Power station inspection unmanned aerial vehicle

Abstract

The invention discloses a power station inspection unmanned aerial vehicle, belongs to the technical field of unmanned aerial vehicles, and aims to solve the problem that the inspection effect is poor when the unmanned aerial vehicle inspects two adjacent power equipment with a small interval, the power station inspection unmanned aerial vehicle comprises an unmanned aerial vehicle main body, two supporting legs are oppositely arranged at the bottom of the unmanned aerial vehicle main body, and a mounting frame is arranged at the bottom of the unmanned aerial vehicle main body; the unmanned aerial vehicle comprises an unmanned aerial vehicle body, a mounting frame is arranged in the unmanned aerial vehicle body, a camera is arranged in the mounting frame, two visual sensors are oppositely arranged at the top of the unmanned aerial vehicle body, four driving assemblies are uniformly arranged in the unmanned aerial vehicle body, storage assemblies are rotatably connected in the four driving assemblies, rotating assemblies are arranged on the outer walls of the storage assemblies, and clamping assemblies are arranged in the four driving assemblies. According to the unmanned aerial vehicle detection device, the unmanned aerial vehicle can be conveniently stored, so that the transverse occupied space is reduced, the unmanned aerial vehicle can enter a narrow gap area of adjacent power equipment for detection, and the adaptability is improved.

Description

Technical Field

[0001] This invention relates to the field of unmanned aerial vehicle (UAV) technology, specifically to a power plant inspection UAV. Background Technology

[0002] With the large-scale development of photovoltaic power plants, the number of equipment in the power plants has increased and the layout has become more complex. Traditional manual inspections are inefficient and costly, and inspections in high-risk areas are also risky. Therefore, in order to meet the inspection requirements, drone inspections have become an important means of operation and maintenance of photovoltaic power plants. Drones, equipped with cameras and other front-end intelligent sensing devices, collect data on the operating conditions, status, parameters, and abnormalities of power production equipment such as photovoltaic panels, combiner boxes, and inverters. The collected data is analyzed and processed by an edge computing device to identify equipment abnormalities and safety hazards, thereby improving the efficiency and safety of power plant operation and maintenance.

[0003] When current inspection drones inspect two adjacent devices with a small gap, the narrow space makes it difficult for the drones to accurately control their flight attitude to ensure the shooting distance and angle. This results in unclear and incomplete data, which reduces the effectiveness of the inspection and may even lead to missed inspections, thus affecting the safe operation of the power plant.

[0004] To address the above issues, a power plant inspection drone is proposed. Summary of the Invention

[0005] The purpose of this invention is to provide a power plant inspection drone. By using this invention, the problem of poor inspection results when drones inspect two adjacent power devices with small intervals is solved.

[0006] To achieve the above objectives, the present invention provides the following technical solution: A power plant inspection drone includes a drone body with two supporting legs positioned opposite each other at the bottom. A mounting frame is located at the bottom of the drone body, housing a camera. Two visual sensors are positioned opposite each other at the top of the drone body. Four drive components are evenly arranged inside the drone body, each with a rotatable storage component rotatably connected to it. A rotating component is located on the outer wall of each storage component. Each of the four drive components has a locking component inside. Each of the four drive components has a moving component at its bottom, fixedly connected to the supporting legs. Four air extraction and pressurization components are evenly arranged inside the drone body and connected to the drive components. An acceleration sensor is located at the top of the drone body. Each of the four drive components has a protective component connected to the air extraction and pressurization components. A limit component is located at the top of the drone body, housing a parachute. Four air outlet components are connected to each of the four air extraction and pressurization components, with the limit component fitting against the four air outlet components.

[0007] Furthermore, the drive assembly includes a protective frame fixedly connected to the main body of the drone, an electric push rod installed inside the protective frame, a U-shaped lifting plate fixedly connected to the movable end of the electric push rod, a fixed frame fixedly connected inside the main body of the drone, a toothed plate slidably connected inside the fixed frame, a lifting rod fixedly connected to the bottom of the toothed plate, the lifting rod being fixedly connected to the U-shaped lifting plate, and two slots opened on the inner wall of the fixed frame.

[0008] Furthermore, the storage component includes a rotating shaft rotatably connected to the fixed frame, a gear fixedly connected to one side of the outer wall of the rotating shaft, the gear meshing with a gear plate, and a rotating rod fixedly connected to the other side of the outer wall of the rotating shaft.

[0009] Furthermore, the rotating assembly includes a fixed base fixedly connected to one end of the rotating rod, a first motor mounted on one side of the fixed base, and a propeller fixedly connected to the output end of the first motor.

[0010] Furthermore, the snap-fit ​​assembly includes a first electromagnet installed inside the toothed plate, a snap-fit ​​block slidably connected inside the toothed plate, the snap-fit ​​block snapping into the snap-fit ​​slot, a first magnet block installed on one side of the snap-fit ​​block, two first springs fixedly connected to one side of the snap-fit ​​block, and the other ends of the two first springs fixedly connected to the inner wall of the toothed plate.

[0011] Furthermore, the movable component includes a first limiting frame fixedly connected within the support leg, an installation frame slidably connected within the first limiting frame, the installation frame being fixedly connected to the lifting rod, a second motor mounted on one side of the installation frame, a moving wheel fixedly connected to the output end of the second motor, and the moving wheel being rotatably connected to the installation frame.

[0012] Furthermore, the air extraction and pressurization assembly includes an air storage cylinder fixedly connected to the main body of the UAV, a gas one-way valve connected to the top of the air storage cylinder, a pressure relief valve connected to the top of the air storage cylinder, a push-pull rod fixedly connected to the top of the U-shaped lifting plate, a piston fixedly connected to one end of the push-pull rod, the piston slidingly connected to the inner wall of the air storage cylinder, a connecting pipe connected to the top of the air storage cylinder, a gas solenoid valve installed inside the fixed frame, and the connecting pipe connected to the gas solenoid valve.

[0013] Furthermore, the protective component includes an airbag disposed within a fixed frame, the airbag being connected to a gas solenoid valve, a connecting frame being disposed on one side of the fixed frame, an elastic fabric being disposed within the connecting frame, and a cross-shaped weak slit being provided on one side of the elastic fabric.

[0014] Furthermore, the limiting component includes a positioning frame fixedly connected to the top of the drone body, a parachute fixedly connected inside the positioning frame, two second limiting frames connected opposite each other on both sides of the positioning frame, a second electromagnet installed in each of the two second limiting frames, a U-shaped limiting plate slidably connected in each of the two second limiting frames, the two U-shaped limiting plates fitting together, a second spring fixedly connected to one side of the U-shaped limiting plate, and the other end of the second spring fixedly connected to the inner wall of the second limiting frame, and a second magnet block installed on one side of the U-shaped limiting plate.

[0015] Furthermore, the air outlet assembly includes an air outlet pipe connected to the air storage cylinder, with a sealing plug at one end of the air outlet pipe, and both the air outlet pipe and the sealing plug are fitted to the U-shaped limiting plate.

[0016] Compared with the prior art, the beneficial effects of the present invention are as follows: By driving the storage and rotating components, the drone can be easily stored, thus reducing its lateral space occupation. At the same time, the driving component pushes the moving component to slide out, facilitating the drone's ground movement. This allows the drone to enter narrow gaps between adjacent power equipment for inspection without having to fly through such narrow gaps, thus overcoming the limitations of existing flight-based inspection scenarios and improving adaptability.

[0017] During the drone storage process, the drive component works in conjunction with the air extraction and pressurization component to extract air and then return it to its original position a short distance upwards, thereby maintaining stable air pressure within the air extraction and pressurization component.

[0018] When a drone is moving and inspecting on the ground, if the accelerometer detects that it is tipping over, the air pumping and pressurizing component can quickly fill the protective component with high-pressure gas, causing the protective component to expand rapidly, thereby preventing the drone from colliding directly with the ground and facilitating protection.

[0019] When a drone is conducting an inspection in flight, if the accelerometer detects a fall, the limiting component, in conjunction with the air extraction and pressurization components and the air exhaust component, removes the restriction on the parachute, facilitating its deployment and allowing high-pressure gas to escape. This helps the parachute to deploy quickly and fully, creating a deceleration buffer and reducing damage to the drone upon impact with the ground. Attached Figure Description

[0020] Figure 1 This is a schematic diagram of the overall structure of the present invention; Figure 2 This is a top view of the overall structure of the present invention; Figure 3 This is a schematic diagram of the overall side cross-sectional structure of the present invention; Figure 4 for Figure 3 Enlarged view of point A; Figure 5 for Figure 3 Enlarged view of point B; Figure 6 for Figure 3 Enlarged view of point C; Figure 7 This is a cross-sectional structural diagram showing the connection relationship between the drive component, storage component, rotation component, and protective component of the present invention. Figure 8 for Figure 7 Enlarged view of point D; Figure 9 This is a schematic diagram of the protective component structure of the present invention; Figure 10 This is a schematic diagram of the overall side view structure of the present invention; Figure 11 for Figure 10 Enlarged view of point E; Figure 12 This is a cross-sectional structural diagram showing the connection relationship between the limiting component, the parachute, and the air venting component of the present invention.

[0021] In the diagram: 1. Drone body; 11. Support leg; 12. Mounting frame; 13. Camera; 2. Visual sensor; 3. Drive assembly; 31. Protective frame; 32. Electric push rod; 33. U-shaped lifting plate; 34. Fixing frame; 35. Gear plate; 36. Lifting rod; 37. Slot; 4. Storage assembly; 41. Rotating shaft; 42. Gear; 43. Rotating rod; 5. Rotating assembly; 51. Fixed base; 52. First motor; 53. Propeller; 6. Snap-fit ​​assembly; 61. First electromagnet; 62. Locking block; 63. First magnet; 64. First spring; 7. Moving assembly; 71. First limiting frame; 72. Mounting frame; 73. Second... 74. Motor; 8. Casters; 9. Air extraction and pressurization assembly; 10. Air tank; 11. Gas check valve; 12. Pressure relief valve; 13. Push-pull rod; 14. Piston; 15. Connecting pipe; 16. Gas solenoid valve; 17. Acceleration sensor; 18. Protective assembly; 19. Airbag; 10. Connecting frame; 10. Elastic fabric; 10. Cross-shaped weak seam; 20. Limiting assembly; 201. Positioning frame; 202. Second limiting frame; 203. Second electromagnet; 204. U-shaped limiting plate; 205. Second spring; 206. Second magnet; 30. Parachute; 40. Air outlet assembly; 401. Air outlet pipe; 402. Sealing plug. Detailed Implementation

[0022] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0023] To address the technical problem of poor inspection results when drones inspect two adjacent power devices with small intervals, such as... Figures 1-8 and Figures 10-12 As shown, the following preferred technical solutions are provided: A power plant inspection drone includes a main body 1, with two supporting legs 11 positioned opposite each other at the bottom of the main body 1 for easy landing. A mounting frame 12 is located at the bottom of the main body 1, housing a camera 13. The main body 1 can support and secure various components. A controller is installed within the main body 1, controlling various electrical components. The controller is existing technology and is not shown in the figure. The main body 1, controller, and camera 13 all employ electromagnetic interference-resistant design to prevent interference with electronic components in the power plant's electromagnetic environment, ensuring accurate data acquisition and flight stability. The mounting frame 12 can adjust the angle of the camera 13, improving the inspection effect. The mounting frame 12 is existing technology and will not be described in detail here. Figure 1 As shown, two visual sensors 2 are installed opposite each other on the top of the main body 1 of the UAV. The visual sensors 2 can easily detect the gap width between power equipment, the position of obstacles and the environmental terrain in the inspection path, providing data support for the UAV to determine whether it is suitable for flight or landing, and avoiding collisions with power equipment. At the same time, the visual sensors 2 are equipped with a metal shielding shell to resist electromagnetic interference and ensure accurate data collection in the electromagnetic environment of the power station. During the initial calibration, the power equipment brackets and fixed signs of known size in the power station are selected as reference objects. The image information of the reference objects is collected by the visual sensors 2 and compared with the preset reference value in the controller. At the same time, the image recognition accuracy of the sensor is adjusted to eliminate the influence of ambient light on the detection results, thereby completing the calibration and providing a reference for subsequent detection.

[0024] Four drive components 3 are evenly arranged inside the main body 1 of the drone. Each of the four drive components 3 is rotatably connected to a storage component 4. A rotating component 5 is provided on the outer wall of the storage component 4. The rotating component 5 can drive the main body 1 of the drone and the camera 13 to fly. Through the camera 13, the operating conditions, running status, index parameters and abnormal conditions of the power equipment can be collected. Each of the four drive components 3 is provided with a snap-fit ​​component 6. Each of the four drive components 3 is provided with a moving component 7 at the bottom. The moving component 7 is fixedly connected to the support leg 11.

[0025] During the inspection, if the distance between two adjacent power devices to be inspected is too small and unsuitable for the drone body 1 to fly and inspect, the controller, in conjunction with the rotating component 5, will land the drone body 1 directly in front of the passage between the two adjacent devices. Then, the controller will disengage the locking component 6 from the drive component 3. Subsequently, the four drive components 3 will drive the storage component 4 and the rotating component 5 to rotate, retracting them to the sides of the drone body 1. This reduces lateral space occupation and prevents the overall width from exceeding the narrow gap between the adjacent power devices. Simultaneously, the movement of the four drive components 3 will cause the moving component 7 to descend a significant distance. After moving away and then resetting a short distance upwards, the controller causes the locking component 6 to re-engage with the drive component 3, facilitating the contact of the moving component 7 with the ground and lifting the drone body 1 off the ground. Subsequently, the controller causes the moving component 7 to move the drone body 1 on the ground for inspection. This allows the drone body 1 to easily enter the narrow gap between two adjacent power devices without having to force its way through the narrow gap, thus avoiding collisions with the power devices. At the same time, it allows the camera 13 to collect data on locations that are easily missed during flight inspections, thereby improving the inspection effect. Compared to existing drones that only rely on flight inspections, this method can overcome the limitations of flight inspection scenarios and improve the adaptability of inspection drones.

[0026] Four air extraction and pressurization components 8 are evenly arranged inside the main body 1 of the drone. The air extraction and pressurization components 8 are connected to the drive component 3, such as... Figures 10-11 As shown, an accelerometer 9 is installed on the top of the drone body 1. The accelerometer 9 can detect whether the drone body 1 tilts during ground movement inspection and whether it falls during flight inspection. The accelerometer 9 is installed at the center of gravity of the drone body 1. The accelerometer 9 is industrial grade, which can improve the detection effect. The accelerometer 9 is equipped with a metal shielding shell to resist electromagnetic interference and avoid the electromagnetic environment of the power station affecting the detection effect. During the initial calibration, the drone body 1 is placed in a flat temporary area in the power station, and the reference gravity acceleration parameter of the accelerometer 9 in the horizontal state is set. At the same time, a preset critical tilt angle is set to calibrate the ground tilt detection threshold. Then, the acceleration judgment curve of the flight fall is calibrated by short-distance simulated fall, and the calibrated reference value is stored in the controller to complete the calibration. Each of the four drive components 3 is equipped with a protective component 10, which is connected to the air extraction and pressurization component 8. A limit component 20 is installed on the top of the drone body 1. Figures 11-12As shown, a parachute 30 is provided inside the limiting component 20, and an ejection mechanism is provided inside the parachute 30. The ejection mechanism can push the parachute 30 out of the limiting component 20, providing initial kinetic energy for the parachute 30 to subsequently deploy in the air. The ejection mechanism is existing technology and is not shown in the figure. Four air extraction and pressurization components 8 are respectively connected to four air outlet components 40, and the limiting component 20 is in contact with the four air outlet components 40.

[0027] During ground-based mobile inspection, if the accelerometer 9 registers abnormal data, indicating that the drone body 1 is about to tip over, the controller rapidly injects high-pressure gas from the four suction and pressurization components 8 into the four protective components 10. This causes the protective components 10 to expand quickly, protecting the drone body 1 and preventing direct collision with the ground upon tipping over. This reduces damage to components such as the drone body 1, camera 13, and vision sensor 2. Subsequently, the drone body 1's alarm sounds, alerting the user to perform maintenance. The alarm is existing technology and is not shown in the diagram. During flight inspection... When the acceleration sensor 9 detects an abnormality and determines that the drone body 1 is about to fall, the controller causes the limiting component 20 to release the limit on the parachute 30. The parachute 30 is then ejected via the ejection mechanism inside the parachute 30. During its movement, the limiting component 20 releases its contact with the four air outlet components 40, allowing the four air outlet components 40 to quickly expel the high-pressure gas from the four suction and pressurization components 8 toward the parachute 30. This provides auxiliary airflow to the ejected parachute 30, enabling it to deploy quickly and fully. This provides timely deceleration and cushioning for the falling drone body 1, reducing the impact force between the drone body 1 and the ground.

[0028] like Figures 1-8 and Figure 10 As shown, the drive assembly 3 includes a protective frame 31 fixedly connected to the drone body 1. An electric push rod 32 is installed inside the protective frame 31. A U-shaped lifting plate 33 is fixedly connected to the movable end of the electric push rod 32. A fixed frame 34 is fixedly connected inside the drone body 1. A toothed plate 35 is slidably connected inside the fixed frame 34. A lifting rod 36 is fixedly connected to the bottom of the toothed plate 35. The lifting rod 36 is fixedly connected to the U-shaped lifting plate 33. Two slots 37 are opened on the inner wall of the fixed frame 34.

[0029] like Figures 1-4 , Figure 7 and Figure 10 As shown, the storage component 4 includes a rotating shaft 41 rotatably connected to the fixed frame 34. A gear 42 is fixedly connected to one outer wall of the rotating shaft 41, and the gear 42 meshes with the toothed plate 35. A rotating rod 43 is fixedly connected to the other outer wall of the rotating shaft 41.

[0030] like Figures 1-3 , Figure 7 and Figure 10 As shown, the rotating assembly 5 includes a fixed base 51 fixedly connected to one end of the rotating rod 43. A first motor 52 is installed on one side of the fixed base 51. A propeller 53 is fixedly connected to the output end of the first motor 52. The four first motors 52 drive the four propellers 53 to rotate respectively, which can easily drive the main body of the UAV 1 to fly and land.

[0031] like Figure 6 and Figure 8 As shown, the snap-fit ​​assembly 6 includes a first electromagnet 61 installed inside the toothed plate 35, a snap-fit ​​block 62 slidably connected inside the toothed plate 35, the snap-fit ​​block 62 snaps into the slot 37, a first magnet block 63 is installed on one side of the snap-fit ​​block 62, and two first springs 64 are fixedly connected to one side of the snap-fit ​​block 62, and the other end of the two first springs 64 is fixedly connected to the inner wall of the toothed plate 35.

[0032] like Figures 1-3 and Figure 5 As shown, the movable component 7 includes a first limiting frame 71 fixedly connected to the support leg 11, an installation frame 72 slidably connected inside the first limiting frame 71, the installation frame 72 being fixedly connected to the lifting rod 36, a second motor 73 being installed on one side of the installation frame 72, and a moving wheel 74 being fixedly connected to the output end of the second motor 73, the moving wheel 74 being rotatably connected to the installation frame 72.

[0033] During the inspection process, when two visual sensors 2 detect that the distance between two adjacent power devices to be inspected is too small and the distance is not suitable for the drone body 1 to fly and inspect, the controller, in conjunction with the rotating assembly 5, lands the drone body 1 directly in front of the passage between the two power devices. Then, the controller causes the first electromagnet 61 to attract the first magnet block 63, causing the locking block 62 to disengage from the upper locking slot 37, simultaneously compressing the two first springs 64. Then, two electric push rods 32 respectively drive the two U-shaped lifting plates 33 to descend, causing the lifting rods 36 and the toothed plate 35 to descend. Through the meshing of the toothed plate 35 and the gear 42, the rotating shaft 41, the rotating rod 43, and the rotating assembly 5 are driven to rotate, allowing the rotating shaft 41, the rotating rod 43, and the rotating assembly 5 to be stored on both sides of the drone body 1, thereby reducing the lateral space occupied and preventing the overall width from exceeding the narrow gap between adjacent power devices. During the descent of the four lifting rods 36, it is possible to... The device can lower the mounting frame 72 and the moving wheel 74 a considerable distance, and then reset it a short distance. At this time, the controller causes the first electromagnet 61 to release its attraction to the first magnet block 63 and reset it through the two first springs 64, causing the locking block 62 to engage with the lower locking slot 37. During this process, the moving wheel 74 contacts the ground and lifts the drone body 1, causing the drone body 1 to leave the ground. Then, the controller causes the second motor 73 to drive the moving wheel 74 to rotate, allowing the drone body 1 to move on the ground for inspection. This makes it easier for the drone body 1 to enter the narrow gap between two adjacent power devices without having to force its way through the narrow gap, thus avoiding collisions with the power devices. At the same time, it allows the camera 13 to collect data on locations that are easily missed during flight inspections, thereby improving the inspection effect. Compared with existing drones that only rely on flight inspections, this device can overcome the limitations of flight inspection scenarios and improve the adaptability of inspection drones.

[0034] To address the technical challenge of protecting drones from tipping over during ground inspections, such as... Figures 1-4 and Figures 6-12 As shown, the following preferred technical solutions are provided: like Figures 1-2 , Figure 4 , Figure 6 , Figure 8 and Figure 10As shown, the air extraction and pressurization assembly 8 includes an air storage cylinder 81 fixedly connected to the main body 1 of the UAV. A gas one-way valve 82 and a pressure relief valve 83 are connected to the top of the air storage cylinder 81. A push-pull rod 84 is fixedly connected to the top of the U-shaped lifting plate 33, and a piston 85 is fixedly connected to one end of the push-pull rod 84. The piston 85 is slidably connected to the inner wall of the air storage cylinder 81. A connecting pipe 86 is connected to the top of the air storage cylinder 81. A gas solenoid valve 87 is installed inside the fixed frame 34, and the connecting pipe 86 is connected to the gas solenoid valve 87. In use, the controller causes the electric push rod 32 to drive the U-shaped lifting plate 33, the push-pull rod 84, and the piston 85 to descend, allowing outside air to enter the air storage cylinder 81 through the gas one-way valve 82. The electric push rod 32 then drives the U-shaped lifting plate 33, the push-pull rod 84, and the piston 85 to descend. When the lifting plate 33 returns to its original position and rises, it drives the push-pull rod 84 and piston 85 to rise, compressing the drawn-in gas. During initial use, the drive assembly 3 performs reciprocating lifting motions to draw a sufficient amount and pressure of air into the air storage cylinder 81 until excess gas is discharged through the pressure relief valve 83. When subsequent ground inspections are required, the drive assembly 3 moves downward a large distance and then returns to its original position a small distance to maintain sufficient pressure in the air storage cylinder 81. The total amount of gas in the air storage cylinder 81 meets the usage requirements. At the same time, a gas pressure sensor is installed inside the air storage cylinder 81 to detect the gas pressure inside the air storage cylinder 81, preventing leakage from affecting use. The gas pressure sensor is existing technology and is not shown in the figure.

[0035] like Figure 3 and Figures 6-9 As shown, the protective component 10 includes an airbag 101 disposed within a fixed frame 34. The airbag 101 is connected to a gas solenoid valve 87. A connecting frame 102 is disposed on one side of the fixed frame 34. The connecting frame 102 is connected to the fixed frame 34 by bolts. An elastic cloth 103 is disposed inside the connecting frame 102. The elastic cloth 103 is a waterproof elastic cloth 103, which can prevent rainwater from seeping in. A cross-shaped weak slit 104 is opened on one side of the elastic cloth 103. By opening a cross-shaped weak slit 104 on one side of the elastic cloth 103, the airbag 101 can be easily guided to unfold in a fixed direction when it breaks, avoiding deviation in the unfolding direction. The gas pressure and total gas volume in the gas storage cylinder 81 can ensure that high-pressure gas enters the airbag 101 quickly and in sufficient quantity, so that the airbag 101 can expand rapidly and fully, which can easily provide buffer protection for the tilted drone body 1.

[0036] like Figures 1-2 and Figures 11-12As shown, the limiting component 20 includes a positioning frame 201 fixedly connected to the top of the drone body 1, a parachute 30 fixedly connected inside the positioning frame 201, two second limiting frames 202 connected opposite to each other on both sides of the positioning frame 201, a second electromagnet 203 installed in each of the two second limiting frames 202, a U-shaped limiting plate 204 slidably connected in each of the two second limiting frames 202, the two U-shaped limiting plates 204 fitting together, a second spring 205 fixedly connected to one side of the U-shaped limiting plate 204, and the other end of the second spring 205 fixedly connected to the inner wall of the second limiting frame 202, and a second magnet block 206 installed on one side of the U-shaped limiting plate 204.

[0037] like Figure 2 and Figures 11-12 As shown, the air outlet assembly 40 includes an air outlet pipe 401 connected to the air storage cylinder 81. A sealing plug 402 is provided at one end of the air outlet pipe 401. Both the air outlet pipe 401 and the sealing plug 402 are in contact with the U-shaped limiting plate 204. The sealing plug 402 can easily seal the air outlet pipe 401 in the non-exhaust state, preventing the leakage of high-pressure gas in the air storage cylinder 81. The gas pressure and total gas volume in the air storage cylinder 81 can ensure that the air outlet assembly 40 can quickly discharge a sufficient amount of high-pressure gas, providing sufficient auxiliary airflow for the deployed parachute 30, helping the parachute 30 to deploy quickly and fully, and timely decelerating and buffering the falling drone body 1, reducing the impact force with the ground.

[0038] During ground-based mobile inspection, if the accelerometer 9 registers abnormal data, indicating that the drone body 1 is about to tip over, the controller activates the gas solenoid valve 87. High-pressure gas from the four gas cylinders 81 rapidly enters the airbag 101, causing it to expand quickly through the cross-shaped weak seam 104 and elastic fabric 103. This protects the drone body 1 from direct collision with the ground upon tipping over, reducing damage to components such as the drone body 1, camera 13, and vision sensor 2. Subsequently, the drone body 1's alarm sounds, alerting the user to perform maintenance. (The alarm is existing technology and not shown in the diagram.) If the accelerometer 9 registers abnormal data during flight inspection, indicating that the drone body 1 is about to tip over... When a fall occurs, the controller causes the second electromagnet 203 to attract the second magnet block 206, causing the two U-shaped limiting plates 204 to slide in opposite directions and compress the second spring 205. This causes the U-shaped limiting plates 204 to release their restriction on the parachute 30. Subsequently, the parachute 30 is ejected through the ejection mechanism inside the parachute 30. At the same time, during the movement, the two U-shaped limiting plates 204 release their contact with the air outlet pipe 401 and the sealing plug 402, causing the high-pressure gas in the four air storage cylinders 81 to push the sealing plug 402 out and quickly discharge towards the parachute 30. This facilitates the provision of auxiliary airflow for the ejected parachute 30, allowing the parachute 30 to deploy quickly and fully, thereby providing timely deceleration and buffer for the falling drone body 1 and reducing the impact force between the drone body 1 and the ground.

[0039] It should be noted that, in this document, relational terms such as "first" and "second" are used only to distinguish one entity or operation from another, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Furthermore, the terms "comprising," "including," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such process, method, article, or apparatus.

[0040] Although embodiments of the invention have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and alterations can be made to these embodiments without departing from the principles and spirit of the invention, the scope of which is defined by the appended claims and their equivalents.

Claims

1. A power plant inspection drone, comprising a drone body (1), two support legs (11) arranged opposite each other at the bottom of the drone body (1), a mounting frame (12) provided at the bottom of the drone body (1), and a camera (13) provided inside the mounting frame (12), characterized in that: The top of the drone body (1) has two visual sensors (2) facing each other. Four drive components (3) are evenly arranged inside the drone body (1). Each of the four drive components (3) is rotatably connected to a storage component (4). A rotating component (5) is provided on the outer wall of the storage component (4). Each of the four drive components (3) is provided with a snap-fit ​​component (6). Each of the four drive components (3) is provided with a moving component (7) at the bottom. The moving component (7) is fixedly connected to the support leg (11). Four air extraction and pressurization components are evenly arranged inside the drone body (1). (8) The air extraction and pressurization component (8) is connected to the drive component (3). An acceleration sensor (9) is installed on the top of the drone body (1). A protective component (10) is installed in each of the four drive components (3). The protective component (10) is connected to the air extraction and pressurization component (8). A limit component (20) is installed on the top of the drone body (1). A parachute (30) is installed in the limit component (20). Four air outlet components (40) are connected in each of the four air extraction and pressurization components (8). The limit component (20) is attached to the four air outlet components (40).

2. The power plant inspection drone according to claim 1, characterized in that: The drive assembly (3) includes a protective frame (31) fixedly connected to the main body of the drone (1). An electric push rod (32) is installed inside the protective frame (31). A U-shaped lifting plate (33) is fixedly connected to the movable end of the electric push rod (32). A fixed frame (34) is fixedly connected inside the main body of the drone (1). A toothed plate (35) is slidably connected inside the fixed frame (34). A lifting rod (36) is fixedly connected to the bottom of the toothed plate (35). The lifting rod (36) is fixedly connected to the U-shaped lifting plate (33). Two slots (37) are opened on the inner wall of the fixed frame (34).

3. The power plant inspection drone according to claim 2, characterized in that: The storage component (4) includes a rotating shaft (41) rotatably connected to the fixed frame (34), a gear (42) is fixedly connected to one side of the outer wall of the rotating shaft (41), the gear (42) meshes with the toothed plate (35), and a rotating rod (43) is fixedly connected to the other side of the outer wall of the rotating shaft (41).

4. The power plant inspection drone according to claim 3, characterized in that: The rotating assembly (5) includes a fixed base (51) fixedly connected to one end of the rotating rod (43), a first motor (52) is installed on one side of the fixed base (51), and a propeller (53) is fixedly connected to the output end of the first motor (52).

5. A power plant inspection drone according to claim 2, characterized in that: The snap-fit ​​assembly (6) includes a first electromagnet (61) installed inside the toothed plate (35), a snap-fit ​​block (62) slidably connected inside the toothed plate (35), the snap-fit ​​block (62) snaps into the snap-fit ​​slot (37), a first magnet block (63) is installed on one side of the snap-fit ​​block (62), and two first springs (64) are fixedly connected to one side of the snap-fit ​​block (62), and the other end of the two first springs (64) is fixedly connected to the inner wall of the toothed plate (35).

6. A power plant inspection drone according to claim 2, characterized in that: The moving component (7) includes a first limiting frame (71) fixedly connected to the support leg (11), a mounting frame (72) slidably connected inside the first limiting frame (71), the mounting frame (72) being fixedly connected to the lifting rod (36), a second motor (73) being installed on one side of the mounting frame (72), a moving wheel (74) being fixedly connected to the output end of the second motor (73), and the moving wheel (74) being rotatably connected to the mounting frame (72).

7. A power plant inspection drone according to claim 2, characterized in that: The air extraction and pressurization assembly (8) includes an air storage cylinder (81) fixedly connected to the main body (1) of the UAV. A gas check valve (82) is connected to the top of the air storage cylinder (81). A pressure relief valve (83) is connected to the top of the air storage cylinder (81). A push-pull rod (84) is fixedly connected to the top of the U-shaped lifting plate (33). A piston (85) is fixedly connected to one end of the push-pull rod (84). The piston (85) is slidably connected to the inner wall of the air storage cylinder (81). A connecting pipe (86) is connected to the top of the air storage cylinder (81). A gas solenoid valve (87) is installed in the fixed frame (34). The connecting pipe (86) is connected to the gas solenoid valve (87).

8. A power plant inspection drone according to claim 7, characterized in that: The protective component (10) includes an airbag (101) disposed in a fixed frame (34), the airbag (101) is connected to a gas solenoid valve (87), a connecting frame (102) is provided on one side of the fixed frame (34), an elastic cloth (103) is provided in the connecting frame (102), and a cross-shaped weak slit (104) is provided on one side of the elastic cloth (103).

9. A power plant inspection drone according to claim 8, characterized in that: The limiting component (20) includes a positioning frame (201) fixedly connected to the top of the drone body (1), a parachute (30) fixedly connected inside the positioning frame (201), two second limiting frames (202) connected opposite to each other on both sides of the positioning frame (201), a second electromagnet (203) installed in each of the two second limiting frames (202), a U-shaped limiting plate (204) slidably connected in each of the two second limiting frames (202), the two U-shaped limiting plates (204) fitting together, a second spring (205) fixedly connected to one side of the U-shaped limiting plate (204), and the other end of the second spring (205) fixedly connected to the inner wall of the second limiting frame (202), and a second magnet (206) installed on one side of the U-shaped limiting plate (204).

10. A power plant inspection drone according to claim 9, characterized in that: The air outlet assembly (40) includes an air outlet pipe (401) connected to the air storage cylinder (81), and a sealing plug (402) is provided at one end of the air outlet pipe (401). Both the air outlet pipe (401) and the sealing plug (402) are in contact with the U-shaped limiting plate (204).

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