CN219154732U - Paddle, propeller and aircraft - Google Patents
Paddle, propeller and aircraft Download PDFInfo
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- CN219154732U CN219154732U CN202222555210.XU CN202222555210U CN219154732U CN 219154732 U CN219154732 U CN 219154732U CN 202222555210 U CN202222555210 U CN 202222555210U CN 219154732 U CN219154732 U CN 219154732U
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Abstract
The utility model relates to the technical field of aircrafts, in particular to a blade, a propeller and an aircrafts, wherein the blade comprises a blade handle and a blade, the blade handle is provided with a mounting part, and the mounting part is used for being mounted on a rotating mechanism; the first end of the blade is connected to the blade handle, the length of the chord line of the section of the blade is gradually reduced along the first direction, the mounting angle of the section of the blade is gradually reduced, the rotation radius of the blade is 304mm to 310mm, and the relative thickness of the blade is in the range of 6.7% to 8.3%. According to the embodiment of the utility model, the chord length and the mounting angle of the blade section of the blade are designed, and particularly, the chord length and the mounting angle are gradually reduced along the direction from the first end to the second end of the blade, so that the mass of the blade is reduced, the force effect is obviously improved, and the power consumed by generating equal pulling force is obviously reduced.
Description
Technical Field
The utility model relates to the technical field of aircrafts, in particular to a blade, a propeller and an aircraft.
Background
The propeller means a device for converting the rotational power of an engine into propulsive force by rotating blades in air or water, and may have two or more blades connected to a hub, the backward side of the blades being a helicoid or an approximate 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 force effect of the propeller is an important index parameter of the propeller, the force effect refers to the power consumed by the propeller to generate unit weight pulling force, and the force effect has an important influence on the cruising ability of the vertical take-off and landing aircraft. The chord length of the existing propeller is generally distributed in a trapezoid manner along the radial direction, and the installation angle adopts a linear negative torsion mode, so that the propeller is high in mass and low in force effect.
Disclosure of Invention
The utility model provides a blade, a propeller and an aircraft, which can lighten the quality of the blade and improve the force effect of the blade.
In order to solve the technical problems, one technical scheme adopted by the embodiment of the utility model is as follows: providing a paddle, wherein the paddle comprises a blade handle and a blade, the blade handle is provided with a mounting part, and the mounting part is used for being mounted 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 304mm to 310mm, and the relative thickness range of the blade is 6.7% to 8.3%; the cross section of the blade is the cross section of the blade along the second direction, the chord line of the cross section is the connecting line from the front edge of the cross section to the tail edge of the cross section along the second direction, the installation angle of the cross section is the included angle between the chord line and the rotation plane, the rotation plane is the plane where the second end of the blade rotates around the rotation center of the rotation mechanism for one circle, the rotation radius is the radius of a track formed by the second end of the blade rotating around the rotation center of the rotation mechanism for one circle, the first direction is the direction from the first end of the blade to the second end, and the second direction is perpendicular to the first direction.
In some embodiments, the blade has a mounting angle of 17.6 ° to 21.6 ° in cross section at a first distance from the center of rotation; and/or the blade has a mounting angle of 10.9 ° to 14.9 ° in cross section at a second distance from the rotation center; and/or the blade has a mounting angle of 6.5 ° to 10.5 ° in cross section at a third distance from the rotation center; and/or the blade has a mounting angle of 3.9 ° to 7.9 ° in cross section at a fourth distance from the rotation center; and/or the blade has a mounting angle of 2.8 ° to 6.8 ° in cross section at a fifth distance from the rotation center; wherein the first distance, the second distance, the third distance, the fourth distance, and the fifth distance are sequentially increased.
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 43.8mm to 47.8mm; and/or the length of the chord line of the cross section of the blade at a second distance from the rotation center is 36.7mm to 40.7mm; and/or the length of the chord line of the cross section of the blade at a third distance from the centre of rotation is 29.6mm to 33.6mm; and/or the length of the chord line of the cross section of the blade at a fourth distance from the rotation center is 22.0mm to 26.0mm; and/or the length of the chord line of the cross section of the blade at a fifth distance from the centre of rotation is 18.3mm to 22.3mm; wherein the first distance, the second distance, the third distance, the fourth distance, and the fifth distance are sequentially increased.
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 further comprises a leaf surface, a blade back, a first side and a second side, the first side being connected at one end to the leaf surface, the first side being connected at the other end to the blade back, the second side being connected at one end to the leaf surface, the second side being connected at the other end to the blade back.
In some embodiments, the first side includes a curved outwardly convex first arch and the second side includes a curved outwardly convex second arch.
In order to solve the technical problems, another technical scheme adopted by the embodiment of the utility model is as follows: there is provided a propeller comprising a blade as claimed in any one of the preceding claims.
In some embodiments, the device further comprises a rotating mechanism, wherein the rotating mechanism is connected with the mounting part and is used for driving the mounting part to rotate, so that the blade is driven to rotate.
In order to solve the above technical problems, another technical solution adopted by the embodiment of the present utility model is: there is provided an aircraft comprising a propeller as claimed in any one of the preceding claims.
In some embodiments, the aircraft is a vertical takeoff and landing aircraft.
Different from the condition of the related art, the blade, the propeller and the aircraft provided by the embodiment of the utility model have the advantages that the chord length and the mounting angle of the blade section of the blade are designed, and particularly, the chord length and the mounting angle are gradually reduced along the direction from the first end to the second end of the blade, so that the quality of the blade is lightened, the force effect is obviously improved, and the power consumed by generating equal pulling force is obviously reduced.
Drawings
FIG. 1 is a schematic structural view of a blade according to an embodiment of the present utility model;
FIG. 2 is a front view of a blade according to an embodiment of the present utility model;
FIG. 3 is a left side view of a blade according to an embodiment of the present utility model;
FIG. 4 is a top view of a blade according to an embodiment of the present utility model;
FIG. 5 is a schematic view in section A-A of FIG. 2;
FIG. 6 is a schematic view in section B-B of FIG. 2;
FIG. 7 is a schematic view in section C-C of FIG. 2;
FIG. 8 is a schematic view of section D-D of FIG. 2;
fig. 9 is a schematic cross-sectional view of E-E in fig. 2.
Reference numerals in the specific embodiments are as follows:
100. a paddle; 1. a petiole; 11. a mounting part;
2. a blade; 21. leaf surfaces; 22. leaf backs; 23. a first side; 231. a first arch portion; 24. a second side; 241. and a second arch portion.
Detailed Description
In order that the utility model may be readily understood, a more particular description thereof will be rendered by reference to specific embodiments that are illustrated in the appended drawings. It should be understood that the specific embodiments described herein are for purposes of illustration only and are not intended to limit the scope of the utility model. It will be understood that when an element is referred to as being "fixed" to another element, it can be directly on the other element or one or more intervening elements may be present therebetween. When an element is referred to as being "connected" to another element, it can be directly connected to the other element or one or more intervening elements may be present therebetween.
In the description of the present utility model, it should be noted that, orientation words such as "front, rear, upper, lower, left, right", "transverse, vertical, horizontal", and "top, bottom", etc., are generally based on the orientation or positional relationship shown in the drawings, and are merely for convenience of describing the present utility model and simplifying the description, and these orientation words do not indicate or imply that the apparatus or elements being referred to must have a specific orientation or be constructed and operated in a specific orientation, and thus should not be construed as limiting the scope of protection of the present utility model; the orientation word "inner and outer" refers to inner and outer relative to the contour of the respective component itself.
In the description of the present utility model, it should be noted that, the terms "first," "second," and the like are used for defining the components, and are merely for convenience in distinguishing the corresponding components, and the terms have no special meaning unless otherwise stated, so they should not be construed as limiting the scope of the present utility model. In the description of the embodiments of the present application, the meaning of "plurality" is two or more unless explicitly 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 utility model belongs. The terminology used in the description of the utility model herein is for the purpose of describing particular embodiments only and is not intended to be limiting of the utility model. The term "and/or" as used in this specification includes any and all combinations of one or more of the associated listed items.
In addition, the technical features described below in the different embodiments of the present application may be combined with each other as long as they do not collide with each other.
In order to solve the above technical problems, as shown in fig. 1, an embodiment of the present utility model provides a blade 100, where the blade 100 includes a blade stem 1 and a blade 2, the blade stem 1 is used to be mounted on a rotating mechanism (not shown), the rotating mechanism is used to be mounted on an aircraft (not shown), a first end of the blade 2 is connected to the blade stem 1, and the rotating mechanism rotates and drives the blade 100 to rotate, so as to drive the aircraft to ascend, descend, advance, retreat and rotate. In this embodiment, the blade shank 1 and the blade 2 are integrally machined.
Next, the specific structure of the above-described blade lever 1 and blade 2 will be described in order.
As shown in fig. 2, the above-mentioned blade lever 1 is provided with an attachment portion 11, and the attachment portion 11 is attached to a rotation mechanism. In the present embodiment, the mounting portion 11 is a mounting hole, and the blade 100 is mounted to the rotation mechanism by fastening the blade handle 1 to the rotation mechanism through the mounting hole by a bolt.
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, wherein 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 blade 100 is mounted on the rotating mechanism, the blade surface 21 faces the rotating mechanism, the blade back 22 faces the side facing 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 arched portion 231 protruding outwards, and the first arched portion 231 smoothly transitions with other portions of the first side 23; the second side 24 includes a curved outwardly convex second arched portion 241, and the second arched portion 241 is smoothly blended with other portions of the second side 24.
The radius of the locus formed by the rotation of the second end of the blade 2 around the rotation center of the rotation mechanism is the rotation radius, and the direction of the first end of the blade 2 toward the second end is the first direction. Five positions are taken along the first direction according to the distance between the blade 2 and the rotation center, namely a first distance, a second distance, a third distance, a fourth distance and a fifth distance. 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 a section of the blade 2 along the second direction, the chord line of the section is a connecting line from the front edge of the section to the tail edge of the section, and the installation angle of the section is an included angle between the chord line and the rotation plane. The rotation plane is a plane where the second end of the blade 2 rotates around the rotation center of the rotation 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 304mm to 310mm.
As shown in fig. 5, the mounting angle a of the cross section of the blade 2 at the first distance from the rotation center is 17.6 ° to 21.6 °, where the mounting angle a may be any value within the range defined by the above-mentioned values; the length La of the chord line of the section of the blade 2 at a first distance from the centre of rotation is 43.8mm to 47.8mm, where the chord length La may be any value within the range defined by the above-mentioned values.
As shown in fig. 6, the mounting angle b of the cross section of the blade 2 at the second distance from the rotation center is 10.9 ° to 14.9 °, where the mounting angle b may be any value within the range defined by the above-mentioned values; the length Lb of the chord line of the cross section of the blade 2 at a first distance from the centre of rotation is 36.7mm to 40.7mm, where the chord length Lb may be any value within the range defined by the above-mentioned values.
As shown in fig. 7, the mounting angle c of the cross section of the blade 2 at the third distance from the rotation center is 6.5 ° to 10.5 °, where the mounting angle c may be any value within the range defined by the above-mentioned values; the length Lc of the chord line of the section of the blade 2 at a first distance from the centre of rotation is 29.6mm to 33.6mm, where the chord length Lc may be any value within the range defined by the above-mentioned values.
As shown in fig. 8, the mounting angle d of the cross section of the blade 2 at the fourth distance from the rotation center is 3.9 ° to 7.9 °, where the mounting angle d may be any value within the range defined by the above-mentioned values; the chord length Ld of the cross section of the blade 2 at a first distance from the centre of rotation is 22.0mm to 26.0mm, where the chord length Ld may be any value within the range defined by the above-mentioned values.
As shown in fig. 9, the mounting angle e of the cross section of the blade 2 at the fifth distance from the rotation center is 2.8 ° to 6.8 °, where the mounting angle e may be any value within the range defined by the above-mentioned values; the length Le of the chord line of the section of the blade 2 at a first distance from the centre of rotation is 18.3mm to 22.3mm, where the chord length Le may be any value within the range defined by the above-mentioned values.
According to fig. 5 to 9, the length of the chord line of the cross section of the blade 2 becomes gradually smaller and the mounting angle of the cross section of the blade 2 becomes gradually smaller in the first direction, i.e. from the first end to the second section of the blade 2.
The cross section of the blade, i.e. the cross section perpendicular to said first direction, the edges of the cross section comprise an upper and a lower profile, said upper and said lower profile being located at the blade face 21 and the blade back 22 of said blade 2, respectively, and being connected end to end.
The thickness of the blade, i.e. any cross section, is the maximum diameter of a circle with its centre at the chord line and tangential to the upper and lower lines. The relative thickness of the blade is the ratio of the thickness of the blade to the chord length in any cross section.
In the first direction, the relative thickness of the blade 2 is gradually reduced or constant; the relative thickness of the blade 2 is in the range of 6.7 to 8.3% at a radius of rotation greater than or equal to 25% from the center of rotation, and the design of the relative thickness can ensure strength and reduce weight. Wherein the blade 2 is shaped and dimensioned to be smoothly overfed with the shank 1 at a radius of rotation of less than 25% of the blade 2 from the centre of rotation.
By performing aerodynamic performance calculation on the blade 100 satisfying the above conditions by using computational fluid dynamics, the force effect thereof can be obtained by calculating the tensile force generated at a specific rotational speed and the required shaft power. The inventor of the present application found that the blade satisfying the above conditions is significantly improved in force efficiency compared with the conventional blade through CFD verification calculation.
The embodiment of the present utility model further provides a propeller (not shown), where the propeller includes a rotation mechanism (not shown) and the blade 100, the rotation mechanism is connected to the mounting portion 11, and the rotation mechanism is used to drive the mounting portion 11 to rotate, so as to drive the blade 100 to rotate. Further, the diameter of the propeller is 24inch to 24.5inch. The propeller has the technical features and advantageous effects of the blade 100 described above, and will not be described here again.
The embodiment of the utility model also provides an aircraft (not shown), which comprises the propeller. Further, the aircraft is a vertical takeoff and landing aircraft. The aircraft has the technical features and advantages of the blade 100 described above, and are not described in detail here.
According to the blade 100, the propeller and the aircraft, provided by the embodiment of the utility model, the chord length and the mounting angle of the section of the blade 2 of the blade 100 are designed, and particularly, the chord length and the mounting angle are gradually reduced along the direction from the first end to the second end of the blade 2, so that the mass of the blade 100 is lightened, the force effect is obviously improved, and the power consumed by generating equal pulling force is obviously reduced.
It should be noted that the description of the present utility model and the accompanying drawings illustrate preferred embodiments of the present utility model, but the present utility model may be embodied in many different forms and should not be construed as limited to the embodiments set forth herein, which are not to be construed as additional limitations of the utility model, but are provided for a more thorough understanding of the present utility model. The above-described features are further combined with each other to form various embodiments not listed above, and are considered to be the scope of the present utility model described in the specification; further, modifications and variations of the present utility model may be apparent to those skilled in the art in light of the foregoing teachings, and all such modifications and variations are intended to be included within the scope of this utility model as defined in the appended claims.
Claims (10)
1. A blade, comprising:
the blade handle is provided with an installation part which is used for being installed on the rotating mechanism; and
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 304mm to 310mm, and the relative thickness range of the blade is 6.7% to 8.3%;
the cross section of the blade is the cross section of the blade along the second direction, the chord line of the cross section is the connecting line from the front edge of the cross section to the tail edge of the cross section along the second direction, the installation angle of the cross section is the included angle between the chord line and the rotation plane, the rotation plane is the plane where the second end of the blade rotates around the rotation center of the rotation mechanism for one circle, the rotation radius is the radius of a track formed by the second end of the blade rotating around the rotation center of the rotation mechanism for one circle, the first direction is the direction from the first end of the blade to the second end, and the second direction is perpendicular to the first direction.
2. The blade according to claim 1, wherein,
the blade has a mounting angle of 17.6 ° to 21.6 ° in cross section at a first distance from the rotation center;
and/or the blade has a mounting angle of 10.9 ° to 14.9 ° in cross section at a second distance from the rotation center;
and/or the blade has a mounting angle of 6.5 ° to 10.5 ° in cross section at a third distance from the rotation center;
and/or the blade has a mounting angle of 3.9 ° to 7.9 ° in cross section at a fourth distance from the rotation center;
and/or the blade has a mounting angle of 2.8 ° to 6.8 ° in cross section at a fifth distance from the rotation center;
wherein the first distance, the second distance, the third distance, the fourth distance, and the fifth distance are sequentially increased.
3. The blade according to claim 1, wherein,
the length of the chord line of the cross section of the blade at a first distance from the rotation center is 43.8mm to 47.8mm;
and/or the length of the chord line of the cross section of the blade at a second distance from the rotation center is 36.7mm to 40.7mm;
and/or the length of the chord line of the cross section of the blade at a third distance from the centre of rotation is 29.6mm to 33.6mm;
and/or the length of the chord line of the cross section of the blade at a fourth distance from the rotation center is 22.0mm to 26.0mm;
and/or the length of the chord line of the cross section of the blade at a fifth distance from the centre of rotation is 18.3mm to 22.3mm;
wherein the first distance, the second distance, the third distance, the fourth distance, and the fifth distance are sequentially increased.
4. A blade according to claim 2 or 3, wherein,
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. The blade according to claim 1, wherein,
the blade further comprises a blade face, a blade back, a first side edge and a second side edge, one end of the first side edge is connected to the blade face, the other end of the first side edge is connected to the blade back, one end of the second side edge is connected to the blade face, and the other end of the second side edge is connected to the blade back.
6. The blade of claim 5, wherein the blade is configured to move,
the first side edge comprises a curved outwardly convex first arched portion, and the second side edge comprises a curved outwardly convex second arched portion.
7. A propeller is characterized in that,
comprising a blade according to any one of claims 1 to 6.
8. The propeller of claim 7, wherein the propeller is configured to rotate,
the rotary mechanism is connected with the mounting part and used for driving the mounting part to rotate so as to drive the paddles to rotate.
9. An aircraft, characterized in that,
comprising a propeller according to claim 7 or 8.
10. The aircraft of claim 9 wherein the aircraft is configured to,
the aircraft is a vertical take-off and landing aircraft.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202222555210.XU CN219154732U (en) | 2022-09-23 | 2022-09-23 | Paddle, propeller and aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202222555210.XU CN219154732U (en) | 2022-09-23 | 2022-09-23 | Paddle, propeller and aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN219154732U true CN219154732U (en) | 2023-06-09 |
Family
ID=86621279
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202222555210.XU Active CN219154732U (en) | 2022-09-23 | 2022-09-23 | Paddle, propeller and aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN219154732U (en) |
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2022
- 2022-09-23 CN CN202222555210.XU patent/CN219154732U/en active Active
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