade is formed by the influence of air viscosity). The velocity of the layer airflow flowing in the direction of the outer wing (ie, the direction of the wing tip), avoiding the loss of the energy of the propeller, increasing the pulling force of the propeller unit power consumption, ensuring that the aircraft equipped with the propeller of the present invention has sufficient power and prolonging the endurance time. And the cruising range, which in turn improves the flight performance of the aircraft.

Since the structure of the reverse paddle is mirror symmetrical with the structure of the positive paddle, the structure of the reverse paddle will not be described again.

The embodiment of the present invention further provides a power device including a driving member and a propeller according to any of the embodiments of the present invention, wherein the propeller is mounted on the driving member through the hub 10. In this embodiment, the driving member is a motor. Optionally, the motor has a KV value of 380 rpm / (minute volts) or 420 rpm / (minute volts). Thereby, the power performance of the power unit can be ensured. It should be noted that the description of the propeller in the above embodiments and embodiments is equally applicable to the power unit of the present invention.

In the power unit of the present invention, by arranging a plurality of blade 30s on the surface of the blade 20 of the propeller in the spanwise direction of the blade 20, the movement of the blade 20 in the spanwise direction during the rotation can be effectively reduced. The airflow reduces the velocity of the boundary layer on the surface of the blade 20 (a thin layer of airflow formed by the influence of air viscosity on the surface of the blade) in the direction of the outer wing (ie, the direction of the wing tip), thereby avoiding loss of energy of the propeller and improving The pulling force of the propeller unit power consumption ensures that the aircraft equipped with the propeller of the invention has sufficient power, and at the same time, prolongs the endurance time and the cruising range, thereby improving the flight performance of the aircraft.

An embodiment of the present invention further provides an aircraft comprising an aircraft body and a power device according to any of the embodiments of the present invention, the power device being mounted on the aircraft body. In this embodiment, the aircraft includes a plurality of power devices, and the plurality of power devices have different directions of rotation. Optionally, The aircraft is a multi-rotor aircraft. It should be noted that the descriptions of the propeller and the power unit in the above embodiments and embodiments are equally applicable to the aircraft of the present invention.

In the aircraft of the present invention, by arranging a plurality of blade cutters 30 in the spanwise direction of the blade 20 on the surface of the blade 20 of the propeller of the power unit, the movement in the spanwise direction of the blade 20 during the rotation can be effectively reduced. The airflow reduces the velocity of the boundary layer on the surface of the blade 20 (a thin layer of airflow formed by the influence of air viscosity on the surface of the blade) in the direction of the outer wing (ie, the direction of the wing tip), thereby avoiding loss of energy of the propeller and improving The pulling force of the propeller unit power consumption ensures that the aircraft equipped with the propeller of the invention has sufficient power, and at the same time, prolongs the endurance time and the cruising range, thereby improving the flight performance of the aircraft.

The above is only a preferred embodiment of the present invention, and is not intended to limit the scope of the present invention. Although the present invention has been disclosed in the above preferred embodiments, it is not intended to limit the present invention. A person skilled in the art can make some modifications or modifications to equivalent embodiments by using the above-disclosed technical contents without departing from the technical scope of the present invention. The present invention is not limited to any simple modifications, equivalent changes and modifications of the above embodiments.

The disclosure of this patent document contains material that is subject to copyright protection. This copyright is the property of the copyright holder. The copyright owner has no objection to the reproduction of the patent document or the patent disclosure in the official records and files of the Patent and Trademark Office.

Claims

A propeller, comprising: a hub and a blade connected to the hub, the surface of the blade being provided with a plurality of blade cutters, the plurality of blade cutters extending along the blade Direction interval setting.
The propeller of claim 1 wherein said paddle includes opposing first and second surfaces, said blade being circumferentially formed on said first surface and said second surface.
The propeller of claim 1 wherein said paddle includes opposing first and second surfaces, said blade being formed on said first surface or said second surface.
The propeller according to claim 1, wherein the blade is a straight strip structure.
The propeller according to claim 4, wherein the blade is disposed along a chordwise direction of the blade.
The propeller of claim 1 wherein said blade is an arcuate structure.
The propeller of claim 6 wherein said blade comprises an arcuate side edge that is bent in a direction away from said hub.
The propeller according to claim 1, wherein the blade is convexly formed in a direction away from the surface of the blade.
The propeller according to claim 8, wherein the paddle includes opposite first and second surfaces, and the blade is formed on the first surface and the second surface; The blade is convexly formed with a first convex portion in a direction away from the first surface, and the blade is convexly formed with a second convex portion in a direction away from the second surface.
A propeller according to claim 2 or 3, wherein said blade further comprises a first side edge and a second side edge connected between the first surface and the second surface, the first side edge being located below the second side edge.
The propeller according to claim 10, wherein the first side edge is a windward side, the second side edge is a leeward side, and the second side edge is convexly formed with a convex portion.
The propeller according to claim 10, wherein the second side edge is a windward side, the first side edge is a leeward side, and the first side edge is convexly formed with a convex portion.
The propeller according to claim 1, wherein said blade further comprises a connecting end connected to said hub and an end facing away from said hub, said blade having a thickness from said connecting end to said The end is gradually reduced.
The propeller of claim 1 wherein said blades are at least two, said at least two blades being centrally symmetrically disposed relative to a center of said hub.
A power unit characterized by comprising a driving member and a propeller, the propeller comprising a hub and a blade connected to the hub, the propeller being mounted on the driving member, a surface of the blade A plurality of blade cutters are provided, the plurality of blade cutters being spaced apart along the spanwise direction of the blade.
The power unit according to claim 15, wherein said blade includes opposite first and second surfaces, said blade being formed on said first surface and said second surface .
The power unit of claim 15 wherein said paddle includes opposing first and second surfaces, said blade being formed on said first surface or said second surface.
The power unit according to claim 15, wherein said blade is a straight strip structure.
A power unit according to claim 18, wherein said blade is disposed along a chordwise direction of said blade.
The power unit of claim 15 wherein said blade is an arcuate structure.
A power unit according to claim 20, wherein said blade comprises an arcuate side edge that is bent in a direction away from said hub.
The power unit according to claim 15, wherein said blade is convexly formed in a direction away from said blade surface.
The power unit according to claim 22, wherein said paddle includes opposite first and second surfaces, said blade being formed on said first surface and said second surface The blade is convexly formed with a first convex portion in a direction away from the first surface, and the blade is convexly formed with a second convex portion in a direction away from the second surface.
A power unit according to claim 16 or 17, wherein said blade further comprises a first side edge and a second side edge connected between said first surface and said second surface, said The first side edge is located below the second side edge.
The power unit according to claim 24, wherein the first side edge is a windward side, the second side edge is a leeward side, and the second side edge is convexly formed with a convex portion.
The power unit according to claim 24, wherein the second side edge is a windward side, the first side edge is a leeward side, and the first side edge is convexly formed with a convex portion.
The power unit according to claim 15, wherein said blade further includes a connecting end connected to said hub and an end facing away from said hub, said blade having a thickness from said connecting end to said connecting end The end is gradually reduced.
The power unit of claim 15 wherein said blades are at least two, said at least two blades being centrally symmetrically disposed relative to a center of said hub.
An aircraft characterized by comprising an aircraft body and a power unit, the power unit including a driving member and a propeller, the propeller including a hub and a blade connected to the hub, the propeller being mounted on the On the driving member, a surface of the blade is provided with a plurality of blade cutters, the plurality of blade cutters are spaced apart along a direction in which the blades extend, and the power device is mounted on the aircraft body.
The power unit according to claim 29, wherein said blade includes opposing first and second surfaces, said blade being formed on said first surface and said second surface .
A power unit according to claim 29, wherein said paddle includes opposing first and second surfaces, said blade being formed on said first surface or said second surface.
The power unit according to claim 29, wherein said blade is a straight strip structure.
A power unit according to claim 29, wherein said blade is disposed along a chordwise direction of said blade.
A power unit according to claim 29, wherein said blade is an arcuate structure.
A power unit according to claim 34, wherein said blade comprises an arcuate side edge that is bent in a direction away from said hub.
A power unit according to claim 29, wherein said blade is away from said A convex portion is formed convexly in the direction of the surface of the blade.
The power unit according to claim 36, wherein said blade includes opposite first and second surfaces, said blade being formed on said first surface and said second surface The blade is convexly formed with a first convex portion in a direction away from the first surface, and the blade is convexly formed with a second convex portion in a direction away from the second surface.
A power unit according to claim 29 or claim 30, wherein said blade further comprises a first side edge and a second side edge connected between said first surface and said second surface, said The first side edge is located below the second side edge.
The power unit according to claim 38, wherein the first side edge is a windward side, the second side edge is a leeward side, and the second side edge is convexly formed with a convex portion.
The power unit according to claim 38, wherein the second side edge is a windward side, the first side edge is a leeward side, and the first side edge is convexly formed with a convex portion.
A power unit according to claim 29, wherein said blade further includes a connecting end connected to said hub and an end facing away from said hub, said blade having a thickness from said connecting end to said connecting end The end is gradually reduced.
A power unit according to claim 29, wherein said blades are at least two, said at least two blades being centrally symmetrically disposed with respect to a center of said hub.