CN218198801U

CN218198801U - Paddle, propeller and aircraft

Info

Publication number: CN218198801U
Application number: CN202222555207.8U
Authority: CN
Inventors: 李子硕; 梁理达; 吉志鹏; 张捷
Original assignee: Shenzhen Hobbywing Technology Co Ltd
Current assignee: Shenzhen Hobbywing Technology Co Ltd
Priority date: 2022-09-23
Filing date: 2022-09-23
Publication date: 2023-01-03
Anticipated expiration: 2032-09-23

Abstract

The utility model relates to the technical field of aircrafts, in particular to a paddle, a propeller and an aircraft, wherein the paddle comprises a blade handle and blades, the blade handle is provided with an installation part, and the installation part is used for being installed on a rotating mechanism; the first end of the blade is connected with the blade handle, the length of a chord line of the section of the blade is gradually reduced along the first direction, the installation angle of the section of the blade is gradually reduced, the rotation radius of the blade is 682.5mm to 690.0mm, and the relative thickness of the blade ranges from 7.5% to 9.0%. The embodiment of the utility model provides a design through chord length and the angle of erection to the blade cross-section of paddle, especially carry out the distributed design that reduces gradually to chord length and angle of erection along blade first end to second end direction, make the quality of paddle alleviate, the power is imitated and is showing the promotion, and the power that the production equals the pulling force and consumes is showing and descends.

Description

Paddle, propeller and aircraft

Technical Field

The utility model relates to an aircraft technical field especially relates to a paddle, screw and aircraft.

Background

The propeller is a device which rotates in the air or water by means of the blades and converts the rotating power of the engine into propulsive force, two or more blades can be connected with the hub, and the backward surface of each blade is a helicoid or is similar to the helicoid. The propeller is an important power component of the vertical take-off and landing aircraft, and can provide upward lift force and horizontal thrust for the vertical take-off and landing aircraft so as to drive the vertical take-off and landing aircraft to fly.

The power effect of the propeller is an important index parameter of the propeller, and the power effect refers to the power consumed by the propeller to generate unit weight tension and has important influence on the endurance of the VTOL aircraft. The chord length of the existing propeller is generally distributed in a trapezoidal mode along the radius direction, and the installation angle adopts a linear negative torsion mode, so that the propeller is large in mass and low in force effect.

SUMMERY OF THE UTILITY MODEL

The utility model provides a paddle, screw and aircraft can alleviate the quality of paddle, improve the power effect of paddle.

In order to solve the above technical problem, the utility model discloses a technical scheme that embodiment adopted is: providing a paddle, wherein the paddle comprises a blade handle and a blade, the blade handle is provided with an installation part, and the installation part is used for being installed on a rotating mechanism; the first end of the blade is connected with the blade handle, the length of a chord line of the section of the blade is gradually reduced along a first direction, the installation angle of the section of the blade is gradually reduced, the rotation radius of the blade is 682.5mm to 690.0mm, and the relative thickness of the blade ranges from 7.5% to 9.0%; the section of blade is the section of blade along the second direction, the chord line of section is for following the second direction the leading edge of section arrives the line of the trailing edge of section, the contained angle of section is the contained angle between chord line and the rotation plane, the rotation plane is the second end of blade winds the plane at the rotatory centre of rotation of rotary mechanism of a week place, the radius of rotation is the second end of blade winds the radius of the rotatory centre of rotation of rotary mechanism of a week formation's orbit, first direction is the direction of blade first end toward the second end, the second direction with first direction is perpendicular.

In some embodiments, the blade has a cross-sectional stagger angle of 19.0 ° to 23.0 ° at a first distance from the center of rotation; and/or the blade has a section at a second distance from the centre of rotation with an angle of incidence of 12.9 ° to 16.9 °; and/or the blade has a section at a third distance from the rotation center with a stagger angle of 8.5 ° to 12.5 °; and/or the blade has a section at a fourth distance from the centre of rotation with an angle of incidence of 6.5 ° to 10.5 °; and/or the blade has a cross-section at a fifth distance from the centre of rotation with an angle of incidence of 6.0 ° to 10.0 °; wherein the first distance, the second distance, the third distance, the fourth distance, and the fifth distance increase in sequence.

In some embodiments, a chord line of a cross-section of the blade at a first distance from the center of rotation has a length of 81.7mm to 85.7mm; and/or the length of a chord line of a cross section of the blade at a second distance from the center of rotation is 80.4mm to 84.4mm; and/or the length of a chord line of a section of the blade at a third distance from the center of rotation is 63.8mm to 67.8mm; and/or the length of a chord line of a section of the blade at a fourth distance from the center of rotation is 43.6mm to 47.6mm; and/or the length of a chord line of a cross section of the blade at a fifth distance from the center of rotation is 39.2mm to 43.2mm; wherein the first distance, the second distance, the third distance, the fourth distance, and the fifth distance increase in sequence.

In some embodiments, the first distance is 30% of the radius of rotation, the second distance is 50% of the radius of rotation, the third distance is 70% of the radius of rotation, the fourth distance is 90% of the radius of rotation, and the fifth distance is 95% of the radius of rotation.

In some embodiments, the blade still includes blade surface, the leaf back, first side and second side, first side one end connect in the blade surface, the first side other end connect in the leaf back, second side one end connect in the blade surface, the second side other end connect in the leaf back.

In some embodiments, the first side edge includes a curved outwardly convex first arch and the second side edge includes a curved outwardly convex second arch.

In some embodiments, the relative thickness of the vanes is tapered or constant along the first direction.

In order to solve the above technical problem, the utility model discloses another technical scheme that embodiment adopted is: there is provided a propeller comprising a blade as claimed in any one of the preceding claims.

In some embodiments, the paddle further comprises a rotating mechanism, the rotating mechanism is connected with the mounting portion, and the rotating mechanism is used for driving the mounting portion to rotate so as to drive the paddle to rotate.

In order to solve the above technical problem, the embodiment of the present invention adopts another technical solution: there is provided an aircraft comprising a propeller as defined in any one of the preceding claims.

Be different from the condition of correlation technique, the utility model discloses paddle, screw and aircraft through the chord length and the erection angle of the blade cross-section to the paddle design, especially carry out the distributed design that reduces gradually to chord length and erection angle along blade first end to second end direction, make the quality of paddle alleviate, the effect is showing and is promoting, and the power that the production equals that the pulling force consumes is showing and is descending.

Drawings

Fig. 1 is a schematic structural view of a blade according to an embodiment of the present invention;

fig. 2 is a front view of a blade according to an embodiment of the invention;

fig. 3 is a left side view of a blade of an embodiment of the invention;

fig. 4 is a top view of a blade according to an embodiment of the invention;

FIG. 5 isbase:Sub>A schematic cross-sectional view A-A of FIG. 2;

FIG. 6 is a schematic cross-sectional view B-B of FIG. 2;

FIG. 7 is a schematic cross-sectional view C-C of FIG. 2;

FIG. 8 is a schematic cross-sectional view D-D of FIG. 2;

fig. 9 is a schematic cross-sectional view E-E of fig. 2.

The reference numerals in the detailed description are as follows:

100. a paddle; 1. a petiole; 11. an installation part;

2. a blade; 21. leaf surfaces; 22. leaf back; 23. a first side edge; 231. a first arching portion; 24. a second side edge; 241. a second arching portion.

Detailed Description

In order to facilitate understanding of the present invention, the present invention will be described in more detail with reference to the accompanying drawings and specific embodiments. It should be understood that the specific embodiments described herein are for purposes of illustration only and are not intended to limit the invention. It will be understood that when an element is referred to as being "secured to" another element, it can be directly on the other element or intervening elements may also be present. When an element is referred to as being "connected" to another element, it can be directly connected to the other element or intervening elements may be present.

In the description of the present invention, it should be noted that the orientation or positional relationship indicated by the orientation words such as "front, back, up, down, left, right", "horizontal, vertical, horizontal" and "top, bottom", etc. are usually based on the orientation or positional relationship shown in the drawings, and are only for convenience of description and simplification of description, and in the case of not making a contrary explanation, these orientation words do not indicate and imply that the device or element referred to must have a specific orientation or be constructed and operated in a specific orientation, and therefore, should not be interpreted as limiting the scope of the present invention; the terms "inner and outer" refer to the inner and outer relative to the profile of the respective component itself.

In the description of the present invention, it should be noted that the terms "first", "second", etc. are used to define the components, and are only used for the convenience of distinguishing the corresponding components, and if not stated otherwise, the terms do not have special meanings, and therefore, should not be construed as limiting the scope of the present invention. In the description of the embodiments of the present application, "a plurality" means two or more unless specifically defined otherwise.

Unless defined otherwise, 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. The terminology used in the description of the invention herein is for the purpose of describing particular embodiments only and is not intended to be limiting of the invention. As used herein, the term "and/or" includes any and all combinations of one or more of the associated listed items.

In addition, the technical features mentioned in the different embodiments of the present application described below may be combined with each other as long as they do not conflict with each other.

In order to solve the above technical problem, as shown in fig. 1, the embodiment of the present invention provides a blade 100, the blade 100 includes a petiole 1 and a blade 2, the petiole 1 is used for being installed on a rotating mechanism (not shown), the rotating mechanism is used for being installed on an aircraft (not shown), a first end of the blade 2 is connected to the petiole 1, the rotating mechanism rotates and drives the blade 100 to rotate, so as to drive the aircraft to realize ascending, descending, advancing, retreating and rotating. In the present embodiment, the blade shank 1 and the blade 2 are integrally formed.

Next, specific structures of the above-described petiole 1 and blade 2 will be explained in order.

As shown in fig. 2, the blade handle 1 is provided with a mounting portion 11, and the mounting portion 11 is used for mounting to the rotating mechanism. In the present embodiment, the mounting portion 11 is a mounting hole, and is fastened to the rotating mechanism by a bolt passing through the mounting hole to mount the petiole 1 to the rotating mechanism, and thus the paddle 100 to the rotating mechanism.

For the above blade 2, as shown in fig. 2 to 4, the blade 2 includes a blade surface 21, a blade back 22, a first side 23 and a second side 24, one end of the first side 23 is connected to the blade surface 21, the other end of the first side 23 is connected to the blade back 22, one end of the second side 24 is connected to the blade surface 21, the other end of the second side 24 is connected to the blade back 22, when the paddle 100 is installed on the rotating mechanism, the blade surface 21 faces the rotating mechanism, the blade back 22 faces the side away from the rotating mechanism, and both the blade surface 21 and the blade back 22 are curved surfaces.

As shown in fig. 2, the first side 23 includes a curved first arch 231 protruding outward, and the first arch 231 smoothly transitions with the other portion of the first side 23; the second side 24 includes a curved outwardly convex second arch portion 241, and the second arch portion 241 is in smooth transition with the rest of the second side 24.

The radius of a track formed by the second end of the blade 2 rotating around the rotation center of the rotation mechanism is a rotation radius, and the direction from the first end of the blade 2 to the second end is a first direction. Along the first direction, five positions are taken according to the distance from the blade 2 to the rotation center, namely a first distance position, a second distance position, a third distance position, a fourth distance position and a fifth distance position. The distances from the rotation center of the blade 2 at the first distance, the second distance, the third distance, the fourth distance, and the fifth distance are 30%, 50%, 70%, 90%, and 95% of the rotation radius of the blade 2, respectively.

The section of the blade 2 is the section of the blade 2 along the second direction, the chord line of the section is the connecting line from the front edge of the section to the tail edge of the section, and the installation angle of the section is the included angle between the chord line and the rotating plane. The rotating plane is a plane on which the second end of the blade 2 rotates around the rotating center of the rotating mechanism for one circle, and the second direction is perpendicular to the first direction.

In the present embodiment, the radius of rotation of the blade 2 is 682.5mm to 690.0mm.

As shown in fig. 5, the sectional mount angle a of the blade 2 at the first distance from the rotation center is 19.0 ° to 23.0 °, where the mount angle a may be any value within the range defined by the above values; the chord length La of the cross section of the blade 2 at the first distance from the center of rotation is 81.7mm to 85.7mm, and the chord length La may be any value within the range defined by the above values.

As shown in fig. 6, the sectional area of the blade 2 at a second distance from the center of rotation has an installation angle b of 12.9 ° to 16.9 °, where the installation angle b may be any value within the range defined by the above values; the chord length Lb of the cross section of the blade 2 at the first distance from the rotation center may be 80.4mm to 84.4mm, and the chord length Lb may be any value within the range defined by the above values.

As shown in fig. 7, the sectional mount angle c of the blade 2 at a third distance from the rotation center is 8.5 ° to 12.5 °, where the mount angle c may be any value within the range defined by the above values; the length Lc of the chord line of the cross section of the blade 2 at the first distance from the centre of rotation is 63.8mm to 67.8mm, where the chord length Lc can be any value within the range defined by the above values.

As shown in fig. 8, the installation angle d of the cross section of the blade 2 at the fourth distance from the rotation center is 6.5 ° to 10.5 °, where the installation angle d may be any value within the range defined by the above values; the chord length Ld of the cross section of the blade 2 at the first distance from the center of rotation is 43.6mm to 47.6mm, where the chord length Ld may be any value within the range defined by the above values.

As shown in fig. 9, the sectional area of the blade 2 at a fifth distance from the rotation center has an installation angle e of 6.0 ° to 10.0 °, where the installation angle e may be any value within the range defined by the above values; the chord length Le of the cross section of the blade 2 at the first distance from the centre of rotation is 39.2mm to 43.2mm, where the chord length Le can be any value within the range defined by the above values.

According to fig. 5 to 9, in a first direction, i.e. from the first end to the second section of the blade 2, the length of the chord line of the cross section of the blade 2 is gradually reduced and the stagger angle of the cross section of the blade 2 is gradually reduced.

The cross section of the blade is a section perpendicular to the first direction, and the boundary line of the cross section comprises an upper profile line and a lower profile line which are respectively located on the blade surface 21 and the blade back 22 of the blade 2 and are connected end to end.

The thickness of the blade, i.e. the maximum diameter of a circle with its centre at the chord line and tangent to said upper and lower profiles, in any cross-section. The relative thickness of the blade is the ratio of the thickness of the blade to the chord length in any cross section.

Along the first direction, the relative thickness of the blade 2 is gradually reduced or constant; at the position where the distance between the blade 2 and the rotation center is larger than or equal to 25% of the rotation radius, the relative thickness of the blade ranges from 7.5% to 9.0%, and through the design of the relative thickness, the strength can be guaranteed, and the weight can be reduced. Wherein the blade 2 is shaped and dimensioned to smoothly transition from the blade shank 1 at a point where the blade 2 is less than 25% of the radius of rotation from the centre of rotation.

The aerodynamic performance of the blade 100 satisfying the above conditions is calculated by computational fluid dynamics, and the drag force generated at a specific rotational speed and the required shaft power are calculated, thereby obtaining the force effect. The inventor of the application verifies calculation through CFD, finds that the blade meeting the above conditions is remarkably improved in force effect compared with the traditional blade.

The embodiment of the present invention further provides a propeller (not shown), the propeller includes a rotating mechanism (not shown) and the above-mentioned paddle 100, the rotating mechanism is connected to the mounting portion 11, and the rotating mechanism is used for driving the mounting portion 11 to rotate, so as to drive the paddle 100 to rotate. Further, the diameter of the propeller is 53.7inch to 54.3inch. The propeller has the technical features and advantages of the blade 100, and the details are not repeated herein.

The utility model discloses the embodiment still provides an aircraft (not shown), and the aircraft includes foretell screw. Further, the aircraft is a vertical take-off and landing aircraft. The aircraft has the technical features and advantages of the blade 100 described above, and the details are not repeated here.

The utility model discloses paddle 100, screw and aircraft designs through chord length and the erection angle to 2 cross-sections of blade 100's blade, especially carries out the distributed design that reduces gradually to chord length and erection angle along 2 first ends of blade to second end directions, makes the quality of paddle 100 alleviate, and the effect is showing and is promoting, and the power that produces equal pulling force and consume is showing and is descending.

It should be noted that the preferred embodiments of the present invention are described in the specification and the drawings, but the present invention can be realized in many different forms, and is not limited to the embodiments described in the specification, and these embodiments are not provided as additional limitations to the present invention, and are provided for the purpose of making the understanding of the disclosure of the present invention more thorough and complete. Moreover, the above technical features are combined with each other to form various embodiments which are not listed above, and all the embodiments are regarded as the scope of the present invention; further, modifications and variations will occur to those skilled in the art in light of the foregoing description, and it is intended to cover all such modifications and variations as fall within the true spirit and scope of the invention as defined by the appended claims.

Claims

1. A blade, comprising:

the blade handle is provided with a mounting part which is used for mounting the rotating mechanism; and

the first end of the blade is connected to the blade handle, the length of a chord line of the section of the blade is gradually reduced along a first direction, the installation angle of the section of the blade is gradually reduced, the rotation radius of the blade is 682.5mm to 690.0mm, and the relative thickness of the blade ranges from 7.5% to 9.0%;

the cross section of the blade is the cross section of the blade along the second direction, a chord line of the cross section is a connecting line from a front edge of the cross section to a tail edge of the cross section along the second direction, an installation angle of the cross section is an included angle between the chord line and a rotating plane, the rotating plane is a plane where a second end of the blade rotates around a rotating center of the rotating mechanism for a circle, the rotating radius is a radius of a track formed by the second end of the blade rotating around the rotating center of the rotating mechanism for a circle, the first direction is a direction from a first end of the blade to the second end, and the second direction is perpendicular to the first direction.

2. Blade according to claim 1,

a stagger angle of a cross section of the blade at a first distance from the center of rotation is 19.0 ° to 23.0 °;

and/or the blade has a section at a second distance from the centre of rotation with an angle of incidence of 12.9 ° to 16.9 °;

and/or the blade has a section at a third distance from the center of rotation with an angle of incidence of 8.5 ° to 12.5 °;

and/or the blade has a section at a fourth distance from the centre of rotation with an angle of incidence of 6.5 ° to 10.5 °;

and/or the blade has a cross-section at a fifth distance from the centre of rotation with an angle of incidence of 6.0 ° to 10.0 °;

wherein the first distance, the second distance, the third distance, the fourth distance, and the fifth distance increase in order.

3. Blade according to claim 1,

a chord line of a cross section of the blade at a first distance from the center of rotation has a length of 81.7mm to 85.7mm;

and/or the length of a chord line of a cross section of the blade at a second distance from the center of rotation is 80.4mm to 84.4mm;

and/or the length of a chord line of a section of the blade at a third distance from the center of rotation is 63.8mm to 67.8mm;

and/or the length of a chord line of a section of the blade at a fourth distance from the center of rotation is 43.6mm to 47.6mm;

and/or the length of the chord line of the section of the blade at a fifth distance from the rotation center is 39.2mm to 43.2mm;

wherein the first distance, the second distance, the third distance, the fourth distance, and the fifth distance increase in sequence.

4. Blade according to claim 2 or 3,

the first distance is 30% of the radius of rotation, the second distance is 50% of the radius of rotation, the third distance is 70% of the radius of rotation, the fourth distance is 90% of the radius of rotation, and the fifth distance is 95% of the radius of rotation.

5. Blade according to claim 1,

the blade still includes blade surface, the leaf back, first side and second side, first side one end connect in the blade surface, the first side other end connect in the leaf back, second side one end connect in the blade surface, the second side other end connect in the leaf back.

6. Blade according to claim 5,

the first side edge comprises a curved outwardly convex first arching portion, and the second side edge comprises a curved outwardly convex second arching portion.

7. Blade according to any one of claims 1 to 6,

the relative thickness of the blade is gradually reduced or constant along the first direction.

8. A propeller is characterized in that a propeller body is provided with a propeller shaft,

comprising a blade according to any one of claims 1 to 7.

9. The propeller of claim 8,

still include rotary mechanism, rotary mechanism with the installation department is connected, rotary mechanism is used for the drive the installation department rotates to the drive the paddle rotates.

10. An aircraft, characterized in that it comprises, in a plane,

comprising a propeller as claimed in claim 8 or 9.