WO2017128743A1

WO2017128743A1 - Propeller, power assembly, and aircraft

Info

Publication number: WO2017128743A1
Application number: PCT/CN2016/099701
Authority: WO
Inventors: 刘峰; 邓涛; 江彬; 王庶
Original assignee: 深圳市大疆创新科技有限公司
Priority date: 2016-01-28
Filing date: 2016-09-22
Publication date: 2017-08-03
Also published as: CN205366054U

Abstract

A propeller, power assembly, and aircraft. The propeller comprises: a propeller hub (10), and a blade (20) connected to the propeller hub (10). At a location having a distance of 44.35% of a radius of the propeller from the center of the propeller hub (10), the blade (20) has an angle of attack of 18.7° ± 2.5°, and a chord length of 29.5 mm ± 5 mm. At a location having a distance of 62.9% of the radius of the propeller from the center of the propeller hub (10), the blade (20) has an angle of attack of 14.1° ± 2.5°, and a chord length of 24.03 mm ± 5 mm. At a location having a distance of 81.45% of the radius of the propeller from the center of the propeller hub (10), the blade (20) has an angle of attack of 11.3° ± 2.5°, and a chord length of 19.16 mm ± 5 mm. The above configuration can optimize the structure of a propeller, thus improving the flight performance of an aircraft.

Description

Propellers, power components and aircraft

Technical field

The present invention relates to the field of aircraft, and more particularly to a propeller and an 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 propeller in the prior art includes a blade and a hub. The shape of the blade is mostly rectangular, and the resistance is large and the efficiency is low, which results in a small flying speed of the aircraft and a short following distance, which seriously affects the flight performance of the aircraft.

Summary of the invention

The invention provides a propeller, a power component and an aircraft 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 hub and a blade, the blade being coupled to the hub;

At a distance of 44.35% of the radius of the propeller from the center of the hub, the angle of attack of the blade is 18.7 ° ± 2.5 °, the chord length of the blade is 29.5 mm ± 5 mm;

At 62.9% of the radius of the propeller from the center of the hub, the angle of attack of the blade is 14.1 ° ± 2.5 °, the chord length of the blade is 24.03 mm ± 5 mm;

At an angle of 81.45% of the radius of the propeller from the center of the hub, the blade has an angle of attack of 11.3° ± 2.5° and the blade has a chord length of 19.16 mm ± 5 mm.

The propeller, preferably, at 25.8% of the radius of the propeller from the center of the hub, the angle of attack of the blade is 23.8° ± 2.5°, and the chord length of the blade is 35.08 Mm ± 5mm.

The propeller, preferably, at a distance of 100% of the radius of the propeller from the center of the hub, the angle of attack of the blade is 6.7° ± 2.5°, and the chord length of the blade is 15.16 Mm ±5mm.

The propeller, preferably, the diameter of the propeller is 345 mm ± 34.5 mm; at an angle of 76.5 mm from the center of the hub, the angle of attack of the blade is 18.7 °, and the chord length of the blade is 29.5 mm; at an angle of 108.5 mm from the center of the hub, the blade has an angle of attack of 14.1°, the blade has a chord length of 24.03 mm; at a distance of 140.5 mm from the center of the hub, The blade has an angle of attack of 11.3° and the blade has a chord length of 19.16 mm.

The propeller, preferably, the diameter of the propeller is 345 mm ± 34.5 mm; at an angle of 44.5 mm from the center of the hub, the angle of attack of the blade is 23.8 °, and the chord length of the blade is 35.08mm.

The propeller, preferably, the diameter of the propeller is 345 mm ± 34.5 mm; at an angle of 172.5 mm from the center of the hub, the angle of attack of the blade is 6.7°, and the chord length of the blade is 15.16mm.

The propeller, preferably, the blade includes a downwardly facing leaf surface, an upwardly facing leaf back, a first edge attached to one side of the leaf back and a leaf surface, and a leaf back and a leaf attached thereto a second edge on the other side of the face; the cross section of the leaf face and the leaf back are both curved, and the first edge is located below the second edge.

In the propeller, preferably, the first edge of the blade is convexly formed with a protrusion.

The propeller, preferably, the blade 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.

The propeller, preferably, the projection is located at the blade near the connection end.

The propeller, preferably, the blades are at least two, the at least two blades being centrally symmetrical about a center of the hub.

The propeller, preferably, has a pitch of 60 mm.

Another aspect of the present invention provides a power assembly including a drive member and a propeller provided by the present invention, the propeller being coupled to the drive member via the hub.

In the power component, preferably, the driving member is a motor, and the motor has a KV value of 380 rpm / (minute volt) or 420 rpm / (minute volt).

Another aspect of the present invention provides an aircraft including a fuselage and a power pack provided by the present invention The power component is coupled to the body.

Based on the above, a propeller provided by the embodiment of the present invention has an angle of attack of 18.7°±2.5° at a distance of 44.35% of the radius of the propeller from the center of the hub. The chord length of the leaf is 29.5 mm ± 5 mm; at 62.9% of the radius of the propeller from the center of the hub, the angle of attack of the blade is 14.1 ° ± 2.5 °, the chord length of the blade 24.03 mm ± 5 mm; at an angle of 81.45% of the radius of the propeller from the center of the hub, the angle of attack of the blade is 11.3 ° ± 2.5 °, and the chord length of the blade is 19.16 mm ± 5mm. Therefore, the air resistance can be reduced, the pulling force and efficiency can be improved, the flying distance of the aircraft can be increased, and the flight performance of the aircraft can be improved.

DRAWINGS

1 is a top plan view of a propeller according to an embodiment of the present invention;

Figure 2 is a cross-sectional view of the B-B section of the propeller of the embodiment of Figure 1 at a distance of 76.5 mm from the center of the hub;

Figure 3 is a cross-sectional view of the C-C section of the propeller of the embodiment of Figure 1 at a distance of 108.5 mm from the center of the hub;

Figure 4 is a cross-sectional view of the D-D section of the propeller of the embodiment of Figure 1 at a distance of 140.5 mm from the center of the hub;

Figure 5 is a cross-sectional view of the A-A section of the propeller of the embodiment shown in Figure 1 at a distance of 44.5 mm from the center of the hub;

Figure 6 is a cross-sectional view of the E-E section of the propeller of the embodiment of Figure 1 at a distance of 172.5 mm from the center of the hub;

Figure 7 is a perspective view of a propeller according to an embodiment of the present invention;

FIG. 8 is a side elevational view of a propeller according to an embodiment of the present invention.

Reference mark:

10: hub; 20: paddle; 21: foliar;

22: leaf back; 23: first edge; 231: bulge;

24: The second edge.

detailed description

Embodiments of the present invention provide a propeller, which may be a positive propeller or a reverse propeller. The so-called positive paddle refers to a propeller that rotates clockwise to generate lift from the tail of the motor, such as the tail of the motor. The so-called reverse paddle refers to the propeller that rotates counterclockwise to generate lift from the tail of the motor to 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.

1 is a plan view of a propeller according to an embodiment of the present invention; FIG. 2 is a cross-sectional view of the BB section of the propeller of the embodiment shown in FIG. 1 at a distance of 76.5 mm from the center of the hub; FIG. 3 is a view of the embodiment of FIG. A cross-sectional view of a CC section at a distance of 108.5 mm from the center of the propeller; FIG. 4 is a cross-sectional view of the DD section of the propeller of the embodiment shown in FIG. 1 at a distance of 140.5 mm from the center of the hub; The embodiment of the invention provides a propeller comprising: a hub 10 and a blade 20, the blade 20 being coupled to the hub 10; of course, the blade 20 may be integrally formed with the hub 10, or may be separately processed. Fixedly mounted in one piece. At an angle D4 from the center of the hub 10 which is 44.35% of the radius of the propeller, the angle of attack α1 of the blade 20 is 18.7° ± 2.5°, and the chord length L1 of the blade 20 is 29.5 mm ± 5 mm; D3 at a distance from the center of the hub 10 of 62.9% of the radius of the propeller, the angle of attack α2 of the blade 20 is 14.1 ° ± 2.5 °, and the chord length L2 of the blade 20 is 24.03 Mm ± 5 mm; at an angle of D4 from the center of the hub 10 of 81.45% of the radius of the propeller, the angle of attack α3 of the blade 20 is 11.3° ± 2.5°, and the chord length L3 of the blade 20 It is 19.16 mm ± 5 mm.

In the present embodiment, since the angle of attack α1 of the blade 20 is 18.7°±2.5° at a distance D4 from the center of the hub 10 which is 44.35% of the radius of the propeller 10, the chord of the blade 20 The length L1 is 29.5 mm ± 5 mm; at a distance of 62.9% of the radius of the propeller 10 from the center of the hub 10, the angle of attack α2 of the blade 20 is 14.1 ° ± 2.5 °, the paddle 20 The chord length L2 is 24.03 mm ± 5 mm; at an angle of 81.45% of the radius of the propeller 10 from the center of the hub 10, the angle of attack α3 of the blade 20 is 11.3 ° ± 2.5 °, the paddle The chord length L3 of the blade 20 is 19.16 mm ± 5 mm, and the blade having a specific shape is defined by the above parameters. The propeller using the blade can reduce the air resistance, increase the pulling force and efficiency, increase the flight distance of the aircraft and improve the distance. Flight performance of the aircraft.

Referring to Table 1, the comparison between the propeller provided in this embodiment and the test results of the existing propeller, as can be seen from the table, when the tensile force is 200g, 600g, 1000g, 1400g, the propeller provided by the embodiment The rotation speed is smaller than the rotation speed of the existing propeller, that is, the propeller provided in the embodiment can provide a larger pulling force at the same rotation speed, and thus the propeller provided in the embodiment is in a high altitude region with low density or a low altitude region. In extreme cases where the take-off weight is large, it can significantly increase the pulling force, ensure sufficient power while prolonging the battery life and improving flight performance.

Table 1

普通桨Common paddle		本发明this invention
转速(RPM)Speed (RPM)	拉力(g)Pull force (g)	转速(RPM)Speed (RPM)	拉力(g)Pull force (g)
24902490	200200	18771877	200200
42604260	600600	31503150	600600
54475447	10001000	40654065	10001000
63706370	14001400	48144814	14001400
max6908Max6908	16411641	54395439	18001800
		max5691Max5691	19591959

Wherein, at an angle D2 from the center of the hub 10 which is 44.35% of the radius of the propeller, the angle of attack α1 of the blade 20 may be 16.2° or 18.7° or 21.2°, or between any two of the above Any of the values, the chord length L1 of the blade 20 may be 24.5 mm or 29.5 mm or 34.5 mm, or a value between any two of the above. At an angle D3 from the center of the hub 10 that is 62.9% of the radius of the propeller, the angle of attack α2 of the blade 20 may be 11.6° or 14.1° or 16.6°, or a value between any two of the above. The chord length L2 of the paddle 20 is 19.03 mm or 24.03 mm or 29.03 mm, or a value between any two of the above. At an angle D4 from the center of the hub 10 that is 81.45% of the radius of the propeller, the angle of attack α3 of the blade 20 is 8.8° or 11.3° or 13.8°, or a value between any two of the above, The chord length L3 of the paddle 20 is 14.16 mm or 19.16 mm or 24.16 mm, or a value between any two of the above.

The hub 10 may be cylindrical, and the hub 10 is provided with a connecting hole at the center, and the connecting hole is sleeved on the output end of the motor. The blade 20 may be in the form of a strip, the blade 20 and the hub 10 Connected and extends in the radial direction of the hub 10. The angle of attack refers to the angle between the chord of the blade 20 and the incoming flow velocity, and the chord length refers to the length of the cross section of the blade 20.

Figure 5 is a cross-sectional view of the propeller of the embodiment of Figure 1 taken along line AA of 44.5 mm from the center of the hub; with reference to Figure 5, in the present embodiment, preferably at the center of the hub 10 The angle of the pitch of the propeller 20 is 23.8°±2.5°, and the chord length L4 of the blade 20 is 35.08 mm±5 mm. To further reduce the air resistance of the propeller, improve the pulling force and efficiency. Wherein, the angle of attack α4 of the blade 20 may be 21.3° or 23.8° or 26.3°, or a value between any two of the above, the chord length L4 of the blade 20 is 30.08 mm or 35.08 mm or 40.08 mm, or The value between any two of the above.

Figure 6 is a cross-sectional view of the EE section of the propeller of the embodiment of Figure 1 at a distance of 172.5 mm from the center of the hub; with reference to Figure 6, in the present embodiment, preferably at the center of the hub 10 At 100% of the radius of the propeller, D5, the angle of attack α5 of the blade 20 is 6.7° ± 2.5°, and the chord length L5 of the blade 20 is 15.16 mm ± 5 mm. To further reduce the air resistance of the propeller, improve the pulling force and efficiency. Wherein, the angle of attack α5 of the blade 20 may be 4.2° or 6.7° or 9.2°, or a value between any two of the above, the chord length L5 of the blade 20 is 10.16 mm or 15.16 mm or 20.16 mm, or any of the above The value between the two.

Referring to FIGS. 1-4, in the present embodiment, preferably, the diameter of the propeller is 345 mm±34.5 mm; at the distance D2 from the center of the hub 10 at 76.5 mm, the angle of attack α1 of the paddle 20 is 18.7°. The chord length L1 of the blade 20 is 29.5 mm; at an angle D3 108.5 mm from the center of the hub 10, the angle of attack α2 of the blade 20 is 14.1°, and the chord length L2 of the blade 20 It is 24.03 mm; at an angle D4 of 140.5 mm from the center of the hub 10, the angle of attack α3 of the blade 20 is 11.3°, and the chord length L3 of the blade 20 is 19.16 mm. Thereby, the air resistance of the propeller can be further reduced, and the pulling force and efficiency can be improved. Wherein, the diameter of the propeller may be 310.5 mm or 345 mm or 379.5 mm, or a value between any two of the above.

Referring to FIG. 5, in the present embodiment, preferably, the diameter of the propeller is 345 mm±34.5 mm; at an angle of 44.5 mm from the center of the hub 10, the angle of attack α4 of the blade 20 is 23.8°. The chord length L4 of the blade 20 is 35.08 mm. Thereby, the air resistance of the propeller can be further reduced, and the pulling force and efficiency can be improved. Wherein, the diameter of the propeller can be 310.5 mm or 345 mm or 379.5 mm, or a value between any two of the above.

Referring to FIG. 6, in the embodiment, preferably, the diameter of the propeller is 345 mm±34.5 mm; at an angle of D5 from the center of the hub 10 at 172.5 mm, the angle of attack α5 of the blade 20 is 6.7°. The chord length L5 of the blade 20 is 15.16 mm. Thereby, the air resistance of the propeller can be further reduced, and the pulling force and efficiency can be improved. Wherein, the diameter of the propeller may be 310.5 mm or 345 mm or 379.5 mm, or a value between any two of the above.

Figure 7 is a perspective view of a propeller according to an embodiment of the present invention; Figure 8 is a side view of a propeller according to an embodiment of the present invention; referring to Figures 1-8, in the present embodiment, preferably, the blade 20 includes a downwardly facing leaf surface 21, an upward leaf back 22, a first edge 23 joined to the leaf back 22 and the leaf surface 21 side, and a first side connected to the leaf back 22 and the other side of the leaf surface 21 The two edges 24; the cross section of the leaf surface 21 and the leaf back 22 are curved, and the first edge 23 is located below the second edge 24. Since the cross-sections of the leaf surface 21 and the blade back 22 are both curved, and the first edge 23 is located below the second edge 24, the resistance of the air can be reduced and the pulling force of the blade 20 can be increased.

In this embodiment, preferably, the first edge 23 of the blade 20 is convexly formed with a protrusion 231. Thereby, the pulling force of the blade 20 can be further increased. Wherein, the protruding portion 231 may be located near the connecting end of the blade 20 to further improve the pulling force of the high blade 20.

In the present embodiment, preferably, the paddle 20 includes a connecting end connected to the hub 10 and an end facing away from the hub 10. The thickness of the paddle 20 is gradually reduced from the connecting end to the end. small. 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. In addition, the end of the blade 20 away from the hub 10 is the thinnest portion of the blade 20, which is advantageous for reducing air resistance.

In the present embodiment, preferably, the paddles 20 are at least two, and the at least two paddles 20 are centrally symmetric with respect to the center of the hub 10. Thereby, the balance of the propeller can be improved.

In the present embodiment, preferably, the pitch of the blade 20 is 60 mm. Thereby, the resistance of the air can be reduced and the pulling force of the blade 20 can be increased.

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.

Embodiments of the present invention provide a power assembly including a drive member and any embodiment of the present invention The propeller is connected to the driving member through the hub 10. The specific structure of the propeller is similar to the foregoing embodiment, and details are not described herein again.

In the present embodiment, preferably, the KV value of the motor is 380 rpm / (minute volt) or 420 rpm / (minute volt). Thereby, the dynamic performance of the power unit can be ensured.

An embodiment of the invention provides an aircraft comprising a fuselage and a power assembly according to any of the embodiments of the invention, the power assembly being coupled to the fuselage. The specific structure of the power component is similar to the foregoing embodiment, and details are not described herein again.

Finally, it should be noted that the above embodiments are merely illustrative of the technical solutions of the present invention, and are not intended to be limiting; although the present invention has been described in detail with reference to the foregoing embodiments, those skilled in the art will understand that The technical solutions described in the foregoing embodiments may be modified, or some or all of the technical features may be equivalently replaced; and the modifications or substitutions do not deviate from the technical solutions of the embodiments of the present invention. The scope of the program.

Claims

A propeller includes: a hub and a blade, the blade being coupled to the hub, wherein:

At a distance of 44.35% of the radius of the propeller from the center of the hub, the angle of attack of the blade is 18.7 ° ± 2.5 °, the chord length of the blade is 29.5 mm ± 5 mm;

At 62.9% of the radius of the propeller from the center of the hub, the angle of attack of the blade is 14.1 ° ± 2.5 °, the chord length of the blade is 24.03 mm ± 5 mm;

At an angle of 81.45% of the radius of the propeller from the center of the hub, the blade has an angle of attack of 11.3° ± 2.5° and the blade has a chord length of 19.16 mm ± 5 mm.
The propeller according to claim 1, wherein said blade has an angle of attack of 23.8° ± 2.5° at a distance of 25.8% of a radius of said propeller from a center of said hub, said blade The chord length is 35.08 mm ± 5 mm.
The propeller according to claim 1, wherein said blade has an angle of attack of 6.7° ± 2.5° at a distance of 100% of a radius of said propeller from a center of said hub, said blade The chord length is 15.16 mm ± 5 mm.
A propeller according to claim 1 wherein:

The diameter of the propeller is 345 mm ± 34.5 mm;

At a distance of 76.5 mm from the center of the hub, the blade has an angle of attack of 18.7° and the blade has a chord length of 29.5 mm;

The angle of attack of the blade is 14.1° at a distance of 108.5 mm from the center of the hub, and the chord length of the blade is 24.03 mm;

At an angle of 140.5 mm from the center of the hub, the blade has an angle of attack of 11.3° and the blade has a chord length of 19.16 mm.
The propeller according to claim 2, wherein the diameter of the propeller is 345 mm ± 34.5 mm;

At an angle of 44.5 mm from the center of the hub, the blade has an angle of attack of 23.8° and the blade has a chord length of 35.08 mm.
The propeller according to claim 3, wherein the diameter of the propeller is 345 mm ± 34.5 mm;

The blade has an angle of attack of 6.7° at a distance of 172.5 mm from the center of the hub, The chord length of the paddle is 15.16 mm.
A propeller according to any one of claims 1 to 6, wherein:

The blade includes a downwardly facing leaf surface, an upwardly facing leaf back, a first edge joined to one side of the leaf back and the leaf surface, and a second edge joined to the other side of the leaf back and the leaf surface ;

The cross section of the leaf surface and the leaf back are both curved, and the first edge is located below the second edge.
The propeller according to claim 7, wherein the first edge of the blade is convexly formed with a projection.
The propeller according to claim 8, wherein said blade 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 The end is gradually reduced.
The propeller according to claim 9, wherein the projection is located at the blade near the connection end.
A propeller according to any one of claims 1-6 and 8-10, wherein said blades are at least two, said at least two blades being centrally symmetrical about a center of said hub.
The propeller according to any one of claims 1-6 and 8 to 10, characterized in that the pitch of the blade is 60 mm.
A power assembly comprising a drive member and a propeller according to any of claims 1-12, wherein the propeller is coupled to the drive member via the hub.
The power pack according to claim 13, wherein said driving member is a motor having a KV value of 380 rpm / (minute volt) or 420 rpm / (minute volt).
An aircraft characterized by comprising a fuselage and the power assembly of claim 13 or 14, the power assembly being coupled to the fuselage.