Propeller for unmanned aerial vehicle and unmanned aerial vehicle

Abstract

The invention relates to the technical field of unmanned aerial vehicles, and particularly provides a propeller for an unmanned aerial vehicle and the unmanned aerial vehicle. The multiple blades are arranged on the side face of the propeller hub in a circumferential array mode, a plurality of flow guide grooves are formed in the front face of each blade, the distance between each flow guide groove and the front edge of the corresponding blade is smaller than the distance between the flow guide groove and the rear end of the corresponding blade, and the extending direction of each flow guide groove is perpendicular to the front edge of the corresponding blade; according to the propeller, the problems that the application scene of the unmanned aerial vehicle is limited due to the fact that the size of the propeller is increased, and the endurance time of the unmanned aerial vehicle is shortened and the service life of a motor is shortened due to the fact that the rotating speed of the propeller is increased are effectively solved while the maximum lift force of the unmanned aerial vehicle is remarkably enhanced.

Description

Technical Field

[0001] The present application relates to the technical field of unmanned aerial vehicles (UAVs), and in particular to a propeller for an unmanned aerial vehicle (UAV) and the UAV. Background Art

[0002] Drones are widely used in aerial photography, rapid transportation, power inspection, disaster relief, and environmental protection. The relevant technology provides lift for the flight of drones by rotating the propellers of drones. In order to enable drones to fly stably at different altitudes and under different conditions, the relevant technology needs to increase the maximum lift of drones. Specifically, the relevant technology can increase the maximum lift of drones by increasing the size of propellers or increasing the maximum speed of propellers. However, since increasing the size of propellers will increase the overall size of drones, the applicable scenarios of drones will be reduced, and increasing the maximum speed of propellers will increase the power consumption of drones and increase the wear of motors. Therefore, the relevant technology cannot achieve the problem of increasing the maximum lift of drones while avoiding the reduction of the use scenarios of drones or the reduction of the endurance of drones and the shortening of the service life of motors.

[0003] There is no effective technical solution to the above problems. It should be noted that the above information disclosed in this section is only used to understand the background of the present invention, and therefore may contain information that does not constitute prior art. Summary of the invention

[0004] The purpose of the present application is to provide a propeller for a drone and a drone, which can significantly enhance the maximum lift of the drone while effectively avoiding the problems of limited application scenarios of the drone due to the increase in the size of the propeller and reduced flight time of the drone and shortened motor service life due to the increase in the speed of the propeller.

[0005] In a first aspect, the present application provides a propeller for a drone, comprising: Propeller hub; A plurality of blades are arranged in a circular array on the side of the hub, and a plurality of guide grooves are arranged on the front of each blade. The distance between the guide groove and the leading edge of the blade is smaller than the distance between the guide groove and the rear end of the blade, and the extension direction of the guide groove is perpendicular to the leading edge of the blade.

[0006] The present application provides a propeller for a drone, which can increase the lift exerted on the blades when the propeller size and rotation speed are the same by setting a plurality of guide grooves on the front side of each blade and extending in a direction perpendicular to the leading edge of the blade, so as to increase the maximum lift of the drone. That is, the present application can increase the maximum lift of the drone without increasing the size or rotation speed of the propeller. Therefore, the present application can significantly enhance the maximum lift of the drone while effectively avoiding the problems of limited application scenarios of the drone due to increased propeller size and reduced flight time of the drone and shortened motor service life due to increased propeller rotation speed.

[0007] Optionally, branch rib groups are provided on both sides of the guide groove, and each branch rib group includes a plurality of branch ribs inclined toward the rear end of the blade.

[0008] The guide groove of this technical solution is provided with branch rib groups on both sides, and each branch rib group includes a plurality of branch ribs inclined toward the rear end of the blade. The branch ribs can guide the airflow and disperse the airflow to further reduce the friction resistance of the airflow and reduce the turbulence generated by the airflow on the front side of the blade, thereby further increasing the maximum lift of the UAV.

[0009] Optionally, the angle between the extension direction of the branch rib and the extension direction of the guide groove is 30-45°.

[0010] This technical solution can avoid the situation where the drag reduction effect of the branch rib and the effect of reducing the turbulence of the airflow on the front side of the blade are insufficient due to the angle between the extension direction of the branch rib and the extension direction of the guide groove being too small, and the separation or eddy of the airflow on the rear side of the bionic bird feather microstructure due to the angle between the extension direction of the branch rib and the extension direction of the guide groove being too large, the energy loss and resistance of the airflow are increased, and the drag reduction effect of the bionic bird feather microstructure is reduced.

[0011] Optionally, the width of the guide groove is 50-200 μm, the width of the branch rib is 10-30 μm, the length of the branch rib is 50-100 μm, the minimum spacing between adjacent branch ribs in the same branch rib group is 30-50 μm, and the minimum spacing between adjacent guide grooves is 20-200 μm.

[0012] This technical solution can avoid the situation where the drag reduction effect of the bionic bird feather microstructure is reduced due to the minimum spacing between adjacent guide grooves being too large, and the fluid retention area is increased and the friction resistance of the airflow is increased due to the minimum spacing between adjacent guide grooves being too small, by setting the minimum spacing between adjacent guide grooves to 20-200μm.

[0013] Optionally, a plurality of drag increasing groove groups are provided on the reverse side of each blade, the arrangement direction of the drag increasing groove groups is perpendicular to the leading edge of the blade, and each drag increasing groove group includes a plurality of drag increasing grooves extending in a direction parallel to the leading edge of the blade.

[0014] Since the extension direction of the drag-increasing groove of the technical solution is parallel to the leading edge of the blade, that is, the gas flow direction is perpendicular to the drag-increasing groove, the drag-increasing groove can disrupt the flow direction of the airflow, cause lateral disturbances in the airflow and increase the vortex effect, so as to increase the airflow friction resistance on the back of the blade, that is, the technical solution is equivalent to forming a plurality of tiny retention areas on the back of the blade so that part of the airflow stagnates in the retention area. Therefore, the technical solution can reduce the airflow velocity on the back of the blade and increase the pressure on the back of the blade when the propeller size and speed are the same by arranging a plurality of drag-increasing grooves on the back of the blade, so as to increase the pressure difference between the front and back sides of the blade, thereby further increasing the maximum lift of the UAV.

[0015] Optionally, the length of the resistance increasing groove is 10-50 μm, and the width of the resistance increasing groove is 5-150 μm.

[0016] Optionally, the drag-increasing groove has a vertical surface and an inclined surface, the vertical surface is perpendicular to the back surface of the blade, the inclined surface is located on the side of the vertical surface close to the leading edge of the blade, and the angle between the vertical surface and the inclined surface is 30-60°.

[0017] Optionally, the depth of the drag increasing groove close to the leading edge of the blade is smaller than the depth of the drag increasing groove far from the leading edge of the blade.

[0018] Optionally, the minimum spacing between adjacent resistance increasing groove groups is 20-200 μm, and the minimum spacing between adjacent resistance increasing grooves in the same resistance increasing groove group is 20-200 μm.

[0019] In a second aspect, the present application also provides a drone, which includes a propeller for a drone provided in the first aspect above.

[0020] The present application provides a drone that can increase the lift exerted on the blades when the propeller size and rotation speed are the same by arranging a plurality of guide grooves on the front side of each blade whose extension direction is perpendicular to the leading edge of the blade, so as to increase the maximum lift of the drone. That is, the present application can increase the maximum lift of the drone without increasing the size or rotation speed of the propeller. Therefore, the present application can significantly enhance the maximum lift of the drone while effectively avoiding the problems of limited application scenarios of the drone due to increased propeller size and reduced flight time of the drone and shortened motor service life due to increased propeller rotation speed.

[0021] From the above, it can be seen that the propeller and drone provided by the present application can increase the lift exerted on the blades when the propeller size and rotation speed are the same by setting multiple guide grooves on the front side of each blade and extending in a direction perpendicular to the leading edge of the blade, so as to increase the maximum lift of the drone. That is, the present application can increase the maximum lift of the drone without increasing the size or rotation speed of the propeller. Therefore, the present application can significantly enhance the maximum lift of the drone while effectively avoiding the problems of limited application scenarios of the drone due to the increase in the size of the propeller and reduced flight time of the drone and shortened motor service life due to the increase in the rotation speed of the propeller. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] Figure 1 A schematic diagram of the structure of a propeller for a drone provided in an embodiment of the present application.

[0023] Figure 2 A schematic diagram of the partial structure of the guide grooves and branch rib groups provided in an embodiment of the present application.

[0024] Figure 3 A schematic diagram of the upward-looking structure of a propeller for a drone provided in an embodiment of the present application.

[0025] Figure 4 A schematic diagram of the cross-sectional structure of the resistance-increasing groove group provided in an embodiment of the present application.

[0026] Figure 5 This is a schematic diagram of the relationship between resistance and time for existing UAV propellers.

[0027] Figure 6 A schematic diagram of the relationship between resistance and time of a propeller for a drone provided in an embodiment of the present application.

[0028] Figure numerals: 1. hub; 2. blade; 3. guide groove; 4. branch rib; 5. drag-increasing groove. DETAILED DESCRIPTION

[0029] The technical solutions in the embodiments of the present application will be clearly and completely described below in conjunction with the drawings in the embodiments of the present application. Obviously, the described embodiments are only a part of the embodiments of the present application, rather than all of the embodiments. The components of the embodiments of the present application described and shown in the drawings here can be arranged and designed in various different configurations. Therefore, the following detailed description of the embodiments of the present application provided in the drawings is not intended to limit the scope of the application claimed for protection, but merely represents the selected embodiments of the present application. Based on the embodiments of the present application, all other embodiments obtained by those skilled in the art without making creative work belong to the scope of protection of the present application.

[0030] It should be noted that similar reference numerals and letters represent similar items in the following drawings, so once an item is defined in one drawing, it does not need to be further defined and explained in subsequent drawings. At the same time, in the description of this application, the terms "first", "second", etc. are only used to distinguish the description and cannot be understood as indicating or implying relative importance.

[0031] First, as Figure 1-Figure 6 As shown, the present application provides a propeller for a drone, which includes: Hub 1; A plurality of blades 2 are arranged in a circular array on the side of the hub 1. A plurality of guide grooves 3 are provided on the front of each blade 2. The distance between the guide groove 3 and the leading edge of the blade 2 is smaller than the distance between the guide groove 3 and the rear end of the blade 2. The extension direction of the guide groove 3 is perpendicular to the leading edge of the blade 2.

[0032] Among them, this embodiment can provide the lift required for the drone to fly by using the motor of the drone to drive the propeller provided by this embodiment to rotate, and by adjusting the speed of the propeller for the drone by adjusting the speed of the motor to adjust the lift. It should be understood that the lift required for the drone to fly is provided by the pressure difference between the front and back sides of the propeller, and the pressure on the front side of the propeller (the side of the propeller away from the ground after the propeller is installed) is less than the pressure on the back side of the propeller. The hub 1 of this embodiment can be the hub 1 of an existing drone propeller, and the cross-sectional shape of the hub 1 is preferably annular. The number of blades 2 in this embodiment is preferably two, the leading edge of the blade 2 is the edge of the blade 2 facing the wind when the propeller rotates, the leading edge of the blade 2 extends in a straight line, and multiple blades 2 are arranged in a circular array on the side of the hub 1, and the front side of each blade 2 (the side of the blade 2 away from the ground after the propeller is installed) is provided with multiple guide grooves 3, the distance between the guide groove 3 and the leading edge of the blade 2 is smaller than the distance between the guide groove 3 and the rear end of the blade 2, one end of the guide groove 3 is preferably connected to the leading edge of the blade 2, and the extension direction of the guide groove 3 is perpendicular to the leading edge of the blade 2. The propeller of the human machine will rotate with the axis of the hub 1 as the rotation center. During the rotation of the propeller, the gas flow direction is perpendicular to the leading edge of the blade 2, and the extension direction of the guide groove 3 of this embodiment is perpendicular to the leading edge of the blade 2. Therefore, this embodiment is equivalent to making the gas flow direction parallel to the guide groove 3. When the airflow passes through the front of the blade 2, the guide groove 3 can guide the flow of the airflow to reduce the lateral disturbance of the airflow and enable the airflow to flow more smoothly along the front of the blade 2, thereby effectively reducing the friction resistance of the airflow and the turbulence generated by the airflow on the front of the blade 2. It should be understood that, since this embodiment can reduce the frictional resistance of the airflow and the turbulence of the airflow on the front side of the blade 2 by providing a plurality of guide grooves 3 on the front side of the blade 2, when the size and rotation speed of the propeller are the same, the front airflow velocity of the blade 2 of this embodiment is greater than the front airflow velocity of the existing blade 2, and since the flow velocity of the fluid is negatively correlated with the pressure of the fluid, that is, the pressure on the front side of the blade 2 of this embodiment is less than the pressure on the front side of the existing blade 2, and the structure of the back side of the blade 2 of this embodiment is the same as the structure of the back side of the existing blade 2, that is, The pressure on the back side of the blade 2 of this embodiment is the same as the pressure on the back side of the existing blade 2, and the pressure on the front side of the blade 2 is less than the pressure on the back side of the blade 2. Therefore, this embodiment can increase the pressure difference between the front and back sides of the blade 2 by reducing the pressure on the front side of the blade 2, so that the pressure difference between the front and back sides of the blade 2 of this embodiment is greater than the pressure difference between the front and back sides of the existing blade 2. Since the lift force exerted on the blade 2 is positively correlated with the pressure difference between the front and back sides of the blade 2, when the size and rotation speed of the propeller are the same, the lift force exerted on the blade 2 of this embodiment is greater than the lift force exerted on the existing blade 2.

[0033] The present application provides a propeller for a drone, which can increase the lift of the blade 2 by setting a plurality of guide grooves 3 extending in a direction perpendicular to the leading edge of the blade 2 on the front of each blade 2, so as to increase the maximum lift of the drone. That is, the present application can increase the maximum lift of the drone without increasing the size or speed of the propeller. Therefore, the present application can significantly enhance the maximum lift of the drone and effectively avoid the problem that the application scenario of the drone is limited due to the increase in the size of the propeller and the problem that the flight time of the drone is reduced and the service life of the motor is shortened due to the increase in the speed of the propeller. In addition, since the present application can increase the maximum lift of the drone when the size and speed of the propeller are the same, the present application can reduce the size and / or speed of the propeller when the maximum lift of the drone is the same, so as to increase the applicable scenarios of the drone and / or increase the flight time of the drone and extend the service life of the motor.

[0034] In some preferred embodiments, branch rib groups are provided on both sides of the guide groove 3, and each branch rib group includes a plurality of branch ribs 4 inclined toward the rear end of the blade 2. The branch rib group of this embodiment and the guide groove 3 form a fishbone groove structure, and the guide groove 3 of this embodiment is provided with branch rib groups on both sides, and each branch rib group includes a plurality of branch ribs 4 inclined toward the rear end of the blade 2. The branch rib 4 can guide the airflow and disperse the airflow, so as to further reduce the friction resistance of the airflow and reduce the turbulence generated by the airflow on the front of the blade 2, thereby further increasing the maximum lift of the drone. It should be understood that since the microstructure of bird feathers is fishbone-shaped, and the branch rib group of this embodiment and the guide groove 3 form a fishbone groove structure, this embodiment is equivalent to forming a bionic bird feather microstructure on the front of the blade 2. Preferably, the two branch rib groups of this embodiment have the same structure, and the two branch rib groups are symmetrically arranged with the center of the guide groove 3 as the symmetry center. This embodiment can improve the stability of the airflow flow and avoid lateral disturbances by symmetrically arranging the branch ribs 4, so that the guided airflow can flow smoothly along the extension direction of the branch ribs 4.

[0035] In some preferred embodiments, the angle between the extension direction of the branch rib 4 and the extension direction of the guide groove 3 is 30-45°. This embodiment can avoid the situation that the drag reduction effect of the branch rib 4 and the effect of reducing the turbulence of the airflow on the front of the blade 2 are insufficient due to the angle between the extension direction of the branch rib 4 and the extension direction of the guide groove 3 being too small, and the separation or eddy flow of the airflow on the rear side of the bionic bird feather microstructure due to the angle between the extension direction of the branch rib 4 and the extension direction of the guide groove 3 being too large, the energy loss and resistance of the airflow are increased, and the drag reduction effect of the bionic bird feather microstructure is reduced. It should be understood that when designing the angle between the extension direction of the branch rib 4 and the extension direction of the guide groove 3, technical personnel in this field can change the angle between the extension direction of the branch rib 4 and the extension direction of the guide groove 3 according to the actual working environment of the propeller. Specifically, if the actual working environment of the propeller is a low-speed fluid environment (the linear velocity of the tip of the blade 2 is less than 100m / s), the angle between the extension direction of the branch rib 4 and the extension direction of the guide groove 3 is preferably 30°. At this time, the bionic bird feather microstructure can reduce the separation and backflow of the airflow while guiding the airflow to flow smoothly through the front of the blade 2, so that the airflow is as closely attached to the front of the blade 2 as possible. If the actual working environment of the propeller is a high-speed fluid environment (the linear velocity of the tip of the blade 2 is greater than 100m / s), the angle between the extension direction of the branch rib 4 and the extension direction of the guide groove 3 is preferably 45°. At this time, the bionic bird feather microstructure can form a stronger boundary layer control in a high-speed fluid environment to reduce the resistance caused by turbulence and eddy currents.

[0036] In some preferred embodiments, the width of the guide groove 3 is 50-200 μm, and the width of the branch rib 4 (refer to Figure 1 L2 in ) is 10-30 μm, and the length of branch rib 4 (ref. Figure 1L1) is 50-100 μm, the minimum spacing between adjacent branch ribs 4 in the same branch rib group is 30-50 μm, and the minimum spacing between adjacent guide grooves 3 is 20-200 μm. This embodiment can avoid the situation where the drag reduction effect of the bionic bird feather microstructure is reduced due to the excessively large minimum spacing between adjacent guide grooves 3, and the situation where the fluid retention area is increased and the friction resistance of the airflow is increased due to the excessively small minimum spacing between adjacent guide grooves 3 by setting the minimum spacing between adjacent guide grooves 3 to 20-200 μm. It should be understood that those skilled in the art can change the minimum spacing between adjacent guide grooves 3 according to the actual working environment of the propeller. Specifically, if the actual working environment of the propeller is a low-speed fluid environment, the minimum spacing between adjacent guide grooves 3 is preferably 20-50 μm. A smaller minimum spacing between adjacent guide grooves 3 can maintain the laminar state of the airflow to reduce the depth of the guide grooves 3 and the branch ribs 4. If the actual working environment of the propeller is a high-speed fluid environment, the minimum spacing between adjacent guide grooves 3 is preferably 50-200 μm. A larger minimum spacing between adjacent guide grooves 3 can prevent adjacent bionic bird feather microstructures from interfering with each other in a high-speed fluid environment.

[0037] In some preferred embodiments, the depths of the guide grooves 3 and the branch ribs 4 are both 10-100 μm. This embodiment can improve the smoothness of the airflow flowing along the front of the blade 2 and avoid the situation where the airflow is separated, the vortex is increased, and the friction resistance of the airflow is increased due to the excessive depth of the guide grooves 3 and the branch ribs 4 by setting the depths of the guide grooves 3 and the branch ribs 4 to 10-100 μm. It should be understood that those skilled in the art can change the depth of the guide grooves 3 and the branch ribs 4 according to the actual working environment of the propeller. Specifically, if the actual working environment of the propeller is a low-speed fluid environment, the depth of the guide grooves 3 and the branch ribs 4 is preferably 10-20 μm. A smaller depth of the guide grooves 3 and the branch ribs 4 is beneficial to laminar flow control of the airflow and maintaining the airflow attachment in the boundary layer to avoid fluid separation. If the actual working environment of the propeller is a high-speed fluid environment, the depth of the guide grooves 3 and the branch ribs 4 is preferably 20-100 μm. A larger depth of the guide grooves 3 and the branch ribs 4 can better control the boundary layer and reduce the generation of turbulence and eddy currents.

[0038] In some preferred embodiments, a plurality of drag-increasing groove groups are provided on the reverse side of each blade 2, the arrangement direction of the drag-increasing groove groups is perpendicular to the leading edge of the blade 2, and each drag-increasing groove group includes a plurality of drag-increasing grooves 5 extending in a direction parallel to the leading edge of the blade. This embodiment can make the arrangement direction of the drag-increasing grooves 5 in the same drag-increasing groove group parallel to the leading edge of the blade 2 by making the extension direction of the drag-increasing grooves 5 in the same drag-increasing groove group parallel to the leading edge of the blade. Since the extension direction of the drag-increasing groove 5 of this embodiment is parallel to the leading edge of the blade 2, that is, the gas flow direction is perpendicular to the drag-increasing groove 5, the drag-increasing groove 5 can disrupt the flow direction of the airflow, cause lateral disturbances in the airflow and increase the vortex effect, so as to increase the airflow friction resistance on the back of the blade 2, that is, this embodiment is equivalent to forming a plurality of tiny retention areas on the back of the blade 2, so that part of the airflow stagnates in the retention area. Therefore, this embodiment can reduce the airflow velocity on the back side of the blade 2 and increase the pressure on the back side of the blade 2 when the size and rotation speed of the propeller are the same by arranging a plurality of drag-increasing grooves 5 on the back side of the blade 2, so as to increase the pressure difference between the front and back sides of the blade 2, thereby further increasing the maximum lift of the drone.

[0039] In some preferred embodiments, the length of the resistance-increasing groove 5 is 10-50 μm, and the width of the resistance-increasing groove 5 is 5-150 μm. This embodiment can enhance the resistance-increasing effect of the resistance-increasing groove 5 by setting the length of the resistance-increasing groove 5 to 10-50 μm and the width of the resistance-increasing groove 5 to 5-150 μm, thereby further increasing the pressure difference between the front and back surfaces of the blade 2, and further increasing the maximum lift of the drone. It should be understood that if the actual working environment of the propeller is a low-speed fluid environment, the length of the resistance-increasing groove 5 is preferably 10-20 μm, and if the actual working environment of the propeller is a high-speed fluid environment, the length of the resistance-increasing groove 5 is preferably 20-50 μm. It should be understood that the shape of the resistance-increasing groove 5 in the top view direction of this embodiment is a rectangle, the length of the resistance-increasing groove is the size of the side of the rectangle parallel to the leading edge of the blade 2, and the width of the resistance-increasing groove is the size of the side of the rectangle perpendicular to the leading edge of the blade 2.

[0040] In some preferred embodiments, the drag-increasing groove 5 has a vertical surface and an inclined surface that are interconnected, the vertical surface is perpendicular to the back surface of the blade 2, the inclined surface is located on the side of the vertical surface close to the leading edge of the blade 2, and the angle between the vertical surface and the inclined surface is 30-60°. Specifically, if the actual working environment of the propeller is a low-speed fluid environment, the angle between the vertical surface and the inclined surface is preferably 30-40°. At this time, the airflow has strong adhesion, and the airflow is gradually guided into the drag-increasing groove 5 to increase the viscous resistance of the airflow. If the actual working environment of the propeller is a high-speed fluid environment, the angle between the vertical surface and the inclined surface is preferably 50-60°. At this time, the drag-increasing groove 5 can quickly disturb the airflow, and the pressure resistance and turbulence intensity of the airflow are increased to form an obvious turbulent area.

[0041] In some preferred embodiments, the minimum spacing between adjacent resistance-increasing groove groups is 20-200 μm, and the minimum spacing between adjacent resistance-increasing grooves 5 in the same resistance-increasing groove group is 20-200 μm. Specifically, if the actual working environment of the propeller is a low-speed fluid environment, the minimum spacing between adjacent resistance-increasing groove groups and the minimum spacing between adjacent resistance-increasing grooves 5 in the same resistance-increasing groove group are both 20-50 μm, so as to form a continuous retention area between adjacent resistance-increasing grooves 5 and increase the adhesion resistance of the airflow. If the actual working environment of the propeller is a high-speed fluid environment, the minimum spacing between adjacent resistance-increasing groove groups and the minimum spacing between adjacent resistance-increasing grooves 5 in the same resistance-increasing groove group are both 50-200 μm, so as to form large-scale turbulence and large-scale eddies and increase the pressure resistance of the airflow.

[0042] In some preferred embodiments, the depth of the drag-increasing groove 5 near the leading edge of the blade 2 is less than the depth of the drag-increasing groove 5 away from the leading edge of the blade 2. This embodiment improves the drag-increasing effect of the drag-increasing groove group by making the depth of the drag-increasing groove 5 near the leading edge of the blade 2 less than the depth of the drag-increasing groove 5 away from the leading edge of the blade 2, so as to further increase the maximum lift of the drone. It should be understood that if the depth of the drag-increasing groove 5 is too large, there may be too much eddy current and energy loss, and the system efficiency of the drone is reduced. Therefore, those skilled in the art need to reasonably set the depth of the drag-increasing groove 5.

[0043] In order to verify the drag reduction effect of the propeller for the drone of the present application, the applicant conducted a resistance comparison experiment on the existing drone propeller and the propeller of the present application with a bionic bird feather microstructure on the front of the blade 2. Specifically, the existing drone propeller and the propeller of the present application have the same size. The width of the guide groove 3 of the bionic bird feather microstructure of the present application is 100μm, the width of the branch rib 4 is 10μm, the length of the branch rib 4 is 50μm, the depth of the guide groove 3 and the branch rib 4 are both 10μm, and the minimum spacing between adjacent guide grooves 3 is 100μm. In the resistance comparison experiment, the propeller rotates around the Y axis at a speed of 8000r / min. The results of the resistance comparison experiment are shown in FIG. Figure 5 and Figure 6 The experimental results of the resistance comparison experiment are shown in the following table: Resistance comparison test results table Resistance in the X-axis direction X-axis drag coefficient Resistance in the Z-axis direction Z-axis drag coefficient Prior art 0.002228101 0.003637716 0.001193637 0.001948795 This application 0.001069425 0.001746 0.000599313 0.000978471 Difference 0.001158676 0.001891716 0.000594324 0.000970324 Drag reduction efficiency 52.0% 52.0% 49.8% 49.8% From the above, it can be seen that the propeller for a drone provided in the present application can increase the lift exerted on the blade 2 by setting a plurality of guide grooves 3 extending in a direction perpendicular to the leading edge of the blade 2 on the front side of each blade 2 when the propeller size and rotation speed are the same, so as to increase the maximum lift of the drone. That is, the present application can significantly enhance the maximum lift of the drone while effectively avoiding the problem of limited application scenarios of the drone due to the increase in the size of the propeller and reduced flight time of the drone and shortened motor service life due to the increase in the rotation speed of the propeller.

[0044] In a second aspect, the present application also provides a drone, which includes a propeller for a drone provided in the first aspect above.

[0045] A drone provided in an embodiment of the present application includes a propeller for a drone provided in the first aspect above. The principle of the drone provided in this embodiment is the same as the principle of the propeller for a drone provided in the first aspect above, and will not be discussed in detail here.

[0046] From the above, it can be seen that the propeller and drone provided in the present application can increase the lift exerted on the blade 2 by setting a plurality of guide grooves 3 extending in a direction perpendicular to the leading edge of the blade 2 on the front side of each blade 2, so as to increase the maximum lift of the drone. That is, the present application can significantly enhance the maximum lift of the drone while effectively avoiding the problem of limited application scenarios of the drone due to the increase in the size of the propeller and reduced flight time of the drone and shortened motor service life due to the increase in the speed of the propeller.

[0047] In the embodiments provided in the present application, it should be understood that, herein, relational terms such as first and second, etc. are merely used to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any such actual relationship or order between these entities or operations.

[0048] The above description is only an embodiment of the present application and is not intended to limit the protection scope of the present application. For those skilled in the art, the present application may have various modifications and variations. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present application shall be included in the protection scope of the present application.

Claims

1. A propeller for a drone, characterized in that: The propeller for the drone comprises: Propeller hub; A plurality of blades are arranged in a circular array on the side of the hub, and a plurality of guide grooves are provided on the front of each blade. The distance between the guide groove and the leading edge of the blade is smaller than the distance between the guide groove and the rear end of the blade, and the extension direction of the guide groove is perpendicular to the leading edge of the blade.

2. The propeller for a drone according to claim 1, characterized in that: Branch rib groups are arranged on both sides of the guide groove, and each of the branch rib groups includes a plurality of branch ribs inclined toward the rear end of the blade.

3. The propeller for a drone according to claim 2, characterized in that: The included angle between the extending direction of the branch rib and the extending direction of the guide groove is 30-45°.

4. The propeller for a drone according to claim 2, characterized in that: The width of the guide groove is 50-200 μm, the width of the branch rib is 10-30 μm, the length of the branch rib is 50-100 μm, the minimum spacing between adjacent branch ribs in the same branch rib group is 30-50 μm, and the minimum spacing between adjacent guide grooves is 20-200 μm.

5. The propeller for a drone according to claim 1, characterized in that: A plurality of drag-increasing groove groups are provided on the reverse side of each blade, and the arrangement direction of the drag-increasing groove groups is perpendicular to the leading edge of the blade. Each drag-increasing groove group includes a plurality of drag-increasing grooves extending in a direction parallel to the leading edge of the blade.

6. The propeller for a drone according to claim 5, characterized in that: The length of the resistance increasing groove is 10-50 μm, and the width of the resistance increasing groove is 5-150 μm.

7. The propeller for a drone according to claim 5, characterized in that: The resistance increasing groove has a vertical surface and an inclined surface, the vertical surface is perpendicular to the back surface of the blade, the inclined surface is located on the side of the vertical surface close to the leading edge of the blade, and the angle between the vertical surface and the inclined surface is 30-60°.

8. The propeller for a drone according to claim 5, characterized in that: The depth of the drag increasing groove close to the leading edge of the blade is smaller than the depth of the drag increasing groove far from the leading edge of the blade.

9. The propeller for a drone according to claim 5, characterized in that: The minimum spacing between adjacent resistance increasing groove groups is 20-200 μm, and the minimum spacing between adjacent resistance increasing grooves in the same resistance increasing groove group is 20-200 μm.

10. A drone, characterized in that: The drone comprises a propeller for a drone as described in any one of claims 1-9.

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