Wind-disturbance-resistant unmanned aerial vehicle rotor wing protection cover structure

Abstract

The utility model discloses an anti-wind disturbance unmanned aerial vehicle rotor wing protective cover structure, which comprises an annular cover and a lead, a plurality of groups of diversion trenches are symmetrically arranged around the surface position of the annular cover, and diversion grids are obliquely arranged in the diversion trenches. According to the utility model, the flow guide grooves and the flow guide grids are adopted, the flow guide grooves are symmetrically formed in the two sides of the surface of the annular cover, the flow guide grids are mounted in the flow guide grooves, the inclination angles of the flow guide grids are different according to different positions, and when the flow guide grooves are located above the rotor wings, the flow guide grids incline upwards, so that the flow guide grids are inclined upwards; when the flow guide grooves are located below the rotor wings, the flow guide grids incline downwards, in this way, when crosswind impact occurs, crosswind can be guided to the upper portion and the lower portion of the rotor wings through flow guide of the flow guide grids at different positions, and then it is avoided that the crosswind directly acts on the rotor wings, air flow is uneven, and flight safety is affected; the device has the advantage of crosswind diversion.

Description

Technical Field

[0001] This utility model relates to the field of rotor protection technology, specifically to a rotor protection structure for wind-resistant unmanned aerial vehicles. Background Technology

[0002] A rotary-wing drone has multiple rotors mounted on its frame, which are driven by motors to rotate at high speed. The high-speed rotation of the rotors is driven by the reaction force of the high-speed airflow, which propels the drone into flight.

[0003] The existing publicly available technology, application number CN202320254522.9, describes a rotor shield for a drone. It prevents the shield from rotating by adding a limiting structure between the connecting and fixing components of the rotor shield, thereby avoiding collisions between the rotor blades and the shield that could cause damage.

[0004] However, the above-mentioned patent still has certain drawbacks in use: although it can provide some protection for the rotor, the surface structure of the protective cover is simple, and crosswinds will directly act on the rotor blades, resulting in uneven lift on the left and right sides, causing the fuselage to tilt or drift, reducing flight safety. At the same time, the protective cover can only perform the most basic protective operations, and its functionality is relatively weak, reducing the practicality of the structure. The overall use effect is not ideal, and there is room for improvement.

[0005] There are currently no effective solutions to the problems in the relevant technologies. Utility Model Content

[0006] To address the shortcomings of existing technologies, this utility model provides a wind-resistant drone rotor shield structure, which has the advantages of crosswind guidance, strong practicality, and good protection, thereby solving the problems mentioned in the background technology.

[0007] To achieve the aforementioned advantages of crosswind guidance, strong practicality, and good protection, the specific technical solution adopted by this utility model is as follows:

[0008] The wind-resistant drone rotor protective cover structure includes an annular cover and wires. Several sets of flow guide grooves are symmetrically arranged around the surface of the annular cover. Flow guide grilles are installed at an angle inside each flow guide groove. The flow guide grilles located above the rotor are inclined upwards, and the flow guide grilles located below the rotor are inclined downwards.

[0009] Furthermore, a heating cavity is formed around one side of the inner surface of the annular cover, and a heating wire is installed inside the heating cavity. The heating wire is electrically connected to the drone control and power supply equipment through a wire. Several sets of heat conduction holes are formed on one side of the heating cavity on the surface of the annular cover, and a temperature sensor is installed on one side of the inner surface of the annular cover.

[0010] Furthermore, a hydrophobic layer is provided on the outer surface of the annular cover.

[0011] Furthermore, several sets of anti-collision strips are installed around the outer surface of the annular cover.

[0012] Furthermore, a locking block is installed on one side of the bottom surface of the annular cover, and fastening holes are symmetrically opened on both sides of the locking block.

[0013] Furthermore, a retaining ring is installed on the other side surface of the bottom of the annular cover.

[0014] Furthermore, the card block surface is provided with a groove, and the groove structure corresponds to the surface structure of the UAV arm.

[0015] Furthermore, the surface of the retaining ring is provided with a groove, and the groove structure corresponds to the base structure where the UAV rotor is located.

[0016] Compared with the prior art, this utility model provides a wind-resistant drone rotor protective cover structure, which has the following beneficial effects:

[0017] (1) This utility model adopts a flow guide groove and a flow guide grid. The surface of the annular cover is symmetrically provided with flow guide grooves on both sides, and a flow guide grid is installed inside each flow guide groove. The angle of inclination of the flow guide grid is different depending on its position. When the flow guide groove is above the rotor, the flow guide grid is tilted upward. When the flow guide groove is below the rotor, the flow guide grid is tilted downward. In this way, when there is a crosswind impact, the crosswind can be guided to the upper and lower positions of the rotor by the flow guide grids at different positions, thereby avoiding the crosswind directly acting on the rotor position and causing uneven airflow that affects flight safety. It has the advantage of crosswind guidance.

[0018] (2) This utility model adopts heating wire, anti-collision strip and hydrophobic layer. In addition to guiding the crosswind through the guide channel, the outer surface of the annular cover is also surrounded by anti-collision strip. When a collision occurs, it can play a certain protective role, reduce the impact directly on the rotor, and improve the protection effect of the rotor. In addition, the surface of the annular cover is provided with a hydrophobic layer, which can reduce the adhesion of water and dust to a certain extent, making it convenient for subsequent cleaning and maintenance. In addition, the annular cover is also provided with heating wire. When flying in a low temperature environment, the operation of the heating wire can transfer heat to the outside through the heat conduction hole, thereby preventing the rotor from icing and ensuring that it can fly normally. The whole structure can not only effectively enrich the functionality through multiple different measures, but also improve the practicality and facilitate better use. It has the advantages of strong practicality and good protection. Attached Figure Description

[0019] To more clearly illustrate the technical solutions in the embodiments of this utility model or the prior art, the drawings used in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of this utility model. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0020] Figure 1 This is a schematic diagram of the wind-resistant UAV rotor shield structure proposed in this utility model;

[0021] Figure 2 This is a schematic diagram of the internal structure of the heating chamber of this utility model;

[0022] Figure 3 This is a schematic diagram of the flow guide channel of this utility model;

[0023] Figure 4 This is a structural schematic diagram of the anti-collision strip of this utility model.

[0024] In the picture:

[0025] 1. Annular cover; 2. Hydrophobic layer; 3. Flow guide channel; 4. Flow guide grid; 5. Anti-collision strip; 6. Locking block; 7. Fastening hole; 8. Wire; 9. Heating chamber; 10. Heat conduction hole; 11. Temperature sensor; 12. Snap ring; 13. Heating wire. Detailed Implementation

[0026] To further illustrate the various embodiments, the present invention provides accompanying drawings, which are part of the disclosure of the present invention. These drawings are mainly used to illustrate the embodiments and can be used in conjunction with the relevant descriptions in the specification to explain the operating principles of the embodiments. With reference to these contents, those skilled in the art should be able to understand other possible implementation methods and the advantages of the present invention. The components in the figures are not drawn to scale, and similar component symbols are usually used to represent similar components.

[0027] According to an embodiment of the present invention, a wind-resistant unmanned aerial vehicle (UAV) rotor shield structure is provided.

[0028] The present invention will now be further described in conjunction with the accompanying drawings and specific embodiments, such as... Figure 1-4As shown, the anti-wind-interference drone rotor protective cover structure according to an embodiment of the present invention includes an annular cover 1 and a guide wire 8. Several sets of guide grooves 3 are symmetrically arranged around the surface of the annular cover 1. Guide grilles 4 are installed at an angle inside each guide groove 3. The guide grilles 4 located above the rotor are inclined upwards, and the guide grilles 4 located below the rotor are inclined downwards. The annular cover 1, as the basic main body of the entire protective cover structure, is circular in shape, with its center coinciding with the rotation center of the drone rotor. It is installed around the outer periphery of the rotor, creating a protective boundary for the rotor. The guide grooves 3 are symmetrically arranged around the outer surface of the annular cover 1, with the vertical central axis of the rotor as the axis of symmetry. Each set of guide channels 3 is evenly distributed along the circumference of the annular cover 1. Its cross-sectional shape is a narrow, elongated groove, with the length of the channel aligned with the generatrix of the annular cover 1. The depth of the guide channels 3 is moderate, ensuring sufficient space for installing the guide grilles 4 without excessively weakening the structural strength of the annular cover 1. Guide grilles 4: Each guide channel 3 has a guide grille 4 installed at an angle inside. The guide grille 4 consists of multiple parallel strips, with both ends of the strips fixedly connected to the side walls of the guide channel 3. The guide grille 4 located above the rotor has its strips tilted upwards, forming an acute angle (denoted as α, typically between 15° and 30°) with the plane of the outer surface of the annular cover 1. The guide grille 4 located below the rotor has its strips tilted downwards, forming another acute angle (denoted as β, typically also between 15° and 30°) with the plane of the outer surface of the annular cover 1. (Within 30°, and α and β can be optimized and adjusted according to actual test results); Structural fit relationship: The symmetrical distribution of the guide slots 3 ensures that the crosswind can be guided by the corresponding guide slots 3 and guide grilles 4 regardless of the horizontal direction from which it blows. The tilt angle of the guide grilles 4 is specifically designed according to its location (above or below the rotor), forming a symmetrical guide structure; Function: Crosswind guidance: When the crosswind (such as the wind blowing from the left or right) impacts the surface of the annular cover 1, the upper guide grille 4 guides the crosswind upward, allowing it to flow over the rotor; the lower guide grille 4 guides the crosswind downward. This allows the crosswind to flow under the rotor, preventing it from acting directly and vertically on the rotor blades and reducing interference with the airflow around the rotor. The airflow is stabilized by the flow guide grille 4, which divides and guides the airflow, making it smoother and reducing turbulence, thus further improving the stability of the UAV flight. Through the combined action of the flow guide slot 3 and the flow guide grille 4, the impact force of the crosswind is decomposed into upward and downward components, changing the direction of the crosswind and making the airflow distribution on the rotor more uniform. This reduces the uneven lift on both sides caused by the crosswind, effectively reducing the risk of fuselage tilting or drifting, and achieving the technical effect of resisting wind disturbance.

[0029] In one embodiment, a heating cavity 9 is formed around one side of the inner surface of the annular cover 1. A heating wire 13 is installed inside the heating cavity 9. The heating wire 13 is electrically connected to the drone control and power supply equipment via a wire 8. Several sets of heat-conducting holes 10 are formed on one side of the heating cavity 9 on the surface of the annular cover 1. A temperature sensor 11 is installed on one side of the inner surface of the annular cover 1. The heating cavity 9 is a closed cavity formed around the circumference of the annular cover 1 on one side of the inner surface of the annular cover 1. The cross-sectional shape of the cavity is rectangular or other shapes suitable for accommodating the heating wire 13. A wall of a certain thickness is left between the heating cavity 9 and the outer surface of the annular cover 1 to ensure that the annular cover 1... The structural strength and thermal conductivity; Heating wire 13: Installed in a spiral or wavy shape inside the heating cavity 9, with both ends of the heating wire 13 led out of the heating cavity 9 through wires 8, electrically connected to the control and power supply equipment of the drone; The material of the heating wire 13 is usually a high resistivity, high temperature resistant alloy material (such as nickel-chromium alloy), and its power is designed and adjusted according to the power supply capacity of the drone and the actual heating requirements; Heat conduction hole 10: Multiple sets of small holes are evenly opened on the surface of the annular cover 1 on one side of the heating cavity 9, each set of small holes contains multiple closely arranged fine holes, and the heat conduction hole 10 penetrates the wall of the annular cover 1, so that the interior of the heating cavity 9 is connected to the outside, which facilitates heat dissipation; Temperature sensor 11: Installed On one side of the inner surface of the annular cover 1, near the heating cavity 9, a device is used to monitor the temperature inside the annular cover 1 in real time and transmit the temperature signal to the UAV control system via the wire 8. The heating wire 13 generates heat after being energized inside the heating cavity 9. The heat is conducted through the wall of the heating cavity 9 to the outer surface of the annular cover 1 and dissipated to the outside through the heat conduction hole 10. The temperature sensor 11 monitors the temperature in real time. When the temperature is too high or too low, it sends a signal to the control system. The control system adjusts the current of the heating wire 13 to control the heating power, thus achieving automatic temperature regulation. Function: Anti-icing: In low-temperature environments, the heat generated by the heating wire 13 is transferred through the heat conduction hole 10. The heating element 13 provides continuous and stable heat to the outer surface of the annular cover 1 and around the rotor, increasing the temperature near the rotor and preventing water vapor in the air from condensing into ice on the rotor, which would affect the normal rotation of the rotor and the generation of lift. Temperature monitoring and control: Temperature sensor 11 monitors the temperature in real time to ensure that the heating system operates within a reasonable temperature range, avoiding damage to the annular cover 1 or other components due to excessively high temperatures, or failure to achieve the anti-icing effect due to excessively low temperatures. Through the coordinated work of heating wire 13, heat conduction hole 10 and temperature sensor 11, continuous and stable heat is provided to the rotor in low-temperature environments, effectively preventing rotor icing, ensuring the normal flight of the UAV in severe weather conditions, and improving the environmental adaptability and practicality of the UAV.

[0030] In one embodiment, a hydrophobic layer 2 is provided on the outer surface of the annular cover 1. The hydrophobic layer 2 is uniformly covered on the outer surface of the annular cover 1 by processes such as spraying, coating, or plating. The material of the hydrophobic layer 2 is usually a material with low surface energy, such as fluoropolymers or silicone materials, and its thickness is relatively thin (usually between a few micrometers and tens of micrometers), so it will not have a significant impact on the structure and flow guiding function of the annular cover 1. The hydrophobic layer 2, as a functional coating on the outer surface of the annular cover 1, together with components such as the flow guiding groove 3 and the anti-collision strip 5, constitutes the outer surface structure of the annular cover 1. There is no direct mechanical connection between them, but they complement each other functionally. Function: Reduce moisture adhesion. Due to the low surface energy of the hydrophobic layer 2, water droplets do not easily adhere to its surface, but instead form water beads and roll off, thereby reducing the retention of rainwater, dew, etc. on the surface of the annular cover 1 and preventing moisture from affecting the flow guiding effect of the flow guide grille 4 and the appearance of the annular cover 1; preventing dust accumulation: the smooth surface of the hydrophobic layer 2 can reduce the adhesion between dust and the surface of the annular cover 1, making it easier for dust to be blown away by the wind or removed during cleaning, facilitating subsequent cleaning and maintenance work; the presence of the hydrophobic layer 2 gives the surface of the annular cover 1 hydrophobic, oleophobic, and anti-fouling properties, reducing the impact of external pollutants on the structure and function of the protective cover, extending the cleaning cycle of the protective cover, and improving its ease of use and practicality.

[0031] In one embodiment, several sets of anti-collision strips 5 are installed around the outer surface of the annular cover 1. The anti-collision strips 5 are made of elastic materials (such as rubber, silicone, etc.), are long strips, and are uniformly installed around the outer surface of the annular cover 1. The two ends of the anti-collision strips 5 are fixedly connected to the outer surface of the annular cover 1 by glue, screws or other fixing methods to ensure that they will not fall off when impacted. The anti-collision strips 5 are installed around the outer surface of the annular cover 1 in the area between the guide grooves 3, and are distributed at intervals with the guide grooves 3. When a collision occurs, the anti-collision strips 5 first come into contact with the colliding object and absorb the collision energy through their own elastic deformation. Function: Collision protection: When the UAV collides with external objects (such as obstacles, ground, etc.), the anti-collision strips 5 absorb the impact force generated by the collision through elastic deformation, reduce the transmission of the impact force to the annular cover 1 and the rotor, and reduce the risk of rotor damage due to collision. As an external protective layer of the annular cover 1, the anti-collision strips 5 effectively improve the anti-collision capability of the protective cover, provide more reliable protection for the rotor, and enhance the safety and reliability of the UAV in complex environments.

[0032] In one embodiment, a locking block 6 is installed on one side of the bottom surface of the annular cover 1. Fastening holes 7 are symmetrically opened on both sides of the locking block 6. The locking block 6 is installed on one side of the bottom surface of the annular cover 1 and has a block-shaped structure. Its surface has a groove. The shape and size of the groove are adapted to the surface structure of the UAV arm to ensure that the locking block 6 can be tightly locked on the arm. The fastening holes 7 are symmetrically opened on both sides of the locking block 6. The axis of the fastening holes 7 is perpendicular to the surface of the locking block 6 and is used to insert fasteners (such as screws, bolts, etc.).

[0033] In one embodiment, a retaining ring 12 is installed on the other side of the bottom surface of the annular cover 1. The retaining ring 12 is installed on the other side of the bottom surface of the annular cover 1, and has an annular structure. Its surface is also provided with a groove. The shape and size of the groove are adapted to the structure of the base where the UAV rotor is located, so that the retaining ring 12 can be accurately engaged in the base.

[0034] In one embodiment, the surface of the card block 6 is provided with a slot, and the slot structure corresponds to the surface structure of the drone arm.

[0035] In one embodiment, the retaining ring 12 has a groove on its surface, and the groove structure corresponds to the base structure where the UAV rotor is located. During installation, first, align the retaining ring 12 at the bottom of the annular cover 1 with the base where the UAV rotor is located, and engage the groove of the retaining ring 12 with the corresponding structure of the base, so that the annular cover 1 is initially positioned in the rotor base direction; then, align the groove of the locking block 6 with the UAV arm, push the annular cover 1, and lock the locking block 6 onto the arm; finally, insert the fasteners into the fastening holes 7 on both sides of the locking block 6, and tighten the fasteners, so that the locking block 6 is firmly fixed to the arm by the tension of the fasteners, thereby achieving a firm connection between the annular cover 1 and the UAV; Functional role Precise Positioning: The slotted structure of the locking block 6 and the retaining ring 12, adapted to the design of the UAV arm and rotor base, ensures that the annular cover 1 can be accurately installed on the outer periphery of the rotor, guaranteeing that the positions of the guide slot 3 and the guide grille 4 correspond to the rotor, achieving optimal wind resistance. Secure Fixing: The locking block 6 is fixed to the arm by fasteners passing through the fastening holes 7, forming a reliable mechanical connection between the annular cover 1 and the UAV, preventing the annular cover 1 from loosening or falling off during flight due to vibration, airflow impact, etc. The combined use of the locking block 6, fastening holes 7, and retaining ring 12 enables rapid, precise installation and secure fixing of the annular cover 1 to the UAV. The design ensures the stability of the protective shield structure during flight, providing a reliable installation foundation for its wind resistance and protection functions. Wind resistance and protection work synergistically: the guide trough 3 and guide grille 4 guide crosswinds, reducing the direct impact of airflow on the rotor and achieving wind resistance; the anti-collision strip 5 absorbs collision energy, protecting the rotor from collision damage. Together, these elements enhance the safety of the UAV in complex environments. Environmental adaptability and practicality work synergistically: the hydrophobic layer 2 reduces moisture and dust adhesion, facilitating cleaning and maintenance; the heating system, consisting of the heating chamber 9, heating wire 13, and temperature sensor 11, prevents rotor icing in low-temperature environments, ensuring... For flight safety, these components collectively enhance the environmental adaptability and practicality of the protective shield. Installation and functional synergy: Installation structures such as the locking block 6, locking ring 12, and fastening hole 7 ensure the ring shield 1 is securely installed on the UAV, allowing components such as the airflow guide 3, airflow guide grille 4, anti-collision strip 5, and heating system to accurately perform their respective functions, achieving the design goals of the entire protective shield structure. Through the coordinated work of the above components in physical connection, structural fit, and functional role, the UAV rotor protective shield structure achieves multiple functions such as crosswind guidance, collision resistance, anti-icing, and easy cleaning, significantly improving the UAV's flight safety, environmental adaptability, and practicality.

[0036] Working Principle: In actual use, the operator can place the annular cover 1 on the outer periphery of the drone rotor. Pushing the annular cover 1 causes the retaining ring 12 on its surface to engage with the base where the rotor is located. Simultaneously, the retaining block 6 on the other side of the annular cover 1 engages with the drone's arm. Fasteners are then inserted into the fastening holes 7 on the surface of the retaining block 6 and tightened to secure the annular cover 1, ensuring its stability during use and providing better protection. Furthermore, the annular cover 1 has symmetrically arranged guide channels 3 on both sides of its surface, and each guide channel 3 is equipped with a guide grille 4. The angle of inclination of the guide grille 4 varies depending on its position. When the guide channel 3 is above the rotor, the guide grille 4 tilts upwards; when the guide channel 3 is below the rotor, the guide grille 4 tilts downwards. This allows the guide grille 4 at different positions to direct crosswinds. The annular cover 1 is positioned above and below the rotor to prevent crosswinds from directly impacting the rotor and causing uneven airflow that could affect flight safety. Furthermore, the outer surface of the annular cover 1 is surrounded by anti-collision strips 5, which provide some protection in the event of a collision, reducing the impact on the rotor and enhancing its protection. The surface of the annular cover 1 also has a hydrophobic layer 2, which reduces moisture and dust adhesion, facilitating subsequent cleaning and maintenance. In addition, the annular cover 1 contains a heating wire 13. When flying in low-temperature environments, the heating wire 13 transfers heat to the outside through the heat conduction holes 10, preventing rotor icing and ensuring normal flight operation. This entire structure, through multiple different measures, not only effectively enriches functionality but also enhances practicality and ease of use. The device as a whole has the advantages of crosswind guidance, strong practicality, and good protection.

[0037] In this utility model, unless otherwise explicitly specified and limited, the terms "installation", "setting", "connection", "fixing", "screw connection", etc., should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral part; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; they can refer to the internal connection of two components or the interaction between two components. Unless otherwise explicitly limited, those skilled in the art can understand the specific meaning of the above terms in this utility model according to the specific circumstances.

[0038] The above description is only a preferred embodiment of the present utility model and is not intended to limit the present utility model. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present utility model should be included within the protection scope of the present utility model.

Claims

1. Anti-wind disturbance unmanned aerial vehicle rotor protection cover structure, comprising a ring cover (1) and a guide wire (8), characterized in that, The annular cover (1) has several sets of guide grooves (3) symmetrically arranged around its surface. The guide grooves (3) are all installed with guide grilles (4) at an angle. The guide grilles (4) located above the rotor are inclined upwards, and the guide grilles (4) located below the rotor are inclined downwards.

2. The wind resistant drone rotor cover structure of claim 1, wherein, A heating chamber (9) is provided around one side of the inner surface of the annular cover (1). A heating wire (13) is installed inside the heating chamber (9). The heating wire (13) is electrically connected to the UAV control and power supply equipment through a wire (8). Several sets of heat conduction holes (10) are provided on one side of the heating chamber (9) on the surface of the annular cover (1). A temperature sensor (11) is installed on one side of the inner surface of the annular cover (1).

3. The wind resistant drone rotor cover structure of claim 1, wherein, The annular cover (1) has a hydrophobic layer (2) on its outer surface.

4. The wind resistant drone rotor cover structure of claim 1, wherein, The outer surface of the annular cover (1) is surrounded by several sets of anti-collision strips (5).

5. The wind resistant drone rotor cover structure of claim 1, wherein, A locking block (6) is installed on one side of the bottom surface of the annular cover (1), and fastening holes (7) are symmetrically opened on both sides of the locking block (6).

6. The wind resistant drone rotor cover structure of claim 1, wherein, A retaining ring (12) is installed on the other side of the bottom surface of the annular cover (1).

7. The wind resistant drone rotor cover structure of claim 5, wherein, The card block (6) has a slot on its surface, and the slot structure corresponds to the surface structure of the UAV arm.

8. The wind resistant drone rotor cover structure of claim 6, wherein, The surface of the retaining ring (12) is provided with a groove, and the groove structure corresponds to the base structure where the UAV rotor is located.

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