WO2019000560A1

WO2019000560A1 - Propeller, power assembly, and aircraft

Info

Publication number: WO2019000560A1
Application number: PCT/CN2017/095865
Authority: WO
Inventors: 刘峰; 陈鹏; 邓涛
Original assignee: 深圳市大疆创新科技有限公司
Priority date: 2017-06-30
Filing date: 2017-08-03
Publication date: 2019-01-03
Also published as: CN206954494U; CN109923036A

Abstract

A propeller, a power assembly, and an aircraft. The propeller comprises a propeller seat (6) and propeller blades (1) connected to the propeller seat; an attack angle of the propeller blade (1) at a position being 45.8% of the radius of the propeller disk from the center of a propeller disk formed by the propeller (6) is 22.59°±2.5°, and a chord length thereof is 26.98mm±5mm; the attack angle of the propeller blade (1) at a position being 62.5% of the radius of the propeller disk from the center of the propeller disk formed by the propeller (6) is 19.57°±2.5°, and the chord length thereof is 21.91mm±5mm; the attack angle of the propeller blade (1) at a position being 79.2% of the radius of the propeller disk from the center of the propeller disk formed by the propeller (6) is 16.56°±2.5°, and the chord length thereof is 17.64mm±5mm. According to the propeller, the power assembly, and the aircraft, by optimizing the structure of the propeller, the rotation resistance of the propeller can be reduced, so that the flight resistance of the aircraft is further reduced, the flight speed and the flight efficiency of the aircraft are improved, and the flight performance of the aircraft is improved.

Description

Propellers, power components and aircraft

Technical field

The present invention relates to propeller structure technology, and more particularly to a propeller, a power assembly, 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.

In the prior art, 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.

Summary of the invention

The invention provides a propeller, a power component and an aircraft to solve the above-mentioned defects in the prior art to optimize the structure of the propeller and improve the flight performance of the aircraft.

An aspect of the invention provides a propeller comprising a paddle that rotates to form a paddle;

The blade has an angle of attack of 22.59°±2.5° at a distance of 45.8% of the blade radius from the screw, and a chord length of 26.98 mm±5 mm;

The blade has an angle of attack of 19.57°±2.5° at a distance of 62.5% of the paddle radius from the center of the paddle formed by the propeller, and a chord length of 21.91 mm±5 mm;

The blade has an angle of attack of 16.56° ± 2.5° at a distance of 79.2% of the paddle radius from the center of the paddle formed by the propeller, and a chord length of 17.64 mm ± 5 mm.

a propeller as described above, the propeller forming a paddle diameter of 240 mm;

The blade is at a distance of 55 mm from the center of the paddle formed by the propeller The angle of attack is 22.59° and the chord length is 26.98 mm;

The blade has an angle of attack of 19.57° at a distance of 75 mm from the center of the paddle formed by the propeller, and a chord length of 21.91 mm;

The blade has an angle of attack of 16.56° at a distance of 95 mm from the center of the paddle formed by the propeller, and a chord length of 17.64 mm.

a propeller as described above,

The blade has an angle of attack of 24.74° ± 2.5° at a distance of 29.2% of the paddle radius from the center of the paddle formed by the propeller, and a chord length of 33.58 mm ± 5 mm.

The blade has an angle of attack of 24.74° at a distance of 35 mm from the center of the paddle formed by the propeller, and a chord length of 33.58 mm.

a propeller as described above,

The blade has an angle of attack of 12.80° ± 2.5° at a distance of 95.8% of the paddle radius from the center of the paddle formed by the propeller, and a chord length of 13.83 mm ± 5 mm.

The blade has an angle of attack of 12.80° at a distance of 115 mm from the center of the paddle formed by the propeller, and a chord length of 13.83 mm.

In the propeller as described above, 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.

a propeller as described above, the blade comprising an upwardly facing leaf surface, a downwardly facing leaf back, and a first side edge connected between the leaf back and a side of the leaf surface, and a joint a second side edge between the leaf back and the other side of the leaf surface, the first side edge being located below the second side edge; the leaf back and the leaf surface are curved surfaces.

a propeller as described above, comprising at least two blades, the propeller further comprising A paddle of the paddle is connected, the at least two blades being evenly distributed along the circumference of the paddle.

a propeller as described above, the first side edge comprising a curved outwardly convex first arch, the second side edge comprising a curved outwardly projecting second arch; The first arching portion and the second arching portion are both close to an end of the blade connected to the paddle; and the first arching portion protrudes more than the second arching portion The degree of bulging.

The pitch of the propeller as described above is 5.5 inches.

Another aspect of the present invention also provides a power assembly including a drive member and a propeller according to any of the above, the propeller being coupled to the drive member by a paddle.

In the power module as described above, the driving member is a motor having a KV value of 750 to 850 rpm / (minute volt).

Yet another aspect of the present invention provides an aircraft comprising a fuselage, further comprising at least one power assembly as described above, the power assembly being coupled to the fuselage.

The aircraft includes a plurality of the power components, and the steering of the plurality of power components is different.

The propeller, the power assembly and the aircraft provided by the present invention have an angle of attack of 22.59°±2.5° at a distance of 45.8% of the paddle radius from the center of the paddle formed by the propeller, and the chord length is 26.98. Mm ± 5 mm; the blade has an angle of attack of 19.57 ° ± 2.5 ° at a distance of 62.5% of the paddle radius from the center of the paddle formed by the propeller, and a chord length of 21.91 mm ± 5 mm; The angle of attack at the center of the paddle formed with the propeller is 79.2% of the paddle radius, which is 16.56° ± 2.5°, and the chord length is 17.64 mm ± 5 mm. Therefore, the resistance of the propeller during the rotation process can be reduced, the flight resistance during the flight of the aircraft can be reduced, the flight efficiency can be improved, the cruising range can be increased, and the flight performance of the aircraft can be improved.

DRAWINGS

1 is a perspective view of a propeller according to a first embodiment of the present invention;

Figure 2 is a front elevational view of the propeller of Figure 1;

Figure 3 is a left side view of the propeller of Figure 1;

Figure 4 is a schematic cross-sectional view of the propeller of Figure 2 taken along line A-A;

Figure 5 is a schematic cross-sectional view of the propeller of Figure 2 taken along line B-B;

Figure 6 is a schematic cross-sectional view of the propeller of Figure 2 taken along line C-C;

Figure 7 is a schematic cross-sectional view of the propeller of Figure 2 taken along line D-D;

Figure 8 is a schematic cross-sectional view of the propeller of Figure 2 taken along line E-E.

Reference mark:

1-blade; 2-leaf; 3-leaf

4-first side edge; 5-second side edge; 6-paddle holder;

401 - first arched portion; 501 - second arched portion.

Detailed ways

The technical solutions in the embodiments of the present invention will be clearly and completely described in conjunction with the drawings in the embodiments of the present invention. It is a partial embodiment of the invention, and not all of the embodiments. All other embodiments obtained by those skilled in the art based on the embodiments of the present invention without creative efforts are within the scope of the present invention.

It should be noted that when a component is referred to as being "fixed" to another component, it can be directly on the other component or the component can be in the middle. When a component is considered to "connect" another component, it can be directly connected to another component or possibly a central component.

All technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this invention belongs, unless otherwise defined. The terminology used in the description of the present invention is for the purpose of describing particular embodiments and is not intended to limit the invention. The term "and/or" used herein includes any and all combinations of one or more of the associated listed items.

Embodiment 1

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. This implementation In the propeller provided by the example, the paddle and the paddle may be integrally formed, or may be connected to each other by other means, for example, by welding, or may be fixedly connected by a detachable connector, such as a screw connection. Fixed, or connected through other connectors. Here, the embodiment is not specifically limited.

In this embodiment, the propeller may be a positive propeller or a reverse propeller, and 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. In the embodiment, 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.

1 is a perspective view of a blade in a propeller according to a first embodiment of the present invention; FIG. 2 is a front view of the blade of FIG. 1; FIG. 4 is a cross-sectional view of the blade of FIG. Schematic diagram of the middle blade along the BB line; Fig. 6 is a schematic cross-sectional view of the blade along line CC in Fig. 1; Fig. 7 is a schematic cross-sectional view of the blade along line DD in Fig. 1; Fig. 8 is the blade along the EE in Fig. A schematic view of the line. 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.

When the paddle of the propeller provided by the embodiment drives the blade to rotate, the circle formed 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 paddle disk. diameter. For a split blade 1 , 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. For a one-piece propeller, the radius of the paddle is the radius of the propeller.

As shown in FIG. 2 and FIG. 5, the paddle 1 is at a distance of 45.8% of the paddle radius from the center of the paddle formed by the propeller, that is, at a BB cross section from the center L2 of the paddle as shown in FIG. The angle of attack A2 of the blade 1 is 22.59°±2.5°, and the chord length D2 is 26.98 mm±5 mm. Wherein, the chord length is the length of the section of the blade 1 projected in the horizontal direction, and the angle of attack is the angle between the chord and the direction in which the gas flows.

As shown in FIGS. 2 and 6, the blade 1 is at a distance of 62.5% of the paddle radius at the center of the paddle formed with the propeller, that is, at a CC section from the center L3 of the paddle as shown in FIG. The angle of attack A3 of the blade 1 is 19.57°±2.5°, and the chord length D3 is 21.91 mm±5 mm.

As shown in FIGS. 2 and 7, the blade 1 is at a distance of 79.2% of the paddle radius at the center of the paddle formed with the propeller, that is, at a DD cross section from the center L4 of the paddle as shown in FIG. The angle of attack of the blade 1 is 16.56 ° ± 2.5 ° for A4 and 17.64 mm ± 5 mm for the chord length D4.

In the present embodiment, by setting the chord length and the attack angle of the above three sections in the blade 1, 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.

Based on the above technical solutions, 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.

As shown in Fig. 2 and Fig. 4, the paddle 1 is at a distance of 29.2% of the paddle radius at the center of the paddle formed with the propeller, that is, at the AA section of the paddle center L1 as shown in Fig. 2. The angle of attack of the blade 1 is 24.74 ° ± 2.5 °, and the chord length is 33.58 mm ± 5 mm.

As shown in FIGS. 2 and 8, the blade 1 is at a distance of 95.8% of the paddle radius at the center of the paddle formed with the propeller, that is, at an EE cross-section from the center L5 of the paddle as shown in FIG. The angle of attack of the blade 1 is 12.80 ° ± 2.5 °, and the chord length is 13.83 mm ± 5 mm.

Of course, it will be understood by those skilled in the art that the positions of the A-A section, the B-B section, the C-C section, the D-D section, and the E-E section may be slightly changed.

For the above technical solution, the present embodiment provides a specific propeller. The diameter of the paddle formed by the propeller is 240 mm, and the distance from the center of the paddle to the end of the blade 1 is half of the diameter of the paddle, that is, the center of the paddle to the paddle. The distance between the ends of 1 is 115 mm.

Taking the paddle diameter of 240 mm as an example, the blade 1 has an angle of attack of 55.59° at a distance of 55 mm from the center of the paddle formed by the propeller (ie, 50% of 115 mm), and a chord length of 26.98 mm; the blade 1 is in the propeller The formed paddles have a center-to-center distance of 75 mm (ie, 66.7% of 115 mm) with an angle of attack of 19.57° and a chord length of 21.91 mm; the blade 1 is formed with the propeller The center of the paddles is 95 mm apart (ie, 79.2% of 115 mm) with an angle of attack of 16.56° and a chord length of 17.64 mm.

Further, at a distance of 35 mm from the center of the paddle (i.e., 33.3% of 115 mm), the blade 1 has an angle of attack of 24.74° and a chord length of 33.58 mm. At a distance of 115 mm from the center of the paddle (i.e., 100% of 115 mm), the blade 1 has an angle of attack of 12.80 and a chord length of 13.83 mm.

It can be understood that 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. Specifically, the driving component may be a motor, and the rotating shaft of the motor is fixedly connected with the center of the paddle 6 for directly transmitting torque, the driving component can drive the paddle 6 to rotate, and the paddle 6 drives the blade 1 to rotate, thereby generating a thrust. Or lift.

The above-mentioned propeller provided by the present embodiment is tested by comparison with the propeller of the prior art. Referring to Table 1, the tensile force provided by the embodiment is greater at the same rotational speed, that is, at a smaller rotational speed. Underneath, it has a larger pulling force, which increases the power of the propeller, reduces the power loss, and increases the cruising distance. In particular, 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.

Table 1 Comparison parameters of the propeller provided in this embodiment and the prior art

Figure 3 is a left side view of the blade of Figure 1; as shown in Figures 1 to 3, the blade of the propeller in this embodiment may include an upwardly facing leaf back 3, a downward facing leaf surface 2, and a connection a first side edge 4 between the leaf back 3 and one side of the leaf surface 2, and a second side edge 5 connected between the leaf back 3 and the other side of the leaf surface 2, the first side edge 4 is located at the Below the two side edges 5; the leaf back 3 and the leaf surface 2 are curved surfaces.

Among them, the leaf back 3 is the side of the blade 1 during the flight, and the blade 2 is the side of the blade 1 when the aircraft is in flight. As shown in FIG. 1, the leaf back 3 and the leaf surface 2 are curved surfaces, and the tendency to bend is: when the blade 1 as a whole is in a horizontal state, the first side edge 4 is located at a position closer than the second side edge 5 The position is low, so the resistance of the air can be reduced and the pulling force of the blade 1 can be increased.

The first side edge 4 may include a curved outwardly convex first arching portion 401, whereby the pulling force of the blade 1 may be further increased, and the first arching portion 401 and the remaining portion of the first side edge 4 are smoothed Transitional connection. The first arching portion 401 is closer to the end where the blade 1 is connected to the paddle 6 with respect to the longitudinal direction of the blade 1 with respect to the end of the blade 1 away from the paddle 6. The first arch 401 not only arches towards one side of the blade 1 but also arches downwards, ie towards the direction in which the foliage 2 is situated, and can form a smooth transitional connection with the foliage 2 .

The second side edge 5 may include a curved, outwardly projecting second arch 501, whereby the pulling force of the blade 1 may be further increased, and the remaining portions of the second arching portion 501 and the second side edge 5 are Smooth transition connection. The second arched portion 501 is closer to the end of the blade 1 connected to the paddle 6 with respect to the longitudinal direction of the blade 1 with respect to the end of the blade 1 away from the paddle 6.

In the present embodiment, 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. Moreover, the surface of the blade 1 has a smooth transition at each position, and there is no sharp twist, so it has a small stress, and the strength is high and it is not easy to be broken, and the entire propeller has high reliability.

The circle formed by the propeller provided in this embodiment during the rotation process is called a paddle. The center of the circle is called the center of the paddle and the diameter of the circle is called the diameter of the paddle. For a split blade 1 , 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. Thus, 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

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.

After the paddle is connected with the driving member, the driving member can drive the paddle to rotate, and the paddle drives the blade to rotate. The number of blades can be set according to actual needs. The driving component may specifically be a motor, and the KV value of the motor is 750-850 rpm/(minute·volt), wherein the KV value is used to measure the sensitivity of the motor speed to the voltage increase, and the voltage of the motor in this embodiment is When the voltage is increased by 1 volt, the motor speed is increased by 750 to 850 rpm.

The power assembly provided by the embodiment can reduce the resistance of the propeller during the rotation process by setting the chord length and the angle of attack of the three sections in the blade, and improve the flight speed of the aircraft, and is extended under a certain power supply condition. Sailing distance to improve flight performance.

Embodiment 3

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.

It should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, and are not limited thereto; although the present invention has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that The techniques described in the foregoing embodiments Modifications, or equivalents to some of the technical features, are not to be construed as a departure from the spirit and scope of the embodiments of the invention.

Claims

A propeller comprising a blade, wherein the blade rotates to form a paddle;

The blade has an angle of attack of 22.59°±2.5° at a distance of 45.8% of the paddle radius from the center of the paddle formed by the propeller, and a chord length of 26.98 mm±5 mm;

The blade has an angle of attack of 19.57°±2.5° at a distance of 62.5% of the paddle radius from the center of the paddle formed by the propeller, and a chord length of 21.91 mm±5 mm;

The blade has an angle of attack of 16.56° ± 2.5° at a distance of 79.2% of the paddle radius from the center of the paddle formed by the propeller, and a chord length of 17.64 mm ± 5 mm.
The propeller according to claim 1, wherein the propeller has a paddle diameter of 240 mm;

The blade has an angle of attack of 25.59° at a distance of 55 mm from the center of the paddle formed by the propeller, and a chord length of 26.98 mm;

The blade has an angle of attack of 19.57° at a distance of 75 mm from the center of the paddle formed by the propeller, and a chord length of 21.91 mm;

The blade has an angle of attack of 16.56° at a distance of 95 mm from the center of the paddle formed by the propeller, and a chord length of 17.64 mm.
The propeller according to claim 1, wherein

The blade has an angle of attack of 24.74° ± 2.5° at a distance of 29.2% of the paddle radius from the center of the paddle formed by the propeller, and a chord length of 33.58 mm ± 5 mm.
The propeller according to claim 3, wherein the propeller forms a paddle having a diameter of 240 mm;

The blade has an angle of attack of 24.74° at a distance of 35 mm from the center of the paddle formed by the propeller, and a chord length of 33.58 mm.
The propeller according to claim 1, wherein

The blade has an angle of attack of 12.80° ± 2.5° at a distance of 95.8% of the paddle radius from the center of the paddle formed by the propeller, and a chord length of 13.83 mm ± 5 mm.
The propeller according to claim 5, wherein the propeller is formed with a paddle diameter of 240 mm;

The blade has an angle of attack of 12.80° at a distance of 115 mm from the center of the paddle formed by the propeller, and a chord length of 13.83 mm.
The propeller according to claim 1, wherein the number of the blades is two, and the two blades are center-symmetrical with respect to the center of the paddle.
The propeller according to claim 1, wherein a thickness of the blade gradually decreases from an end of the blade near a center of the paddle to an end of the blade away from a center of the paddle.
The propeller according to any one of claims 1 to 8, wherein the blade comprises an upwardly facing leaf surface, a downwardly facing leaf back, and a side connected to the leaf back and the leaf surface a first side edge between and a second side edge connected 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 The back and the leaf surface are curved surfaces.
The propeller according to claim 9, wherein said propeller includes at least two blades, said propeller further comprising a paddle connecting said blades, said at least two blades being circumferentially along said paddle Uniform distribution.
The propeller according to claim 10, wherein said first side edge comprises a curved outwardly convex first arch, said second side edge comprising a curved outwardly convex a second arching portion; the first arching portion and the second arching portion are both adjacent to an end of the blade connected to the paddle; and the first arching portion is convex more than The degree of protrusion of the second arched portion.
A propeller according to any one of claims 1 to 8, wherein the pitch of the propeller is 5.5 inches.
A power assembly characterized by comprising a driving member and a propeller, the driving member being a motor, the motor having a KV value of 750 to 850 rpm / (minute·volt), the propeller including a paddle, the paddle The leaves rotate to form a paddle;

The blade has an angle of attack of 22.59°±2.5° at a distance of 45.8% of the paddle radius from the center of the paddle formed by the propeller, and a chord length of 26.98 mm±5 mm;

The blade has an angle of attack of 19.57°±2.5° at a distance of 62.5% of the paddle radius from the center of the paddle formed by the propeller, and a chord length of 21.91 mm±5 mm;

The blade has an angle of attack of 16.56°±2.5° at a distance of 79.2% of the paddle radius from the center of the paddle formed by the propeller, and a chord length of 17.64 mm±5 mm;

The propeller is coupled to the drive member via a paddle.
The power assembly according to claim 13, wherein the propeller is formed with a paddle diameter of 240 mm;

The blade has an angle of attack of 25.59° at a distance of 55 mm from the center of the paddle formed by the propeller, and a chord length of 26.98 mm;

The blade has an angle of attack of 19.57° at a distance of 75 mm from the center of the paddle formed by the propeller, and a chord length of 21.91 mm;

The blade has an angle of attack of 16.56° at a distance of 95 mm from the center of the paddle formed by the propeller, and a chord length of 17.64 mm.
A power assembly according to claim 13 wherein:

The blade has an angle of attack of 24.74° ± 2.5° at a distance of 29.2% of the paddle radius from the center of the paddle formed by the propeller, and a chord length of 33.58 mm ± 5 mm.
The power assembly according to claim 15, wherein the propeller is formed with a paddle diameter of 240 mm;

The blade has an angle of attack of 24.74° at a distance of 35 mm from the center of the paddle formed by the propeller, and a chord length of 33.58 mm.
A power assembly according to claim 13 wherein:

The blade has an angle of attack of 12.80° ± 2.5° at a distance of 95.8% of the paddle radius from the center of the paddle formed by the propeller, and a chord length of 13.83 mm ± 5 mm.
The power assembly of claim 17 wherein said propeller The formed paddle diameter is 240 mm;

The blade has an angle of attack of 12.80° at a distance of 115 mm from the center of the paddle formed by the propeller, and a chord length of 13.83 mm.
The power assembly of claim 13 wherein the number of blades is two and the two blades are centrally symmetric about the center of the paddle.
The power assembly of claim 13 wherein the thickness of the blade is gradually reduced from an end of the blade adjacent the center of the paddle to an end of the blade remote from the center of the paddle .
A power assembly according to any one of claims 13 to 20, wherein said blade includes an upwardly facing leaf surface, a downwardly facing leaf back, and a first one coupled to said leaf back and said leaf surface a first side edge between the sides and a second side edge connected 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 power assembly of claim 21 wherein said propeller includes at least two blades, said propeller further comprising a paddle connecting said blades, said at least two blades along said paddle The circumferential direction is evenly distributed.
A power assembly according to claim 22, wherein said first side edge comprises a curved outwardly convex first arch, said second side edge comprising a curved outwardly convex a second arching portion; the first arching portion and the second arching portion are both near an end of the blade connected to the paddle; and the degree of protrusion of the first arching portion Greater than the degree of protrusion of the second arch.
A power assembly according to any one of claims 13 to 20, wherein the pitch of the propeller is 5.5 inches.
An aircraft comprising a fuselage, further comprising a power component, the power component comprising a driving member and a propeller, wherein the driving member is a motor, and the motor has a KV value of 750 to 850 rpm / (minute·volt The propeller includes a paddle that rotates to form a paddle;

The blade has an angle of attack of 22.59°±2.5° at a distance of 45.8% of the paddle radius from the center of the paddle formed by the propeller, and a chord length of 26.98 mm±5 mm;

The blade has an angle of attack of 19.57°±2.5° at a distance of 62.5% of the paddle radius from the center of the paddle formed by the propeller, and a chord length of 21.91 mm±5 mm;

The blade has an angle of attack of 16.56°±2.5° at a distance of 79.2% of the paddle radius from the center of the paddle formed by the propeller, and a chord length of 17.64 mm±5 mm;

The propeller is connected to the driving member through a paddle;

The power assembly is coupled to the body.
The aircraft according to claim 25, wherein the propeller forms a paddle having a diameter of 240 mm;

The blade has an angle of attack of 25.59° at a distance of 55 mm from the center of the paddle formed by the propeller, and a chord length of 26.98 mm;

The blade has an angle of attack of 19.57° at a distance of 75 mm from the center of the paddle formed by the propeller, and a chord length of 21.91 mm;

The blade has an angle of attack of 16.56° at a distance of 95 mm from the center of the paddle formed by the propeller, and a chord length of 17.64 mm.
The aircraft of claim 25, wherein

The blade has an angle of attack of 24.74° ± 2.5° at a distance of 29.2% of the paddle radius from the center of the paddle formed by the propeller, and a chord length of 33.58 mm ± 5 mm.
The aircraft according to claim 27, wherein the propeller forms a paddle having a diameter of 240 mm;

The blade has an angle of attack of 24.74° at a distance of 35 mm from the center of the paddle formed by the propeller, and a chord length of 33.58 mm.
The aircraft of claim 25, wherein

The blade has an angle of attack of 12.80° ± 2.5° at a distance of 95.8% of the paddle radius from the center of the paddle formed by the propeller, and a chord length of 13.83 mm ± 5 mm.
The aircraft according to claim 29, wherein the propeller is formed with a paddle diameter of 240 mm;

The blade has an angle of attack of 12.80° at a distance of 115 mm from the center of the paddle formed by the propeller, and a chord length of 13.83 mm.
The aircraft of claim 25 wherein the number of blades is two and the two blades are centrally symmetric about the center of the paddle.
The aircraft according to claim 25, wherein the thickness of the blade gradually decreases 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 aircraft according to any one of claims 25 to 32, wherein the blade comprises an upwardly facing leaf surface, a downwardly facing leaf back, and a side connected to the leaf back and the leaf surface. a first side edge between and a second side edge connected 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 The back and the leaf surface are curved surfaces.
The aircraft according to claim 33, wherein said propeller includes at least two blades, said propeller further comprising a paddle connecting said blades, said at least two blades being circumferentially along said paddle Uniform distribution.
The aircraft according to claim 34, wherein said first side edge comprises a curved outwardly convex first arch, said second side edge comprising a curved outwardly projecting a second arching portion; the first arching portion and the second arching portion are both adjacent to an end of the blade connected to the paddle; and the first arching portion is convex more than The degree of protrusion of the second arched portion.
An aircraft according to any one of claims 25 to 32, wherein the propeller has a pitch of 5.5 inches.