WO2017070980A1

WO2017070980A1 - Propeller and aircraft

Info

Publication number: WO2017070980A1
Application number: PCT/CN2015/093868
Authority: WO
Inventors: 李晓亮; 梁智颖
Original assignee: 深圳市道通智能航空技术有限公司
Priority date: 2015-10-30
Filing date: 2015-11-05
Publication date: 2017-05-04
Also published as: CN105253295A

Abstract

Provided are a propeller and an aircraft. The propeller (100) comprises a propeller ring (110) and at least two propeller blades (120); when the ratio of the distance from the center of the propeller ring to the radius of the propeller is P, the angle of attack of the propeller blade is β, β being a continuous function concerning the radius ratio P and satisfying the following conditions: when 0≤P≤25％, 10°≤β≤12°; when 25％<P≤90％, 8.75°≤β<12°; when 90％<P≤100％, 8°≤β≤9°. In the propeller, different angles of attack are set for different parts of the propeller blade, reducing aerodynamic drag and improving efficiency, thereby improving the flight speed and flight distance of the aircraft; furthermore, the angle of attack β of the propeller changes continuously, improving the stability of the propeller and thereby improving the flight performance of the aircraft.

Description

Propeller and aircraft

Technical field

The invention relates to the technical field of drones, in particular to a propeller and an aircraft.

Background technique

The propeller is the power component that generates the lift, tension and operating force necessary for the flight of the aircraft. Improving the efficiency of the propeller can greatly improve the flight performance of the aircraft.

The existing propeller has large resistance, low efficiency, and poor stability, 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 present invention aims to provide a propeller having low resistance and high efficiency and an aircraft using the propeller.

In order to solve the above technical problems, the present invention provides the following technical solutions:

In one aspect, the present invention provides a propeller comprising a paddle and at least two blades connected to the paddle, at a ratio P of a radius of the propeller from a center of the paddle, the paddle The angle of attack of the leaf is β, which is a continuous function with respect to the radius ratio P, and satisfies the following conditions: when 0 ≤ P ≤ 25%, 10 ° ≤ β ≤ 12 °; when 25% < P ≤ 90% When, 8.75 ° ≤ β < 12 °; when 90% < P ≤ 100%, 8 ° ≤ β ≤ 9 °.

In some embodiments, the radius ratio P and the angle of attack β may also satisfy the following conditions: when P=25%, β=12°; when P=30%, β=10.75°; when P=40% When β = 10.5 °; when P = 50%, β = 10.25 °; when P = 80%, β = 9 °; when P = 90%, β = 8.75 °.

In some embodiments, the radius ratio P and the angle of attack β may also satisfy the following conditions: when P=95%, β=8°; when P=100%, β=9°.

In some embodiments, the β may be a piecewise function and satisfy the following conditions: β = 8P + 10° when 0 ≤ P ≤ 25%; β = -25P + when 25% < P ≤ 30% 18.25°; when 30%<P≤50%, β=-2.5P+11.5°; when 50%<P≤80%, β=-25P/6+(37°)/3; when 80%< When P ≤ 90%, β = -2.5P + 11 °.

In some embodiments, the β further satisfies the following conditions:

When 90% < P ≤ 95%, β = -15P + 22.5 °, when 95% < P ≤ 100%, β = 20P - 11 °;

Or when 90% < P ≤ 95%, β = 5P + 4.25 °, when 95% < P ≤ 100%, β = -20P + 28 °;

Or when 90% < P ≤ 100%, β = -7.5P + 15.5 °.

In some embodiments, the angle of attack β may be a smooth function, and when 0≤P≤25%, the angle of attack β is the same curve; when 25%<P≤90%, the angle of attack β is a second spline curve; when 90% < P ≤ 95%, the angle of attack β is a third spline curve; when 95% < P ≤ 100%, the angle of attack β is a fourth spline curve.

In some embodiments, the first bar curve, the second spline curve, the third spline curve, and the fourth spline curve may each be a non-uniform rational B-spline curve.

In some embodiments, the paddle may include two oppositely disposed foliates, a first side edge connected between one side of the two foliar faces, and another side connected to the two foliar faces A second side edge between the leaves is a smooth curved surface.

In some embodiments, the first side edge may include a first protruding portion that protrudes outward, and the second side edge may include a second protruding portion that protrudes outward, the first protruding portion. Located at a distance of 20-25% from the center of the paddle to the radius of the propeller, the second protrusion is located at a distance of 20-25 from the center of the paddle to the radius of the propeller. %.

In some embodiments, there may be two blades, the propeller being a 9.4 inch propeller.

In another aspect, the present invention provides an aircraft comprising a fuselage, a flight controller disposed to the fuselage, and a propeller as described above, the flight controller for controlling rotation of the propeller.

Compared with the prior art, the beneficial effects of the present invention are that the propeller of the present invention greatly reduces the air resistance and improves the efficiency while ensuring the lift force by setting different angles of attack at different portions of the blade; The angle of attack β of the propeller is continuously varied, improving the stability of the propeller. By using the propeller, the flight speed and flight distance of the aircraft can be improved, thereby improving the flight performance of the aircraft.

DRAWINGS

In order to more clearly illustrate the technical solution of the present invention, the drawings to be used in the embodiments will be briefly described below. It is understood that the drawings in the following description are only some of the embodiments of the present invention, and those skilled in the art can obtain other drawings based on these drawings without any creative work.

1 is a view in the horizontal direction of a first embodiment of a propeller according to an embodiment of the present invention.

Fig. 2 is a view of the vertical direction of the propeller shown in Fig. 1.

Fig. 3 is a schematic structural view of a second embodiment of a propeller according to an embodiment of the present invention.

Figure 4 is a schematic cross-sectional view of the propeller shown in Figure 2 at A-A.

Figure 5 is a schematic cross-sectional view of the propeller shown in Figure 2 at B-B.

Figure 6 is a schematic cross-sectional view of the propeller shown in Figure 2 at C-C.

Figure 7 is a schematic cross-sectional view of the propeller shown in Figure 2 at D-D.

Fig. 8 is a functional relationship diagram of P-β in the third embodiment of the propeller according to the embodiment of the present invention.

Fig. 9 is a functional relationship diagram of P-β in the fourth embodiment of the propeller according to the embodiment of the present invention.

Fig. 10 is a functional relationship diagram of P-β in the fifth embodiment of the propeller according to the embodiment of the present invention.

Fig. 11 is a functional relationship diagram of P-β in the sixth embodiment of the propeller according to the embodiment of the present invention.

Fig. 12 is a functional relationship diagram of P-β in the seventh embodiment of the propeller according to the embodiment of the present invention.

Figure 13 is a graph showing the relationship of P-? in the eighth embodiment of the propeller according to the embodiment of the present invention.

Figure 14 is a schematic view showing the structure of an aircraft according to an embodiment of the present invention.

detailed description

The technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. It is to be understood that the embodiments described herein are merely illustrative of the invention and are not intended to be limiting.

The existing propeller design has the defects of high resistance and low efficiency in the application, which results in the flight speed of the aircraft is small and the following distance is short, which seriously affects the flight performance of the aircraft. Based on this invention, a novel propeller design scheme is proposed to reduce drag and improve efficiency. For example, when the design of the present invention is applied to a conventional 9.4 inch propeller, a higher efficiency than the existing 9.4 inch propeller can be obtained. However, it should be understood by those skilled in the art that the technical solution of the present invention does not require a specific size and model of the propeller, nor is it limited to a conventional 9.4-inch propeller, but is also applicable to propellers of other sizes and models.

Referring to Figures 1 and 2, an embodiment of the present invention provides a propeller 100 that includes a paddle 110 and at least two blades 120 coupled to the paddles 110. At a distance P from the center of the paddle 110 to the propeller radius, the angle of attack of the blade 120 is β, β=f(P), and a rectangular coordinate system in which the horizontal axis is the P axis and the vertical axis is the β axis can be established. . In the Cartesian coordinate system, β is a continuous function with respect to the radius ratio P, and satisfies the following conditions: when 0 ≤ P ≤ 25%, 10 ° ≤ β ≤ 12 °; when 25% < P ≤ 90%, 8.75 ° ≤ β < 12 °; when 90% < P ≤ 100%, 8 ° ≤ β ≤ 9 °.

The propeller 100 has different angles of attack at different portions of the blade 110 to ensure the same lift At the same time, the air resistance is greatly reduced, the efficiency is improved, and the flying speed and flight distance of the aircraft can be improved. Moreover, the angle of attack β of the propeller 100 is continuously changed, which improves the stability of the propeller 100, thereby improving the flight performance of the aircraft.

Further, the blade 120 includes two oppositely disposed leaf faces 121, a first side edge 122 connected between one side of the two leaf faces 121, and a second side connected between the other sides of the two leaf faces 121. Side edge 123. The leaf surface 121 is a smooth curved surface.

Preferably, the first side edge 122 includes an outwardly convex first protrusion 122a, and the second side edge 123 includes an outwardly protruding second protrusion 123a. The first protrusion 122a is located at a distance from the paddle 110. The center of the propeller radius is 20-25%, and the second protrusion 123a is located at a distance of 20-25% from the center of the paddle 110 to the propeller radius. From the end of the blade 120 near the paddle 110 to the first projection 122a, the width of the blade 120 gradually increases, and the width of the blade gradually increases from the first projection 122a to the end of the blade 120 away from the paddle 110. The width of the paddle 120, which is spaced away from the end of the paddle 120, is minimized.

Referring to FIG. 2, the first embodiment of the present invention is also proposed. In the first embodiment of the embodiment of the present invention, there are two blades 120, and the two blades 120 are centrally symmetric with respect to the center of the paddle 110.

Referring to FIG. 3, a second embodiment of the present invention is also provided. In the second embodiment of the embodiment of the present invention, in other embodiments of the embodiment of the present invention, the blade 120 has three, three blades 120. The center of the paddle 110 is centrally symmetrical.

Referring to FIG. 4 to FIG. 8 , the third embodiment of the present invention further provides that the radius ratio P and the angle of attack β satisfy the following conditions:

When P = 25%, β = 12 °, refer to Figure 4;

When P = 30%, β = 10.75 °;

When P=40%, β=10.5°;

When P=50%, β=10.25°, refer to FIG. 5;

When P=80%, β=9°;

When P = 90%, β = 8.75 °, refer to Figure 6;

When P = 95%, β = 8 °, refer to Figure 7;

When P=100%, β=9°;

When 0 ≤ P ≤ 25%, β = 8P + 10 °;

When 25% < P ≤ 30%, β = -25P + 18.25 °;

When 30% < P ≤ 50%, β = -2.5P + 11.5 °;

When 50% < P ≤ 80%, β = -25P / 6 + (37 °) / 3;

When 80% < P ≤ 90%, β = -2.5P + 11 °;

When 90% < P ≤ 95%, β = -15P + 22.5 °;

When 95% < P ≤ 100%, β = 20P - 11 °.

In the third embodiment of the embodiment of the present invention, the propeller 100 reduces air resistance and improves efficiency by providing different angles of attack at different portions of the blade 110, thereby improving the flight speed and flight distance of the aircraft. Moreover, the angle of attack β of the propeller 100 is continuously changed, which improves the stability of the propeller 100, thereby improving the flight performance of the aircraft. Moreover, the angle of attack β is linearly changed in sections, which improves the manufacturability of the propeller and saves costs.

Referring to FIG. 9, the fourth embodiment of the present invention is further provided. In the fourth embodiment of the present invention, the radius ratio P and the angle of attack β satisfy the following conditions:

When P=25%, β=12°;

When P = 30%, β = 10.75 °;

When P=40%, β=10.5°;

When P=50%, β=10.25°;

When P=80%, β=9°;

When P = 90%, β = 8.75 °;

When P = 95%, β = 9 °;

When P = 100%, β = 8 °;

When 0 ≤ P ≤ 25%, β = 8P + 10 °;

When 25% < P ≤ 30%, β = -25P + 18.25 °;

When 30% < P ≤ 50%, β = -2.5P + 11.5 °;

When 50% < P ≤ 80%, β = -25P / 6 + (37 °) / 3;

When 80% < P ≤ 90%, β = -2.5P + 11 °;

When 90% < P ≤ 95%, β = 5P + 4.25 °;

When 95% < P ≤ 100%, β = -20P + 28°.

In the fourth embodiment of the embodiment of the present invention, the propeller 100 reduces air resistance and improves efficiency by providing different angles of attack at different portions of the blade 110, thereby improving the flight speed and flight distance of the aircraft. Moreover, the angle of attack β of the propeller 100 is continuously changed, which improves the stability of the propeller 100, thereby improving the flight performance of the aircraft. Moreover, the angle of attack β is linearly changed in sections, which improves the manufacturability of the propeller and saves costs.

Referring to FIG. 10, an embodiment of the present invention further provides a fifth embodiment. In the fifth embodiment of the present invention, the radius ratio P and the angle of attack β satisfy the following conditions:

When P=25%, β=12°;

When P = 30%, β = 10.75 °;

When P=40%, β=10.5°;

When P=50%, β=10.25°;

When P=80%, β=9°;

When P = 90%, β = 8.75 °;

When P = 100%, β = 8 °;

When 0 ≤ P ≤ 25%, β = 8P + 10 °;

When 25% < P ≤ 30%, β = -25P + 18.25 °;

When 30% < P ≤ 50%, β = -2.5P + 11.5 °;

When 50% < P ≤ 80%, β = -25P / 6 + (37 °) / 3;

When 80% < P ≤ 90%, β = -2.5P + 11 °;

When 90% < P ≤ 100%, β = -7.5P + 15.5 °.

In the fifth embodiment of the embodiment of the present invention, the propeller 100 reduces air resistance and improves efficiency by providing different angles of attack at different portions of the blade 110, thereby improving the flying speed and flight distance of the aircraft. Moreover, the angle of attack β of the propeller 100 is continuously changed, which improves the stability of the propeller 100, thereby improving the flight performance of the aircraft. Moreover, the angle of attack β is linearly changed in sections, which improves the manufacturability of the propeller and saves costs.

Referring to FIG. 11, a sixth embodiment is also provided in the embodiment of the present invention. In the sixth embodiment of the present invention, the angle of attack β is a smooth function, and the radius ratio P and the angle of attack β satisfy the following conditions:

When P=25%, β=12°;

When P = 30%, β = 10.75 °;

When P=40%, β=10.5°;

When P=50%, β=10.25°;

When P=80%, β=9°;

When P = 90%, β = 8.75 °;

When P = 95%, β = 8 °;

When P=100%, β=9°;

When 0 ≤ P ≤ 25%, the angle of attack β is the same curve, at the starting point, the cutting of the first curve The line is parallel or perpendicular to the β axis (or at any angle to the β axis), at the end point (25%, 12°), the tangent to the first curve is parallel to the P axis, preferably the first curve passes Point (0,10°), (25%, 12°).

When 25% < P ≤ 90%, the angle of attack β is a second spline curve. At the starting point (25%, 12°), the tangent of the second spline curve is parallel to the P axis, at the end point (90%). At 9°), the tangent of the second spline curve is parallel to the P axis. Obviously, the second spline curve passes through the points (25%, 12°), (30%, 10.75°), (40%, 10.5°). ), (50%, 10.25°), (80%, 9°), (90%, 8.75°).

When 90% < P ≤ 95%, the angle of attack β is a third spline curve. At the starting point (90%, 8.75°), the tangent of the third spline curve is parallel to the P axis, at the end point (95%). At 8°), the tangent of the third spline curve is parallel to the P axis. Obviously, the third spline curve passes through the points (90%, 8.75°), (95%, 8°).

When 95% < P ≤ 100%, the angle of attack β is a fourth spline curve. At the starting point (95%, 8°), the tangent of the third spline curve is parallel to the P axis, at the end point (100%). At 9°), the tangent of the third spline curve is parallel or perpendicular to the P axis (or at any angle to the P axis).

In the sixth embodiment of the embodiment of the present invention, the propeller 100 reduces the air resistance by setting different angles of attack at different portions of the blade 110, thereby improving the efficiency and thereby improving the flying speed and the flying distance of the aircraft. Moreover, the angle of attack β of the propeller 100 is continuously changed, which improves the stability of the propeller 100, thereby improving the flight performance of the aircraft. Moreover, the angle of attack β is linearly changed in sections, which improves the manufacturability of the propeller and saves costs.

Referring to FIG. 12, an embodiment of the present invention further provides a seventh embodiment. In the seventh embodiment of the present invention, the angle of attack β is a smooth function, and the radius ratio P and the angle of attack β satisfy the following conditions:

When P=25%, β=12°;

When P = 30%, β = 10.75 °;

When P=40%, β=10.5°;

When P=50%, β=10.25°;

When P=80%, β=9°;

When P = 90%, β = 8.75 °;

When P = 95%, β = 9 °;

When P = 100%, β = 8 °;

When 0 ≤ P ≤ 25%, the angle of attack β is the same curve. At the starting point, the tangent of the first curve is parallel or perpendicular to the β axis (or at any angle to the β axis), at the end point. (25%, 12°), the tangent of the first curve is parallel to the P axis, preferably, the first curve passes the point (0, 10°), (25%, 12°).

When 90% < P ≤ 95%, the angle of attack β is a third spline curve. At the starting point (90%, 8.75°), the tangent of the third spline curve is parallel to the P axis, at the end point (95%). At 9°), the tangent of the third spline curve is parallel to the P axis. Obviously, the third spline curve passes through the points (90%, 8.75°), (95%, 9°).

When 95% < P ≤ 100%, the angle of attack β is a fourth spline curve. At the starting point (95%, 9°), the tangent of the third spline curve is parallel to the P axis, at the end point (100%). At 8°), the tangent of the third spline curve is parallel or perpendicular to the P axis (or at any angle to the P axis).

In the seventh embodiment of the embodiment of the present invention, the propeller 100 reduces air resistance and improves efficiency by providing different angles of attack at different portions of the blade 110, thereby improving the flying speed and flight distance of the aircraft. Moreover, the angle of attack β of the propeller 100 is continuously changed, which improves the stability of the propeller 100, thereby improving the flight performance of the aircraft. Moreover, the angle of attack β is linearly changed in sections, which improves the manufacturability of the propeller and saves costs.

Referring to FIG. 13, an embodiment of the present invention further provides an eighth embodiment. In the eighth embodiment of the present invention, the angle of attack β is a smooth function, and the radius ratio P and the angle of attack β satisfy the following conditions:

When P=25%, β=12°;

When P = 30%, β = 10.75 °;

When P=40%, β=10.5°;

When P=50%, β=10.25°;

When P=80%, β=9°;

When P = 90%, β = 8.75 °;

When P = 100%, β = 8 °;

When 0 ≤ P ≤ 25%, the angle of attack β is the same curve. At the starting point, the tangent of the first curve is parallel or perpendicular to the β axis (or at any angle to the β axis), at the end point. At (25%, 12°), the tangent to the first curve is parallel to the P axis, preferably the first curve passes the point (0, 10°), (25%, 12°).

When 25% < P ≤ 90%, the angle of attack β is a second spline curve. At the starting point (25%, 12°), the tangent of the second spline curve is parallel to the P axis, at the end point (90%). , 9°), the second spline The tangent is parallel to the P axis. Obviously, the second spline passes the point (25%, 12°), (30%, 10.75°), (40%, 10.5°), (50%, 10.25°), (80 %, 9°), (90%, 8.75°).

When 90% < P ≤ 100%, the angle of attack β is a fourth spline curve. At the starting point (90%, 8.75°), the tangent of the third spline curve is parallel to the P axis, at the end point (100%). At 8°), the tangent of the third spline curve is parallel or perpendicular to the P axis (or at any angle to the P axis).

In the eighth embodiment of the embodiment of the present invention, the propeller 100 reduces the air resistance by setting different angles of attack at different portions of the blade 110, thereby improving the efficiency and thus improving the flight speed and flight distance of the aircraft. Moreover, the angle of attack β of the propeller 100 is continuously changed, which improves the stability of the propeller 100, thereby improving the flight performance of the aircraft. Moreover, the angle of attack β is linearly changed in sections, which improves the manufacturability of the propeller and saves costs.

In the above embodiment, the first bar curve, the second spline curve, the third spline curve, and the fourth spline curve are all non-uniform rational B-spline curves. This further facilitates the computer to fit the angle of β, further facilitating the manufacture of the propeller.

Referring to Figure 14, an embodiment of the present invention further provides an aircraft comprising a fuselage 200, a flight control device disposed in the fuselage 200, and the propeller 100 described above, the flight control device for controlling rotation of the propeller 100.

The above is a preferred embodiment of the present invention, and it should be noted that those skilled in the art can also make several improvements and retouchings without departing from the principles of the present invention. It is within the scope of protection of the present invention.

Claims

A propeller, comprising: a paddle and at least two blades connected to the paddle, at a ratio P of a radius of the propeller from a center of the paddle, the paddle The angle of attack is β, which is a continuous function of the radius ratio P and satisfies the following conditions:

When 0 ≤ P ≤ 25%, 10 ° ≤ β ≤ 12 °;

When 25% < P ≤ 90%, 8.75 ° ≤ β < 12 °;

When 90% < P ≤ 100%, 8 ° ≤ β ≤ 9 °.
The propeller according to claim 1, wherein the radius ratio P and the angle of attack β satisfy the following conditions:

When P=25%, β=12°;

When P = 30%, β = 10.75 °;

When P=40%, β=10.5°;

When P=50%, β=10.25°;

When P=80%, β=9°;

When P = 90%, β = 8.75°.
The propeller according to claim 1, wherein the radius ratio P and the angle of attack β satisfy the following conditions:

When P = 95%, β = 8 °;

When P = 100%, β = 9°.
The propeller according to claim 1, wherein said β is a piecewise function and satisfies the following conditions:

When 0 ≤ P ≤ 25%, β = 8P + 10 °;

When 25% < P ≤ 30%, β = -25P + 18.25 °;

When 30% < P ≤ 50%, β = -2.5P + 11.5 °;

When 50% < P ≤ 80%, β = -25P / 6 + (37 °) / 3;

When 80% < P ≤ 90%, β = -2.5P + 11 °.
The propeller according to claim 4, wherein said β further satisfies the following conditions:

When 90% < P ≤ 95%, β = -15P + 22.5 °, when 95% < P ≤ 100%, β = 20P - 11 °;

Or when 90% < P ≤ 95%, β = 5P + 4.25 °, when 95% < P ≤ 100%, β = -20P + 28 °;

Or when 90% < P ≤ 100%, β = -7.5P + 15.5 °.
The propeller according to claim 1, wherein said angle of attack β is a smooth function,

When 0 ≤ P ≤ 25%, the angle of attack β is the same curve;

When 25% < P ≤ 90%, the angle of attack β is a second spline curve;

When 90% < P ≤ 95%, the angle of attack β is a third spline curve;

When 95% < P ≤ 100%, the angle of attack β is a fourth spline curve;

The first bar curve, the second spline curve, the third spline curve and the fourth spline curve are all non-uniform rational B-spline curves.
The propeller according to claim 1, wherein said blade includes two oppositely disposed vanes, a first side edge connected between one side of said two leaf faces, and said two A second side edge between the other side of the leaf surface, the leaf surface being a smooth curved surface.
The propeller according to claim 7, wherein said first side edge comprises a first protruding portion that protrudes outward, and said second side edge comprises a second protruding portion that protrudes outwardly. The first protrusion is located at a ratio of 20-25% of the radius of the propeller from the center of the paddle, and the second protrusion is located at a distance from the center of the paddle to the radius of the propeller The proportion is 20-25%.
The propeller of claim 1 wherein said propeller is a 9.4 inch propeller.
An aircraft characterized by comprising a fuselage, a flight control device disposed on the fuselage, and a propeller according to any one of claims 1-9, the flight control device for controlling rotation of the propeller.