Unmanned aerial vehicle fan wheel structure

Abstract

The utility model discloses an unmanned plane fan blade wheel structure, including the wheel hub that is equipped with the axle hole in the center, the hub outer circle is equipped with the blade subassembly through angle adjusting assembly, and the inside of fan blade is equipped with main strengthening beam and at least one group of auxiliary strengthening rib plate, main strengthening beam is along the fan blade and extends from the root to the tip, and auxiliary strengthening rib plate extends from the web of main strengthening beam to the direction of leaf face and back, and is surrounded into triangle support cavity with leaf face, back and main strengthening beam, is equipped with a plurality of lightening holes on auxiliary strengthening rib plate, the utility model discloses the triangle support cavity that is formed by the main strengthening beam and auxiliary strengthening rib plate of I -shaped, and the stress dispersion hole optimization stress distribution of main strengthening beam web, and the lightening weight of auxiliary strengthening rib plate lightening weight, and the angle adjusting assembly is limited to the cooperation of fan blade and is gathered, reaches the excellent effect of promotion fan blade structure strength, the inhibition airflow mutation deformation, the stable rotation axis center without deviation, the fixed angle of high -speed rotation setting, the enhancement flight stability.

Description

Technical Field

[0001] This utility model relates to the technical field of drone fans, and specifically to a drone fan impeller structure. Background Technology

[0002] Drones are widely used in scenarios such as power line inspection, logistics distribution, and agricultural plant protection. Fixed-wing drones adopt a ducted fan structure and suppress tip vortices and noise with a ring fairing, making them suitable for complex low-altitude urban environments. Their high thrust characteristics are outstanding in fields such as aerial surveying and security. For example, drones equipped with lidar can quickly complete centimeter-level precision mapping of 100,000 square meters of construction sites, and the data collection efficiency is more than 20 times higher than that of manual labor.

[0003] The performance of a drone fan directly affects the drone's flight stability, endurance, and adaptability to extreme environments. In the current technology, pure plastic fan blades are low in cost and easy to process, but they have the defects of low strength and easy deformation. They are only suitable for toy-grade small drones. When rotating at high speed, they are prone to large deformation due to sudden changes in airflow, which in turn affects flight stability. Summary of the Invention

[0004] The purpose of this invention is to overcome the shortcomings of existing technologies and provide a UAV fan impeller structure. This structure utilizes a triangular support cavity formed by an I-shaped main reinforcing beam and auxiliary reinforcing ribs. Stress dispersion holes in the main reinforcing beam web optimize stress distribution, while weight-reducing holes in the auxiliary reinforcing ribs reduce weight. Combined with a shock-absorbing ring embedded in the hub's annular groove for counterweight adjustment, and an angle adjustment component for limiting the fan blade's expansion and contraction, this invention solves the technical problems of low strength and easy deformation of pure plastic fan blades, high-speed rotation axis misalignment, difficulty in adjusting and limiting the assembly angle, and insufficient adaptability to extreme environments. This achieves excellent results in improving the fan blade structure strength, suppressing sudden airflow deformation, maintaining a stable and unmisaligned rotation axis, ensuring a fixed high-speed rotation angle, and enhancing flight stability.

[0005] To achieve the above objectives, the present invention adopts the following technical solution:

[0006] A drone fan impeller structure includes a hub with a central shaft hole. A blade assembly is provided around the outer periphery of the hub via an angle adjustment component, which limits the movement of the blade assembly. The angle adjustment component includes a fixed base on the hub, a limiting handle on the fixed base, and a limiting shaft linked to the limiting handle. The blade assembly includes at least two sets of blades, one end of which has a rotating shaft rotatably connected to the fixed base. A limiting hole is provided on one side of the rotating shaft to engage with the limiting bearing. A main reinforcing beam is provided inside the blade. The main reinforcing beam extends from the root to the tip along the blade span, with an I-shaped cross-section. The main reinforcing beam includes an upper flange, a lower flange, and a web between the upper and lower flanges. The upper flange is attached to the inner side of the blade surface, and the lower flange is attached to the inner side of the blade back. The auxiliary reinforcing ribs extend from the web of the main reinforcing beam toward the blade surface and blade back, forming a triangular support cavity together with the blade surface, blade back, and main reinforcing beam. The auxiliary reinforcing ribs are provided with several weight-reducing holes, which are evenly distributed along the length of the auxiliary reinforcing ribs.

[0007] The main reinforcing beam, auxiliary reinforcing ribs, and fan blade body are integrally formed.

[0008] The auxiliary reinforcing ribs are provided with rounded corners at the connection between the blade surface and the blade back.

[0009] The web thickness of the main reinforcing beam gradually decreases from the root to the tip, and is set according to the curvature and thickness of the fan blade.

[0010] The main reinforcing beam has stress dispersion holes on its web, which are located in the middle of the web and distributed along the spanwise direction.

[0011] The fan blade surface is coated with a nano-ceramic coating.

[0012] The hub is fitted with a shock-absorbing ring, which is used to prevent resonance when the fan blades rotate.

[0013] The shock-absorbing ring is annular, and its diameter matches the annular groove on the wheel hub.

[0014] The fan blade is an asymmetric airfoil with a leading edge curvature greater than a trailing edge curvature.

[0015] The inner wall of the hub's shaft hole is provided with a keyway, which is used to mate with the motor shaft key.

[0016] The beneficial effects of this utility model are as follows: through the triangular support cavity formed by the I-shaped main reinforcing beam and the auxiliary reinforcing ribs, the stress distribution is optimized by the stress dispersion holes in the web of the main reinforcing beam, and the weight is reduced by the weight reduction holes in the auxiliary reinforcing ribs. Combined with the adjustment of the counterweight center of gravity by embedding the shock-absorbing ring into the annular groove of the hub, and the limiting cooperation of the angle adjustment component for the expansion and contraction of the fan blades, the excellent technical effects of improving the structural strength of the fan blades, suppressing sudden deformation of airflow, maintaining the stability of the rotation axis without deviation, ensuring the fixed setting angle of high-speed rotation, and enhancing flight stability are achieved. Attached Figure Description

[0017] Figure 1 This is one of the perspective views of this utility model.

[0018] Figure 2 This is the second perspective view of this utility model.

[0019] Figure 3 This is a perspective view of the fan blade of this utility model.

[0020] Figure 4 This is a partial cross-sectional view of the fan blade of this utility model.

[0021] Explanation of icon numbers:

[0022] 1-Hub, 10-Shaft hole, 11-Keyway, 2-Shock damping ring, 3-Angle adjustment assembly, 30-Fixing seat, 31-Limit handle, 32-Limit shaft, 4-Blade assembly, 40-Fan blade, 400-Rotating shaft, 401-Limit hole, 41-Main reinforcing beam, 410-Upper wing plate, 411-Lower wing plate, 412-Web plate, 413-Stress dispersion hole, 42-Auxiliary reinforcing rib, 420-Weight reduction hole. Detailed Implementation

[0023] The present invention will be further described below with reference to the accompanying drawings:

[0024] like Figure 1-4As shown, this utility model relates to a fan impeller structure for a drone, including a hub 1 with a central shaft hole 10, a shock-absorbing ring 2 embedded in the hub 1 to prevent resonance when the fan blades 40 rotate. The shock-absorbing ring 2 is annular, and its diameter matches the annular groove on the hub 1. The inner wall of the shaft hole 10 of the hub 1 has a keyway 11 for engaging with a motor shaft key. A blade assembly 4 is provided on the outer periphery of the hub 1 via an angle adjustment component 3, which limits the movement of the blade assembly 4. The angle adjustment component 3 includes a fixed component on the hub 1. The assembly includes a fixed base 30, a limiting handle 31 mounted on the fixed base 30, and a limiting shaft 32 linked to the limiting handle 31. The blade assembly 4 includes at least two sets of fan blades 40. The surface of the fan blades 40 is coated with a nano-ceramic coating to enhance their corrosion resistance and wear resistance. The main body of the fan blades 40 is an asymmetrical airfoil with a leading edge curvature greater than the trailing edge curvature. One end of the fan blades 40 is provided with a rotating shaft 400 rotatably connected to the fixed base 30, and a limiting hole 401 is provided on one side of the rotating shaft 400 to engage with the limiting shaft 32. The fan blades 40 are internally provided with a main reinforcing beam 41 and multiple sets of auxiliary beams. Auxiliary reinforcing rib 42; Main reinforcing beam 41 extends from the root to the tip along the longitudinal direction of fan blade 40, with an I-shaped cross-section. The main reinforcing beam 41 includes an upper flange 410, a lower flange 411, and a web 412 disposed between the upper flange 410 and the lower flange 411. The upper flange 410 is attached to the inner side of the fan blade 40, and the lower flange 411 is attached to the inner side of the back of the fan blade 40. Auxiliary reinforcing rib 42 extends from the web 412 of the main reinforcing beam 41 towards the fan blade and the back of the fan blade, forming a triangular support cavity together with the fan blade, the back of the fan blade, and the main reinforcing beam 41. An auxiliary reinforcing rib 42 is provided on the auxiliary reinforcing rib 42. There are several weight-reducing holes 420, which are evenly distributed along the length of the auxiliary reinforcing rib 42. The main reinforcing beam 41, the auxiliary reinforcing rib 42 and the fan blade 40 are integrally formed. The connection between the auxiliary reinforcing rib 42 and the blade surface and blade back is provided with a rounded transition fillet to disperse the stress distribution at the connection. The thickness of the web plate 412 of the main reinforcing beam 41 gradually decreases from the root to the tip, and is set according to the curvature and thickness of the fan blade 40. The web plate 412 of the main reinforcing beam 41 is provided with stress dispersion holes 413, which are located in the middle of the web plate 412 and distributed along the spanwise direction.

[0025] like Figure 1-4As shown, titanium alloy powder is used as raw material to prepare the internal support frame of the fan blade 40. It is formed by laser 3D printing technology. After forming, the main reinforcing beam 41 and the auxiliary reinforcing rib 42 are integrated into a support frame. When the fan blade 40 rotates at high speed, the airflow first acts on the blade surface of the fan blade 40. The generated aerodynamic load is transferred to the auxiliary reinforcing rib 42 through the blade surface. The auxiliary reinforcing rib 42 converts the load into axial tensile and compressive stress, which is transferred to the web plate 412 of the main reinforcing beam 41 through the triangular support cavity. Then, it is dispersed to the root of the fan blade 40 by the upper wing plate 410 and the lower wing plate 411, and finally transferred to the motor shaft through the hub 1. The I-shaped main reinforcing beam 41 is subjected to spanwise bending stress. It is supported by multiple sets of auxiliary reinforcing ribs 42 to avoid local deformation of the blade surface and blade back. The damping ring 2 increases the weight at the center of the hub 1. At high speed, the center of gravity is kept on the center line of the motor shaft, so that the rotation axis of the fan blade 40 does not shift when it rotates, and the fan surface does not vibrate or deform significantly.

[0026] During assembly, firstly, the shock-absorbing ring 2 is embedded into the annular groove on the hub 1. Secondly, the fixing seat 30 of the angle adjustment component 3 is mechanically connected to the outer circumference of the hub 1 by welding or bolts. Next, the limiting handle 31 is lifted so that the limiting shaft 32 is pulled out of the fixing seat 30 a certain distance. Then, the fan blade 40 is pulled upward to the horizontal position. At this time, the blade surface of the fan blade 40 abuts against the fixing seat 30, and the limiting hole 401 on the fan blade 40 is aligned with the limiting shaft 32. Then, the limiting handle 31 is pressed down to insert the limiting shaft 32 into the limiting hole 401. After the limiting handle 31 is locked into the slot of the fixing seat 30, it is fixed, and the fan blade 40 is unfolded. Each set of fan blades 40 is unfolded in the same way.

[0027] The above description is only a preferred embodiment of the present utility model and is not intended to limit the scope of the present utility model. Therefore, without departing from the design spirit of the present utility model, any equivalent changes or modifications made by those skilled in the art to the structure, features and principles of the present utility model should fall within the protection scope of the patent application of the present utility model.

Claims

1. A fan impeller structure for a drone, comprising a hub with a central shaft hole, characterized in that: The outer circumference of the hub is provided with a blade assembly via an angle adjustment component, which is used to limit the position of the blade assembly. The angle adjustment component includes a fixed seat on the hub, a limiting handle on the fixed seat, and a limiting shaft linked to the limiting handle. The blade assembly includes at least two sets of fan blades. One end of the fan blade is provided with a rotating shaft that is rotatably connected to the fixed seat, and a limiting hole is provided on one side of the rotating shaft to cooperate with the limiting bearing. The fan blade is provided with a main reinforcing beam and at least one set of auxiliary reinforcing ribs. The main reinforcing beam extends from the root to the tip along the blade span and has an I-shaped cross-section. The main reinforcing beam includes an upper flange, a lower flange, and a web between the upper and lower flanges. The upper flange is attached to the inner side of the blade surface, and the lower flange is attached to the inner side of the blade back. The auxiliary reinforcing rib extends from the web of the main reinforcing beam toward the blade surface and blade back, forming a triangular support cavity together with the blade surface, blade back, and main reinforcing beam. The auxiliary reinforcing rib has several weight-reducing holes, which are evenly distributed along the length of the auxiliary reinforcing rib.

2. The UAV fan impeller structure according to claim 1, characterized in that: The main reinforcing beam, auxiliary reinforcing ribs, and fan blade body are integrally formed.

3. The UAV fan impeller structure according to claim 1, characterized in that: The auxiliary reinforcing rib is provided with a rounded transition corner at the connection between it and the blade surface / blade back.

4. The UAV fan impeller structure according to claim 1, characterized in that: The web thickness of the main reinforcing beam gradually decreases from the root to the tip, and is set according to the curvature and thickness of the fan blade.

5. The UAV fan impeller structure according to claim 1, characterized in that: The main reinforcing beam has stress dispersion holes on its web, which are located in the middle of the web and distributed along the spanwise direction.

6. The UAV fan impeller structure according to claim 1, characterized in that: The fan blade surface is coated with a nano-ceramic coating.

7. The UAV fan impeller structure according to claim 1, characterized in that: The hub is fitted with a shock-absorbing ring, which is used to prevent resonance when the fan blades rotate.

8. The UAV fan impeller structure according to claim 7, characterized in that: The shock-absorbing ring is annular, and its diameter matches the annular groove on the wheel hub.

9. The UAV fan impeller structure according to claim 1, characterized in that: The fan blade is an asymmetric airfoil with a leading edge curvature greater than a trailing edge curvature.

10. The UAV fan impeller structure according to claim 1, characterized in that: The inner wall of the hub's shaft hole is provided with a keyway, which is used to mate with the motor shaft key.

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