A remote control inspection aircraft of low altitude cable

Abstract

This utility model relates to the field of low-altitude aircraft technology and discloses a remote-controlled inspection aircraft for low-altitude cables. It includes a flight mechanism and an inspection mechanism. The flight mechanism comprises a main body, a cross-shaped frame, a rotor drive assembly, a rotor body, a remote control and communication assembly, an electric rotating shaft, a support frame, anti-slip blocks, and connectors. The cross-shaped frame is mounted on the main body. The rotor drive assembly is fitted to the rotor body and engages with the cross-shaped frame via a rotor adapter slot. The remote control and communication assembly is integrated inside and above the main body. This utility model, through the angle design of the cross-shaped frame and the rotor adapter slot (30°–60°), combined with the electric rotating shaft adjusting the support frame (0°–90°), enables the aircraft to adapt to the complex flight attitudes and terrain requirements of low-altitude cable inspection, ensuring flight stability and comprehensive inspection coverage, and flexibly responding to different cable layouts and terrain conditions.

Description

Technical Field

[0001] This utility model relates to the field of low-altitude aircraft technology, specifically a remote-controlled inspection aircraft for low-altitude cables. Background Technology

[0002] Low-altitude cables are widely used in power transmission, communications, and other fields. Being exposed to the outdoors for extended periods, they are susceptible to damage from natural environments (such as wind, rain, and dust) and external forces (such as impacts from foreign objects), leading to problems like breakage, deformation, and foreign object attachment. If these issues are not detected and addressed promptly, they can cause malfunctions or even safety accidents. Traditional manual inspection methods are inefficient, labor-intensive, and difficult to access in certain areas (such as complex terrain or high altitudes).

[0003] Existing low-altitude cable inspection drones have the following shortcomings: First, the coordination between the flight mechanism and the inspection mechanism is poor, and the flight attitude is difficult to adapt to the needs of cable inspection, affecting the inspection coverage and detection accuracy; second, remote control communication is susceptible to interference, and data transmission stability is insufficient, making it impossible to transmit inspection information in real time and accurately; third, the protective structure is rudimentary, and the airframe and inspection equipment are easily damaged during takeoff, landing, and obstacle encounters, reducing the durability of the device. Therefore, there is an urgent need to design a low-altitude cable remote-controlled inspection drone that is stable in flight, highly efficient in inspection, has good protection, and is easy to maintain. Utility Model Content

[0004] (a) Technical problems to be solved.

[0005] To address the shortcomings of existing technologies, this invention provides a remote-controlled aerial vehicle for inspecting low-altitude cables, thus solving the problems mentioned in the background section.

[0006] (ii) Technical solution.

[0007] To achieve the above objectives, this utility model provides the following technical solution: a remote-controlled inspection aircraft for low-altitude cables, comprising a flight mechanism and an inspection mechanism.

[0008] The flight mechanism includes the main body of the aircraft, a cross frame, a rotor drive assembly, a rotor body, a remote control and communication assembly, an electric pivot, a support frame, anti-slip rubber blocks, and connectors. The cross frame is mounted on the main body of the aircraft. The rotor drive assembly is adapted to the rotor body and cooperates with the cross frame through a rotor adapter slot. The remote control and communication assembly is integrated inside and above the main body of the aircraft for remote control and data transmission. The connectors are used to connect the flight mechanism with the inspection mechanism. The electric pivot connects the support frame to the main body of the aircraft. Anti-slip rubber blocks are set at the bottom of the support frame to enhance stability during takeoff and landing.

[0009] The inspection mechanism includes a visual acquisition component, cameras, a bottom protective frame, a peripheral protective frame, and buffer blocks. Multiple cameras are arranged at equal angles around the visual acquisition component to acquire cable images from multiple directions. The bottom protective frame is located at the bottom of the visual acquisition component, and the peripheral protective frame is located around the visual acquisition component. The two are connected to form a protective structure that can protect the inspection mechanism and some parts of the flight mechanism. The buffer blocks are fixedly connected to the bottom of the bottom protective frame for shock absorption.

[0010] As a further improvement of this utility model: the main body of the aircraft and the cross frame are integrated or detachable, and the rotor adapter slot on the cross frame and the installation angle of the rotor body are adapted to the flight attitude requirements of low-altitude cable inspection. The installation angle range is 30°-60°, ensuring flight stability and inspection coverage.

[0011] As a further improvement of this utility model: the remote control and communication component supports multi-band wireless communication, which can realize the transmission of remote control commands and inspection data, including real-time transmission of data such as images and flight status, and has anti-interference encrypted transmission function. The communication frequency band covers 2.4GHz and 5.8GHz, ensuring stable communication in complex electromagnetic environments.

[0012] As a further improvement of this utility model: the electric rotating shaft can drive the support frame to rotate relative to the main body of the aircraft to adjust the angle, with an adjustment range of 0°-90°, to adapt to the take-off, landing and inspection needs of different terrains and cable layouts. The anti-slip rubber block enhances the stability during take-off and landing and avoids slippage.

[0013] As a further improvement of this utility model, the visual acquisition component of the inspection mechanism includes an image recognition processing module, which can perform real-time analysis on the cable images acquired by the camera, identify abnormal states such as cable damage, foreign object attachment, and deformation, and mark the abnormal locations. The image recognition response time is ≤0.5 seconds, thereby improving the inspection accuracy and efficiency.

[0014] As a further improvement of this utility model: the bottom protective frame and the peripheral protective frame are made of lightweight and high-strength alloy material, and the buffer rubber block is made of elastic rubber material. When the aircraft takes off and lands or encounters obstacles in flight, it protects and reduces shock to the aircraft body and inspection equipment. The compression rebound rate of the buffer rubber block is ≥80%, which effectively protects the equipment and extends its service life.

[0015] As a further improvement of this utility model, the flight mechanism and the inspection mechanism are connected by a plug-in or magnetic quick-connect structure, which facilitates the installation, disassembly, maintenance and replacement of the inspection mechanism. The plug-in / magnetic connection operation time is ≤10 seconds, reducing maintenance difficulty and time cost.

[0016] As a further improvement of this utility model, the blades of the rotor body are made of noise-reducing, high-strength composite material, namely carbon fiber, which can reduce flight noise while ensuring flight power and structural strength. The blade noise is ≤65 decibels (measured at a distance of 1 meter), and the blade tensile strength is ≥500MPa.

[0017] Compared with the prior art, the beneficial effects of this utility model are:

[0018] 1. In this utility model, the angle design of the cross frame and rotor adapter slot (30°-60°), combined with the electric rotating shaft adjustment support frame (0°-90°), enables the aircraft to adapt to the complex flight attitude and terrain requirements of low-altitude cable inspection, ensuring flight stability and comprehensive inspection coverage. It can flexibly cope with different cable layouts and terrain rings. Furthermore, the use of a multi-camera perimeter layout + image recognition processing module (response ≤0.5 seconds) enables multi-directional cable detection and rapid anomaly identification, improving inspection accuracy and efficiency, reducing manual judgment costs, and timely detection of minor cable problems, providing accurate basis for subsequent maintenance.

[0019] 2. In this utility model, the lightweight, high-strength alloy protective frame and high-resilience buffer blocks (resilience rate ≥80%) effectively resist external impacts and absorb vibrations, protecting the machine body and inspection equipment. It adapts to complex outdoor inspection environments, extends the service life of the device, and reduces economic losses caused by equipment damage. In addition, the use of plug-in / magnetic connectors (operation ≤10 seconds) simplifies the disassembly and assembly process of the inspection mechanism, reducing maintenance difficulty and time costs. The detachable main frame facilitates individual repair and replacement of components, improving the maintenance efficiency and economy of the equipment. Attached Figure Description

[0020] Figure 1 The overall three-dimensional structure of this utility model Figure 1 ;

[0021] Figure 2 The overall three-dimensional structure of this utility model Figure 2 ;

[0022] Figure 3 This is a perspective view of the flight mechanism of this utility model;

[0023] Figure 4 This is a three-dimensional view of the inspection mechanism of this utility model.

[0024] In the diagram: 1. Flight mechanism; 2. Inspection mechanism; 11. Main body of the aircraft; 12. Cross frame; 13. Rotor drive assembly; 14. Rotor body; 15. Rotor adapter slot; 16. Remote control and communication assembly; 17. Electric shaft; 18. Support frame; 19. Anti-slip rubber block; 110. Connector; 21. Visual acquisition assembly; 22. Camera; 23. Bottom protective frame; 24. Peripheral protective frame; 25. Buffer rubber block. Detailed Implementation

[0025] The embodiments of this utility model will be described in further detail below with reference to the accompanying drawings and examples. The following examples are for illustrative purposes only and should not be construed as limiting the scope of this utility model.

[0026] In the description of this utility model, unless otherwise stated, "a plurality of" means two or more; the terms "upper," "lower," "left," "right," "inner," "outer," "front end," "rear end," "head," "tail," etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings, and are only for the convenience of describing this utility model and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of this utility model. In addition, the terms "first," "second," "third," etc., are used for descriptive purposes only and should not be construed as indicating or implying relative importance.

[0027] In the description of this utility model, it should be noted that, unless otherwise explicitly specified and limited, the terms "connected" and "linked" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; 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. Those skilled in the art can understand the specific meaning of the above terms in this utility model based on the specific circumstances.

[0028] Please see Figures 1-4 In this embodiment of the present invention, a remote-controlled inspection aircraft for low-altitude cables includes a flight mechanism 1 and an inspection mechanism 2.

[0029] The flight mechanism 1 includes an aircraft main body 11, a cross frame 12, a rotor drive assembly 13, a rotor body 14, a remote control and communication assembly 16, an electric rotating shaft 17, a support frame 18, anti-slip rubber blocks 19, and a connector 110. The cross frame 12 is mounted on the aircraft main body 11. The rotor drive assembly 13 is adapted to the rotor body 14 and cooperates with the cross frame 12 through a rotor adapter slot 15. The remote control and communication assembly 16 is integrated inside and above the aircraft main body 11. The connector 110 is used to connect the flight mechanism 1 with the inspection mechanism 2. The system includes a visual acquisition component 21, cameras 22, a bottom protective frame 23, a peripheral protective frame 24, and buffer blocks 25. Multiple cameras 22 are arranged at equal angles around the visual acquisition component 21. The bottom protective frame 23 is located at the bottom of the visual acquisition component 21, and the peripheral protective frame 24 is located around the visual acquisition component 21. The bottom protective frame 23 and the peripheral protective frame 24 are connected. The bottom protective frame 23 and the peripheral protective frame 24 can be used to protect the inspection mechanism 2 and part of the flight mechanism 1. The buffer blocks 25 are fixedly connected to the bottom of the bottom protective frame 23 for shock absorption and cushioning.

[0030] In this embodiment:

[0031] The main body 11 of the aircraft and the cross frame 12 are integrated or detachable. The rotor adapter slot 15 on the cross frame 12 and the installation angle of the rotor body 14 are adapted to the flight attitude requirements of low-altitude cable inspection. The installation angle range is 30°-60°, which ensures flight stability and inspection coverage. The detachable connection facilitates equipment transportation and individual component maintenance.

[0032] The remote control and communication component 16 supports multi-band wireless communication, enabling remote control command transmission and inspection data, including real-time transmission of data such as images and flight status. It also features anti-interference encrypted transmission, with communication frequency bands covering 2.4GHz and 5.8GHz, ensuring stable communication and anti-interference encryption to protect data security in complex electromagnetic environments, such as strong electromagnetic areas near cables.

[0033] The electric rotating shaft 17 is used to connect the support frame 18 and the main body of the aircraft 11. The anti-slip rubber block 19 is set at the bottom of the support frame 18. The electric rotating shaft 17 can drive the support frame 18 to rotate relative to the main body of the aircraft 11 to adjust the angle. The adjustment range is 0°-90° to adapt to the take-off, landing and inspection needs of different terrains and cable layouts. The anti-slip rubber block 19 enhances the friction with the contact surface during take-off and landing, avoids slippage and improves stability.

[0034] The visual acquisition component 21 of the inspection mechanism 2 includes an image recognition processing module, which can analyze the cable images acquired by the camera 22 in real time, identify abnormal states such as cable damage, foreign object attachment, and deformation, and mark the abnormal locations. The image recognition response time is ≤0.5 seconds, which can quickly and accurately detect cable problems and provide a basis for maintenance.

[0035] The bottom protective frame 23 and the peripheral protective frame 24 are made of lightweight and high-strength alloy materials, such as aluminum alloy-carbon fiber composite material, and the buffer rubber block 25 is made of elastic rubber material. When the aircraft takes off and lands or encounters obstacles in flight, it protects and reduces shock to the aircraft body and inspection equipment. The compression rebound rate of the buffer rubber block 25 is ≥80%, which effectively absorbs the impact force and protects the internal components.

[0036] The flight mechanism 1 and the inspection mechanism 2 are connected by a plug-in or magnetic quick-connect structure via connector 110, which facilitates the installation, disassembly, maintenance and replacement of the inspection mechanism 2. The plug-in / magnetic connection operation time is ≤10 seconds, reducing maintenance difficulty and time cost.

[0037] The blades of the rotor body 14 are made of noise-reducing, high-strength composite material, namely carbon fiber, which can reduce flight noise while ensuring flight power and structural strength. The blade noise is ≤65 decibels, and the tensile strength of the blade is ≥500MPa when measured at a distance of 1 meter. This ensures flight performance while reducing noise pollution to the environment.

[0038] Working principle: During use, assembly preparation is first performed: the inspection mechanism 2 is quickly connected to the flight mechanism 1 via connector 110 to check the stability of each component. The angle of the support frame 18 is adjusted using the electric rotating shaft 17, adapting to the appropriate angle within the range of 0°-90° according to the takeoff and landing terrain, such as mountains or flat ground. Anti-slip rubber blocks 19 are attached to the takeoff and landing surface to enhance stability. Then, flight inspection is carried out. The operator sends flight commands via the remote control and communication component 16, activating the rotor drive component 13, which drives the rotor body 14 to rotate. The cross frame 12 engages with the rotor adapter slot 15, enabling the aircraft to fly stably at a flight attitude adapted to the installation angle of 30°-60°. During flight, multiple cameras set at equal angles record video. The head 22 collects cable images from all directions. The visual acquisition component 21 has a built-in image recognition and processing module that analyzes the images in real time within ≤0.5 seconds, identifies abnormalities such as cable damage, foreign object attachment, and deformation, and marks their locations. At the same time, the remote control and communication component 16 transmits flight status data and abnormal information back to the control terminal in real time via the 2.4GHz or 5.8GHz frequency band for operators to monitor and make decisions. After completing the inspection, the aircraft is controlled to return to the take-off and landing point, and the electric rotating shaft 17 adjusts the support frame 18 for a smooth landing. If maintenance of the inspection mechanism 2 is required, it can be quickly disassembled and assembled within ≤10 seconds through plug-in or magnetic connectors 110 to inspect and replace the visual acquisition component 21, camera 22, etc., to ensure continuous and effective operation of the equipment.

[0039] The above description is only a preferred embodiment of the present utility model, but the protection scope of the present utility model is not limited thereto. Any equivalent substitutions or changes made by those skilled in the art within the technical scope disclosed in the present utility model, based on the technical solution and the inventive concept of the present utility model, should be included within the protection scope of the present utility model.

Claims

1. A remote-controlled inspection aircraft for low-altitude cables, comprising a flight mechanism (1) and an inspection mechanism (2). Its features are: The flight mechanism (1) includes an aircraft main body (11), a cross frame (12), a rotor drive assembly (13), a rotor body (14), a remote control and communication assembly (16), an electric rotating shaft (17), a support frame (18), anti-slip rubber blocks (19), and a connector (110). The cross frame (12) is installed on the aircraft main body (11). The rotor drive assembly (13) is adapted to the rotor body (14) and cooperates with the cross frame (12) through the rotor adapter slot (15). The remote control and communication assembly (16) is integrated inside and above the aircraft main body (11). The connector (110) is used to connect the flight mechanism (1) with the inspection mechanism (2). The inspection mechanism (2) includes a visual acquisition component (21), a camera (22), a bottom protective frame (23), a peripheral protective frame (24), and a buffer rubber block (25). The camera (22) is multiple and is arranged at equal angles around the visual acquisition component (21). The bottom protective frame (23) is located at the bottom of the visual acquisition component (21). The peripheral protective frame (24) is located around the visual acquisition component (21). The bottom protective frame (23) is connected to the peripheral protective frame (24). The buffer rubber block (25) is fixedly connected to the bottom of the bottom protective frame (23).

2. The remote-controlled inspection aircraft for low-altitude cables according to claim 1, characterized in that: The main body (11) of the aircraft and the cross frame (12) are integrated or detachable, and the rotor adapter slot (15) on the cross frame (12) and the rotor body (14) are installed at an angle that is adapted to the flight attitude requirements of low-altitude cable inspection.

3. The remote-controlled inspection aircraft for low-altitude cables according to claim 1, characterized in that: The remote control and communication component (16) supports multi-band wireless communication.

4. The remote-controlled inspection aircraft for low-altitude cables according to claim 1, characterized in that: The electric rotating shaft (17) is used to connect the support frame (18) and the main body of the aircraft (11), and the anti-slip rubber block (19) is set at the bottom of the support frame (18).

5. The remote-controlled inspection aircraft for low-altitude cables according to claim 1, characterized in that: The visual acquisition component (21) of the inspection mechanism (2) includes an image recognition and processing module.

6. The remote-controlled inspection aircraft for low-altitude cables according to claim 1, characterized in that: The bottom protective frame (23) and the peripheral protective frame (24) are made of lightweight and high-strength alloy material, and the buffer rubber block (25) is made of elastic rubber material.

7. The remote-controlled inspection aircraft for low-altitude cables according to claim 1, characterized in that: The flight mechanism (1) and the inspection mechanism (2) are connected by a connector (110) in a plug-in or magnetic quick-connect structure.

8. The remote-controlled inspection aircraft for low-altitude cables according to claim 1, characterized in that: The blades of the rotor body (14) are made of noise-reducing, high-strength composite materials.

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