A power inspection drone

Abstract

The present invention belongs to the technical field of aviation equipment industry, and in particular, relates to an electric power inspection UAV, including a UAV main body, and also including: a high-definition camera, a temperature-sensitive rheostat, a flame-spraying foreign matter removal mechanism, a load reduction feedback mechanism, a rotor speed self-adjusting compensation mechanism, a lubrication state intuitive display mechanism, and a PLC controller. The present invention can automatically adjust the UAV rotor speed based on the ambient temperature and the fuel consumption of the flame-spraying mechanism during use, resulting in a reduction in the UAV load, to ensure the stability of the UAV flight, and can avoid the problem that excessive lift will make the UAV more sensitive to changes in airflow and wind direction, affecting the flight stability, and can automatically calculate the lubricating oil loss during the flight of the UAV, so that the staff can arrange the maintenance time more reasonably and avoid unnecessary maintenance too early or too late.

Description

Technical Field

[0001] The present invention belongs to the technical field of aviation equipment industry, and in particular relates to an electric power inspection UAV. Background Art

[0002] The power inspection drone is a high-tech equipment used to inspect power facilities. It can quickly cover a large area of ​​power lines and equipment, improve inspection efficiency, reduce the risk of manual inspection, and avoid personnel working in dangerous environments such as high altitude and complex terrain. It is equipped with high-definition cameras and sensors and can accurately detect faults and hidden dangers of power equipment. Among them, the rotor drone can take off and land vertically in a very small space and does not need a long runway like a fixed-wing drone. This makes it have great advantages when conducting power inspections in complex terrain and small spaces. The rotor drone has excellent hovering ability and can maintain stable hovering at a specific position to carefully observe and photograph power facilities. This is very important for checking the details of power lines and discovering potential fault points. Therefore, rotor drones are widely promoted and used in power inspection work. For example, the patent with patent announcement number CN115285342A proposes a power inspection drone.

[0003] When using rotorcraft drones for power inspections in the cold winter environment, the low temperature weakens the thermal motion of air molecules, and the thermal motion of molecules determines their average kinetic energy and degree of diffusion. Low temperature reduces the kinetic energy of molecules, reduces the range of molecular activity, and relatively increases the distance between molecules, which leads to a decrease in the number of air molecules per unit volume, thereby reducing the air density. Based on the lift formula of rotorcraft drones: L=1 / 2ρv²SCI (where L is lift, ρ is air density, v is the flow rate of air around the rotor, S is the area of ​​the rotor, and CI is the lift coefficient), it can be seen that the reduction in air density will directly lead to a decrease in lift, which in turn affects the flight stability of the rotorcraft drone, which directly leads to the fact that the flight stability of the rotorcraft drone will be greatly affected due to changes in ambient temperature during power inspections, and cannot meet the needs of power inspections well. Summary of the invention

[0004] The purpose of the present invention is to provide a power inspection drone in view of the above problems.

[0005] To achieve the above object, the present invention adopts the following technical solutions: an electric power inspection drone, including a drone body, and also including:

[0006] A high-definition camera is fixedly mounted on the top of the drone body;

[0007] A temperature-sensitive variable resistance plate, installed on the top of the high-definition camera;

[0008] A flame-spraying foreign matter removal mechanism is fixedly mounted on the bottom of the drone body;

[0009] A load reduction feedback mechanism is fixedly mounted in the flame-spraying foreign matter removal mechanism;

[0010] The rotor speed self-regulating compensation mechanism is fixedly installed in the flame-spraying foreign matter removal mechanism, and the temperature-sensitive variable resistance plate and the load reduction feedback mechanism are both connected in series to the power supply circuit of the rotor speed self-regulating compensation mechanism;

[0011] A lubrication status visual display mechanism, which is fixedly installed in the flame-spraying foreign matter removal mechanism and is electrically connected to the rotor speed self-adjusting compensation mechanism;

[0012] The PLC controller is fixedly installed in the flame-spraying foreign matter removal mechanism and is electrically connected to the flame-spraying foreign matter removal mechanism, the load reduction feedback mechanism, the rotor speed self-adjusting compensation mechanism and the lubrication status visual display mechanism respectively.

[0013] In the above-mentioned power inspection UAV, the flame-spraying foreign matter removal mechanism includes a fixed bracket fixedly installed at the bottom of the UAV body, a fuel tank is fixedly installed in the fixed bracket, a rotating tube is rotatably sleeved on the bottom of the fixed bracket, the upper end of the rotating tube is fixedly connected to the fuel tank through a rotating sealing joint, the lower end of the rotating tube is fixedly connected to a flamethrower, the rear end of the flamethrower is fixedly connected to a counterweight block, the end of the counterweight block away from the flamethrower is fixedly connected to a compensating fan through a connecting bracket, and a limiting mechanism is installed between the fixed bracket, the rotating tube and the flamethrower.

[0014] In the above-mentioned power inspection drone, the load reduction feedback mechanism includes a feedback shell, the inner wall of the feedback shell is rotatably connected to an adjusting screw, the outer wall of the feedback shell is fixedly provided with an adjusting motor for driving the adjusting screw to rotate, the rod wall of the adjusting screw is threadedly sleeved with an adjusting seat, the inner wall of the feedback shell is fixedly provided with a feedback resistor rod arranged parallel to the adjusting screw, and one end of the adjusting seat is fixedly connected to a feedback conductive contact piece electrically in contact with the feedback resistor rod.

[0015] In the above-mentioned electric power inspection UAV, the rotor speed self-adjusting compensation mechanism includes a compensation shell, the inner wall of the compensation shell is fixedly connected to multiple guide slide rods in parallel, and the multiple guide slide rods are slidably sleeved with the same sliding plate, and the sliding plate and the compensation shell are fixedly connected on the opposite side with multiple reset springs sleeved on the outside of the guide slide rods, and the sliding plate is fixedly connected to a force-bearing permanent magnet plate on the side away from the reset spring. The inner wall of the compensation shell is fixedly equipped with a force-adding electromagnetic plate arranged opposite to the force-bearing permanent magnet plate, and the inner wall of the compensation shell is fixedly equipped with a compensation resistor rod arranged parallel to the guide slide rod, and one end of the sliding plate is fixedly connected with a compensation conductive contact electrically in contact with the compensation resistor rod.

[0016] In the above-mentioned electric power inspection drone, the lubrication status intuitive display mechanism includes a display shell, a transmission screw is rotatably connected inside the display shell, a servo motor for driving the transmission screw to rotate is fixedly installed on the outer wall of the display shell, a transmission seat is threadedly sleeved on the rod wall of the transmission screw, a pointer is fixedly connected to one side of the transmission seat, and the end of the pointer away from the transmission seat passes through a strip-shaped opening opened on the side wall of the display shell and extends out of the display shell, and a scale plate corresponding to the position of the pointer is fixedly installed on the outer wall of the display shell.

[0017] In the above-mentioned power inspection drone, the limiting mechanism includes a rotating cylinder fixedly sleeved on the outside of the rotating tube, the lower end of the fixed bracket is fixedly connected with a limiting connecting block of an annular structure, the cross-section of the limiting connecting block is a T-shaped structure, the upper end of the rotating cylinder is provided with a limiting connecting groove that matches and slides with the limiting connecting block, and a plurality of supporting blocks are fixedly connected between the lower end of the rotating cylinder and the outer surface of the flamethrower.

[0018] In the above-mentioned power inspection drone, the outer wall of the adjustment seat is fixedly connected to a first limit slider, and the inner wall of the feedback shell is provided with a first limit sliding groove that matches and slides with the first limit slider.

[0019] In the above-mentioned power inspection drone, the outer wall of the transmission seat is fixedly connected to a second limit slider, and the inner wall of the display shell is provided with a second limit sliding groove that matches and slides with the second limit slider.

[0020] Compared with the prior art, the present invention has the following beneficial effects:

[0021] 1. By setting up the drone main body and the flame-spraying foreign matter removal mechanism, the rotor drone used for power inspection also has a flame-spraying function. In the process of the drone conducting power inspection, if some small foreign objects such as kite lines and plastic films are entangled in the power lines, the foreign objects can be burned off quickly and accurately under the remote control of the ground personnel, avoiding the problem of foreign objects causing continuous damage to the power lines. In addition, the compensation fan can provide a reverse thrust during the drone's flame-spraying work, thereby offsetting the recoil generated by the flame-spraying, avoiding the problem of thrust on the drone during the flame-spraying process affecting the stable hovering of the drone, and improving the accuracy and safety of the flame-spraying.

[0022] 2. Through the load reduction feedback mechanism, rotor speed self-adjustment compensation mechanism and temperature-sensitive variable resistor plate, the drone rotor speed can be automatically adjusted based on the ambient temperature and the fuel consumption during the use of the flamethrower mechanism, which leads to the reduction of the drone load. The rotor speed can be increased in a low temperature environment because low temperature will weaken the thermal motion of air molecules, and the thermal motion of molecules determines their average kinetic energy and diffusion degree. Low temperature reduces the kinetic energy of molecules, reduces the range of molecular activity, and relatively increases the distance between molecules, which leads to a decrease in the number of air molecules per unit volume, thereby reducing the air density. Based on the lift formula of the rotor drone: L=1 / 2 ρv²SCI (where L is lift, ρ is air density, v is the velocity of the air around the rotor, S is the area of ​​the rotor, and CI is the lift coefficient). It can be seen that a decrease in air density will directly lead to a decrease in lift, which in turn affects the flight stability of the rotorcraft. Increasing the rotor speed can compensate for the lift loss caused by the decrease in air density and ensure the stability of the drone's flight. When the jet fuel consumption increases and the drone's load becomes lower, the rotor speed is automatically reduced, which not only saves energy and extends the drone's flight time, but also avoids the problem that excessive lift will make the drone more sensitive to changes in airflow and wind direction, affecting flight stability.

[0023] 3. Through the intuitive display mechanism of lubrication status and the self-adjusting compensation mechanism of rotor speed, the lubricating oil loss during the flight of the UAV can be automatically calculated, so that the staff can arrange the maintenance time more reasonably and avoid unnecessary maintenance too early or too late. The calculation degree can be automatically adjusted based on the rotor speed, and the calculation of lubricating oil loss is more accurate. BRIEF DESCRIPTION OF THE DRAWINGS

[0024] Figure 1 It is a three-dimensional structural schematic diagram of the present invention;

[0025] Figure 2 It is a front view structural schematic diagram of the present invention;

[0026] Figure 3It is a structural schematic diagram of the flame spraying foreign matter removal mechanism of the present invention;

[0027] Figure 4 is a cross-sectional structural schematic diagram of the load reduction feedback mechanism of the present invention;

[0028] Figure 5 It is a schematic cross-sectional view of the rotor speed self-adjusting compensation mechanism of the present invention;

[0029] Figure 6 It is a cross-sectional structural schematic diagram of the lubrication state intuitive display mechanism of the present invention;

[0030] Figure 7 It is a schematic cross-sectional structural diagram of the limiting mechanism of the present invention;

[0031] Figure 8 yes Figure 7 Schematic diagram of the three-dimensional structure of the central rotating cylinder.

[0032] In the figure: 1 UAV body, 2 flame spray foreign body removal mechanism, 21 fixed bracket, 22 fuel tank, 23 rotating tube, 24 flame spray gun, 25 counterweight, 26 connecting bracket, 27 compensation fan, 28 motor rotating assembly, 3 load reduction feedback mechanism, 31 feedback shell, 32 adjustment screw, 33 adjustment motor, 34 adjustment seat, 35 feedback resistor rod, 36 feedback conductive contact piece, 4 rotor speed self-adjusting compensation mechanism, 41 compensation shell, 42 guide slide rod, 43 Sliding plate, 44 return spring, 45 force-bearing permanent magnet plate, 46 force-adding electromagnetic plate, 47 compensation resistor rod, 48 compensation conductive contact piece, 5 lubrication status visual display mechanism, 51 display shell, 52 transmission screw, 53 servo motor, 54 transmission seat, 55 pointer, 56 strip-shaped opening, 57 scale plate, 6 limit mechanism, 61 rotating cylinder, 62 limit connecting block, 63 limit connecting groove, 64 supporting block, 7 high-definition camera, 8 temperature-sensitive variable resistor plate, 9 PLC controller. Implementation

[0033] The technical solutions in the embodiments of the present invention will be described clearly and completely below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, rather than all the embodiments.

[0034] like Figure 1-Figure 8 As shown, a power inspection drone includes a drone body 1 and also includes:

[0035] A high-definition camera 7 is fixedly mounted on the top of the drone body 1;

[0036] The temperature-sensitive variable resistance plate 8 is installed on the top of the high-definition camera 7;

[0037] The flame-spraying foreign matter removal mechanism 2 is fixedly installed at the bottom of the UAV body 1. The flame-spraying foreign matter removal mechanism 2 includes a fixed bracket 21 fixedly installed at the bottom of the UAV body 1. A fuel tank 22 is fixedly installed in the fixed bracket 21. A rotating tube 23 is rotatably sleeved at the bottom of the fixed bracket 21. The upper end of the rotating tube 23 is fixedly connected to the fuel tank 22 through a rotating sealing joint. The lower end of the rotating tube 23 is fixedly connected to a flamethrower 24. A counterweight block 25 is fixedly connected to the rear end of the flamethrower 24. The end of the counterweight block 25 away from the flamethrower 24 is fixedly connected to a compensating fan 27 through a connecting bracket 26. A limiting mechanism 6 is installed between the fixed bracket 21, the rotating tube 23 and the flamethrower 24. In the process of the UAV conducting power inspection, for some small foreign objects such as kite lines, plastic films, etc. that are entangled in the power lines, under the remote control of ground personnel, the foreign objects can be quickly and accurately burned off to avoid the problem of continuous harm to the power lines caused by foreign objects.

[0038] The limiting mechanism 6 includes a rotating cylinder 61 fixedly sleeved on the outside of the rotating tube 23, a limiting connecting block 62 of an annular structure is fixedly connected to the lower end of the fixed bracket 21, the cross section of the limiting connecting block 62 is a T-shaped structure, and a limiting connecting groove 63 matching and slidingly connected with the limiting connecting block 62 is opened at the upper end of the rotating cylinder 61, and a plurality of supporting blocks 64 are fixedly connected between the lower end of the rotating cylinder 61 and the outer surface of the flamethrower 24.

[0039] The load reduction feedback mechanism 3 is fixedly installed in the flame-throwing foreign matter removal mechanism 2. The load reduction feedback mechanism 3 includes a feedback shell 31. The inner wall of the feedback shell 31 is rotatably connected to an adjusting screw 32. The outer wall of the feedback shell 31 is fixedly installed with an adjusting motor 33 for driving the adjusting screw 32 to rotate. The rod wall of the adjusting screw 32 is threadedly sleeved with an adjusting seat 34. The inner wall of the feedback shell 31 is fixedly installed with a feedback resistor rod 35 arranged parallel to the adjusting screw 32. One end of the adjusting seat 34 is fixedly connected with a feedback conductive contact 36 in electrical contact with the feedback resistor rod 35. The UAV rotor speed can be automatically adjusted based on the ambient temperature and the reduction of the UAV load caused by the consumption of fuel during the use of the flame-throwing mechanism, so as to increase the rotor speed in a low temperature environment.

[0040] The rotor speed self-adjusting compensation mechanism 4 is fixedly installed in the flame-spraying foreign matter removal mechanism 2, and the temperature-sensitive variable resistor plate 8 and the load reduction feedback mechanism 3 are both connected in series to the power supply circuit of the rotor speed self-adjusting compensation mechanism 4. The rotor speed self-adjusting compensation mechanism 4 includes a compensation shell 41, and the inner wall of the compensation shell 41 is fixedly connected with multiple guide slides 42 in parallel, and the multiple guide slides 42 are slidably sleeved with the same sliding plate 43. The sliding plate 43 and the compensation shell 41 are fixedly connected on the opposite side with multiple reset springs 44 sleeved on the outside of the guide slide 42, and the sliding plate 43 is fixedly connected with a force permanent magnet plate 45 on the side away from the reset spring 44. The inner wall of the compensation shell 41 is fixedly installed with a force electromagnetic plate 46 arranged opposite to the force permanent magnet plate 45, and the inner wall of the compensation shell 41 is fixedly installed with a compensation resistor rod 47 arranged parallel to the guide slide rod 42, and one end of the sliding plate 43 is fixedly connected with a compensation conductive contact piece 48 electrically in contact with the compensation resistor rod 47.

[0041] The lubrication status intuitive display mechanism 5 is fixedly installed in the flame-spraying foreign matter removal mechanism 2 and is electrically connected to the rotor speed self-adjusting compensation mechanism 4. The lubrication status intuitive display mechanism 5 includes a display shell 51, in which a transmission screw 52 is rotatably connected, and a servo motor 53 for driving the transmission screw 52 to rotate is fixedly installed on the outer wall of the display shell 51. A transmission seat 54 is threadedly sleeved on the rod wall of the transmission screw 52, ​​and a pointer 55 is fixedly connected to one side of the transmission seat 54. The end of the pointer 55 away from the transmission seat 54 passes through a strip-shaped opening 56 opened on the side wall of the display shell 51 and extends out of the display shell 51. A scale plate 57 corresponding to the position of the pointer 55 is fixedly installed on the outer wall of the display shell 51, which can automatically calculate the lubricating oil loss during the flight of the UAV, so that the staff can arrange the maintenance time more reasonably and avoid unnecessary premature or late maintenance. The calculation degree can be automatically adjusted based on the rotation speed of the rotor, and the calculation of the lubricating oil loss is more accurate.

[0042] The PLC controller 9 is fixedly installed in the flame-spraying foreign matter removing mechanism 2, and is electrically connected to the flame-spraying foreign matter removing mechanism 2, the load reduction feedback mechanism 3, the rotor speed self-adjusting compensation mechanism 4 and the lubrication state visual display mechanism 5 respectively.

[0043] The outer wall of the adjustment seat 34 is fixedly connected with a first limit slider, and the inner wall of the feedback housing 31 is provided with a first limit sliding groove matching and slidingly connected with the first limit slider.

[0044] The outer wall of the transmission seat 54 is fixedly connected with a second limit sliding block, and the inner wall of the display housing 51 is provided with a second limit sliding groove matching and slidingly connected with the second limit sliding block.

[0045] The operating principle of the present invention is described as follows: the drone body 1 takes off to perform power inspection work, which can quickly cover a large area of ​​power lines and equipment, thereby improving inspection efficiency. When the drone body 1 cooperates with the high-definition camera 7 to display that there are foreign objects entangled in the power lines, the ground operator controls the drone body 1 to move to the foreign objects, and sprays flames through the flamethrower 24 and the fuel tank 22 to burn the foreign objects, thereby preventing the existence of foreign objects from causing continuous damage to the power lines. The flamethrowing intensity is determined based on the type and size of the foreign objects. At the same time, when spraying flames, the compensation fan 27 is synchronously turned on to form a thrust in the opposite direction of the flamethrowing direction, thereby compensating for the recoil generated by the flamethrower 24 when spraying flames. The greater the flamethrowing intensity, the greater the working power of the compensation fan 27, and the better the recoil generated by the flamethrowing, so that the drone hovers more stably, and the accuracy and safety of the flamethrowing are improved.

[0046] The temperature-sensitive variable resistor plate 8 monitors the ambient temperature in real time. The temperature-sensitive variable resistor plate 8 is specifically a positive temperature coefficient thermistor, which is made of barium titanate as the main material, and then doped with an appropriate amount of rare earth elements, and is manufactured using a ceramic process. At low temperatures, the crystal structure of the temperature-sensitive variable resistor plate 8 is in a relatively disordered state, and the migration of carriers (electrons or holes) in the material is relatively easy. At this time, the resistance value is small, and as the temperature increases, the crystal structure inside the material changes, and an ordered crystal structure is gradually formed, which makes the migration of carriers difficult and the resistance value increases rapidly;

[0047] At the beginning, the central controller in the drone body 1 controls the power supply equipment to supply a fixed power supply current to the force electromagnetic plate 46. The force electromagnetic plate 46 is energized to generate the same magnetism as the force-bearing permanent magnet plate 45, thereby driving the sliding plate 43 along the guide slide rod 42, overcoming the elastic force of the reset spring 44 and sliding in the compensation shell 41, thereby causing the compensation conductive contact 48 to slide a certain distance on the compensation resistor rod 47, and the temperature-sensitive variable resistor plate 8 is connected in series to the power supply circuit of the force electromagnetic plate 46. In a low temperature environment, the resistance value of the temperature-sensitive variable resistor plate 8 becomes smaller. At this time, the power supply current of the force electromagnetic plate 46 is larger, which makes the magnetism of the force electromagnetic plate 46 stronger, thereby causing the sliding plate 43 to be subjected to a greater thrust, driving the compensation conductive contact 48 to slide a greater distance on the compensation resistor rod 47, thereby making the access to the compensation resistor rod 47 The resistance value is smaller, and the resistance value signal fed back to the central controller in the drone body 1 by the compensation conductive contact 48 and the compensation resistor rod 47 is smaller. The central controller controls the brushless DC motor at the corresponding rotor of the drone body 1 to operate at a greater working power through the electronic speed regulator, thereby allowing the drone body 1 to increase the rotor speed, thereby compensating for the reduction in air density caused in a low temperature environment. Based on the lift formula of the rotor drone: L=1 / 2ρv²SCI (where L is lift, ρ is air density, v is the flow rate of air around the rotor, S is the area of ​​the rotor, and CI is the lift coefficient), it can be seen that the reduction in air density will directly lead to a reduction in lift, thereby affecting the flight stability of the rotor drone, and increasing the rotor speed can compensate for the lift loss caused by the reduction in air density, thereby ensuring the stability of the drone flight;

[0048] When the flamethrower 24 is in operation, the fuel in the fuel tank 22 will be consumed, thereby gradually reducing the load of the UAV body 1. When the flamethrower 24 is in use, the central controller controls the adjusting motor 33 to act synchronously, and the adjusting motor 33 drives the adjusting screw 32 to rotate. The threaded connection between the adjusting screw 32 and the adjusting seat 34 enables the adjusting seat 34 to drive the feedback conductive contact 36 to slide on the feedback resistor rod 35, thereby gradually increasing the access resistance of the feedback resistor rod 35. Specifically, the greater the flamethrower intensity of the flamethrower 24, the faster the rotation speed of the adjusting motor 33 controlled by the central controller, the faster the feedback conductive contact 36 slides on the feedback resistor rod 35, and the faster the access resistance of the feedback resistor rod 35 increases, indicating that the fuel in the fuel tank 22 is consumed faster. The feedback conductive contact 36 and the feedback resistor rod 35 are connected in series to the power supply circuit of the force electromagnetic plate 46. When the fuel in the fuel tank 22 is consumed more, the access resistance of the feedback resistor rod 35 is larger, thereby making the power supply current of the force electromagnetic plate 46 smaller. Under the push-back action of the reset spring 44, the sliding plate 43 drives the compensation conductive contact 48 to slide on the compensation resistor rod 47. The larger the access resistance of the compensation resistor rod 47, the larger the resistance value signal fed back to the central controller. The central controller controls the brushless DC motor to work at a lower speed through the electronic speed regulator, which can not only save energy and extend the flight time of the drone, but also avoid the problem that excessive lift will make the drone more sensitive to changes in airflow and wind direction, affecting flight stability.

[0049] When the drone body 1 is flying, the rotor is rotating, and there is a loss of lubricating oil at its rotating connection, and the faster the rotation speed, the greater the loss of lubricating oil. During the flight of the drone, the central controller controls the servo motor 53 to act synchronously, and the servo motor 53 drives the transmission screw 52 to rotate. The threaded socket connection between the transmission screw 52 and the transmission seat 54 enables the transmission seat 54 to drive the pointer 55 to move. The central controller first controls the rotation speed of the servo motor 53 based on the difference in flight speed corresponding to the rotor speed. When the flight speed of the drone needs to be fast, the rotation speed of the rotor is also accelerated accordingly. The central controller controls the servo motor 53 to work at a higher rotation speed, so that the movement speed of the pointer 55 is accelerated, corresponding to the state of faster lubricating oil loss at this time. The compensating conductive contact 48 and the compensating resistor rod 47 are also connected in series to the power supply circuit of the servo motor 53. When the low temperature environment and flamethrower operation cause the UAV load to decrease and the access resistance of the compensation resistor rod 47 to change, the rotation speed of the servo motor 53 will also change synchronously. When the low temperature environment makes the access resistance of the compensation resistor rod 47 small and the rotor speed increases, the rotation speed of the servo motor 53 also increases, thereby improving the calculation speed of the lubricating oil loss state. When the UAV load is reduced and the rotor speed decreases during the flamethrower operation, the access resistance of the compensation resistor rod 47 is relatively larger, thereby making the rotation speed of the servo motor 53 slower. The lubricating oil loss during the flight of the UAV can be automatically calculated, so that the staff can arrange the maintenance time more reasonably, avoid unnecessary maintenance too early or too late, and can automatically adjust the calculation degree based on the rotor speed, so that the calculation of the lubricating oil loss is more accurate.

[0050] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principle of the present invention should be included in the protection scope of the present invention.

Claims

1. A power inspection drone, comprising a drone body (1), characterized in that: Also includes: A high-definition camera (7) is fixedly mounted on the top of the drone body (1); A temperature-sensitive variable resistance plate (8) mounted on the top of the high-definition camera (7); A flame-spraying foreign matter removal mechanism (2) is fixedly mounted on the bottom of the drone body (1); A load reduction feedback mechanism (3) is fixedly mounted in the flame-spraying foreign matter removal mechanism (2); The rotor speed self-regulating compensation mechanism (4) is fixedly mounted in the flame-spraying foreign matter removal mechanism (2), and the temperature-sensitive variable resistance plate (8) and the load reduction feedback mechanism (3) are both connected in series to the power supply circuit of the rotor speed self-regulating compensation mechanism (4); A lubrication state visual display mechanism (5) is fixedly mounted in the flame-spraying foreign matter removal mechanism (2) and is electrically connected to the rotor speed self-adjusting compensation mechanism (4); A PLC controller (9) is fixedly mounted in the flame-spraying foreign matter removal mechanism (2) and is electrically connected to the flame-spraying foreign matter removal mechanism (2), the load reduction feedback mechanism (3), the rotor speed self-adjusting compensation mechanism (4) and the lubrication state visual display mechanism (5); The rotor speed self-regulating compensation mechanism (4) comprises a compensation shell (41), the inner wall of the compensation shell (41) is fixedly connected to a plurality of guide slide bars (42) in parallel, the plurality of guide slide bars (42) are slidably sleeved with a same sliding plate (43) outside, a plurality of return springs (44) sleeved outside the guide slide bars (42) are fixedly connected to the opposite side of the sliding plate (43) and the compensation shell (41), a side of the sliding plate (43) away from the return spring (44) is fixedly connected to a force-bearing permanent magnetic plate (45), the inner wall of the compensation shell (41) is fixedly provided with a force-applying electromagnetic plate (46) arranged opposite to the force-bearing permanent magnetic plate (45), the inner wall of the compensation shell (41) is fixedly provided with a compensation resistor rod (47) arranged parallel to the guide slide bars (42), and one end of the sliding plate (43) is fixedly connected to a compensation conductive contact piece (48) in electrical contact with the compensation resistor rod (47).

2. The power inspection drone according to claim 1, characterized in that: The flame spraying foreign matter removal mechanism (2) comprises a fixed bracket (21) fixedly mounted on the bottom of the UAV body (1), a fuel tank (22) fixedly mounted in the fixed bracket (21), a rotating tube (23) rotatably sleeved on the bottom of the fixed bracket (21), the upper end of the rotating tube (23) fixedly connected to the fuel tank (22) via a rotating sealing joint, a flame spray gun (24) fixedly connected to the lower end of the rotating tube (23), a counterweight (25) fixedly connected to the rear end of the flame spray gun (24), an end of the counterweight (25) away from the flame spray gun (24) fixedly connected to a compensating fan (27) via a connecting bracket (26), a motor rotating assembly (28) for driving the rotating tube (23) to rotate, and a limiting mechanism (6) is mounted between the fixed bracket (21), the rotating tube (23) and the flame spray gun (24).

3. The power inspection drone according to claim 1, characterized in that: The load reduction feedback mechanism (3) comprises a feedback shell (31), the inner wall of the feedback shell (31) is rotatably connected to an adjusting screw (32), the outer wall of the feedback shell (31) is fixedly provided with an adjusting motor (33) for driving the adjusting screw (32) to rotate, the rod wall of the adjusting screw (32) is threadedly sleeved with an adjusting seat (34), the inner wall of the feedback shell (31) is fixedly provided with a feedback resistor rod (35) arranged parallel to the adjusting screw (32), and one end of the adjusting seat (34) is fixedly connected to a feedback conductive contact piece (36) in electrical contact with the feedback resistor rod (35).

4. The power inspection drone according to claim 1, characterized in that: The lubrication state visual display mechanism (5) comprises a display shell (51), a transmission screw (52) rotatably connected inside the display shell (51), a servo motor (53) for driving the transmission screw (52) to rotate is fixedly mounted on the outer wall of the display shell (51), a transmission seat (54) is threadedly sleeved on the rod wall of the transmission screw (52), a pointer (55) is fixedly connected to one side of the transmission seat (54), an end of the pointer (55) away from the transmission seat (54) passes through a strip-shaped through hole (56) provided on the side wall of the display shell (51) and extends out of the display shell (51), and a scale plate (57) corresponding to the position of the pointer (55) is fixedly mounted on the outer wall of the display shell (51).

5. The power inspection drone according to claim 2, characterized in that: The limiting mechanism (6) comprises a rotating cylinder (61) fixedly sleeved on the outside of the rotating tube (23); a limiting connection block (62) of an annular structure is fixedly connected to the lower end of the fixed bracket (21); the cross section of the limiting connection block (62) is a T-shaped structure; a limiting connection groove (63) matching and slidingly connected with the limiting connection block (62) is formed at the upper end of the rotating cylinder (61); and a plurality of supporting blocks (64) are fixedly connected between the lower end of the rotating cylinder (61) and the outer surface of the flamethrower (24).

6. The power inspection drone according to claim 3, characterized in that: A first limiting sliding block is fixedly connected to the outer wall of the adjustment seat (34), and a first limiting sliding groove matching and slidingly connected with the first limiting sliding block is formed on the inner wall of the feedback housing (31).

7. The power inspection drone according to claim 4, characterized in that: A second limiting sliding block is fixedly connected to the outer wall of the transmission seat (54), and a second limiting sliding groove matching and slidingly connected with the second limiting sliding block is provided on the inner wall of the display housing (51).

Images