Paddle, propeller and aircraft

Abstract

The embodiment of the utility model relates to the technical field of aircrafts, in particular to a paddle, a propeller and an aircraft, the paddle comprises a paddle handle and a paddle blade, the paddle handle is used for being connected with a paddle seat of the propeller, the paddle blade comprises a blade main body and a blade tip, one end of the blade main body is connected with the paddle handle, and the other end of the blade main body is connected with the propeller. One end of the blade main body is connected with the blade tip, the other end of the blade main body is connected with the blade tip, the chord length of the section of the blade is gradually reduced in the direction from the first distance from the blade to the central axis of the blade seat to the blade tip, and the mounting angle of the section of the blade is gradually reduced; and the section of the paddle blade is the section of the paddle blade in the direction perpendicular to one end of the blade main body to the other end of the blade main body. According to the embodiment of the utility model, the force effect of the paddle can be improved.

Description

Technical Field

[0001] The embodiments of the utility model relate to the technical field of aircraft, and in particular to a blade, a propeller and an aircraft. Background Art

[0002] As the core power component of an aircraft, the performance of a propeller is directly related to the flight performance of the aircraft. A propeller generally includes a propeller seat and at least two blades. One end of the blade is installed on the propeller seat. The propeller is driven to rotate around the central axis of the propeller seat to provide lift or thrust to the aircraft. Therefore, the structure of the blade plays a vital role in the aircraft.

[0003] However, in the process of realizing the utility model, the inventors found that the chord length of the propeller blades currently on the market generally adopts a trapezoidal distribution along the radial direction, and the installation angle of the blade adopts a linear negative torsion. However, the blades with this structural design make the propeller power efficiency low. The power efficiency of a propeller refers to the power consumed by the propeller to generate a unit weight of pulling force. Utility Model Content

[0004] In view of the above problems, the embodiments of the present utility model provide a blade, a propeller and an aircraft, which overcome the above problems or at least partially solve the above problems.

[0005] According to one aspect of an embodiment of the utility model, a blade is provided, comprising a blade handle and a blade, wherein the blade handle is used to be connected to a propeller seat, and the blade comprises a blade body and a blade tip, wherein one end of the blade body is connected to the blade handle, and the other end of the blade body is connected to the blade tip; wherein, at a first distance between the blade and the central axis of the propeller seat, a ratio of a chord length of a cross section of the blade to a rotation radius is 0.105 to 0.125, and the rotation radius is a radius of a rotation plane formed by rotating the blade around the central axis of the propeller seat, and the first distance is 25% of the rotation radius; along the first distance between the blade and the central axis of the propeller seat toward the blade tip, the chord length of the cross section of the blade gradually decreases, and the installation angle of the cross section of the blade gradually decreases, and the cross section of the blade is a cross section of the blade along a direction perpendicular to one end of the blade body toward the other end.

[0006] In some embodiments, at a second distance between the paddle blade and the central axis of the paddle seat, a ratio of a chord length of a cross section of the paddle blade to a rotation radius is 0.1 to 0.12, and the second distance is 37% of the rotation radius;

[0007] And / or, at a third distance between the paddle blade and the central axis of the paddle seat, the ratio of the chord length of the cross section of the paddle blade to the rotation radius is 0.091 to 0.111, and the third distance is 50% of the rotation radius; and / or, at a fourth distance between the paddle blade and the central axis of the paddle seat, the ratio of the chord length of the cross section of the paddle blade to the rotation radius is 0.08 to 0.1, and the fourth distance is 62% of the rotation radius; and / or, at a fifth distance between the paddle blade and the central axis of the paddle seat, the chord length of the cross section of the paddle blade is 0.091 to 0.111, and the third distance is 50% of the rotation radius. The ratio of the chord length of the cross section of the paddle blade to the rotation radius is 0.07 to 0.09, and the fifth distance is 75% of the rotation radius; and / or, at a sixth distance between the paddle blade and the central axis of the paddle seat, the ratio of the chord length of the cross section of the paddle blade to the rotation radius is 0.055 to 0.075, and the sixth distance is 87% of the rotation radius; and / or, at a seventh distance between the paddle blade and the central axis of the paddle seat, the ratio of the chord length of the cross section of the paddle blade to the rotation radius is 0.034 to 0.054, and the seventh distance is 98% of the rotation radius.

[0008] In some embodiments, at the first distance, the installation angle and chord length of the cross-section of the blade are 16° to 20° and 88 mm to 96 mm, respectively.

[0009] In some embodiments, at the second distance, the installation angle and chord length of the cross-section of the blade are 15° to 19° and 84 mm to 92 mm, respectively.

[0010] In some embodiments, at the third distance, the installation angle and chord length of the cross-section of the blade are 12° to 16° and 76 mm to 84 mm, respectively.

[0011] In some embodiments, at the fourth distance, the installation angle and chord length of the cross-section of the paddle blade are 9.5° to 13.5° and 68 mm to 76 mm, respectively; and / or, at the fifth distance, the installation angle and chord length of the cross-section of the paddle blade are 7° to 11° and 60 mm to 68 mm, respectively.

[0012] In some embodiments, at the sixth distance, the installation angle and chord length of the cross-section of the paddle blade are 4.5° to 8.5° and 48 mm to 56 mm, respectively; and / or, at the seventh distance, the installation angle and chord length of the cross-section of the paddle blade are 1.5° to 5.5° and 31 mm to 39 mm, respectively.

[0013] In some embodiments, the rotation radius is 711.2 mm to 889 mm.

[0014] According to one aspect of the embodiments of the utility model, a propeller is provided, comprising a propeller seat and the above-mentioned blades, wherein the blades are mounted on the propeller seat.

[0015] According to one aspect of the embodiments of the utility model, there is provided an aircraft, comprising a fuselage, a drive assembly and the above-mentioned propeller, wherein the drive assembly is connected to the fuselage, and the propeller is connected to the drive assembly.

[0016] The beneficial effects of the embodiment of the utility model are as follows: different from the prior art, the embodiment of the utility model provides a blade, comprising a blade handle and a blade, wherein the blade handle is used to be connected to a propeller seat; the blade comprises a blade body and a blade tip, wherein one end of the blade body is connected to the blade handle, and the other end of the blade body is connected to the blade tip; wherein, at a first distance between the blade and the central axis of the propeller seat, a ratio of a chord length of a cross section of the blade to a rotation radius is 0.105 to 0.125, and the rotation radius is a radius of a rotation plane formed by the blade rotating around the central axis of the propeller seat, and the first distance is 25% of the rotation radius; along the first distance between the blade and the central axis of the propeller seat toward the blade tip, the chord length of the cross section of the blade gradually decreases, and the installation angle of the cross section of the blade gradually decreases, and the cross section of the blade is a cross section of the blade along a direction perpendicular to one end of the blade body toward the other end. The above method can be used to optimize the structural dimensions of the blades, so that when the blades rotate, the pulling force generated at the same rotation speed is increased, thereby improving the force efficiency of the blades. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings required for use in the embodiments of the present application will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present application. For ordinary technicians in this field, other drawings can be obtained based on the drawings without paying creative work.

[0018] Figure 1 It is a front view of the blade provided by the embodiment of the utility model;

[0019] Figure 2 yes Figure 1 A diagram of the annotated blades;

[0020] Figure 3 yes Figure 2 AA section view;

[0021] Figure 4 yes Figure 2 BB cross-sectional view;

[0022] Figure 5 yes Figure 2 CC section view;

[0023] Figure 6 yes Figure 2 DD cross-sectional view;

[0024] Figure 7 yes Figure 2 EE cross-sectional view;

[0025] Figure 8 yes Figure 2 FF cross-sectional view;

[0026] Fig. 9 yes Figure 2 GG cross-sectional view.

[0027] The reference numerals in the specific implementation manner are as follows:

[0028] 100, paddle blade;

[0029] 10. paddle handle; 11. through hole;

[0030] 20. paddle blade; 21. blade body; 22. blade tip; 23. leading edge; 231. first raised portion; 24. trailing edge; 241. second raised portion;

[0031] 30. Connectors. DETAILED DESCRIPTION

[0032] In order to facilitate the understanding of the utility model, the utility model is described in more detail below in conjunction with the accompanying drawings and specific embodiments. It should be noted that when an element is described as "fixed to" another element, it can be directly on the other element, or there can be one or more centered elements therebetween. When an element is described as "connected to" another element, it can be directly connected to the other element, or there can be one or more centered elements therebetween. The terms "vertical", "horizontal", "left", "right" and similar expressions used in this specification are for illustrative purposes only.

[0033] Unless otherwise defined, all technical and scientific terms used in this specification have the same meaning as those commonly understood by technicians in the technical field of the present invention. The terms used in this specification are only for the purpose of describing specific embodiments and are not used to limit the present invention. The term "and / or" used in this specification includes any and all combinations of one or more related listed items.

[0034] The propeller blade is an important power component in the propeller of an aircraft. The propeller blade is installed on the propeller seat and rotates around the central axis of the propeller seat, thereby providing lift or thrust to the aircraft.

[0035] The existing blade chord length is generally distributed in a trapezoidal shape along the radial direction, and the installation angle adopts linear negative torsion, so the propeller force efficiency (ie, the power consumed by the propeller to generate unit weight pulling force) is not high.

[0036] In the embodiment of the present application, the chord length and the installation angle of the cross section of the propeller blade are designed to gradually decrease from a first distance from the propeller blade to the central axis of the propeller seat toward the tip of the blade, so that when the propeller blade rotates, the pulling force generated at the same rotational speed is increased, thereby improving the force efficiency of the blade.

[0037] In order to facilitate readers to understand the inventive concept of the present application, the specific structure of the blade is described below:

[0038] See also Figure 1-2 The blade 100 includes a propeller handle 10 and a propeller blade 20. The propeller blade 20 is connected to the propeller handle 10. The propeller handle 10 is used to connect to a propeller seat of a propeller (not shown) so that the blade 100 is fixed to the propeller seat of the propeller. Driven by the drive assembly of the propeller, the blade 100 can rotate around the central axis S of the propeller seat, thereby generating lift or thrust to drive the aircraft to rise, fall, move forward, retreat, turn or hover.

[0039] In some embodiments, the paddle blade 20 is detachably connected to the paddle handle 10, so that the user can easily replace or repair the paddle blade 20 without interfering with other parts of the aircraft. In actual application, the paddle blade 20 is more easily damaged than the paddle handle 10. Therefore, when the paddle blade 20 is damaged, the cost of replacing the paddle handle 10 at the same time can be saved by only removing and replacing the paddle blade 20. In addition, the propeller seat of the propeller is generally fixedly connected to the paddle handle 10 of at least two blades 100. When the paddle 100 is replaced by removing the paddle handle 10 from the paddle seat, other blades 100 that do not need to be replaced will also be removed, affecting the replacement efficiency. By adopting the method of detachably connecting the paddle blade 20 to the paddle handle 10, the paddle blade 20 of the damaged blade 100 can be quickly replaced, thereby improving the replacement efficiency. Specifically, the paddle blade 20 can be detachably fixed to the paddle handle 10 by screws, buckles or locking structures. For example, a protrusion (not shown) is provided at one end of the paddle blade 20, and a groove (not shown) is provided at the paddle handle 10, and the protrusion is snap-fitted into the groove.

[0040] In some embodiments, the paddle 100 further includes a connector 30, one end of which is connected to one end of the paddle blade 20, and the other end of the connector 30 is connected to the paddle handle 10. When the paddle blade 20 is rotating, the connector 30 can effectively transfer the force and torque generated by the paddle blade 20 to the paddle handle 10, and then to the entire rotating system; in addition, the connector 30 can assist in fixing and positioning the paddle blade 20 on the paddle handle 10, and prevent the paddle blade 20 from deviating or shaking during the rotation process; in addition, the connector 30 can be made of a cushioning material, such as foam The connecting piece 30 is made of foam or rubber material. When the paddle blade 20 is impacted or vibrated, the connecting piece 30 can absorb part of the energy to play a role in buffering and shock absorption. Furthermore, the connecting piece 30 is detachably connected to one end of the paddle blade 20 to facilitate the replacement of the paddle blade 20. For example, the paddle blade 20 can be detachably fixed to the connecting piece 30 by screws, buckles or locking structures. In addition, the connecting piece 30 can be adjusted in position relative to the paddle handle 10, thereby assisting the paddle blade 20 to be adjusted to a certain extent relative to the paddle handle 10 to adapt to different working conditions or requirements.

[0041] For the above-mentioned propeller handle 10, the propeller handle 10 is provided with a through hole 11, and the through hole 11 is used to connect with the fixed shaft of the propeller seat so that the propeller blade 100 is fixed to the propeller seat. In some embodiments, the propeller seat is provided with a screw hole corresponding to the through hole 11, and the bolt of the propeller can pass through the through hole 11 and connect with the screw hole so that the propeller blade 100 is fixed to the propeller seat.

[0042] For the above-mentioned paddle blade 20, the paddle blade 20 includes a blade body 21, a blade tip 22, a leading edge 23 and a trailing edge 24. One end of the blade body 21 is connected to the paddle handle 10, and the other end of the blade body 21 is connected to the blade tip 22. The leading edge 23 is respectively connected to one side of the blade body 21 and one side of the blade tip, and the leading edge 23 is in a curved shape to reduce the air resistance on one side of the blade 100, so that the blade 100 has better pulling force or lift when rotating. The trailing edge 24 is respectively connected to the other side of the blade body 21 and the other side of the blade tip, and the trailing edge 24 is in a curved shape to reduce the air resistance on the other side of the blade 100, so that the blade 100 has better pulling force or lift when rotating.

[0043] In some embodiments, the blade tip 22 bends along the leading edge 23 toward the trailing edge 24 so that when the aircraft is flying, the blade tip 22 can reduce the strength of the tip vortex, thereby reducing the vortex interference of the blade 100, and can also reduce the noise generated when the aircraft is flying. The tip vortex refers to the eddy current formed near the blade tip when the aircraft is flying, and the vortex interference refers to the three-dimensional non-steady-state phenomenon that occurs when the blade 100 and the tip vortex generated by the previous blade 100 approach or collide with each other when the aircraft is flying; the blade tip 22 bends downward along the upper side of the horizontal plane, which is beneficial to offset the spiral trajectory of the tip vortex toward the bottom of the blade 20, thereby reducing the influence of the subsequent blade 100 on the tip vortex formed by the rotation of the previous blade 100, thereby reducing the vortex interference of the subsequent blade 100.

[0044] In some embodiments, the side of the leading edge 23 away from the trailing edge 24 bulges outward to form a first protrusion 231, and the first protrusion 231 is curved, and the first protrusion smoothly transitions with other parts of the leading edge 23 to better reduce the air resistance on the leading edge 23, so that the blade 100 has better pulling force or lift when rotating; the part of the first protrusion 231 close to the propeller handle 10 bulges outward more obviously to better reduce the air resistance on the propeller handle 10; along the direction from the propeller handle 10 to the propeller tip, the cross-sectional area of ​​the first protrusion 231 gradually decreases, so that the strength of the blade 100 close to the propeller handle 10 is enhanced, thereby improving the life of the blade 100, and the cross-section of the first protrusion 231 is the cross-section of the first protrusion 231 along the direction perpendicular to the propeller handle 10 to the blade tip 22. The side of the trailing edge 24 away from the leading edge 23 is convex to form a second protrusion 241, which is in a curved shape and smoothly transitions with the other parts of the trailing edge 24 to better reduce the air resistance of the trailing edge 24. In the part close to the propeller handle 10, the second protrusion 241 is more convex than the first protrusion 231, so that the blade 100 has better pulling force or lifting force when rotating.

[0045] In some embodiments, the blade body 21 is slightly raised above the horizontal plane, and / or the leading edge 23 is slightly raised above the horizontal plane, and / or the trailing edge 24 is slightly raised above the horizontal plane, so as to better reduce the air resistance of the paddle blade 20, so that the paddle blade 100 has better pulling force or lift when rotating.

[0046] In the embodiment of the present application, the blade 100 can rotate around the central axis S of the propeller seat to form a rotation plane, the radius of the rotation plane is the rotation radius R, and the rotation plane is the plane where the blade tip track is located when the blade 100 rotates around the central axis S of the rotating propeller seat. Along the direction from the blade body 21 to the tip 22, the chord length of the cross section of the propeller blade 20 first gradually increases and then gradually decreases, that is, the chord length of the cross section of the propeller blade 20 has a maximum value, and the maximum chord length of the cross section of the propeller blade 20 is close to the propeller handle 10. Along the maximum chord length of the cross section of the propeller blade 20 toward the tip 22, the chord length of the cross section of the propeller blade 20 gradually decreases, and the installation angle of the cross section of the propeller blade 20 gradually decreases, so that when the propeller 100 rotates, the pulling force generated under the same rotation speed state is improved, so that its force efficiency is significantly improved; the chord length of the cross section of the propeller blade 20 gradually decreases, which is conducive to reducing the volume and mass of the propeller blade 20. Among them, the cross-section of the paddle blade 20 is the cross-section of the paddle blade 20 along the direction perpendicular to the blade body 21 to the blade tip 22, the chord length is the length of the line connecting the leading edge 23 to the trailing edge 24 of the cross-section of the paddle blade 20, and the installation angle is the angle between the line connecting the leading edge 23 to the trailing edge 24 of the cross-section of the paddle blade 20 and the rotation plane.

[0047] In this embodiment, the applicant of the utility model has obtained a preferred design embodiment of the above-mentioned blade 20 after a lot of fluid mechanics calculations and creative work, as follows:

[0048] In some embodiments, at a first distance between the paddle blade 20 and the central axis of the paddle seat, a ratio of the chord length of the cross section of the paddle blade 20 to the rotation radius R is 0.105 to 0.125, and the first distance is 25% of the rotation radius R. The ratio here can be any value within the range defined by the above numerical values, and the first distance is greater than the distance between the maximum chord length of the cross section of the paddle blade 20 and the central axis of the paddle seat.

[0049] In some embodiments, at a second distance between the paddle blade 20 and the central axis of the paddle seat, a ratio of the chord length of the cross section of the paddle blade 20 to the rotation radius R is 0.1 to 0.12, and the second distance is 37% of the rotation radius R. The ratio here can be any value within the range defined by the above numerical values.

[0050] In some embodiments, at a third distance between the paddle blade 20 and the central axis of the paddle seat, a ratio of the chord length of the cross section of the paddle blade 20 to the rotation radius R is 0.091 to 0.111, and the third distance is 50% of the rotation radius R. The ratio here can be any value within the range defined by the above numerical values.

[0051] In some embodiments, at a fourth distance between the paddle blade 20 and the central axis of the paddle seat, a ratio of the chord length of the cross section of the paddle blade 20 to the rotation radius R is 0.08 to 0.1, and the fourth distance is 62% of the rotation radius R. The ratio here can be any value within the range defined by the above numerical values.

[0052] In some embodiments, at the fifth distance between the paddle blade 20 and the central axis of the paddle seat, the ratio of the chord length of the cross section of the paddle blade 20 to the rotation radius R is 0.07 to 0.09, and the fifth distance is 75% of the rotation radius R. The ratio here can be any value within the range defined by the above numerical values.

[0053] In some embodiments, at the sixth distance between the paddle blade 20 and the central axis of the paddle seat, the ratio of the chord length of the cross section of the paddle blade 20 to the rotation radius R is 0.055 to 0.075, and the sixth distance is 87% of the rotation radius R. The ratio here can be any value within the range defined by the above numerical values.

[0054] In some embodiments, at the seventh distance between the paddle blade 20 and the central axis of the paddle seat, the ratio of the chord length of the cross section of the paddle blade 20 to the rotation radius R is 0.034 to 0.054, and the seventh distance is 98% of the rotation radius R. The ratio here can be any value within the range defined by the above numerical values.

[0055] In some embodiments, please refer to Figure 3 At the first distance, the installation angle of the cross-section of the blade 20 is 16° to 20°, where the installation angle a can be any value within the range defined by the above numerical values, and the chord length is 88 mm to 96 mm, where the chord length La can be any value within the range defined by the above numerical values, wherein the installation angle a is preferably 18°, and the chord length La is preferably 92 mm.

[0056] In some embodiments, please refer to Figure 4 At the second distance, the installation angle of the cross-section of the blade 20 is 15° to 19°, where the installation angle b can be any value within the range defined by the above numerical values, and the chord length is 84 mm to 92 mm, where the chord length Lb can be any value within the range defined by the above numerical values, wherein the installation angle b is preferably 17°, and the chord length Lb is preferably 88 mm.

[0057] In some embodiments, please refer to Figure 5At the third distance, the installation angle of the cross-section of the blade 20 is 12° to 16°, where the installation angle c can be any value within the range defined by the above numerical values, and the chord length is 76 mm to 84 mm, where the chord length Lc can be any value within the range defined by the above numerical values, wherein the installation angle c is preferably 14°, and the chord length Lc is preferably 80 mm.

[0058] In some embodiments, please refer to Figure 6 At the fourth distance, the installation angle of the cross-section of the blade 20 is 9.5° to 13.5°, where the installation angle d can be any value within the range defined by the above numerical values, and the chord length is 68 mm to 76 mm, where the chord length Ld can be any value within the range defined by the above numerical values, wherein the installation angle d is preferably 11.5°, and the chord length Ld is preferably 72 mm.

[0059] In some embodiments, please refer to Figure 7 At the fifth distance, the installation angle of the cross-section of the blade 20 is 7° to 11°, where the installation angle e can be any value within the range defined by the above numerical values, and the chord length is 60 mm to 68 mm, where the chord length Le can be any value within the range defined by the above numerical values, wherein the installation angle e is preferably 9°, and the chord length Le is preferably 64 mm.

[0060] In some embodiments, please refer to Figure 8 At the sixth distance, the installation angle of the cross-section of the blade 20 is 4.5° to 8.5°, where the installation angle f can be any value within the range defined by the above numerical values, and the chord length is 48 mm to 56 mm, where the chord length Lf can be any value within the range defined by the above numerical values, wherein the installation angle f is preferably 6.5°, and the chord length Lf is preferably 52 mm.

[0061] In some embodiments, please refer to Fig. 9 At the seventh distance, the installation angle of the cross-section of the blade 20 is 1.5° to 5.5°, where the installation angle g can be any value within the range defined by the above numerical values, and the chord length is 31 mm to 39 mm, where the chord length Lg can be any value within the range defined by the above numerical values, wherein the installation angle g is preferably 3.5°, and the chord length Lg is preferably 35 mm.

[0062] In some embodiments, the rotation radius R is 711.2 mm to 889 mm, wherein the rotation radius R is preferably 800.1 mm.

[0063] The applicant of the utility model uses computational fluid dynamics (CFD) to calculate and verify the aerodynamic performance of the blade 100 of the above-designed propeller, calculates the thrust generated by the propeller at a specific speed and the required shaft power, further obtains its force efficiency, and compares and analyzes it with the existing propeller. Through CFD verification calculation, the rotor with the above-mentioned chord length and installation angle distribution law has the highest force efficiency in the design set generated by the design iteration process, that is, it generates equal thrust and consumes the least power.

[0064] Through the above preferred embodiments, the structural dimensions of the blade 100 can be optimized, so that when the blade 100 rotates, the pulling force generated at the same rotation speed is increased, thereby improving the force efficiency of the blade 100. In addition, compared with blades of the same diameter level, the blade 100 of the present application has a small size, light weight and long life.

[0065] In an embodiment of the utility model, a blade 100 includes a propeller handle 10 and a propeller blade 20, wherein the propeller blade 20 includes a blade body 21 and a blade tip 22, wherein one end of the blade body 21 is connected to the propeller handle 10, and the other end of the blade body 21 is connected to the blade tip 22, wherein at a first distance between the propeller blade 20 and the central axis of the propeller seat, a ratio of a chord length of a cross section of the propeller blade 20 to a rotation radius is 0.105 to 0.125; along the direction from the first distance between the propeller blade 20 and the central axis of the propeller seat to the blade tip 22, the chord length of the cross section of the propeller blade 20 gradually decreases, and the installation angle of the cross section of the propeller blade 20 gradually decreases; in the above manner, the structural dimensions of the propeller blade 100 can be optimized, so that when the propeller 100 rotates, the pulling force generated under the same rotation speed state is increased, thereby improving the force efficiency of the propeller 100.

[0066] The utility model also provides a propeller embodiment, which includes a propeller seat and the above-mentioned blade 100, and the propeller handle 10 of the blade 100 is installed on the propeller seat. The function and structure of the blade 100 can be referred to the above embodiment, which will not be described here one by one.

[0067] The utility model also provides an aircraft embodiment, the aircraft includes a fuselage, a drive assembly and the above-mentioned propeller, the drive assembly is connected to the fuselage, the propeller seat of the propeller is connected to the drive assembly, the drive assembly is used to drive the propeller seat to rotate, thereby driving the blades 100 to rotate, thereby generating lift or thrust to drive the aircraft to rise and fall, move forward, retreat, turn or hover.

[0068] It should be noted that the preferred embodiments of the utility model are given in the specification and drawings of the utility model, but the utility model can be implemented in many different forms and is not limited to the embodiments described in the specification. These embodiments are not used as additional restrictions on the content of the utility model. The purpose of providing these embodiments is to make the understanding of the disclosure of the utility model more thorough and comprehensive. In addition, the above-mentioned technical features continue to be combined with each other to form various embodiments not listed above, which are all regarded as the scope of the description of the utility model; further, for ordinary technicians in this field, they can be improved or transformed according to the above description, and all these improvements and transformations should belong to the scope of protection of the claims attached to the utility model.

Claims

1. A blade, characterized in that: include: A propeller handle, the propeller handle being connected to a propeller seat; A paddle blade, comprising a blade body and a blade tip, wherein one end of the blade body is connected to the paddle handle, and the other end of the blade body is connected to the blade tip; A protrusion is provided at one end of the paddle blade, and a groove is provided at the paddle handle, and the protrusion is clamped in the groove; Among them, at a first distance between the paddle blade and the central axis of the paddle seat, a ratio of the chord length of the cross-section of the paddle blade to the rotation radius is 0.105 to 0.125, the rotation radius is the radius of a rotation plane formed by the paddle blade rotating around the central axis of the paddle seat, and the first distance is 25% of the rotation radius; along the first distance from the paddle blade to the central axis of the paddle seat toward the tip of the blade, the chord length of the cross-section of the paddle blade gradually decreases, and the installation angle of the cross-section of the paddle blade gradually decreases, and the cross-section of the paddle blade is a cross-section of the paddle blade along a direction perpendicular to one end of the blade body to the other end.

2. The blade according to claim 1, characterized in that: At a second distance between the blade and the central axis of the blade seat, a ratio of a chord length of a cross section of the blade to a rotation radius is 0.1 to 0.12, and the second distance is 37% of the rotation radius; and / or, at a third distance between the paddle blade and the central axis of the paddle seat, a ratio of a chord length of a cross section of the paddle blade to a rotation radius is 0.091 to 0.111, and the third distance is 50% of the rotation radius; and / or, at a fourth distance between the paddle blade and the central axis of the paddle seat, a ratio of a chord length of a cross section of the paddle blade to a rotation radius is 0.08 to 0.1, and the fourth distance is 62% of the rotation radius; and / or, at a fifth distance between the paddle blade and the central axis of the paddle seat, a ratio of a chord length of a cross section of the paddle blade to a rotation radius is 0.07 to 0.09, and the fifth distance is 75% of the rotation radius; and / or, at a sixth distance between the paddle blade and the central axis of the paddle seat, a ratio of a chord length of a cross section of the paddle blade to a rotation radius is 0.055 to 0.075, and the sixth distance is 87% of the rotation radius; And / or, at a seventh distance between the paddle blade and the central axis of the paddle seat, a ratio of a chord length of a cross section of the paddle blade to a rotation radius is 0.034 to 0.054, and the seventh distance is 98% of the rotation radius.

3. The blade according to claim 2, characterized in that: At the first distance, the installation angle and chord length of the cross section of the paddle blade are 16° to 20° and 88 mm to 96 mm respectively.

4. The blade according to claim 2, characterized in that: At the second distance, the installation angle and chord length of the cross section of the paddle blade are 15° to 19° and 84 mm to 92 mm respectively.

5. The blade according to claim 2, characterized in that: At the third distance, the installation angle and chord length of the cross section of the blade are 12° to 16° and 76 mm to 84 mm respectively.

6. The blade according to claim 2, characterized in that: At the fourth distance, the installation angle and chord length of the cross section of the paddle blade are 9.5° to 13.5° and 68 mm to 76 mm respectively; and / or, At the fifth distance, the installation angle and chord length of the cross section of the blade are 7° to 11° and 60 mm to 68 mm respectively.

7. The blade according to claim 2, characterized in that: At the sixth distance, the installation angle and chord length of the cross section of the paddle blade are 4.5° to 8.5° and 48 mm to 56 mm respectively; and / or, At the seventh distance, the installation angle and chord length of the cross section of the paddle blade are 1.5° to 5.5° and 31 mm to 39 mm respectively.

8. The blade according to any one of claims 1 to 7, characterized in that: The rotation radius is 711.2 mm to 889 mm.

9. A propeller, characterized in that: It comprises a propeller seat and a propeller blade as described in any one of claims 1 to 8, wherein the propeller blade is installed on the propeller seat.

10. An aircraft, characterized in that: It comprises a fuselage, a driving assembly and the propeller according to claim 9, wherein the driving assembly is connected to the fuselage, and the propeller is connected to the driving assembly.

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