WO2018157426A1

WO2018157426A1 - Propeller, power assembly and aircraft

Info

Publication number: WO2018157426A1
Application number: PCT/CN2017/078258
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: 2017-02-28
Filing date: 2017-03-27
Publication date: 2018-09-07
Also published as: CN206691356U; CN109641648A

Abstract

A propeller, a power assembly and an aircraft, the propeller comprising a propeller base and a blade (1) connected thereon. The blade (1) has an angle of attack of 14.05°±2.5° and a chord length of 11.94mm±5mm at a position where the distance between the blade (1) and the center of a propeller disk formed by the propeller is 59.32% of the radius of the propeller disk; the blade (1) has an angle of attack of 11.44°±2.5° and a chord length of 10.25mm±5mm at a position where the distance between the blade (1) and the center of the propeller disk formed by the propeller is 76.27% of the radius of the propeller disk; and the blade (1) has an angle of attack of 9.99°±2.5° and a chord length of 8.64mm±5mm at a position where the distance between the blade (1) and the center of the propeller disk formed by the propeller is 93.22% of the radius of the propeller disk. A propeller configured using the described parameters may reduce resistance during the rotation process of the propeller, thereby improving the flight performance of the aircraft.

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 defects in the prior art, reduce the flight resistance of the propeller, improve the flight efficiency of the propeller, and improve the flight performance of the aircraft.

A first aspect of the invention provides a propeller comprising a blade, the blade rotating to form a paddle;

The blade is at an angle of attack of 59.32% of the blade radius at the center of the paddle formed by the propeller, and has an angle of attack of 14.05°±2.5° and a chord length of 11.94 mm±5 mm;

The blade has an angle of attack of 11.44°±2.5° at a distance of 76.27% of the paddle radius from the center of the paddle formed by the propeller, and a chord length of 10.25 mm±5 mm;

The blade has an angle of attack of 93.22% of the paddle radius at the center of the paddle formed by the propeller, and has an angle of attack of 9.99°±2.5° and a chord length of 8.64 mm±5 mm.

A second aspect of the present invention provides a power assembly including a driving member and a propeller, wherein the propeller is coupled to the driving member through a paddle;

The propeller includes a paddle that rotates to form a paddle;

A third aspect of the invention provides an aircraft comprising a fuselage and at least one power component, the power component being coupled to the fuselage;

The power assembly includes: a driving member and a propeller, wherein the propeller is connected to the driving member through a paddle;

The propeller includes a paddle that rotates to form a paddle;

The propeller, the power component and the aircraft provided by the invention have an angle of attack of 14.05°±2.5° at a distance of 59.32% of the paddle radius of the paddle formed by the propeller, and a chord length of 11.94 mm±5 mm; The blade has an angle of attack of 11.44°±2.5° at a distance of 76.27% of the paddle radius from the center of the paddle formed by the propeller, and a chord length of 10.25 mm±5 mm; The center of the paddle formed by the propeller is 93.22% of the blade radius, the angle of attack is 9.99 ° ± 2.5 °, and the chord length is 8.64 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 blade in a propeller according to a first embodiment of the present invention;

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

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

Figure 4 is a right side view of the blade of Figure 1;

Figure 5 is a bottom plan view of the blade of Figure 1;

Figure 6 is a plan view of the blade of Figure 1;

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

Figure 8 is a schematic cross-sectional view of the blade of Figure 2 taken along line B-B;

Figure 9 is a schematic cross-sectional view of the blade of Figure 2 taken along line C-C;

Figure 10 is a schematic cross-sectional view of the blade of Figure 2 taken along line D-D;

Figure 11 is a schematic cross-sectional view of the blade of Figure 2 taken along line E-E.

Reference mark:

1-blade; 2-connecting hole; 3-leaf surface

4-leaf back; 5-first side edge; 6-second side edge;

501 - first arched portion; 601 - second arched portion.

detailed description

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 present. When a component is considered to "connect" another component, it can be directly connected to another component or possibly a central component.

Unless otherwise defined, all technical and scientific terms used herein are the same as Those skilled in the art of the invention generally understand the same meaning. 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.

In this embodiment, the propeller may be a positive propeller or a reverse propeller, and the so-called positive propeller refers to a propeller that rotates clockwise to generate lift from the perspective of the aircraft overlooking; the so-called reverse propeller refers to the perspective of the aircraft from above. a propeller that rotates counterclockwise to produce lift. 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.

In the propeller provided in this embodiment, the paddle and the paddle may be integrally formed, or may be connected to each other by other means, for example, by welding, or may be fixedly connected by a detachable connector, for example. Screwed or fixed, or connected by other connectors. The number of the blades may be one or more, and the plurality of blades may be evenly spaced along the circumferential direction of the paddle. In this embodiment, preferably, the number of the blades is at least two, and at least two blades are along the paddle. The circumferential direction is evenly distributed. The plurality of blades may be integrally formed or may be independent of each other, which is not specifically limited in the present invention.

1 is a perspective view of a blade in a propeller according to a first embodiment of the present invention; FIG. 2 is a front view of the blade shown in FIG. 1; FIG. 3 is a left side view of the blade shown in FIG. Figure 5 is a bottom view of the blade of Figure 1; Figure 6 is a plan view of the blade of Figure 1. As shown in FIGS. 1 to 6, the blade of the propeller in this embodiment may include an upwardly facing leaf back 4, a downwardly facing leaf surface 3, and a side connected to the leaf back 4 and the leaf surface 3 a first side edge 5, and a second side edge 6 connected between the leaf back 4 and the other side of the leaf surface 3, the first side edge 5 being located below the second side edge 6; the leaf back 4 and the leaf surface 3 Both are surfaces.

The leaf back 4 is the side of the blade 1 during the flight, and the blade 3 is the side of the blade 1 during the flight. As shown in Figure 3 and Figure 4, Both the leaf back 4 and the leaf surface 3 are curved surfaces, and the tendency to bend is that when the blade 1 as a whole is in a horizontal state, the first side edge 5 is located lower than the position where the second side edge 6 is located.

The first side edge 5 may comprise a curved, outwardly projecting first bulge 501, the first bulging portion 501 being in a smooth transitional connection with the remainder of the first side edge 5. The first arched portion 501 is closer to the end of the blade 1 connected to the paddle than the end of the blade 1 away from the paddle in the longitudinal direction of the entire blade 1. The first arch 501 not only arches towards one side of the blade 1 but also arches downwards, ie in the direction in which the foliage 3 is situated, and can form a smooth transitional connection with the foliage 3.

The second side edge 6 may include a curved, outwardly projecting second arch 601, the second arching portion 601 being in a smooth transitional connection with the remainder of the second side edge 6. The second arched portion 601 is closer to the end of the blade 1 connected to the paddle than the end of the blade 1 away from the paddle in the longitudinal direction of the entire blade 1.

In the present embodiment, the degree of protrusion of the first arching portion 501 may be greater than the degree of protrusion of the second arching portion 601. The apex of the first arching portion 501 and the apex of the second arching portion 601 are 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 is called a paddle, and the center of the circle is called the center of the paddle, and the diameter of the circle is called the diameter of the paddle. 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.

Figure 7 is a schematic cross-sectional view of the blade of Figure 2 along line AA; Figure 8 is a schematic cross-sectional view of the blade of Figure 2 along line BB; Figure 9 is a schematic cross-sectional view of the blade of Figure 2 along line CC; Figure 10 is a schematic view of Figure 2 Schematic diagram of the middle blade along the DD line; Fig. 11 is a schematic cross-sectional view of the blade of Fig. 2 along the EE line.

As shown in FIGS. 7 to 11, the embodiment can improve the dimensions of the five sections of the blade, wherein the dimensions of the B-B section, the C-C section and the D-D section are advanced. The improvement of the line is the most important.

Specifically, as shown in FIGS. 2 and 8, the blade 1 is at a distance of 59.32% of the paddle radius at the center of the paddle formed with the propeller, that is, a BB section from the center L2 of the paddle as shown in FIG. Where, the angle of attack A2 of the blade 1 is 14.05°±2.5°, and the chord length D2 is 11.94 mm±5 mm; wherein the chord length is the length of the section of the blade 1 projected in the horizontal direction, the angle of attack It is the angle between the chord and the flow direction of the gas.

As shown in FIGS. 2 and 9, the blade 1 is at a distance of 76.27% 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 11.44°±2.5°, and the chord length D3 is 10.25 mm±5 mm.

As shown in FIGS. 2 and 10, the blade 1 is at a center of the paddle formed by the propeller at a distance of 93.22% of the paddle radius, 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 9.99°±2.5° for A4 and 8.64 mm±5 mm for 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 resistance of the propeller during the rotation can be reduced, the flight speed and flight efficiency of the aircraft can be improved, and the power supply can be increased under certain power conditions. The flight distance improves 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. 7, the paddle 1 is at a distance of 42.37% 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. The angle of attack of the blade 1 is 16.61 ° ± 2.5 °, and the chord length is 13.48 mm ± 5 mm.

As shown in FIGS. 2 and 11, the blade 1 is at a distance of 100% of the blade radius at the center of the paddle formed with the propeller, that is, at an EE cross section from the center L5 of the paddle as shown in FIG. The angle of attack of the blade 1 is 9.61 ° ± 2.5 °, and the chord length is 8.34 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 embodiment provides a specific propeller. The diameter of the paddle formed by the propeller is 118 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 at the end of 1 is 59 mm.

Taking the pad diameter of 118 mm as an example, the blade 1 has an angle of attack of 35 mm at the center of the paddle formed by the propeller (ie 59.32% of 59 mm) and a chord length of 11.94 mm; the blade 1 is in the propeller The center of the formed paddle is 45mm (ie, 76.27% of 59mm) with an angle of attack of 11.44° and a chord length of 10.25mm; the blade 1 is 55mm away from the center of the paddle formed by the propeller (ie 59mm) 93.22%) has an angle of attack of 9.99° and a chord length of 8.64 mm.

Further, at a distance of 35 mm from the center of the paddle (ie, 38.9% of 59 mm), the blade 1 has an angle of attack of 16.61° and a chord length of 13.48 mm. At a distance of 59 mm from the center of the paddle (i.e., 100% of 59 mm), the blade 1 has an angle of attack of 9.61° and a chord length of 8.34 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. In this embodiment, the blade 1 may be provided with a connecting hole 2. The paddle 1 can be connected to the paddle through the connecting hole 2, and has a simple structure and is easy to operate.

Further, according to the propeller provided in the present embodiment, the pitch of the blade 1 may be 30 inches, that is, the blade 1 is rotated one revolution, and the theoretical rising distance is 30 inches.

It can be understood that the propeller can also be an integrated paddle, and the length of the entire paddle is 118 mm.

The above-mentioned propeller provided by this embodiment is tested by comparison with the propeller of the prior art. Referring to Table 1, the power of the propeller provided by this embodiment is lower under the same pulling force, that is, at a smaller Under the power condition, it has a larger pulling force, thereby reducing the power loss and increasing the cruising distance.

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

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 2100 rpm/(min·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 the embodiment is increased by 1 Volt, the motor increases by 2100 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 the power components in the aircraft may be one or more. In this embodiment, the number of power components is plural, and the rotational directions of the plurality of power components are different. The aircraft in this embodiment may include three, four, five, six, eight, etc. power components, and thus may be a corresponding number of rotorcraft.

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 Recorded in the foregoing embodiments The technical solutions are modified or equivalently replaced with some of the technical features; and the modifications or substitutions do not deviate from the spirit and scope of the technical solutions of the embodiments of the present invention.

Claims

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

The blade is at an angle of attack of 59.32% of the blade radius at the center of the paddle formed by the propeller, and has an angle of attack of 14.05°±2.5° and a chord length of 11.94 mm±5 mm;

The blade has an angle of attack of 11.44°±2.5° at a distance of 76.27% of the paddle radius from the center of the paddle formed by the propeller, and a chord length of 10.25 mm±5 mm;

The blade has an angle of attack of 93.22% of the paddle radius at the center of the paddle formed by the propeller, and has an angle of attack of 9.99°±2.5° and a chord length of 8.64 mm±5 mm.
The propeller according to claim 1, wherein the propeller has a paddle diameter of 118 mm;

The blade has an angle of attack of 14.05° at a distance of 35 mm from the center of the paddle formed by the propeller, and a chord length of 11.94 mm;

The blade has an angle of attack of 11.44° at a distance of 45 mm from the center of the paddle formed by the propeller, and a chord length of 10.25 mm;

The blade has an angle of attack of 9.99° at a distance of 55 mm from the center of the paddle formed by the propeller, and a chord length of 8.64 mm.
A propeller according to claim 1 or 2, wherein

The blade has an angle of attack of 16.61 ° ± 2.5 ° at a distance of 42.37% of the paddle radius from the center of the paddle formed by the propeller, and a chord length of 13.48 mm ± 5 mm.
The propeller according to claim 3, wherein the propeller forms a paddle having a diameter of 118 mm;

The blade has an angle of attack of 16.61° at a distance of 25 mm from the center of the paddle formed by the propeller, and a chord length of 13.48 mm.
A propeller according to claim 1 or 2, wherein

The blade has an angle of attack of 9.61 ° ± 2.5 ° at a distance of 100% of the paddle radius from the center of the paddle formed by the propeller, and a chord length of 8.34 mm ± 5 mm.
The propeller according to claim 5, wherein the propeller has a paddle diameter of 118 mm;

The blade has an angle of attack of 9.61° at a distance of 59 mm from the center of the paddle formed by the propeller, and a chord length of 8.34 mm.
The propeller of claim 1 wherein said propeller further comprises a paddle, said blade being detachably coupled to said paddle.
The propeller according to claim 1, wherein the number of the blades is at least two, and the at least two blades are evenly distributed along the circumference 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, 2, 4, and 6 to 9, wherein the blade includes an upwardly facing leaf back, a downwardly facing leaf surface, and is coupled to the leaf back and a first side edge between one side of the leaf surface, and a second side edge connected between the leaf back and the other side of the leaf surface, the first side edge being located in the second side Below the side edge; the leaf back and the leaf surface are curved surfaces.
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, 2, 4 and 6 to 9, wherein the propeller has a pitch of 30 inches.
A power assembly, comprising: a driving member and a propeller, wherein the propeller is connected to the driving member through a paddle;

The propeller includes a paddle that rotates to form a paddle;

The blade is at an angle of attack of 59.32% of the blade radius at the center of the paddle formed by the propeller, and has an angle of attack of 14.05°±2.5° and a chord length of 11.94 mm±5 mm;

The blade has an angle of attack of 11.44°±2.5° at a distance of 76.27% of the paddle radius from the center of the paddle formed by the propeller, and a chord length of 10.25 mm±5 mm;

The paddle is at a paddle radius at the center of the paddle formed with the propeller The angle of attack at 93.22% is 9.99 ° ± 2.5 °, and the chord length is 8.64 mm ± 5 mm.
The power assembly according to claim 13, wherein the propeller has a paddle diameter of 118 mm;

The blade has an angle of attack of 14.05° at a distance of 35 mm from the center of the paddle formed by the propeller, and a chord length of 11.94 mm;

The blade has an angle of attack of 11.44° at a distance of 45 mm from the center of the paddle formed by the propeller, and a chord length of 10.25 mm;

The blade has an angle of attack of 9.99° at a distance of 55 mm from the center of the paddle formed by the propeller, and a chord length of 8.64 mm.
A power unit according to claim 13 or 14, wherein

The blade has an angle of attack of 16.61 ° ± 2.5 ° at a distance of 42.37% of the paddle radius from the center of the paddle formed by the propeller, and a chord length of 13.48 mm ± 5 mm.
The power module according to claim 15, wherein the propeller has a paddle diameter of 118 mm;

The blade has an angle of attack of 16.61° at a distance of 25 mm from the center of the paddle formed by the propeller, and a chord length of 13.48 mm.
A power unit according to claim 13 or 14, wherein

The blade has an angle of attack of 9.61 ° ± 2.5 ° at a distance of 100% of the paddle radius from the center of the paddle formed by the propeller, and a chord length of 8.34 mm ± 5 mm.
The power assembly according to claim 17, wherein the propeller has a paddle diameter of 118 mm;

The blade has an angle of attack of 9.61° at a distance of 59 mm from the center of the paddle formed by the propeller, and a chord length of 8.34 mm.
The power assembly of claim 13 wherein said propeller further comprises a paddle, said blade being detachably coupled to said paddle.
The power assembly of claim 13 wherein said number of blades is at least two, said at least two blades being evenly distributed along said circumference of said 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, 14, 16 and 18 to 21, wherein said blade includes an upwardly facing leaf back, a downwardly facing leaf surface, and is coupled to said leaf back And a first side edge between one side of the leaf surface and a second side edge connected between the leaf back and the other side of the leaf surface, the first side edge being located at the Below the two side edges; the leaf back and the leaf surface are curved surfaces.
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 of claims 13, 14, 16 and 18 to 21 wherein the pitch of the propeller is 30 inches.
The power pack according to claim 13, wherein said driving member is a motor having a KV value of 2100 rpm / (minute volt).
An aircraft characterized by comprising a fuselage and at least one power component, the power component being coupled to the fuselage;

The power assembly includes: a driving member and a propeller, wherein the propeller is connected to the driving member through a paddle;

The propeller includes a paddle that rotates to form a paddle;

The blade is at an angle of attack of 59.32% of the blade radius at the center of the paddle formed by the propeller, and has an angle of attack of 14.05°±2.5° and a chord length of 11.94 mm±5 mm;

The blade has an angle of attack of 11.44°±2.5° at a distance of 76.27% of the paddle radius from the center of the paddle formed by the propeller, and a chord length of 10.25 mm±5 mm;

The blade has an angle of attack of 93.22% of the paddle radius at the center of the paddle formed by the propeller, and has an angle of attack of 9.99°±2.5° and a chord length of 8.64 mm±5 mm.
The aircraft according to claim 26, wherein the propeller forms a paddle having a diameter of 118 mm;

The blade has an angle of attack of 14.05° at a distance of 35 mm from the center of the paddle formed by the propeller, and a chord length of 11.94 mm;

The blade has an angle of attack of 11.44° at a distance of 45 mm from the center of the paddle formed by the propeller, and a chord length of 10.25 mm;

The blade has an angle of attack of 9.99° at a distance of 55 mm from the center of the paddle formed by the propeller, and a chord length of 8.64 mm.
An aircraft according to claim 26 or 27, wherein

The blade has an angle of attack of 16.61 ° ± 2.5 ° at a distance of 42.37% of the paddle radius from the center of the paddle formed by the propeller, and a chord length of 13.48 mm ± 5 mm.
The aircraft according to claim 28, wherein the propeller forms a paddle having a diameter of 118 mm;

The blade has an angle of attack of 16.61° at a distance of 25 mm from the center of the paddle formed by the propeller, and a chord length of 13.48 mm.
An aircraft according to claim 26 or 27, wherein

The blade has an angle of attack of 9.61 ° ± 2.5 ° at a distance of 100% of the paddle radius from the center of the paddle formed by the propeller, and a chord length of 8.34 mm ± 5 mm.
The aircraft according to claim 30, wherein the propeller forms a paddle having a diameter of 118 mm;

The blade has an angle of attack of 9.61° at a distance of 59 mm from the center of the paddle formed by the propeller, and a chord length of 8.34 mm.
The aircraft of claim 26 wherein said propeller further comprises a paddle, said blade being detachably coupled to said paddle.
The aircraft according to claim 26, wherein the number of the blades is at least two, and the at least two blades are evenly distributed along the circumference of the paddle.
The aircraft according to claim 26, 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 26, 27, 29 and 31 to 34, wherein the blade includes an upwardly facing leaf back, a downwardly facing leaf surface, and is coupled to the leaf back and a first side edge between one side of the leaf surface, and a second side edge connected between the leaf back and the other side of the leaf surface, the first side edge being located in the second side Below the side edge; the leaf back and the leaf surface are curved surfaces.
The aircraft according to claim 35, wherein said first side edge comprises a curved outwardly projecting 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.
The aircraft according to any one of claims 26, 27, 29 and 31 to 34, wherein the pitch of the propeller is 30 inches.
The aircraft according to claim 26, wherein said driving member is a motor having a KV value of 2100 rpm / (minute volt).
The aircraft of claim 15 wherein said aircraft includes a plurality of power assemblies, said plurality of power assemblies having different directions of rotation.