Maintenance and inspection unmanned aerial vehicle equipment

Abstract

The invention discloses maintenance and inspection unmanned aerial vehicle equipment which comprises an unmanned aerial vehicle body, a plurality of air holes are formed in a top cover of the unmanned aerial vehicle body, a fixed ring plate is detachably arranged above the top cover, and meanwhile a plurality of parachute ropes are arranged on the fixed ring plate in a penetrating mode; a limiting assembly is further arranged above the top cover, the limiting assembly comprises two shielding shells which are symmetrically arranged, and the shielding shells can move relative to the top cover; the parachute can be stored in a space formed by the shielding shell and the top cover, and the parachute covers the air hole; the parachute is arranged above the unmanned aerial vehicle body, and the parachute can be unfolded in the falling process of the unmanned aerial vehicle body, so that the landing resistance of the unmanned aerial vehicle body is increased, the falling speed of the unmanned aerial vehicle body is reduced, and the probability that the unmanned aerial vehicle body is impacted and damaged during landing is further reduced.

Description

Technical Field

[0001] This invention relates to the field of unmanned aerial vehicles (UAVs), specifically to a maintenance and inspection UAV device. Background Technology

[0002] In recent years, drone technology has developed rapidly and demonstrated enormous application potential in numerous fields. Leveraging its advantages such as flexible flight in complex environments and the ability to operate without direct human contact, drones have been widely applied in various industries, including power line inspection, oil pipeline inspection, bridge inspection, forestry resource monitoring, and urban building inspection. For example, in power line inspection, drones can fly along transmission lines, using onboard high-definition cameras and various sensors to quickly and accurately detect potential safety hazards such as damaged conductors, aging insulators, and foundation settlement of towers. In bridge inspection, drones can fly to various critical parts of bridges, conducting close-up observations of piers, bridge decks, cables, and other structures, assisting inspectors in determining whether there are cracks, corrosion, or other problems, greatly improving inspection efficiency and accuracy while also ensuring the personal safety of inspectors.

[0003] Therefore, drones equipped with high-definition cameras and various sensors can greatly facilitate maintenance in various fields. Currently, there are many types of drones used for inspection. For example, a Chinese patent with publication number CN111268131B discloses a drone inspection device, which includes a drone body, support columns, protective curtains, and protective doors. The drone body has a slide rail on which a camera is slidably mounted. There are four support columns, symmetrically arranged in pairs around the slide rail. One end of each support column is connected to the drone body, and the other end is connected to a base plate. The support columns have vertical grooves. There are three protective curtains, located between two support columns, and they can slide along the vertical grooves on the support columns on both sides. There are two protective doors, each located on two adjacent support columns and facing the camera lens. The two protective doors can move towards each other to close, and the protective doors and curtains protect the camera by closing. The drone inspection device provided by the above patent ensures the cleanliness of the camera and the effectiveness of its shooting.

[0004] Regardless of the drones mentioned above or other types, while they offer high flexibility, their flight stability is severely challenged in adverse weather conditions such as strong winds, turbulence, and heavy rain. They may even be swept away by air currents and lose control. Even high-performance drones cannot guarantee absolutely safe flight in extreme weather. Furthermore, drones are relatively sophisticated and expensive devices, especially those used in specialized fields (such as industrial inspection and surveying). Damage from accidental crashes is often severe, potentially involving breakage or deformation of critical components. Even after repair, it's difficult to restore them to their original performance level, and they may even experience frequent malfunctions, shortening the overall lifespan of the equipment.

[0005] Therefore, it is necessary to provide security for drones that conduct long-distance inspections. Summary of the Invention

[0006] The purpose of this invention is to provide a maintenance and inspection drone device, which aims to improve the problem of damage caused by accidental crashes of inspection drones.

[0007] The present invention is implemented as follows: a maintenance and inspection drone device includes a drone body, a top cover of the drone body with multiple air vents, and a detachable fixing ring plate above the top cover, with multiple parachute ropes passing through the fixing ring plate; a limiting component is also provided above the top cover, the limiting component including two symmetrically arranged shielding shells, the shielding shells being movable relative to the top cover; the parachutes can be stored in the space formed by the shielding shells and the top cover, and the parachutes are arranged to cover the air vents.

[0008] Preferably, an annular groove is provided at the inner edge of the lower side of the fixed ring plate, and a pressing ring plate is provided at the annular groove. The inner diameter of the pressing ring plate is equal to the inner diameter of the fixed ring plate, and its height is greater than the height of the annular groove.

[0009] Preferably, a first extrusion groove and a second extrusion groove are respectively provided on the top surface of the annular groove and the top surface of the pressing ring plate, and the first extrusion groove and the second extrusion groove are arranged opposite each other; a through hole is provided on the top surface of the fixing ring plate, and the through hole is connected to the first extrusion groove.

[0010] Preferably, the two shielding shells are spliced ​​together to form a cylindrical structure with the opening facing downwards, and ear plates are fixedly provided at the corners of the shielding shells near the edge. At the same time, the two ear plates of the two shielding shells on the same side are threaded onto the same bidirectional screw, one of which is connected to the power output shaft of the motor.

[0011] Preferably, a support plate is provided at the end of the bidirectional screw via a bearing connection. The support plate is configured as an L-shaped structure and its end is connected to the top cover. A sprocket is fitted at the end of each of the two bidirectional screws. The diameter of the sprocket is greater than the height of the shielding shell, and the two sprockets are connected by a chain.

[0012] Preferably, a guide device is provided on each of the two shielding shells on the side that is far apart from each other. The guide device includes a bracket and a first guide rod. The bottom of the bracket is connected to the top cover and the top is provided with a threaded hole. The first guide rod is threaded through the threaded hole and its end is inserted into the guide hole of the shielding shell.

[0013] Preferably, the shielding shell includes a first rib, a third rib, and multiple second ribs. The first rib and the third rib are distributed on both sides of the multiple third ribs, with the first rib being the longest and the third rib being the shortest. Deformable elements are provided on the sidewalls of the first rib, the third rib, and the multiple second ribs.

[0014] Preferably, a guide device is provided on each of the two shielding shells on the side away from each other. The guide device includes a bracket, a second guide rod and a spring. The bottom of the bracket is detachably connected to the top cover. The second guide rod is threaded through the bracket and its end is inserted into the guide hole of the third rib. The spring is sleeved on the second guide rod and is in a compressed state. At the same time, the two ends of the spring are in contact with the third rib and the bracket, respectively.

[0015] Preferably, a baffle is provided on the inner side of the shielding shell. The baffle is detachably mounted on the top cover and is fitted to the inner side wall of the third rib.

[0016] Preferably, two shielding shells are spliced ​​together to form a cylindrical structure with the opening facing downwards, and ear plates are fixedly provided at the corners of the shielding shells near the edges; each ear plate is threaded with a threaded post, and the two threaded posts located on the same side of the two shielding shells are connected to the same shaft at their close ends, and a support frame is sleeved on the shaft through a bearing, and the support frame is installed on the top cover; one of the threaded posts is connected to the power output shaft of the motor, and the threaded post located on the shielding shell is connected by a sprocket and a chain.

[0017] Compared with the prior art, the present invention has the following beneficial effects:

[0018] 1. The present invention provides a parachute above the drone body, which can be deployed during the descent of the drone body to increase the drag of the drone body during descent, reduce its descent speed, and further reduce the probability of the drone body being damaged by impact upon landing.

[0019] 2. The present invention provides a shielding shell, which restricts the parachute from being stored on the top of the drone body. The parachute can be unrestricted by moving the shielding shell, thus providing support for the parachute to deploy and slow down the descent of the drone body.

[0020] 3. The present invention includes a motor, a bidirectional screw, and a threaded column, which can control the rotation of the bidirectional screw and the threaded column under the operation of the motor. Since the bidirectional screw and the threaded column are threaded through the ear plate of the shielding shell, the movement of the shielding shell can be controlled, providing support for releasing the parachute's restriction during the descent of the UAV body. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] Figure 1 This is a schematic diagram of the overall structure of the present invention;

[0022] Figure 2 This is a schematic diagram of the top cover of the present invention;

[0023] Figure 3 This is a schematic diagram of the structure of the fixing ring plate of the present invention;

[0024] Figure 4 This is a first structural schematic diagram of the limiting component of the present invention;

[0025] Figure 5 This is a first structural schematic diagram of the shielding shell of the present invention;

[0026] Figure 6 This is a first structural schematic diagram of the guiding device of the present invention;

[0027] Figure 7 This is a schematic diagram of the second structure of the limiting component of the present invention;

[0028] Figure 8 This is a schematic diagram of the second structure of the shielding shell of the present invention;

[0029] Figure 9 This is a schematic diagram of the second structure of the guiding device of the present invention;

[0030] Figure 10 This is a schematic diagram of the third structure of the limiting component of the present invention.

[0031] In the diagram: 1. UAV body; 11. Top cover; 12. Vent; 2. Parachute; 21. Fixing ring plate; 22. Pressing ring plate; 23. Perforation; 24. Annular groove; 25. First extrusion groove; 26. Second extrusion groove; 3. Limiting component; 31. Motor; 32. Support plate; 33. Bidirectional screw; 34. Support frame; 35. Threaded post; 4. Guide device; 41. First guide rod; 42. Threaded hole; 43. Bracket; 44. Second guide rod; 45. Spring; 46. Baffle; 5. Shielding shell; 51. Guide hole; 52. Ear plate; 53. First rib; 54. Second rib; 55. Deformation component; 56. Third rib. DETAILED DESCRIPTION

[0032] In this invention, unless otherwise explicitly specified and limited, the terms "installation," "connection," "linking," and "fixing," 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 communication of two components or the interaction between two components. Those skilled in the art can understand the specific meaning of the above terms in this invention according to the specific circumstances.

[0033] The following description, in conjunction with the accompanying drawings and specific embodiments, provides further details:

[0034] Example 1

[0035] like Figure 1 As shown, to reduce the probability of damage caused by accidental crashes during drone inspections, this embodiment introduces a new drone technology solution. This solution includes a drone body 1 and a parachute 2 positioned above the drone body 1. During normal inspections, the parachute 2 is stored on top of the drone body 1. If the drone body 1's attitude sensor detects that the drone's tilt angle exceeds the normal flight range and persists for a certain period, the parachute 2 is released. Subsequently, the parachute 2 deploys under the influence of wind, slowing the descent rate of the drone body 1 and thus reducing the probability of damage from impact.

[0036] like Figure 1 As shown, the aforementioned drone body 1 has been publicly disclosed, and its structure will be briefly described here. It includes a fuselage frame, rotor system, landing gear, flight control motherboard, GPS module, receiver, battery, camera, sensors, data transmission module, power management module, etc.

[0037] The fuselage frame supports and connects the various components, and is generally made of lightweight yet high-strength materials such as carbon fiber and aluminum alloy. The landing gear, mounted below the fuselage frame, supports the fuselage and cushions landing impact. The rotor system consists of motors, propellers, and electronic speed controllers (ESCs). The motors provide rotational power to the propellers, and their performance parameters (such as power and speed) affect the drone's lift and thrust. The propeller's size, pitch, and material determine the thrust and flight efficiency; common materials include plastics and carbon fiber. The ESC controls the motor speed, precisely adjusting the motor speed according to commands from the flight control system to achieve attitude control and stable flight.

[0038] The flight control motherboard is essentially the "brain" of a drone, integrating various sensors (such as accelerometers, gyroscopes, magnetometers, or attitude sensors) and core components like a microprocessor. Accelerometers measure the drone's acceleration in various directions, gyroscopes detect its rotational angular velocity, and magnetometers help determine its heading. The microprocessor performs rapid calculations based on the data collected by these sensors and then sends control commands to various actuators (such as motors and ESCs) to achieve precise control of the drone's flight attitude (such as pitch, roll, and yaw).

[0039] The GPS module receives satellite signals to determine the drone's real-time geographical coordinates (longitude, latitude, altitude, etc.), providing precise positioning information. A receiver, installed on the drone, receives wireless signals from the remote controller and transmits them to the flight control motherboard, which then performs corresponding flight control actions based on the instructions. The remote controller works in conjunction with the receiver; it's the device used by the operator to send control commands to the drone and has multiple channels to control different flight maneuvers (such as ascent, descent, forward, and backward).

[0040] Batteries are the energy source for electric drones, with lithium batteries being the most common. Their capacity, voltage, discharge rate, and other parameters determine the drone's flight time and power output.

[0041] Cameras are a common payload for drones, used for image acquisition in aerial photography, inspection, and other tasks. There are various types, including standard high-definition cameras, wide-angle cameras capable of panoramic shots, and thermal imaging cameras with infrared capabilities. Different cameras meet different shooting needs. For example, in power line inspection, infrared thermal imaging cameras can detect potential overheating hazards in power lines, while standard high-definition cameras can check for external damage to the lines. Sensors can be configured as ultrasonic sensors for distance detection, helping drones avoid obstacles during flight; lidar sensors can build high-precision 3D environmental maps and are commonly used in surveying, terrain modeling, and other tasks.

[0042] The data transmission module is responsible for transmitting data collected by the drone (such as images captured by the camera and data detected by the sensors) back to the ground control station. It also receives control commands and updated flight parameters from the ground control station. Common wireless communication technologies include Wi-Fi, Bluetooth, and 4G / 5G. Different communication methods have their own advantages and disadvantages in terms of transmission distance, speed, and stability, and the appropriate method must be selected based on the specific application scenario. The power management module manages the drone's power supply, such as monitoring battery level, voltage, and charging / discharging status. It also coordinates the power requirements of various components to prevent over-discharging or overcharging of the battery due to abnormal power consumption in any component.

[0043] like Figure 1 As shown, in order to stably connect the deployed parachute 2 to the drone body 1, a fixing ring plate 21 is connected to the bottom of the parachute 2 rope. The fixing ring plate 21 is detachably mounted on the top cover 11 of the drone body 1 by bolts. Therefore, under the action of the fixing ring plate 21, the parachute 2 rope is stably connected to the drone body 1.

[0044] like Figure 3 As shown, to ensure a stable connection between the parachute 2's rope and the fixing ring plate 21, an annular groove 24 is provided at the inner edge of the lower side of the fixing ring plate 21. A pressure ring plate 22 is provided at the annular groove 24. The inner diameter of the pressure ring plate 22 is equal to the inner diameter of the fixing ring plate 21, and its height is greater than the height of the annular groove 24. Therefore, the parachute 2's rope can pass through the contact surface of the fixing ring plate 21 and the pressure ring plate 22. Then, when the fixing ring plate 21 is bolted onto the UAV body 1, the rope is stably positioned relative to the fixing ring plate 21 under the pressure of the fixing ring plate 21 and the pressure ring plate 22. This design not only achieves a stable connection between the parachute 2 and the UAV body 1, but also facilitates the disassembly of the parachute 2 as needed.

[0045] Specifically, a first compression groove 25 and a second compression groove 26 are respectively provided on the top surface of the annular groove 24 and the top surface of the pressure ring plate 22, with the first compression groove 25 and the second compression groove 26 facing each other. Additionally, a through hole 23 is provided on the top surface of the fixed ring plate 21, which communicates with the first compression groove 25. Therefore, the parachute 2's rope passes through the through hole 23 and extends into the space formed by the first compression groove 25 and the second compression groove 26. Because the diameter of the space formed by the first compression groove 25 and the second compression groove 26 is smaller than the diameter of the rope, the rope is compressed when the pressure ring plate 22 and the fixed ring plate 21 are close to each other, ensuring stable installation relative to the fixed ring plate 21.

[0046] like Figure 1 , Figure 4 As shown, in order to store the unused parachute 2 on the top of the drone body 1, a limiting component 3 is also provided above the top cover 11. The limiting component 3 includes two symmetrically arranged shielding shells 5. The two shielding shells 5 are spliced ​​together to form a cylindrical structure with the opening facing downward. Therefore, the two shielding shells 5 cooperate with the top cover 11 to form a space for storing the parachute 2, and under the action of the shielding shells 5, the parachute 2 is restricted to be placed stably relative to the drone body 1.

[0047] In order to deploy the parachute 2 in time when the drone body 1 falls, the shielding shell 5 is movable relative to the top cover 11. That is, after the drone tilts at an angle that exceeds the normal flight range and continues for a certain period of time, the two shielding shells 5 move away from each other under the action of external force, thereby releasing the restriction of the parachute 2 and deploying it during the descent of the drone body 1.

[0048] like Figure 4 , Figure 5 As shown, specifically, a bidirectional screw 33 is provided on both sides of the two shielding shells 5, and an ear plate 52 is fixedly provided at the corners of the two shielding shells 5 near their edges. At the same time, the two ear plates 52 located on the same side of the two shielding shells 5 are threaded onto the same bidirectional screw 33. Therefore, when the bidirectional screw 33 rotates, the movement of the two shielding shells 5 towards or away from each other can be controlled.

[0049] like Figure 10 As shown, threaded posts 35 are provided on both sides of each shielding shell 5, with the number of threaded posts 35 equal to the number of ear plates 52, and the threads of the threaded posts 35 penetrate through the ear plates 52. The ends of the two threaded posts 35 located on the same side of the two shielding shells 5 are connected to the same shaft. A support frame 34 is sleeved on the shaft through a bearing connection. The support frame 34 is mounted on the top cover 11. Therefore, under the action of the support frame 34, the threaded posts 35 are stably mounted on the top cover 11. A sprocket is sleeved on one of the shafts, and a sprocket is also provided on the power output shaft of the motor 31 located on its side. Therefore, the motor 31 is connected to the shaft through a chain. In addition, the threaded posts 35 located on both sides of the shielding shell 5 are connected through sprockets and chains. Therefore, the rotation of the four threaded posts 35 can be controlled by the action of the motor 31. The threads of the two threaded posts 35 connected together are in opposite directions. Therefore, the movement of the two shielding shells 5 towards or away from each other can be controlled.

[0050] like Figure 4 As shown, to enable the bidirectional screw 33 to rotate and to ensure its stable installation, a support plate 32 is connected to the end of the bidirectional screw 33 via a bearing. The support plate 32 has an L-shaped structure, and its end is connected to the top cover 11. A motor 31 (which can be a stepper motor or a servo motor) is located at the end of one of the bidirectional screws 33. This motor 31 is fixedly connected to the support plate 32 via a frame, and the power output shaft of the motor 31 is connected to the end of the bidirectional screw 33 via a coupling. Therefore, when the motor is operating, the rotation of the bidirectional screw 33 can be controlled.

[0051] like Figure 4 As shown, to control the synchronous rotation of the two bidirectional screws 33, sprockets are fitted at the ends of both bidirectional screws 33, and the two sprockets are connected by a chain. Therefore, the power transmission between the bidirectional screws 33 is achieved through the cooperation of the sprockets and the chain. In addition, the diameter of the sprocket is larger than the height of the shielding shell 5, and the two sides of the chain are distributed on the upper and lower sides of the shielding shell 5 to avoid the presence of the chain affecting the movement of the shielding shell 5.

[0052] The aforementioned motor 31 is connected to the flight control motherboard via signal lines, enabling it to receive commands from the motherboard. Each motor is connected to one of the four motor interfaces on the flight control motherboard via a corresponding electronic speed controller (ESC). The flight control motherboard determines whether the motor 31 operates based on attitude information collected by its built-in sensors. The power cable of the motor 31 is typically connected to the power input interface of the ESC, which in turn connects to the output of the power management module or the battery via a power cable.

[0053] like Figure 4 , Figure 6 As shown, to restrict the movement of the shielding shells 5, guide devices 4 are provided on the sides of the two shielding shells 5 that are far apart from each other. Each guide device 4 includes a bracket 43 and a first guide rod 41. The bottom of the bracket 43 is connected to the top cover 11, and the top is provided with a threaded hole 42. The first guide rod 41 is threaded through the threaded hole 42, and its end is inserted into the guide hole 51 of the shielding shell 5. When the two shielding shells 5 are joined together, the end of the first guide rod 41 is located in the guide hole 51 and blocks the guide hole 51. When the two shielding shells 5 are far apart from each other, the first guide rod 41 passes through the guide hole 51, thereby restricting the movement of the shielding shells 5.

[0054] like Figure 2 As shown, after the shielding shells 5 move away from each other and the restriction of the parachute 2 is lifted, the parachute 2 rebounds, recovers its deformation, and then unfolds. At the same time, multiple air vents 12 are provided on the top cover 11. During the descent of the UAV body 1, the airflow passes through the air vents 12 and enters the interior of the parachute 2, accelerating the unfolding of the parachute 2.

[0055] Example 2

[0056] like Figure 7 , Figure 8 As shown, based on Embodiment 1, in order to enable the shielding shell 5 to release the restriction on the parachute 2 within a small area, the shielding shell 5 includes a deformable element 55, a first rib 53, a third rib 56, and multiple second ribs 54. The first rib 53 and the third rib 56 are distributed on both sides of the multiple second ribs 54, with the first rib 53 being the longest and the third rib 56 being the shortest, forming the skeleton of the shielding shell 5. The shape of the shielding shell 5 can be adjusted by the relative movement of the first rib 53, the third rib 56, and the second ribs 54, changing the current situation of the overall adjustment position of the shielding shell 5. The deformable element 55 may be provided with a mesh fabric and is provided on the sidewalls of the first rib 53, the third rib 56, and the multiple second ribs 54. Therefore, the deformable element 55 can deform as the first rib 53, the third rib 56, and the multiple second ribs 54 move, providing support for restricting the storage of the parachute 2 and releasing the restriction on the parachute 2.

[0057] like Figure 9As shown, in the above structure, in order to restrict the movement of the shielding shell 5 and provide sufficient space for the parachute 2 to deploy, a guide device 4 (replacing the guide device in Embodiment 1) is provided on each side of the two shielding shells 5 that are far apart from each other. The guide device 4 includes a bracket 43, a second guide rod 44, and a spring 45. The bottom of the bracket 43 is detachably connected to the top cover 11. The second guide rod 44 is threaded through the bracket 43 and its end is inserted into the guide hole 51 of the third rib 56. The spring 45 is sleeved on the second guide rod 44 and is in a compressed state. At the same time, both ends of the spring 45 are in contact with the third rib 56 and the bracket 43, respectively. In addition, a baffle 46 is provided on the inner side of the shielding shell 5. The baffle 46 is detachably provided on the top cover 11 and is set against the inner sidewall of the third rib 56. Therefore, with the cooperation of the guide device 4 and the baffle 46, the third rib 56 can be stably placed relative to the top cover 11, and support can be provided for the third rib 56 to move a short distance relative to the top cover 11, so as to realize the restriction of the parachute 2 by the shielding shell 5, and to provide support for the movement of the shielding shell 5 to release the restriction of the parachute 2.

[0058] The above are merely preferred embodiments of the present invention and are not intended to limit the present invention. For those skilled in the art, the present invention can have various modifications and variations. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the scope of protection of the present invention.

Claims

1. A maintenance and inspection drone equipment, characterized in that: The invention comprises an unmanned aerial vehicle body (1), a top cover (11) of the unmanned aerial vehicle body (1) is provided with a plurality of wind holes (12), and a fixing ring plate (21) is detachably provided above the top cover (11), and ropes of a plurality of parachutes (2) are passed through the fixing ring plate (21); a limiting component (3) is also provided above the top cover (11), and the limiting component (3) comprises two symmetrically arranged shielding shells (5), and the shielding shells (5) can be movably arranged relative to the top cover (11); the parachute (2) can be stored in a space formed by the shielding shell (5) and the top cover (11), and the parachute (2) is arranged to cover the wind hole (12).

2. A maintenance and inspection drone device according to claim 1, characterized in that: An annular groove (24) is provided at the inner edge of the lower side of the fixed ring plate (21), and a pressing ring plate (22) is provided at the annular groove (24). The inner diameter of the pressing ring plate (22) is equal to the inner diameter of the fixed ring plate (21), and the height is greater than the height of the annular groove (24).

3. A maintenance and inspection drone device according to claim 2, characterized in that: A first extrusion groove (25) and a second extrusion groove (26) are respectively arranged on the top surface of the annular groove (24) and the top surface of the pressure ring plate (22), and the first extrusion groove (25) and the second extrusion groove (26) are arranged opposite to each other; a through hole (23) is arranged on the top surface of the fixed ring plate (21), and the through hole (23) is connected to the first extrusion groove (25).

4. A maintenance and inspection drone device according to claim 1, characterized in that: The two shielding shells (5) are spliced ​​to form a cylindrical structure with an opening facing downward, and an ear plate (52) is fixedly provided at the end corner of the shielding shell (5) near the edge, and the two ear plates (52) on the same side of the two shielding shells (5) are threadedly sleeved on the same bidirectional screw (33), and one of the bidirectional screws (33) is connected to the power output shaft of the motor (31).

5. A maintenance and inspection drone device according to claim 4, characterized in that: A support plate (32) is provided at the end of the bidirectional screw rod (33) via a bearing connection, the support plate (32) is provided in an L-shaped structure, and the end thereof is connected to the top cover (11); sprockets are sleeved at the ends of the two bidirectional screw rods (33), the diameter of the sprockets is greater than the height of the shielding shell (5), and the two sprockets are connected via a chain.

6. A maintenance and inspection drone device according to claim 5, characterized in that: A guide device (4) is provided on the side of the two shielding shells (5) that is away from each other. The guide device (4) comprises a bracket (43) and a first guide rod (41). The bottom of the bracket (43) is connected to the top cover (11), and a threaded hole (42) is provided on the top. The first guide rod (41) is threadedly penetrated through the threaded hole (42), and the end portion is inserted into the guide hole (51) of the shielding shell (5).

7. A maintenance and inspection drone device according to claim 5, characterized in that: The shielding shell (5) comprises a first rib (53), a third rib (56) and a plurality of second ribs (54); the first rib (53) and the third rib (56) are distributed on both sides of the plurality of third ribs (56), and the first rib (53) is the longest and the third rib (56) is the shortest; and a deformable member (55) is provided on the side walls of the first rib (53), the third rib (56) and the plurality of second ribs (54).

8. A maintenance and inspection drone device according to claim 7, characterized in that: A guide device (4) is provided on the side of the two shielding shells (5) that are away from each other. The guide device (4) comprises a bracket (43), a second guide rod (44) and a spring (45). The bottom of the bracket (43) is detachably connected to the top cover (11). The second guide rod (44) is threadedly penetrated on the bracket (43), and the end thereof is inserted into the guide hole (51) of the third rib plate (56). The spring (45) is sleeved on the second guide rod (44) and is in a compressed state. At the same time, the two ends of the spring (45) are respectively in contact with the third rib plate (56) and the bracket (43).

9. A maintenance and inspection drone device according to claim 8, characterized in that: A baffle (46) is arranged on the inner side of the shielding shell (5); the baffle (46) is detachably arranged on the top cover (11) and is arranged in contact with the inner side wall of the third rib (56).

10. A maintenance and inspection drone device according to claim 1, characterized in that: The two shielding shells (5) are spliced ​​to form a cylindrical structure with an opening facing downward, and an ear plate (52) is fixedly arranged at the end corner of the shielding shell (5) near the edge; a threaded column (35) is threadedly penetrated on each ear plate (52), and the two threaded columns (35) located on the same side of the two shielding shells (5) are connected to the same shaft at one end close to each other, and a support frame (34) is provided on the shaft through a bearing connecting sleeve, and the support frame (34) is installed on the top cover (11); one of the threaded columns (35) is connected to the power output shaft of the motor (31), and the threaded columns (35) located on both sides of the shielding shell (5) are connected through a sprocket and a chain.

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