CN112249319A

CN112249319A - Paddle, propeller and aircraft

Info

Publication number: CN112249319A
Application number: CN202011097637.9A
Authority: CN
Inventors: 翟占超
Original assignee: Zhuhai Frontier Intelligent Drive Technology Co ltd
Current assignee: Zhuhai Frontier Intelligent Drive Technology Co ltd
Priority date: 2020-10-14
Filing date: 2020-10-14
Publication date: 2021-01-22

Abstract

The invention discloses a paddle which is connected with a fixed seat in the field of aircrafts and aims to improve the flight efficiency and increase the endurance time of the aircrafts, wherein the attack angle of the paddle is 20.4 degrees +/-1 degrees at a position which is 30 percent L +/-3 mm away from the fixed center of the fixed seat, and the chord length of the paddle is 106.5mm +/-3 mm; at the position 50% L +/-3 mm away from the fixed center, the attack angle of the paddle is 14.98 degrees +/-1 degree, and the chord length of the paddle is 91.5mm +/-3 mm; at the position 70% L +/-3 mm away from the fixed center, the attack angle of the paddle is 10.85 degrees +/-1 degrees, and the chord length of the paddle is 75mm +/-3 mm; at the position of 95 percent L +/-3 mm away from the fixed center, the attack angle of the paddle is 7.87 degrees +/-1 degree, and the chord length of the paddle is 50.9mm +/-3 mm; the radius of the paddle is L; by applying the paddle, the flight efficiency can be effectively improved, and the endurance time of the aircraft is increased; the invention also provides a propeller and an aircraft.

Description

Paddle, propeller and aircraft

Technical Field

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

Background

Among the current flying devices, the propeller is an important component for providing thrust to the aircraft, and is used for converting the torque of the power device of the aircraft into the thrust of the aircraft, so as to drive the aircraft to advance.

In the middle of the existing propeller, the profile and the structure are simpler, in the middle of the operation process of the aircraft, the resistance of the propeller is larger, the efficiency is low, the endurance time of the aircraft is shorter, and the expected thrust requirement can not be met during operation.

Disclosure of Invention

The present invention is directed to solving at least one of the problems of the prior art. Therefore, the invention provides the paddle which can improve the flight efficiency and increase the endurance time of the aircraft.

The paddle is connected with the fixed seat, the radius of the paddle is L, the attack angle of the paddle is 20.4 degrees +/-1 degree at the position of 30 percent L +/-3 mm away from the fixed center of the fixed seat, and the chord length of the paddle is 106.5mm +/-3 mm; at the position 50% L +/-3 mm away from the fixed center, the attack angle of the paddle is 14.98 degrees +/-1 degree, and the chord length of the paddle is 91.5mm +/-3 mm; at the position 70% L +/-3 mm away from the fixed center, the attack angle of the paddle is 10.85 degrees +/-1 degrees, and the chord length of the paddle is 75mm +/-3 mm; at 95% L + -3 mm from the fixed center, the attack angle of the blade is 7.87 degrees + -1 degree, and the chord length of the blade is 50.9mm + -3 mm.

According to some embodiments of the invention, the diameter of the blade is 1193.8mm ± 50 mm.

According to some embodiments of the invention, the attack angle of the blade is 20.4 ° and the chord length of the blade is 106.5mm at a distance of 179mm from the fixed center of the holder.

According to some embodiments of the invention, the attack angle of the blade is 14.98 ° and the chord length of the blade is 91.5mm at 298.4mm from the fixed center of the fixed base.

According to some embodiments of the invention, the attack angle of the blade is 10.85 ° and the chord length of the blade is 75mm at 417.8mm from the fixed center of the fixed base.

According to some embodiments of the invention, the angle of attack of the blade is 7.87 ° and the chord length of the blade is 50.9mm at a distance of 567mm from the fixed centre of the holder.

According to some embodiments of the invention, the surface of the blade comprises an upper blade surface and a lower blade surface, the junction of the upper blade surface and the lower blade surface having a leading edge and a trailing edge, the cross-section of the upper blade surface and the cross-section of the lower blade surface both being curved.

According to some embodiments of the invention, the blade is convex at the upper blade surface, the leading edge and the trailing edge.

The propeller comprises a fixed seat and at least two blades, wherein the blades are connected with the fixed seat and are distributed along the circumferential direction of the fixed seat.

The aircraft of the third aspect of the invention comprises a power device and the propeller, wherein the propeller can rotate under the driving of the power device.

According to the experimental result, compared with the propeller in the prior art, the propeller blade has the advantages that under the same test environment and thrust, the current input of the driving motor is obviously reduced, and the power consumption is reduced; and under the condition of adopting the same motor, the maximum thrust of the propeller is obviously increased, and the maneuvering performance of the aircraft is effectively improved.

Additional aspects and advantages of the invention will be set forth in part in the description which follows and, in part, will be obvious from the description, or may be learned by practice of the invention.

Drawings

The above and/or additional aspects and advantages of the present invention will become apparent and readily appreciated from the following description of the embodiments, taken in conjunction with the accompanying drawings of which:

FIGS. 1-3 are schematic views of a blade at different angles in an embodiment of the invention;

FIG. 4 is a front view of a blade in an embodiment of the invention;

FIGS. 5-8 are sectional views in the four directions A-A, B-B, C-C and D-D of FIG. 4, in that order;

the above figures contain the following reference numerals.

Detailed Description

Reference will now be made in detail to embodiments of the present invention, examples of which are illustrated in the accompanying drawings, wherein like or similar reference numerals refer to the same or similar elements or elements having the same or similar function throughout. The embodiments described below with reference to the accompanying drawings are illustrative only for the purpose of explaining the present invention, and are not to be construed as limiting the present invention.

In the description of the present invention, it should be understood that the orientation or positional relationship referred to in the description of the orientation, such as the upper, lower, front, rear, left, right, etc., is based on the orientation or positional relationship shown in the drawings, and is only for convenience of description and simplification of description, and does not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and thus, should not be construed as limiting the present invention.

In the description of the present invention, the meaning of a plurality of means is one or more, the meaning of a plurality of means is two or more, and more than, less than, more than, etc. are understood as excluding the present number, and more than, less than, etc. are understood as including the present number. If the first and second are described for the purpose of distinguishing technical features, they are not to be understood as indicating or implying relative importance or implicitly indicating the number of technical features indicated or implicitly indicating the precedence of the technical features indicated.

In the description of the present invention, unless otherwise explicitly limited, terms such as arrangement, installation, connection and the like should be understood in a broad sense, and those skilled in the art can reasonably determine the specific meanings of the above terms in the present invention in combination with the specific contents of the technical solutions.

Referring to fig. 4 to 8, the blade of the present embodiment is connected to the fixing base, and the shape thereof meets the following conditions:

1. at the position 30% L +/-3 mm away from the fixed center 110 of the fixed seat, the attack angle of the paddle is 20.4 degrees +/-1 degree, and the chord length of the paddle is 106.5mm +/-3 mm;

2. at the position 50% L +/-3 mm away from the fixed center 110, the attack angle of the blade is 14.98 degrees +/-1 degree, and the chord length of the blade is 91.5mm +/-3 mm;

3. at 70% L +/-3 mm from the fixed center 110, the attack angle of the paddle is 10.85 degrees +/-1 degrees, and the chord length of the paddle is 75mm +/-3 mm;

4. at the position of 95 percent L +/-3 mm from the fixed center 110, the attack angle of the paddle is 7.87 degrees +/-1 degree, and the chord length of the paddle is 50.9mm +/-3 mm; wherein the radius of the blade is L.

According to the experimental result, compared with the propeller in the prior art, the propeller blade of the embodiment has the advantages that under the same test environment and thrust, the current input of the driving motor is obviously reduced, and the power consumption is reduced; and under the condition of adopting the same motor, the maximum thrust of the propeller is obviously increased, and the maneuvering performance of the aircraft is effectively improved.

In the present embodiment, the angle of attack is also called angle of attack, which refers to the angle between the advancing direction of the wing (equivalent to the direction of airflow) and the wing chord, and the meaning is the same as the general meaning in the art; and the meaning of chord length also refers to the distance of the leading and trailing edges 230 as is common in the art.

It is noted that in the present embodiment, expressions such as 7.87 ° ± 1 ° and 95% L ± 3mm each refer to an interval rather than to both end points, for example, an angle of attack of a blade of 7.87 ° ± 1 ° refers to any value of an angle of attack of a blade of between 6.87 ° and 8.87 °, and the rest of the expressions are similar.

It should be noted that, in this embodiment, when the entire propeller works, the blades rotate around the center of the fixing base to form a circular paddle disk, and the diameter and radius of the paddle disk are the diameter 2L and radius L of the blades.

In the present embodiment, the diameter 2L of the blade is 1193.8mm + -50 mm.

When the diameter of the paddle is fixed to be 1193.8mm +/-50 mm, 30% L is 179 mm; the attack angle of the blade is 20.4 degrees, and the chord length of the blade is 106.5 mm; that is, the diameter of the blade ranges from 1143.8mm to 1243.8 mm.

Correspondingly, the 50% L is 298.4mm, where the angle of attack of the blade is 14.98 and the chord length of the blade is 91.5 mm.

Similarly, 70% L is 417.8mm, the attack angle of the blade is 10.85 degrees +/-1 degree, and the chord length of the blade is 75mm +/-3 mm.

Further, 95% L is 567mm, the attack angle of the blade is 7.87 degrees at a position 110567mm away from the fixed center of the fixed seat, and the chord length of the blade is 50.9 mm.

As shown in fig. 1 to 3, the blade surface includes an upper blade surface 250 and a lower blade surface 260, the boundary between the upper blade surface 250 and the lower blade surface 260 has a leading edge 220 and a trailing edge 230, and the cross section of the upper blade surface 250 and the cross section of the lower blade surface 260 are both curved surfaces.

Specifically, the blade is convex outward at the upper blade surface 250, the leading edge 220, and the trailing edge 230; these raised portions reduce the vortex formed by the blade tip 240 and reduce the strength of the vortex in the blade tip 240, thereby reducing the air resistance experienced by the blade; here, "outer" refers to a direction directed from the blade body to an external space around the blade.

Regarding other specific structures of the blades, reference may be made to the propeller disclosed in CN108945396A and the related structure of the blades.

In a second aspect of the present embodiment, a propeller is provided, which includes a fixing base and at least two blades as described above, where the at least two blades are connected to the fixing base and circumferentially distributed along the fixing base.

The blades can be fixedly arranged on the fixed seat, or a rotating mechanism can be arranged on the fixed seat, and the blades are arranged on the rotating mechanism, so that the blade pitch can be conveniently adjusted in the flight process; it is of course also possible to use foldable paddles mounted on a stationary seat.

As shown in fig. 1 and 4, when the blade is fixed to the fixing base, the distance from the center of the blade shank 210 of the blade to the fixing center 110 of the fixing base is preferably 50 mm.

In addition, two blades can be symmetrical along the center of the paddle disk and are set into an integrated straight paddle.

The embodiment also provides an aircraft, which comprises a power device and the propeller, wherein the power device can drive the propeller to rotate; the power device can drive the propeller to rotate in various modes, for example, the motor drives the propeller to rotate; or the propeller is driven to rotate by the piston engine or the turbine shaft engine, etc.

Table 1 shows preferred parameters of the blade in this embodiment.

[ TABLE 1 ]

Finally, in order to fully illustrate the beneficial effects brought by the blade of this embodiment, this embodiment uses an experimental method to test the propeller and the conventional propeller of this embodiment, the propeller and the conventional propeller of this embodiment are respectively mounted on a motor, and the tensile force and the motor power are tested, and the test results are shown in table 2.

[ TABLE 2 ]

As can be seen from table 2, with the propeller of the present embodiment, under the same thrust, the power consumption of the motor is greatly reduced, which not only effectively reduces the energy consumption, increases the endurance time, but also reduces the noise generated by the operation of the motor; meanwhile, the maximum tension of the propeller is greatly increased, and the maneuvering performance of the aircraft is effectively improved.

The embodiments of the present invention have been described in detail with reference to the accompanying drawings, but the present invention is not limited to the above embodiments, and various changes can be made within the knowledge of those skilled in the art without departing from the gist of the present invention.

Claims

1. The utility model provides a paddle, is connected with the fixing base, its characterized in that, the radius of paddle is L:

at a position 30% L +/-3 mm away from the fixed center (110) of the fixed seat, the attack angle of the paddle is 20.4 degrees +/-1 degrees, and the chord length of the paddle is 106.5mm +/-3 mm;

at 50% L + -3 mm from the fixed center (110), the angle of attack of the blade is 14.98 ° + -1 °, the chord length of the blade is 91.5mm + -3 mm;

at 70% L + -3 mm from the fixed center (110), the angle of attack of the blade is 10.85 DEG + -1 DEG, and the chord length of the blade is 75mm + -3 mm;

at 95% L + -3 mm from the fixed center (110), the angle of attack of the blade is 7.87 DEG + -1 DEG, and the chord length of the blade is 50.9mm + -3 mm.

2. A blade according to claim 1 wherein the diameter of the blade is 1193.8mm ± 50 mm.

3. A blade according to claim 2, characterized in that the angle of attack of the blade is 20.4 ° and the chord length of the blade is 106.5mm at 179mm from the fixed centre (110) of the holder.

4. A blade according to claim 2, characterized in that the angle of attack of the blade is 14.98 ° and the chord length of the blade is 91.5mm at 298.4mm from the fixed centre (110) of the holder.

5. A blade according to claim 2, characterized in that the angle of attack of the blade is 10.85 ° and the chord length of the blade is 75mm at 417.8mm from the fixed centre (110) of the holder.

6. A blade according to claim 2, characterized in that the angle of attack of the blade is 7.87 ° and the chord length of the blade is 50.9mm at a distance of 567mm from the fixed centre (110) of the holder.

7. The blade according to claim 1 wherein the surface of the blade comprises an upper blade surface (250) and a lower blade surface (260), the interface of the upper blade surface (250) and the lower blade surface (260) having a leading edge (220) and a trailing edge (230), the cross-section of the upper blade surface (250) and the cross-section of the lower blade surface (260) being curved.

8. The blade of claim 7 wherein the blade is outwardly convex at each of the upper blade surface (250), the leading edge (220) and the trailing edge (230).

9. A propeller, comprising:

a fixed seat;

the at least two paddles are connected with the fixed seat and distributed along the circumferential direction of the fixed seat;

the blade is according to any one of claims 1 to 8.

10. An aircraft, characterized in that it comprises:

a power plant;

the propeller of claim 9, being capable of rotation under the drive of said power means.