High-altitude electric power facility deicing device and method using liquid energy storage air

Abstract

The invention belongs to the technical field of high-altitude electric power facility maintenance, and particularly relates to a high-altitude electric power facility deicing device and method using liquid energy storage air, and the high-altitude electric power facility deicing device comprises an unmanned aerial vehicle, a self-pressure-stabilizing liquid air tank, a self-heating system and a jet system. The deicing process of the electric power facility comprises the specific steps that the unmanned aerial vehicle carrying the liquid air tank is lifted to a preset height through the remote monitoring system, liquid air forms high-temperature compressed air through the self-heating system, the high-temperature compressed air is accelerated through the jet system to form supersonic pulse airflow, and ice covering the surface of the electric power facility is removed. The device not only avoids high-altitude operation of power maintenance personnel, but also solves the bottleneck that deicing of power facilities in northern winter and alpine regions is limited by geographical and space factors.

Description

Technical Field

[0001] The present invention belongs to the technical field of high-altitude power facility maintenance, and in particular relates to a high-altitude power facility deicing device and method using liquid energy storage air. Background Art

[0002] Icing can cause transmission line failures, leading to widespread power outages and other safety incidents. Icing on insulators can degrade insulation performance, causing breakdown or flashover, increasing the risk of grid failures and resulting in significant economic losses. Therefore, timely de-icing measures in winter are crucial for protecting transmission lines to ensure the normal operation of the transmission system. Common de-icing methods currently include thermal de-icing, mechanical de-icing, and laser de-icing.

[0003] Thermal de-icing methods include overcurrent de-icing, AC short-circuit de-icing, and DC de-icing. All of these methods increase the current in the conductors, generating Joule heat in the high-voltage circuits and raising the surface temperature of the lines, thereby melting and removing the ice. However, this method is costly, places a heavy burden on the power grid system, and is ineffective against electrical equipment such as insulators. Mechanical de-icing methods include external force hammering, where workers hammer the ice to break it off, posing a safety hazard and inefficient. Pulley scraping de-icing involves ground operators pulling a pulley across the line, bending the conductors and generating stress to remove the ice. However, due to geographical constraints, it is not suitable for areas at high altitudes or with complex terrain. Robotic de-icing utilizes different de-icing devices carried by robots, including hammering, impact, and milling. However, the robot's working environment is complex and variable, influenced by climate, terrain, and other conditions, and requires a reliable motion mechanism design. Laser deicing method. Currently, there are two general directions for laser deicing. One is to use continuous laser irradiation; the other is to use ultra-high power density pulsed laser. However, this method has low deicing efficiency and high cost, and electrical materials may also be damaged after being irradiated by laser.

[0004] To provide a better solution to the problem of icing disasters on transmission lines and insulators, patent number CN202010258778.8 has been published, which discloses an "air hot wire deicing gun." Using hot air flow for deicing can reduce damage to electrical equipment, and the equipment does not need to be shut down for operation. However, the device requires a hot air flow supply from the ground, and is restricted by geographical conditions. It is not suitable for areas with high altitudes and complex terrain. It requires close human control of the equipment for deicing, which poses a personal safety hazard. Using air jets for deicing has the advantages of low cost, significant effect, and improved grid reliability. Therefore, this invention proposes a method and device for air jet deicing using liquid energy storage air mounted on a drone. Summary of the Invention

[0005] The purpose of the present invention is to provide a method and device for deicing high-altitude power facilities using liquid energy storage air, providing a solution with the advantages of low cost, breaking through space limitations, and improving power grid reliability to solve the problem of icing disasters on existing transmission lines and insulators.

[0006] In order to achieve the above object, the technical solution adopted by the present invention is: A deicing device for high-altitude power facilities using liquid energy storage air includes a self-stabilizing liquid air tank, which is connected to a self-heating system via a high-pressure pipeline, and the self-heating system is connected to a jet system via a high-pressure hose. An electromagnetic pressure reducing valve and an air pressure sensor are provided at the outlet of the self-stabilizing liquid air tank; a controller is electrically connected to the electromagnetic pressure reducing valve and the air pressure sensor, the air pressure sensor detects gas pressure, and adjusts the electromagnetic pressure stabilizing valve to stabilize the output pressure at around P1; the device also includes a base and a connecting bracket provided on the base and connected to a drone, the self-stabilizing liquid air tank, the self-heating system, and the jet system are all fixedly mounted on the base, and the device also includes a controller, which is electrically controlled and connected to the self-stabilizing liquid air tank, the self-heating system, and the jet system.

[0007] Furthermore, the self-stabilizing liquid air tank includes a first air tank and a second air tank, the outlet of the first air tank is provided with a first pressure gauge, the outlet of the second air tank is provided with a second pressure gauge, and the high-pressure pipeline at the outlet of the self-stabilizing liquid air tank is provided with a first electromagnetic pressure reducing valve and a third pressure gauge; the first air tank and the second air tank are both provided with a liquid energy storage chamber, an electromagnetic pressure stabilizing valve and an air chamber, and the liquid energy storage chamber and the air chamber are connected through the electromagnetic pressure stabilizing valve.

[0008] Furthermore, the self-heating system includes a plurality of heating elements connected in series, each heating element including a cylindrical cavity and a connecting shaft arranged in the center of the cavity, circular honeycomb heating plates are sequentially sleeved on the connecting shaft, and a heating cavity is formed between adjacent honeycomb heating plates, and a heating source is provided in the honeycomb hole of each honeycomb heating plate, and the heating source is in the shape of a honeycomb reaction chamber, which can increase the contact area between the energy storage air and the heating source, increase the heat exchange rate, and thereby increase the heat of the jet air, and can accelerate the local melting of the ice layer through heat conduction, reduce the adhesion strength of the ice, and assist the impact and peeling effect of the air jet. The heating source is an electric heating wire or a chemical heating source composed of iron powder, activated carbon and sodium chloride. After the liquid air enters the heater, the oxygen therein reacts with the iron powder to directly release heat to heat the energy storage air. After performing a de-icing task, the internal heating source can be disassembled and replaced, and the use of a disposable heating device can reduce the load of the UAV; the high-pressure hose at the outlet of the self-heating system is provided with a second electromagnetic pressure reducing valve, a fourth pressure gauge and a temperature sensor.

[0009] Furthermore, the jet system includes an adjustable lifting air pressure support, a movable straight pipe, a jet straight pipe, a self-excited oscillation nozzle and a Laval nozzle. The adjustable lifting air pressure support includes an adjustable front air pressure support and an adjustable rear air pressure support. The adjustment of the front and rear air pressure supports depends on the existing hydraulic adjustment. By adjusting the front and rear lifting heights of the front and rear air pressure supports, the pitch angle of the self-excited oscillation nozzle can be continuously adjusted within the range of ±45°; the movable straight pipe is provided on the adjustable front air pressure support and the adjustable rear air pressure support, and the rear end of the movable straight pipe is provided with a Laval nozzle. al nozzle, a self-excited oscillation nozzle is provided at the outlet of the jet straight pipe and is flexibly connected, the air inlet of the movable straight pipe is connected to the air outlet of the heating system, a pressure regulating chamber and a pressure regulating piston are provided on the outer edge of the movable straight pipe, the pressure regulating piston and the movable straight pipe are integrated, the pressure regulating chamber is slidingly sleeved outside the movable straight pipe, a spring is provided between the pressure regulating piston and the pressure regulating chamber, an air inlet pipe and an air outlet pipe are provided on the pressure regulating chamber, and a third electromagnetic pressure reducing valve is also provided on the air inlet pipe; a periodic reaction force will be generated during the jet process of the front self-excited oscillation nozzle, and two non- For the same nozzle, the Laval nozzle outlet axis is collinear with the self-excited oscillation nozzle axis and arranged 180° in the opposite direction. This allows the Laval nozzle to provide a stable reverse thrust at a relatively low gas volume under varying jet parameters, counteracting the impact of the self-excited oscillation nozzle. The flexible connection between the jet pipe and the movable pipe further minimizes the impact of periodic forces on the equipment, thereby maintaining the equipment's posture and stability. A jet pipe is positioned at the front end of the movable pipe. Compressed gas enters the pressure-regulating chamber in the movable pipe through a pressure reducing valve, generating air pressure P. This compressed gas pushes the pressure-regulating piston, which in turn drives the movable pipe. The set extension length is achieved when the air pressure P balances the force of the spring within the pressure-regulating chamber. The spring displacement, x = PA / k, can be calculated from the force F = PA applied by the compressed gas and the pressure-regulating piston and the spring force F = kx. Controlling P precisely controls the movable pipe's travel length, enabling jet parameter control during high-altitude jetting operations. After the equipment is activated, the operator can control the drone's horizontal motion to achieve linear cutting, further improving jet deicing efficiency.

[0010] Furthermore, it also includes a camera and an ultrasonic sensor arranged on the base. The ultrasonic sensor calculates the distance and angle between the nozzle and the target through sound wave detection. The operator can observe the image returned by the camera for real-time control. The controller is electrically connected to the adjustable lifting air pressure bracket, the first electromagnetic pressure reducing valve, the second electromagnetic pressure reducing valve, the third electromagnetic pressure reducing valve, the electromagnetic pressure stabilizing valve, the first pressure gauge, the second pressure gauge, the third pressure gauge, the fourth pressure gauge, the temperature sensor, the camera, and the ultrasonic sensor; the control of the controller belongs to the existing technology, and the opening of the electromagnetic valve is controlled by reading the feedback data of various sensors to achieve the effect of automatic control.

[0011] Another object of the present invention is to provide a deicing method comprising the following steps: S1. After connecting the device, check the air tightness of each valve and pipe connection, check whether the solenoid pressure reducing valve, air pressure sensor, air pressure bracket, movable straight pipe and camera can be used normally, and close all valves after confirming that they are correct; S2. Connect the drone to the mounting bracket and secure it securely. Then, fly the drone to the designated location. S3. Control the drone using the real-time camera feed, adjusting the front and rear pneumatic supports and the movable tube position to achieve the desired incident angle and target distance. S4. Click the start button on the controller to start the device. The device automatically runs and sets the pressure parameter to P2. When the pressure is greater than P2, the solenoid pressure reducing valve automatically reduces the pressure. When the pressure is lower than P2, the solenoid pressure reducing valve automatically increases the pressure. You can also manually increase the pressure parameter to P1 for difficult de-icing tasks. S5. The electromagnetic pressure reducing valve is used to control the introduction of stored energy air at a pressure of P2 into the jet system. The gas jet from the self-excited oscillating nozzle effectively removes ice gaps. The drone is controlled to achieve mobile cutting, and the ice blocks are finally dropped by their own weight.

[0012] The advantages of the present invention are: 1. By using liquid energy storage air mounted on a drone, this invention eliminates the ground-based air supply pipelines and air compressors required for traditional air jet deicing, achieving self-generating functionality. This overcomes the geographical and spatial limitations of traditional air jet deicing, making it suitable for use in areas with high altitudes and complex terrain. Maintenance personnel can remotely monitor deicing operations, achieving inherent safety. 2. The air jet de-icing method used in this invention is a non-contact de-icing method. It avoids the impact of traditional mechanical de-icing on equipment and reduces damage to power equipment. Maintenance personnel are far away from power equipment and do not need to shut down the power for de-icing, which greatly improves the reliability of the power grid. 3. The jet system designed in this invention enables comprehensive jet parameter adjustment and self-balancing of the device. Operators can adjust the jet pitch angle by controlling the height of the front and rear pneumatic supports and manipulate the movable straight pipe to determine the jet position, target distance, and de-icing method. By selecting the optimal jet parameters, combining the jet's impact force and heat conduction with different cutting methods, and leveraging the coupling effect of the ice's deadweight and the shear and peeling forces of the air jet, optimal de-icing is achieved, improving de-icing efficiency. The Laval nozzle provides continuous reverse thrust and periodic buffering for the device's posture balance, maintaining its stability. 4. The present invention adopts a self-heating replaceable device and selects iron powder as the reactant, which has high energy density and low cost. Since the air jet itself participates in the reaction, its fluidity, oxygen supply and honeycomb structure can be utilized to fully and quickly react. Activated carbon is used as a carrier and sodium chloride as a catalyst to further increase the heat release rate, quickly increase the temperature of the air jet itself, and enhance heat conduction to partially melt the ice layer. This not only improves the efficiency of de-icing, but also greatly reduces the endurance burden of the UAV, and can meet the needs of air heating and mission continuity. BRIEF DESCRIPTION OF THE DRAWINGS

[0013] Figure 1 It is a schematic diagram of the overall structure of the present invention.

[0014] Figure 2 It is a structural schematic diagram of the heating element in the present invention.

[0015] Figure 3 yes Figure 2 sectional view of .

[0016] Figure 4 It is a structural diagram of the injection system.

[0017] Figure 5 It is a diagram of the internal structure of the pressure tank in the present invention.

[0018] In the figure: 1. Self-temperature and pressure liquid air tank; 2. First pressure gauge; 3. Second pressure gauge; 4. First solenoid pressure reducing valve; 5. Third pressure gauge; 6. Self-heating system; 7. Second solenoid pressure reducing valve; 8. Fourth pressure gauge; 9. Rear air pressure bracket; 10. Front air pressure bracket; 11. Movable straight pipe air inlet; 12 Movable straight pipe; 13. Jet straight pipe; 14. Self-excited oscillation nozzle; 15. Laval nozzle; 16. Connecting bracket; 17. Camera; 18. Controller; 19. Base; 20. Honeycomb heating plate; 21. Connecting shaft; 22. Heating chamber; 23. Third solenoid pressure reducing valve; 24. Inlet pipe; 25. Outlet pipe; 26. Pressure regulating chamber; 27. Pressure regulating piston; 28. Spring; 29. ​​Liquid energy storage chamber; 30. Solenoid pressure regulating valve; 31. Air chamber; 32. Ultrasonic sensor. DETAILED DESCRIPTION

[0019] like Figure 1-5As shown, a high-altitude power facility deicing device using liquid energy storage air includes a self-stabilizing liquid air tank 1, which is connected to a self-heating system 6 through a high-pressure pipeline, and the self-heating system is connected to a jet system through a high-pressure hose. The outlet of the self-stabilizing liquid air tank is provided with an electromagnetic pressure reducing valve and an air pressure sensor; it also includes a base and a connecting bracket 16 arranged on the base and connected to a drone, the self-stabilizing liquid air tank, the self-heating system and the jet system are all fixedly mounted on the base, and also includes a controller 18, the controller is electrically controlled and connected to the self-stabilizing liquid air tank, the self-heating system and the jet system, and the controller 18 is electrically connected to the electromagnetic pressure reducing valve and the air pressure sensor The air pressure sensor detects the gas pressure and adjusts the electromagnetic pressure-stabilizing valve to stabilize the output pressure at around P1; the self-stabilizing liquid air tank includes a first air tank and a second air tank, the outlet of the first air tank is provided with a first pressure gauge 2, the outlet of the second air tank is provided with a second pressure gauge 3, and the high-pressure pipeline at the outlet of the self-stabilizing liquid air tank is provided with a first electromagnetic pressure reducing valve 4 and a third pressure gauge 5; the first air tank and the second air tank are both provided with a liquid energy storage chamber 29, an electromagnetic pressure-stabilizing valve 30 and an air chamber 31, and the liquid energy storage chamber and the air chamber are connected through the electromagnetic pressure-stabilizing valve; the self-heating system includes a plurality of heating elements connected in series, each heating element includes a cylindrical cavity, which is arranged at the center of the cavity The connecting shaft 22 is provided with circular honeycomb heating plates 20 in sequence, and a heating chamber 21 is formed between adjacent honeycomb heating plates. A heating source is provided in the honeycomb hole of each honeycomb heating plate. The heating source is in the shape of a honeycomb reaction chamber, which can increase the contact area between the energy storage air and the heating source, increase the heat exchange rate, and thus increase the heat of the jet air. It can accelerate the local melting of the ice layer through heat conduction, reduce the adhesion strength of the ice, and assist the impact and peeling effect of the air jet. The heating source is an electric heating wire or a chemical heating source composed of iron powder, activated carbon and sodium chloride. After the liquid air enters the heater, the oxygen in the liquid air reacts with the iron powder to directly release heat to heat the energy storage air, thereby performing a de-icing task. The internal heat source can be disassembled and replaced later, and the use of a disposable heating device can reduce the load of the drone; the high-pressure hose at the outlet of the self-heating system is provided with a second electromagnetic pressure reducing valve 7, a fourth pressure gauge 8 and a temperature sensor; the jet system includes an adjustable lifting air pressure support, a movable straight pipe 12, a jet straight pipe 13, a self-excited oscillation nozzle 14 and a Laval nozzle 15, and the adjustable lifting air pressure support includes an adjustable front air pressure support 10 and an adjustable rear air pressure support 9. The adjustment of the front and rear air pressure supports depends on the existing hydraulic adjustment. By adjusting the front and rear lifting heights of the front and rear air pressure supports, the pitch angle of the self-excited oscillation nozzle can be continuously adjusted within the range of ±45°;A movable straight pipe 12 is provided on the adjustable front air pressure support and the adjustable rear air pressure support, a Laval nozzle 15 is provided at the rear end of the movable straight pipe, a self-excited oscillation nozzle is provided at the outlet of the jet straight pipe and is flexibly connected, the air inlet 11 of the movable straight pipe is connected to the air outlet of the heating system, a pressure regulating chamber 26 and a pressure regulating piston 27 are provided on the outer edge of the movable straight pipe, the pressure regulating piston and the movable straight pipe are integrally arranged, the pressure regulating chamber is slidably sleeved outside the movable straight pipe, a spring 28 is provided between the pressure regulating piston and the pressure regulating chamber, an air inlet pipe 24 and an air outlet pipe 25 are provided on the pressure regulating chamber, and a third electromagnetic pressure reducing valve 23 is also provided on the air inlet pipe; in the front self-excited oscillation During the nozzle jet process, a periodic reaction force will be generated. In order to achieve the stability of the equipment, two different nozzles are installed at both ends of the straight pipe. The axis of the Laval nozzle outlet is collinear with the axis of the self-excited oscillation nozzle and is arranged 180 degrees in the opposite direction. In this way, the Laval nozzle can provide a stable reverse thrust at a smaller gas volume under different jet parameters to balance the impact force brought by the self-excited oscillation nozzle. The flexible connection between the jet straight pipe and the movable straight pipe can further reduce the impact of the periodic force on the equipment, thereby achieving the equipment posture maintenance and stability. A jet straight pipe is provided at the front end of the movable straight pipe; the compressed gas enters through the third solenoid pressure reducing valve. The pressure regulating chamber in the movable straight pipe forms an air pressure P, and the compressed gas pushes the pressure regulating piston to move, thereby driving the movable straight pipe to move. After the air pressure P and the spring set in the pressure regulating chamber form a force balance, the set telescopic length can be achieved. The displacement x=PA / k of the spring can be calculated by the action force F=PA of the compressed gas and the pressure regulating piston and the elastic force F=kx of the spring. By controlling the size of P, the moving length of the movable straight pipe can be accurately controlled, so that the jet parameter control of high-altitude jet operation can be realized. After the equipment is started, the operator can control the drone to move horizontally to achieve linear mobile cutting, further improving the efficiency of jet deicing; it also includes A camera 17 and ultrasonic sensor 32 are mounted on the base. The ultrasonic sensor calculates the distance and angle between the nozzle and the target through acoustic detection. The operator can observe the image returned by the camera for real-time control. The controller is electrically connected to the adjustable lift air pressure support, the first solenoid pressure reducing valve, the second solenoid pressure reducing valve, the third solenoid pressure reducing valve, the solenoid pressure regulating valve, the first pressure gauge, the second pressure gauge, the third pressure gauge, the fourth pressure gauge, the temperature sensor, the camera, and the ultrasonic sensor. The controller operates according to existing technology and automatically controls the opening of the solenoid valve by reading feedback data from various sensors.

[0020] When in use, the liquid energy storage air is delivered from the self-stabilizing liquid air tank 1 to the self-heating system 6 at a predetermined pressure P1. Figure 5As shown, the self-stabilizing liquid air tank 1 is equipped with a liquid energy storage chamber 29, an electromagnetic pressure regulating valve 30, and an air chamber 31. The electromagnetic pressure regulating valve 30 can be controlled to stabilize the gas pressure in the air chamber 31 at P1. The controller 18 controls the first electromagnetic pressure reducing valve 4 to stabilize the air at P1 by detecting the reading of the third pressure gauge 5. After entering the self-heating system 6, the air is heated. Figure 2 、 3 The self-heating system 6 shown is provided with a replaceable honeycomb heating plate 20 and a rigid connecting shaft 22 connecting the heating plates. Then, air enters the honeycomb heating plate 20 and the heating chamber 21, and the temperature of the air is heated to T1. The second electromagnetic pressure reducing valve 7 is controlled to allow the heated high-temperature compressed air to enter the movable straight pipe 12 at a pressure of P2 until it enters the self-excited oscillation nozzle to form a supersonic pulse airflow and impact the ice surface to break the ice. The jet system is as follows Figure 4 The jet system shown is provided with two self-excited oscillation nozzles 14 and Laval nozzles 15 with an angle of 180°. The large thrust characteristic of the Laval nozzle is used to maintain the stability of the flight attitude of the device. The jet system is also provided with a third electromagnetic pressure reducing valve 23, an air inlet pipe 24, an air outlet pipe 25, a pressure regulating chamber 26, a pressure regulating piston 27, and a spring 28. When adjusting the length of the movable straight pipe, the compressed gas is injected into the pressure regulating chamber 26 from the third electromagnetic pressure reducing valve 23 and the air inlet pipe 24 at P3 to form a certain air pressure and stabilize with the spring 28 to reach the specified position. The staff can adjust the specific jet parameters, such as the target distance, jet pressure and incident angle, on the second electromagnetic pressure reducing valve 7, the first electromagnetic pressure reducing valve 4, the rear air pressure support 9, the front air pressure support 10, the movable straight pipe 12, etc. on the control device through the images and data returned by the equipped camera 17 and the ultrasonic sensor to form an efficient ice breaking solution.

Claims

1. A deicing device for high-altitude power facilities using liquid energy-storage air, characterized by: It includes a self-stabilizing liquid air tank, which is connected to the self-heating system through a high-pressure pipeline, and the self-heating system is connected to the jet system through a high-pressure hose; it also includes a base and a connecting bracket arranged on the base and connected to the drone, the self-stabilizing liquid air tank, the self-heating system and the jet system are all fixedly installed on the base, and also includes a controller, which is electrically controlled and connected to the self-stabilizing liquid air tank, the self-heating system and the jet system; the self-stabilizing liquid air tank includes a first air tank and a second air tank, the outlet of the first air tank is provided with a first pressure gauge, the outlet of the second air tank is provided with a second pressure gauge, and the high-pressure pipeline of the self-stabilizing liquid air tank outlet is provided with a first electromagnetic pressure reducing valve and a third pressure gauge; the first air tank and the second air tank are both provided with a liquid energy storage chamber, an electromagnetic pressure stabilizing valve and an air chamber, and the liquid energy storage chamber and the air chamber are connected through the electromagnetic pressure stabilizing valve.

2. The high-altitude power facility deicing device using liquid energy-storage air as claimed in claim 1, characterized in that: The self-heating system includes multiple heating elements connected in series, each heating element includes a cylindrical cavity, a connecting shaft arranged in the center of the cavity, circular honeycomb heating plates are sequentially sleeved on the connecting shaft, and a heating cavity is formed between adjacent honeycomb heating plates. A heating source is provided in the honeycomb hole of each honeycomb heating plate, and the heating source is an electric heating wire or a chemical heating source composed of iron powder, activated carbon and sodium chloride. A second electromagnetic pressure reducing valve, a fourth pressure gauge and a temperature sensor are provided on the high-pressure hose at the outlet of the self-heating system.

3. The high-altitude power facility deicing device using liquid energy-storage air as claimed in claim 2, characterized in that: The jet system includes an adjustable lifting air pressure support, a movable straight pipe, a jet straight pipe, a self-excited oscillation nozzle and a Laval nozzle. The adjustable lifting air pressure support includes an adjustable front air pressure support and an adjustable rear air pressure support. The adjustable front air pressure support and the adjustable rear air pressure support are clamped with a movable straight pipe, the rear end of the movable straight pipe is provided with a Laval nozzle, the front end of the movable straight pipe is provided with a jet straight pipe, and the outlet of the jet straight pipe is provided with a self-excited oscillation nozzle. The air inlet of the movable straight pipe is connected with the air outlet of the heating system, the outer edge of the movable straight pipe is provided with a pressure regulating chamber and a pressure regulating piston, the pressure regulating piston and the movable straight pipe are integrated, the pressure regulating chamber is slidably sleeved outside the movable straight pipe, a spring is provided between the pressure regulating piston and the pressure regulating chamber, the pressure regulating chamber is provided with an air inlet pipe and an air outlet pipe, and the air inlet pipe is also provided with a third electromagnetic pressure reducing valve.

4. The high-altitude power facility deicing device using liquid energy-storage air as claimed in claim 3, characterized in that: It also includes a camera and an ultrasonic sensor arranged on the base, and the controller is electrically connected to the adjustable lifting air pressure bracket, the first solenoid pressure reducing valve, the second solenoid pressure reducing valve, the third solenoid pressure reducing valve, the first pressure gauge, the second pressure gauge, the third pressure gauge, the fourth pressure gauge, the temperature sensor, the camera, and the ultrasonic sensor.

5. The deicing method of the device according to any one of claims 1 to 4, characterized in that: The following steps are involved: S1. After connecting the device, check the air tightness of each valve and pipe connection, check whether the solenoid pressure reducing valve, air pressure sensor, air pressure bracket, movable straight pipe and camera can be used normally, and close all valves after confirming that they are correct; S2. Connect the drone to the mounting bracket and secure it securely. Then, fly the drone to the designated location. S3. Control the drone using the real-time camera feed, adjusting the front and rear pneumatic supports and the movable tube position to achieve the desired incident angle and target distance. S4. Click the start button on the controller to start the device. The device automatically runs and sets the pressure parameter to P2. When the pressure is greater than P2, the solenoid pressure reducing valve automatically reduces the pressure. When the pressure is lower than P2, the solenoid pressure reducing valve automatically increases the pressure. You can also manually increase the pressure parameter to P1 for difficult de-icing tasks. S5. The electromagnetic pressure reducing valve is used to control the introduction of stored energy air at a pressure of P2 into the jet system. The gas jet from the self-excited oscillating nozzle effectively removes ice gaps. The drone is controlled to achieve mobile cutting, and the ice blocks are finally dropped by their own weight.

Images