Propeller and unmanned aerial vehicle

Abstract

The propeller comprises a propeller hub and a plurality of blades, the blades are fixed to the propeller hub, each blade comprises a supporting framework and a blade surface wrapping the supporting framework, the supporting framework comprises a wing spar and a wing rib, the wing spar extends in the first direction, the wing rib extends in the second direction, the first direction is the length direction of the blades, and the second direction is the length direction of the blades. The second direction is perpendicular to the first direction, the multiple wing ribs are arranged at intervals in the first direction, the center of each wing rib is provided with an installation hole for the corresponding spar to penetrate through, the wing ribs and the spar are all made of carbon fiber multilayer plates, the carbon fiber multilayer plates are formed by laying multiple layers of carbon fiber cloth in a stacked mode, and the carbon fiber cloth is arranged in the installation hole. And two adjacent layers of carbon fiber cloth are connected in a bonding manner. According to the propeller, the supporting framework is made of the carbon fiber material, the wing spar is arranged to improve the structural strength of the propeller blades, the weight of the propeller blades can be reduced, meanwhile, the structural strength of the propeller blades can be guaranteed, the reliability of the propeller is improved, and the service life of the propeller is prolonged.

Description

Technical Field

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

[0002] With the continuous development of drone technology, drones are being used more and more widely in logistics, aerial photography and other fields. Propellers are important components of drones, used to convert motor power into thrust or lift to enable drones to take off and land, hover and turn.

[0003] In order to avoid the overall load-bearing capacity of the UAV, the weight of the propeller needs to be reduced as much as possible. At the same time, since the propeller needs to rotate for a long time when working, the bending or breaking of the propeller will directly affect the flight of the UAV. Therefore, there are high requirements for the structural strength of the propeller blades, such as shear resistance and bending resistance, fatigue resistance, hardness, stiffness, etc. Summary of the invention

[0004] In order to overcome the above-mentioned shortcomings of the related art, the present application aims to provide a propeller and a drone.

[0005] In order to achieve the above objectives, this application adopts the following technical solutions:

[0006] According to a first aspect of the present application, a propeller is provided, comprising a hub and a plurality of blades, wherein the plurality of blades are fixed to the hub, the blades comprising a support frame and a blade surface covered by the support frame, and the support frame comprises:

[0007] a spar extending along a first direction, wherein the first direction is a length direction of the blade;

[0008] A wing rib extends along a second direction, the second direction is perpendicular to the first direction, the number of the wing ribs is multiple, the multiple wing ribs are arranged at intervals along the first direction, and a mounting hole for the spar to pass through is arranged at the center of each wing rib;

[0009] Wherein, the wing rib and the wing beam are both made of carbon fiber multilayer plates, and the carbon fiber multilayer plates are made of multiple layers of carbon fiber cloth stacked and laid, and two adjacent layers of carbon fiber cloth are bonded and connected.

[0010] In a possible implementation manner, the wing spar is a circular tube.

[0011] In a possible embodiment, the blade is divided into a plurality of blade segments of equal length along the first direction, the blade segment farthest from the hub is the first segment, and the number of ribs arranged in the first segment is greater than the number of ribs arranged in the other blade segments.

[0012] In a possible implementation, a plane passing through the wing beam and perpendicular to the thickness direction of the blade is used as a reference plane, and a preset angle is provided between the rib and the reference plane, and the preset angle ranges from 5° to 45°.

[0013] In a possible embodiment, the rib includes a first side and a second side opposite to each other, one end of the first side is directly connected to one end of the second side to form a pointed structure, and an arc transition section is provided between the other end of the first side and the other end of the second side, and the two ends of the arc transition section are respectively connected to the first side and the second side.

[0014] In a possible implementation manner, the first side is convex in a direction away from the second side, and the second side is a straight side or the second side is concave toward the first side.

[0015] In a possible implementation manner, the blade surface includes a blade base and a blade back, the first edge is connected to the blade back, and the second edge is connected to the blade base.

[0016] In a possible implementation, the blade basin and the blade back are both formed by curing carbon fiber prepreg cloth, the carbon fiber prepreg cloth is made of carbon fiber cloth impregnated with a resin matrix, the blade basin is bonded to the supporting frame by epoxy resin, and the blade back is bonded to the supporting frame by epoxy resin.

[0017] In a possible implementation, the number of the blades is three, the three blades are evenly arranged along the circumference of the hub, and the angle between the axes of two adjacent blades is 120°.

[0018] According to a second aspect of the present application, a drone is provided, comprising the propeller as described in the first aspect of the present application.

[0019] The advantages of the present application are that in the propeller of the present application, the supporting frame is made of carbon fiber material, and a wing beam is provided to improve the structural strength of the blade, which is beneficial to reducing the weight of the blade, while also ensuring its structural strength and improving the reliability and service life of the propeller.

[0020] Other features and advantages of the present application will be set forth in the subsequent description, and in part will become apparent from the description, or may be understood through implementation of the present application. The objects and other advantages of the present application may be realized and obtained through the structures particularly pointed out in the description, claims and drawings. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] The accompanying drawings, which are incorporated into the specification and constitute a part of the specification, illustrate embodiments of the present application and are used together with the description to explain the principles of the present application. In these drawings, similar reference numerals are used to identify similar elements. The drawings described below are some embodiments of the present application, rather than all embodiments. For those of ordinary skill in the art, other drawings can be obtained based on these drawings without paying creative work.

[0022] Figure 1 is one of the structural schematic diagrams of a propeller according to an exemplary embodiment.

[0023] Figure 2 This is a second schematic diagram of the structure of a propeller according to an exemplary embodiment.

[0024] Figure 3 This is a third schematic diagram of the structure of a propeller according to an exemplary embodiment.

[0025] Figure 4 This is a fourth schematic diagram of the structure of a propeller according to an exemplary embodiment.

[0026] Figure 5 is a schematic structural diagram of a rib according to an exemplary embodiment. DETAILED DESCRIPTION

[0027] In order to make the purpose, technical scheme and advantages of the embodiments of the present application clearer, the technical scheme 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 part of the embodiments of the present application, rather than all of the embodiments. Based on the embodiments of the present application, all other embodiments obtained by ordinary technicians in this field without making creative work are within the scope of protection of this application. It should be noted that, in the absence of conflict, the embodiments in the present application and the feature vectors in the embodiments can be arbitrarily combined with each other.

[0028] With the continuous development of drone technology, drones are being used more and more widely in logistics, aerial photography and other fields. Propellers are important components of drones, used to convert motor power into thrust or lift to enable drones to take off and land, hover and turn.

[0029] In order to avoid the overall load-bearing capacity of the UAV, the weight of the propeller needs to be reduced as much as possible. At the same time, since the propeller needs to rotate for a long time when working, the bending or breaking of the propeller will directly affect the flight of the UAV. Therefore, there are high requirements for the structural strength of the propeller blades, such as shear resistance and bending resistance, fatigue resistance, hardness, stiffness, etc.

[0030] To solve the above problems, the present application provides a propeller and a UAV. In the propeller of the present application, the supporting frame is made of carbon fiber material, and a wing beam is provided to improve the structural strength of the blade, which is beneficial to reducing the weight of the blade. At the same time, it can also ensure its structural strength and improve the reliability and service life of the propeller.

[0031] According to an exemplary embodiment, Figure 1-Figure 5 As shown, an embodiment of the present application provides a propeller, which is applied to a drone. The propeller includes a hub 10 and a plurality of blades 20. The plurality of blades 20 are all fixed to the hub 10. The hub 10 can be connected to the output end of a driving motor (not shown in the figure) of the propeller. The driving motor drives the hub 10 to rotate, thereby driving the blades 20 fixed to the hub 10 to rotate. When the blades 20 rotate, they act on the surrounding airflow, thereby generating lift or thrust for the drone.

[0032] like Figure 1-Figure 5 As shown, the blade 20 includes a support frame 21 and a blade surface 22. The support frame 21 is arranged inside the blade 20, and is used to form the main body of the blade 20 and play a supporting role, thereby improving the overall structural strength of the blade 20. The blade surface 22 is covered on the support frame 21, and the blade surface 22 is used to form the outer surface of the blade 20. The support frame 21 includes a spar 211 and a rib 212. The spar 211 extends along a first direction, which is the length direction of the blade 20, that is, the axial direction of the blade 20. The rib 212 extends along a second direction, which is perpendicular to the first direction, and is the width direction of the blade, that is, Figure 3 There are multiple ribs 212, which are spaced apart along the first direction, and the intervals between two adjacent ribs 212 can be equal or unequal. A mounting hole 213 for the spar 211 to pass through is set at the center of each rib 212, and the spar 211 passes through the mounting holes 213 of each rib 212 and is fixed to the rib 212 to improve the structural stability of the support frame 21, thereby improving the structural strength of the blade 20.

[0033] The rib 212 and the spar 211 are both made of a carbon fiber multilayer plate (not shown in the figure), and the carbon fiber multilayer plate is made of multiple layers of carbon fiber cloth stacked and laid, and two adjacent layers of carbon fiber cloth are bonded and connected. The carbon fiber cloth can be formed by laying carbon fiber filaments in a certain arrangement direction, impregnating a resin matrix, and curing, wherein the laying angle of the carbon fiber cloth can be 0°, 30°, -30°, 45°, -45°, 60°, -60°, 90°, -90°, etc.

[0034] When the ply angle of the carbon fiber cloth is 0°, that is, the arrangement direction of the carbon fiber filaments is the same as the load direction, the formed carbon fiber multilayer board has higher tensile strength and stiffness, but relatively low shear strength and bending strength; when the ply angle of the carbon fiber cloth is 90° or -90°, that is, the arrangement direction of the carbon fiber filaments is perpendicular to the load direction, the formed carbon fiber multilayer board has higher shear strength and bending strength, but lower tensile strength and stiffness. It can be understood that the larger the ply angle of the carbon fiber cloth, the higher the shear strength and bending strength of the carbon fiber multilayer board, the lower the tensile strength and stiffness, and the smaller the ply angle of the carbon fiber cloth, the opposite is true. In addition, between the multiple layers of carbon fiber cloth, the arrangement direction of the carbon fiber filaments of each layer of carbon fiber cloth can have a preset angle with the arrangement direction of the carbon fiber filaments of the previous layer, so as to improve the balance of the force performance of the carbon fiber multilayer board at different angles. Those skilled in the art can select a suitable plying method according to the actual mechanical properties and structural strength requirements of different parts of the propeller, and the embodiments of the present application do not impose too many restrictions on this.

[0035] In the embodiment of the present application, the supporting frame of the propeller is made of carbon fiber material, and a wing beam is provided to improve the structural strength of the blade, which is beneficial to reducing the weight of the blade, while also ensuring its structural strength and improving the reliability and service life of the propeller.

[0036] In some embodiments, the wing spar 211 is a round tube. The shape of the mounting hole 213 is adapted to the cross-sectional shape of the wing spar 211. Correspondingly, when the wing spar 211 is a round tube, the shape of the mounting hole 213 is a round hole. The wing spar 211 adopts a round tube made of carbon fiber material. Compared with a solid cylinder, a hollow round tube can reduce its own weight while ensuring structural strength, thereby achieving a lightweight design, thereby reducing the overall weight of the blade 20 and avoiding affecting the load-bearing capacity of the drone. Of course, it is understandable that the use of a round tube for the wing spar 211 can ensure balanced force in all directions. When the requirements for force balance are not high, or there are special requirements for force, the wing spar 211 can also adopt other shapes such as a triangular tube, a square tube, an elliptical tube, etc., and the embodiments of the present application do not impose special restrictions on this.

[0037] In some embodiments, the fixed connection between the blade 20 and the hub 10 can have a variety of connection methods. In one example, the blade 20 is bonded to the hub 10. In another example, the blade 20 and the hub 10 are fastened together by a connection block and a screw, a screw, a bolt, or other connector. The connection block can be, for example, a Z-shaped connection block, a U-shaped connection block, etc. One end of the connection block is fixedly connected to the hub 10 through a threaded connector, and the other end is fixedly connected to the blade 20 through a threaded connector, thereby fixing the blade 20 to the hub 10. In another example, the hub 10 is integrally formed with the spar 211 or the blade surface 22 of the blade 20. Of course, it can be understood that the fixed connection between the blade 20 and the hub 10 is not limited to the above-mentioned several methods listed in the embodiments of the present application. Other connection methods or a combination of multiple connection methods can also be used to improve the connection reliability. The embodiments of the present application do not impose too many restrictions on this, and those skilled in the art can choose according to actual needs.

[0038] In some embodiments, the width of the middle portion of the blade 20 is greater than the width of the ends of the blade 20. Figure 1-Figure 4 As shown, the first end 23 of the blade 20 is used to be fixedly connected to the hub 10, and the second end 24 of the blade 20 is opposite to the first end 23, that is, the second end 24 is far away from the hub 10, wherein the widths of the first end 23 and the second end 24 are both smaller than the width of the middle part of the blade 20, that is, the width of the middle part of the blade 20 is larger than the widths of the two ends, thereby guiding the airflow and avoiding excessive force on the two ends of the blade 20.

[0039] In some embodiments, the blade 20 is divided into a plurality of blade segments of equal length along the first direction. Among the plurality of blade segments into which the blade 20 is divided, the first segment 201 is the farthest from the hub 10, and the number of ribs 212 provided in the first segment 201 is greater than the number of ribs 212 provided in other blade segments. Figure 1-Figure 4 As shown, the embodiment of the present application is described by taking the blade 20 being divided into two sections of equal length along the first direction as an example, wherein the blade 20 is divided into a first section 201 and a second section 202, and the distance between the first section 201 and the hub 10 is greater than the distance between the second section 202 and the hub 10, that is, the first section 201 is closer to the wing tip of the blade 20, and the second section 202 is closer to the wing root of the blade 20. Since the first section 201 is located at a section away from the hub 10 when the blade 20 rotates, the first section 201 has a larger rotation stroke, and is subject to greater resistance during rotation, and is more likely to collide with other objects. Therefore, more ribs 212 are provided in the first section 201, which can enhance the support force for the first section 201 and enhance the structural strength of the first section 201, thereby enhancing the structural stability and reliability of the blade.

[0040] Among them, it is worth noting that, in the embodiment of the present application, the blade 20 is taken as an example to include a first section 201 and a second section 202 of equal length. In the actual production and design process, those skilled in the art can also divide the blade 20 into more blade sections of equal length according to actual needs, wherein the number of ribs 212 in the first section 201 farthest from the hub 10 is greater than the number of ribs 212 in other blade sections, and the number of ribs 212 in other blade sections can be equal or unequal. In one example, the number of ribs 212 in the first section 201 is greater than the number of ribs 212 in other blade sections, and the number of ribs 212 in each other blade section is equal. In another example, the number of ribs 212 in each blade section is unequal, and the number of ribs 212 in each blade section gradually increases along the direction from close to the hub 10 to away from the hub 10. Of course, it is understandable that the embodiment of the present application does not impose too many restrictions on the number of blade segments and the number of ribs 212 in each blade segment, and those skilled in the art can make settings according to actual needs.

[0041] In some embodiments, at least a portion of the ribs 212 are disposed at an angle relative to the hub 10. Figure 1-Figure 4 As shown, the thickness direction (i.e. Figure 4 A plane perpendicular to the vertical direction (the vertical direction shown in the figure) is a reference plane (not shown in the figure), rib 212 is perpendicular to spar 211, and there is a preset angle between rib 212 and the reference plane. By tilting at least part of rib 212 at a certain angle, at least part of blade 20 can be tilted with a certain inclination, thereby increasing the contact area between blade 20 and the air when rotating, improving the effect of blade 20 on the airflow, so as to increase the lift or thrust generated on the drone when blade 20 rotates, and achieve a better flight effect.

[0042] In one example, all ribs 212 are tilted so that the blade 20 is tilted as a whole, and the blade 20 has a larger contact area with the air, thereby effectively increasing the lift or thrust generated by the blade 20. In another example, only part of the ribs 212 are tilted, and the partial tilting of the blade 20 increases the contact area between the blade 20 and the air while avoiding excessive air resistance that affects the rotation rate of the blade 20. Those skilled in the art can tilt all or part of the ribs 212 according to actual needs, and the embodiments of the present application do not impose too many restrictions on this.

[0043] In some embodiments, the preset angle ranges from 5° to 45°, and the preset angles between different ribs 212 and the reference plane may be the same or different. In one example, the preset angles between each rib 212 and the reference plane are the same, so that the blade 20 forms an inclined plane, increasing the contact and force-bearing area with the air. In another example, the preset angles between each rib 212 and the reference plane are different, for example, the angle gradually increases or decreases, so that the blade 20 forms a smoothly transitioned inclined curved surface, while increasing the contact area between the blade 20 and the air and minimizing the rotational resistance. Of course, it is understandable that the preset angles between each rib 212 and the reference plane may also be partially the same or partially different, and the embodiments of the present application do not impose too many restrictions on this. In the ribs 212 with different preset angles from the reference plane, the change trend of the preset angle may also be designed and adjusted by those skilled in the art according to actual needs.

[0044] In some embodiments, the rib 212 includes a first side 2121 and a second side 2122 that are opposite to each other. Figure 5 As shown, one end of the first side 2121 is directly connected to one end of the second side 2122 to form a pointed structure 2123, and an arc transition section 2124 is provided between the other end of the first side 2121 and the other end of the second side 2122, and the two ends of the arc transition section 2124 are respectively connected to the first side 2121 and the second side 2122, that is, the other end of the first side 2121 and the other end of the second side 2122 are smoothly connected through the arc transition section 2124. When the blade 20 rotates, the airflow flows from the arc transition section 2124 to the pointed structure 2123, that is, the arc transition section 2124 is the leading edge of the blade 20, and the pointed structure 2123 is the trailing edge of the blade 20. Among them, the R angle of the arc transition section 212 can be set by those skilled in the art according to actual needs, and the embodiments of the present application do not impose too many restrictions on this.

[0045] In some embodiments, the first side 2121 is convex in a direction away from the second side 2122 , and the second side 2122 is a straight side or the second side 2122 is concave toward the first side 2121 .

[0046] In one example, if Figure 5 As shown, the first side 2121 protrudes in the direction away from the second side 2122, and the second side 2122 is a straight side. Since the first side 2121 is a curved side and the second side 2122 is a straight side when the starting point and the ending point are the same, the length of the first side 2121 is greater than the length of the second side 2122, and the flow rate of the airflow on the first side 2121 is greater than the flow rate of the airflow on the second side 2122, thereby being able to provide lift.

[0047] In another example, the first side 2121 is convex in a direction away from the second side 2122, the second side 2122 is concave toward the first side 2121, and the curvature of the second side 2122 is smaller than the curvature of the first side 2121. By setting the second side 2122 as a curved side, the second side 2122 can still provide lift when the curvature is smaller than the curvature of the first side 2121, and by adjusting the curvature of the second side 2122, the magnitude of the lift that the blade 20 can provide can be adjusted, so that the drone can fly more stably.

[0048] In some embodiments, the blade surface 22 includes a blade pot 221 and a blade back 222, the first side 2121 of the rib 212 is connected to the blade back 222, and the second side 2122 is connected to the blade pot 221. The blade back 222 generally refers to the raised side of the blade 20, and the blade pot 221 generally refers to the horizontal or concave side of the blade 20. The first side 2121 of the rib 212 is connected to the blade back 222, thereby supporting the blade surface 22, propping up and forming the raised blade back 222, so that the air flow forms a flow velocity difference between the blade back 222 and the blade pot 221 of the blade 20, thereby providing lift or thrust to the drone through the blade 20.

[0049] In some embodiments, the blade basin 221 and the blade back 222 are both formed by curing carbon fiber prepreg. The carbon fiber prepreg is made of carbon fiber cloth impregnated with a resin matrix, and the resin matrix can be made of thermoplastic resins such as polyvinyl chloride, polyphenylene ether, and epoxy resin. The carbon fiber prepreg is placed in a blade basin mold (not shown in the figure) or a blade back mold (not shown in the figure) and cured to form a hard blade basin 221 or blade back 222 with strong structural stability and excellent mechanical properties. The curing process can be thermal curing or light curing, and the embodiment of the present application does not impose too many restrictions on this. Those skilled in the art can choose according to the material properties.

[0050] Among them, the blade basin 221 and the blade back 222 are both bonded to the support frame 21, and the support frame 21 is used to provide support force for the blade basin 221 and the blade back 222, maintain the preset shape, and improve the overall structural strength of the blade 20. The blade basin 221 and the support frame 21, as well as the blade back 222 and the support frame 21 can be bonded by epoxy resin. Of course, it is understandable that the blade basin 221 and the blade back 222 can also be bonded to the support frame 21 by other adhesives such as polyurethane, polystyrene, and polyacrylate. The embodiment of the present application does not impose too many restrictions on this, and those skilled in the art can choose according to actual needs.

[0051] In some embodiments, the wing beam 211 and the wing rib 212 use unidirectional carbon fiber multilayer boards, and the blade basin 221 and the blade back 222 use multi-directional carbon fiber multilayer boards. That is, the carbon fiber multilayer boards used by the wing rib 212 and the wing beam 211 are stacked and laid with multiple layers of carbon fiber cloth, and the two adjacent layers of carbon fiber cloth are bonded and connected, and the arrangement direction of the carbon fiber fibers in each layer of carbon fiber cloth is the same. For example, in the carbon fiber multilayer boards used by the wing rib 212 and the wing beam 211, the laying angle of the carbon fiber cloth is 0°, that is, the fiber direction and the load direction coincide, and the load direction is along the length direction of the wing rib 212 and the wing beam 211, thereby improving the hardness and tensile strength of the wing rib 212 and the wing beam 211, and improving the structural strength of the support frame 21.

[0052] The blade basin 221 and the blade back 222 use a complex carbon fiber multilayer board, that is, between the multiple layers of carbon fiber cloth, the arrangement direction of the carbon fiber filaments of each layer of carbon fiber cloth can have a preset angle with the arrangement direction of the carbon fiber filaments of the previous layer, so as to improve the balance of the force performance of the carbon fiber multilayer board at different angles. The preset angle can be 30°, -30°, 45°, -45°, 60°, -60°, 90°, -90° and other angles. It can be understood that the larger the laying angle of the carbon fiber cloth, the higher the shear strength and bending strength, and the lower the tensile strength and stiffness. The smaller the laying angle of the carbon fiber cloth, the lower the shear strength and bending strength, and the higher the tensile strength and stiffness. In addition, the more layers of carbon fiber cloth, the higher the overall strength of the complex carbon fiber multilayer board, and the more balanced the mechanical properties along all directions. Those skilled in the art may also select different laying methods for the blade basin 221 and the blade back 222 according to different requirements for the mechanical properties and structural strength of the blade basin 221 and the blade back 222. The embodiments of the present application do not impose too many restrictions on this, and those skilled in the art may make a choice according to actual needs.

[0053] In some embodiments, a filling layer (not shown in the figure) may be further provided inside the blade 20. Figure 1-Figure 4As shown, there is a gap between the support frame 21 and the blade surface 22. In order to further improve the structural strength of the blade 20 and avoid bending, depression and other problems of the blade surface 22 at the position where there is no support from the support frame 21, a filling layer can also be set in the gap between the support frame 21 and the blade surface 22. The filling layer can be made of materials such as resin, plastic, foam plastic, etc., preferably PMI (polymethacrylimide) foam plastic, which has the advantages of light weight, excellent mechanical properties, high specific strength and specific modulus, etc., and is applied to the blade 20. It can greatly improve the mechanical properties and structural strength of the blade 20 without adding too much weight. In addition, the filling layer can be fixed in the blade 20 by bonding, clamping, threaded connection, etc., and can also be formed by injection molding. The embodiment of the present application does not impose too many restrictions on the specific material and setting method of the filling layer, and those skilled in the art can set it according to actual needs.

[0054] In some embodiments, the number of blades 20 may be arranged in different ways.

[0055] In one example, there are two blades 20. The two blades 20 extend opposite to each other, and the angle between the axes of the two blades 20 is 180°, that is, the angle between the spars 211 of the two blades 20 is 180°.

[0056] In another example, the number of blades 20 is three. Figure 3 As shown, the three blades 20 are evenly arranged along the circumference of the hub 10, and the angle between the axes of two adjacent blades 20 is 120°, that is, the angle between the wing beams 211 of two adjacent blades 20 is 120°.

[0057] In another example, the number of blades 20 is four. The four blades 20 are evenly arranged along the circumference of the hub 10, and the axes of two adjacent blades 20 are perpendicular to each other, that is, the angle between the spar 211 of two adjacent blades 20 is 90°.

[0058] Of course, it can be understood that the number of blades 20 in the embodiment of the present application can be increased by technical personnel in this field according to actual needs, as long as the multiple blades 20 are evenly arranged along the circumference of the hub 10. The embodiment of the present application does not impose too many restrictions on the specific number of blades 20.

[0059] According to an exemplary embodiment, Figure 1-Figure 5As shown, an embodiment of the present application provides a drone, and the drone includes a propeller as described in the above embodiment. The propeller includes a hub 10 and a plurality of blades 20, and the plurality of blades 20 are fixed on the hub 10. The blade 20 includes a support frame 21 and a blade surface 22, and the blade surface 22 is coated on the support frame 21 to form the outer surface of the blade 20. The support frame 21 includes a spar 211 and a rib 212. The spar 211 extends along a first direction, and the rib 212 extends along a second direction. The first direction is the length direction of the blade 20, and the second direction is perpendicular to the first direction and is the width direction of the blade. The number of ribs 212 is multiple, and the plurality of ribs 212 are arranged at intervals along the first direction. The center of each rib 212 is provided with a mounting hole 213 for the spar 211 to pass through. Among them, the rib 212 and the spar 211 are both made of carbon fiber multilayer boards, and the carbon fiber multilayer boards are stacked and laid by multiple layers of carbon fiber cloth, and the adjacent two layers of carbon fiber cloth are bonded and connected.

[0060] The following will be combined Figure 1-Figure 5 , the manufacturing process of the propeller in the embodiment of the present application is explained.

[0061] First, the carbon fiber prepreg is laid in the blade basin mold and the blade back mold respectively, and the carbon fiber prepreg is tightly fitted by vacuuming to remove the bubbles between the carbon fiber prepreg and the mold; then the blade basin mold and the blade back mold are placed in a high-temperature furnace and cured, and the blade basin 221 and the blade back 222 are demoulded after molding; then, the ribs 212 and the spar 211 are assembled to form a support skeleton 21, and the support skeleton 21 is bonded to one of the blade basin 221 and the blade back 222 with epoxy resin, or the ribs 212 are bonded to one of the blade basin 221 and the blade back 222, and then the spar 211 is passed through the mounting holes 213 of multiple ribs 212 to form a support skeleton 21; finally, the blade basin 221 and the blade back 222 are molded together, and the blade basin 221 and the blade back 222 are glued so that the two are bonded and connected, and finally a complete blade 20 is formed.

[0062] In some embodiments, the blade basin 221 and the blade back 222 are both formed by curing. The carbon fiber prepreg is made of carbon fiber cloth impregnated with a resin matrix, and the resin matrix can be made of thermoplastic resins such as polyvinyl chloride, polyphenylene ether, and epoxy resin. The carbon fiber prepreg is placed in a blade basin mold (not shown in the figure) or a blade back mold (not shown in the figure) and cured to form a hard blade basin 221 or blade back 222 with strong structural stability and excellent mechanical properties. The curing process can be thermal curing or light curing, and the embodiment of the present application does not impose too many restrictions on this. Those skilled in the art can choose according to the material properties.

[0063] It should be noted that, in this article, relational terms such as first and second, etc. are only 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. Moreover, the terms "include", "comprise" or any other variants thereof are intended to cover non-exclusive inclusion, so that a process, method, article or device comprising a series of elements includes not only those elements, but also other elements not explicitly listed, or also includes elements inherent to such process, method, article or device. In the absence of further restrictions, the elements defined by the statement "include..." do not exclude the existence of other identical elements in the process, method, article or device comprising the elements.

[0064] Finally, it should be noted that the above embodiments are only used to illustrate the technical solution of the present application, rather than to limit it. The present application is described in detail with reference to the preferred embodiments only. Those skilled in the art should understand that the technical solution of the present application can be modified or replaced by equivalents without departing from the spirit and scope of the technical solution of the present application, and should be included in the scope of the claims of the present application.

Claims

1. A propeller, characterized in that: The invention comprises a propeller hub and a plurality of propeller blades, wherein the plurality of propeller blades are fixed on the propeller hub, the propeller blades comprise a supporting frame and a blade surface covered on the supporting frame, and the supporting frame comprises: a spar extending along a first direction, wherein the first direction is a length direction of the blade; a wing rib extending along a second direction, the second direction being perpendicular to the first direction, the number of the wing ribs being multiple, the multiple wing ribs being arranged at intervals along the first direction, and a mounting hole for the spar to pass through being arranged at the center of each wing rib; Wherein, the wing rib and the wing beam are both made of carbon fiber multilayer plates, and the carbon fiber multilayer plates are made of multiple layers of carbon fiber cloth stacked and laid, and two adjacent layers of carbon fiber cloth are bonded and connected.

2. The propeller according to claim 1, characterized in that: The wing spar is a circular tube.

3. The propeller according to claim 1, characterized in that: The blade is divided into a plurality of blade segments of equal length along the first direction, the blade segment farthest from the hub is the first segment, and the number of ribs arranged in the first segment is greater than the number of ribs arranged in the other blade segments.

4. The propeller according to claim 1, characterized in that: A plane passing through the wing beam and perpendicular to the thickness direction of the blade is taken as a reference plane, and a preset angle is provided between the rib and the reference plane, and the range of the preset angle is 5° to 45°.

5. The propeller according to claim 1, characterized in that: The wing rib includes a first side and a second side opposite to each other, one end of the first side is directly connected to one end of the second side to form a pointed structure, an arc transition section is provided between the other end of the first side and the other end of the second side, and both ends of the arc transition section are respectively connected to the first side and the second side.

6. The propeller according to claim 5, characterized in that: The first side is convex in a direction away from the second side, and the second side is a straight side or the second side is concave toward the first side.

7. The propeller according to claim 6, characterized in that The blade surface includes a blade base and a blade back, the first side is connected to the blade back, and the second side is connected to the blade base.

8. The propeller according to claim 7, characterized in that The blade basin and the blade back are both formed by curing carbon fiber prepreg cloth, and the carbon fiber prepreg cloth is made of carbon fiber cloth impregnated with a resin matrix. The blade basin is bonded to the supporting frame by epoxy resin, and the blade back is bonded to the supporting frame by epoxy resin.

9. The propeller according to claim 1, characterized in that: The number of the blades is three, and the three blades are evenly arranged along the circumference of the hub, and the angle between the axes of two adjacent blades is 120°.

10. A drone, characterized in that: Comprising a propeller as claimed in any one of claims 1 to 9.

Images