A de-icing device for high-altitude power facilities utilizing liquid-stored air

Abstract

This utility model belongs to the field of high-altitude power facility maintenance technology, and particularly relates to a high-altitude power facility de-icing device utilizing liquid-stored air, comprising a drone, a self-stabilized liquid air tank, a self-heating system, and a jet system. The specific de-icing process is as follows: a drone carrying the liquid air tank is raised to a preset altitude using a remote monitoring system. The liquid air is then heated by the self-heating system to form high-temperature compressed air, which is accelerated by the jet system to form a supersonic pulsed airflow, thus removing ice from the surface of the power facility. This device avoids high-altitude operations for power maintenance personnel and solves the bottleneck of geographical and spatial limitations on power facility de-icing in northern winters and cold regions.

Description

Technical Field

[0001] This utility model belongs to the field of high-altitude power facility maintenance technology, and in particular relates to a de-icing device for high-altitude power facilities that utilizes liquid energy storage air. Background Technology

[0002] Ice accumulation on power lines can lead to transmission line faults, causing widespread power outages and other safety accidents. Ice accumulation on insulators reduces their insulation performance, leading to insulator breakdown or flashover, increasing the risk of power grid failures and resulting in significant economic losses. Therefore, timely de-icing measures in winter are crucial for ensuring the normal operation of the transmission system and for the protection of transmission lines. Currently, commonly used methods for line de-icing include thermal melting, mechanical de-icing, and laser de-icing.

[0003] Thermal de-icing methods include overcurrent de-icing, AC short-circuit current de-icing, and DC current de-icing. All these methods increase the current in the conductor, generating Joule heat in the high-voltage circuit and raising the surface temperature of the line, thus melting and removing the ice. However, this method is costly, places a heavy burden on the power grid system, and is ineffective for electrical equipment such as insulators. Mechanical de-icing methods include external force knocking de-icing, where workers knock the ice to break it off, posing personal safety hazards and being inefficient; pulley scraping de-icing, where ground operators pull pulleys along the line, bending the conductor to create stress and remove the ice, but this method is limited by geographical conditions and is not suitable for high-altitude or complex terrain areas; and robotic de-icing, which mainly uses different de-icing devices carried by robots, including striking, impact, and milling types. However, the working environment of these robots is complex and variable due to climate and terrain conditions, and requires a reliable motion mechanism design. Laser de-icing methods currently have two main approaches: one is to use continuous laser irradiation; the other is to use ultra-high power density pulsed lasers. However, these methods have low de-icing efficiency, high cost, and may damage electrical materials after laser irradiation.

[0004] To address the problem of icing damage to insulators on power transmission lines, patent CN202010258778.8, entitled "An Air Hot-Wire De-icing Cutting Gun," was published. This device uses hot airflow for de-icing, reducing damage to electrical equipment and eliminating the need for power outages. However, it requires a ground-based hot airflow supply and is limited by geographical conditions, making it unsuitable for high-altitude and complex terrain areas. Furthermore, it requires close-range manual operation, posing safety hazards. Air jet de-icing offers advantages such as low cost, significant effectiveness, and improved power grid reliability. Therefore, this paper proposes an air jet de-icing device using a liquid-energy-storage air-mounted UAV. Utility Model Content

[0005] The purpose of this invention is to provide a de-icing device for high-altitude power facilities that utilizes liquid-stored air, offering a low-cost solution that overcomes spatial limitations and improves grid reliability to address the problem of icing disasters on insulators in existing transmission lines.

[0006] To achieve the above objectives, the technical solution adopted by this utility model is as follows:

[0007] A de-icing device for high-altitude power facilities utilizing liquid energy storage air includes a self-regulating liquid air tank. The self-regulating liquid air tank is connected to a self-heating system via a high-pressure pipeline. The self-heating system is connected to a jet system via a high-pressure hose. The outlet of the self-regulating liquid air tank is equipped with an electromagnetic pressure reducing valve and a pressure sensor. A controller is electrically connected to the electromagnetic pressure reducing valve and the pressure sensor. The pressure sensor detects the gas pressure and adjusts the electromagnetic pressure reducing valve to stabilize the output pressure at approximately P1. The device also includes a base and a connecting bracket mounted on the base for connection to a drone. The self-regulating liquid air tank, the self-heating system, and the jet system are all fixedly installed on the base. The device also includes a controller electrically connected to the self-regulating liquid air tank, the self-heating system, and the jet system.

[0008] Furthermore, the self-regulating liquid air tank includes a first air tank and a second air tank. The outlet of the first air tank is equipped with a first pressure gauge, the outlet of the second air tank is equipped with a second pressure gauge, and the high-pressure pipeline at the outlet of the self-regulating liquid air tank is equipped with a first electromagnetic pressure reducing valve and a third pressure gauge.

[0009] Furthermore, the self-heating system includes multiple heating elements connected in series. Each heating element includes a cylindrical cavity and a connecting shaft located at the center of the cavity. Circular honeycomb heating plates are sequentially fitted onto the connecting shaft, forming a heating cavity between adjacent honeycomb heating plates. Each honeycomb heating plate has a heat source within its honeycomb holes. The heat source is shaped like a honeycomb reaction chamber, which increases the contact area between the stored air and the heat source, increases the heat exchange rate, and thus improves 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 in the impact and peeling effect of the air jet. The heat source is an electric heating wire or a chemical heat source composed of iron powder, activated carbon, and sodium chloride. After the liquid air enters the heater, the oxygen in it reacts with the iron powder to directly release heat and heat the stored air. After one de-icing task, the internal heat source can be disassembled and replaced. Using a disposable heating device can reduce the payload of the UAV. The high-pressure hose at the outlet of the self-heating system is equipped with a second electromagnetic pressure reducing valve, a fourth pressure gauge, and a temperature sensor.

[0010] Furthermore, the jet system includes an adjustable lifting pneumatic support, a movable straight pipe, a jet straight pipe, a self-excited oscillating nozzle, and a Laval nozzle. The adjustable lifting pneumatic support includes an adjustable front pneumatic support and an adjustable rear pneumatic support. The adjustment of the front and rear pneumatic supports relies on existing hydraulic adjustment. By adjusting the lifting height of the front and rear pneumatic supports, the elevation angle of the self-excited oscillating nozzle can be continuously adjusted within a range of ±45°. The movable straight pipe is mounted on the adjustable front and rear pneumatic supports, and a Laval nozzle is located at the rear end of the movable straight pipe. The nozzle is a self-excited oscillating nozzle with a flexible connection at the outlet of the jet straight pipe. 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 is integrally formed with the movable straight pipe, and the pressure regulating chamber is slidably sleeved on the outside of 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. During the jetting process of the pre-mounted self-excited oscillating nozzle, a periodic reaction force is generated. To achieve equipment stability, two non-reactive nozzles are installed at both ends of the straight pipe. The Laval nozzle and the self-excited oscillating nozzle are arranged 180° opposite each other, with the Laval nozzle outlet axis being collinear. This allows the Laval nozzle to provide a stable counter-thrust with a small air volume under different jet parameters to balance the impact force from the self-excited oscillating nozzle. The flexible connection between the jet straight pipe and the movable straight pipe further reduces the impact of periodic forces on the equipment, thereby maintaining the equipment's attitude and stability. The movable straight pipe has a jet straight pipe at its front end. Compressed gas enters the pressure regulating chamber in the movable straight pipe through a pressure reducing valve to form a pressure P. The compressed gas pushes the pressure regulating piston to move, which in turn moves the movable straight pipe. After the pressure P and the spring set in the pressure regulating chamber are balanced, the set extension length can be reached. The spring displacement x = PA / k can be calculated by the force F = PA of the compressed gas and the pressure regulating piston and the spring force F = kx. Controlling the value of P can precisely control the moving length of the movable straight pipe, thus realizing the control of jet parameters for high-altitude jet operations. After the equipment is started, the operator can control the drone to move horizontally to achieve linear moving cutting, further improving the jet de-icing efficiency.

[0011] Furthermore, it also includes a camera and an ultrasonic sensor mounted 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 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's control is existing technology, and it achieves automatic control by reading feedback data from various sensors to control the opening of the electromagnetic valves.

[0012] The advantages of this utility model are:

[0013] 1. This utility model overcomes the need for ground-based air supply pipelines and air compressors required for traditional air jet de-icing by using liquid energy storage air to mount drones. It realizes the self-generating function of the device, solves the geographical and spatial limitations of traditional air jet de-icing, and is applicable to high-altitude and complex terrain areas. Moreover, maintenance personnel can remotely monitor the de-icing work, achieving inherent safety.

[0014] 2. The air jet de-icing method used in this utility model is a non-contact de-icing method, which avoids the impact on equipment caused by traditional mechanical de-icing, reduces damage to electrical equipment, and allows maintenance personnel to stay away from electrical equipment without having to shut down the power for de-icing, greatly improving the reliability of the power grid.

[0015] 3. The jet system designed in this utility model can achieve all-round adjustment of jet parameters and self-balancing attitude of the device. The operator can adjust the jet pitch angle by controlling the height of the two front and rear air pressure supports, and adjust the movable straight pipe to determine the jet position, target distance and de-icing method. By selecting the optimal jet parameters and combining the impact force and heat conduction of the jet itself with different cutting methods, the optimal de-icing effect can be achieved by utilizing the coupling effect of the weight of the ice and the shear force and peeling force of the air jet, thus improving the de-icing efficiency. The Laval nozzle used provides continuous counter-thrust and periodic buffer for the attitude balance of the device, which can maintain the stability of the device itself. Attached Figure Description

[0016] Figure 1 This is a schematic diagram of the overall structure of this utility model.

[0017] Figure 2 This is a schematic diagram of the heating element in this utility model.

[0018] Figure 3 yes Figure 2 A sectional view.

[0019] Figure 4 This is a schematic diagram of the injection system.

[0020] In the diagram: 1. Self-heating and pressurizing liquid air tank; 2. First pressure gauge; 3. Second pressure gauge; 4. First electromagnetic pressure reducing valve; 5. Third pressure gauge; 6. Self-heating system; 7. Second electromagnetic pressure reducing valve; 8. Fourth pressure gauge; 9. Rear air pressure support; 10. Front air pressure support; 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 electromagnetic pressure reducing valve; 24. Air inlet pipe; 25. Air outlet pipe; 26. Pressure regulating chamber; 27. Pressure regulating piston; 28. Spring; 32. Ultrasonic sensor. Detailed Implementation

[0021] like Figure 1-4As shown, a de-icing device for high-altitude power facilities utilizing liquid energy storage air includes a self-stabilized liquid air tank 1. The self-stabilized liquid air tank is connected to a self-heating system 6 via a high-pressure pipeline. The self-heating system is connected to a jet system via a high-pressure hose. The outlet of the self-stabilized liquid air tank is equipped with an electromagnetic pressure reducing valve and a pressure sensor. It also includes a base and a connecting bracket 16 mounted on the base for connection to a drone. The self-stabilized liquid air tank, self-heating system, and jet system are all fixedly installed on the base. Furthermore, it includes a controller 18, which is electrically connected to the self-stabilized liquid air tank, self-heating system, and jet system. Electrically connected to an electromagnetic pressure reducing valve and a pressure sensor, the pressure sensor detects the gas pressure, and the electromagnetic pressure regulating valve stabilizes the output pressure at approximately P1. The self-regulating liquid air tank includes a first air tank and a second air tank. A first pressure gauge 2 is installed at the outlet of the first air tank, and a second pressure gauge 3 is installed at the outlet of the second air tank. A first electromagnetic pressure reducing valve 4 and a third pressure gauge 5 are installed on the high-pressure pipeline at the outlet of the self-regulating liquid air tank. The self-heating system includes multiple heating elements connected in series. Each heating element includes a cylindrical cavity, with a connecting shaft 22 located at the center of the cavity. Circular honeycomb heating plates 20 are sequentially sleeved on the connecting shaft. A heating cavity 21 is formed between adjacent honeycomb heating plates. Each honeycomb heating plate has a heat source inside its honeycomb holes. The heat source is shaped like a honeycomb reaction chamber, which increases the contact area between the stored air and the heat source, increases the heat exchange rate, and thus increases 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 air jet impact and peeling effect. The heat source is an electric heating wire or a chemical heat source composed of iron powder, activated carbon, and sodium chloride. After the liquid air enters the heater, the oxygen in it reacts with the iron powder to directly release heat to heat the stored air. After one de-icing task, the internal heat source can be disassembled and replaced. The use of a disposable heating device can reduce the payload of the UAV; the high-pressure hose at the outlet of the self-heating system is equipped 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. 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 relies on 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 tube 12 is mounted on an adjustable front air pressure support and an adjustable rear air pressure support. A Laval nozzle 15 is located at the rear end of the movable straight tube. A self-excited oscillation nozzle with a flexible connection is located at the outlet of the jet straight tube. The air inlet 11 of the movable straight tube is connected to the air outlet of the heating system. A pressure regulating chamber 26 and a pressure regulating piston 27 are located on the outer edge of the movable straight tube. The pressure regulating piston is integrally formed with the movable straight tube. The pressure regulating chamber is slidably sleeved outside the movable straight tube. A spring 28 is located between the pressure regulating piston and the pressure regulating chamber. An air inlet pipe 24 and an air outlet pipe 25 are located on the pressure regulating chamber. A third electromagnetic pressure reducing valve 23 is also located on the air inlet pipe. A self-excited oscillation nozzle is located at the front end. During the jetting process, periodic reaction forces are generated. To achieve equipment stability, two different nozzles are installed at both ends of the straight pipe. The outlet axis of the Laval nozzle is collinear with the axis of the self-excited oscillating nozzle, and they are arranged 180° opposite each other. In this way, the Laval nozzle can provide a stable counter-thrust with a small gas volume under different jetting parameters to balance the impact force brought by the self-excited oscillating nozzle. The flexible connection between the jetting straight pipe and the movable straight pipe can further reduce the impact of the periodic forces on the equipment, thereby achieving equipment attitude maintenance and stability. The front end of the movable straight pipe is equipped with a jetting straight pipe; compressed gas enters through the third electromagnetic pressure reducing valve. A pressure-regulating chamber within the movable straight tube generates a pressure P. The compressed gas pushes the pressure-regulating piston, which in turn moves the straight tube. Once the pressure P and the spring within the pressure-regulating chamber reach equilibrium, the set extension / retraction length is achieved. The spring displacement x = PA / k can be calculated using the force F = PA and the spring force F = kx. Controlling the magnitude of P precisely controls the length of the moving straight tube, thus enabling jet parameter control in high-altitude jet operations. After the equipment is started, the operator can control the drone to move horizontally, achieving linear moving cuts and further improving jet de-icing efficiency. This also includes... A camera 17 and an ultrasonic sensor 32 are mounted on the base. The ultrasonic sensor calculates the distance and angle between the nozzle and the target using sound wave detection. The operator can observe the image returned by the camera for real-time control. The controller is electrically connected to an adjustable lifting pneumatic support, a first electromagnetic pressure reducing valve, a second electromagnetic pressure reducing valve, a third electromagnetic pressure reducing valve, an electromagnetic pressure regulating valve, a first pressure gauge, a second pressure gauge, a third pressure gauge, a fourth pressure gauge, a temperature sensor, the camera, and the ultrasonic sensor. The controller's operation is based on existing technology; it achieves automatic control by reading feedback data from various sensors to control the opening of the electromagnetic valves.

[0022] In practical use, liquid energy-storing air is delivered from the self-stabilized liquid air tank 1 to the self-heating system 6 at a predetermined pressure P1. The self-stabilized liquid air tank 1 is equipped with a liquid energy storage chamber, an electromagnetic pressure regulating valve, and a gas chamber. The electromagnetic pressure regulating valve can be controlled to stabilize the gas pressure in the gas chamber 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 includes a replaceable honeycomb heating plate 20 and a rigid connecting shaft 22 connecting the heating plate. Air then enters the honeycomb heating plate 20 and the heating chamber 21, heating the air to T1. The second electromagnetic pressure reducing valve 7 controls the heated high-temperature compressed air to enter the movable straight pipe 12 at a pressure of P2, until it enters the self-excited oscillating nozzle, forming a supersonic pulse airflow that impacts the ice surface to break the ice. The jet system is as follows: Figure 4 The jet system shown has two nozzles with an included angle of 180°: a self-excited oscillating nozzle 14 and a Laval nozzle 15. The high thrust of the Laval nozzle is used to maintain the stability of the device's flight attitude. The jet system also includes a third electromagnetic pressure reducing valve 23, an inlet pipe 24, an 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, compressed gas is injected from the third electromagnetic pressure reducing valve 23 and the inlet pipe 24 at P3 into the pressure regulating chamber 26 to form a certain air pressure. After stabilizing with the spring 28, the gas reaches the designated position. The operator can adjust specific jet parameters, such as target distance, jet pressure, and incident angle, through the images and data returned by the equipped camera 17 and the ultrasonic sensor, controlling 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, and the movable straight pipe 12 on the control device. This forms an efficient ice-breaking scheme.

Claims

1. A high altitude power facility de-icing device utilizing liquid energy storage air, characterized by: The system includes a drone, a self-regulating liquid air tank, the self-regulating liquid air tank being connected to a self-heating system via a high-pressure pipeline, and the self-heating system being connected to a jet system via a high-pressure hose. The outlet of the self-regulating liquid air tank is equipped with an electromagnetic pressure reducing valve and a pressure sensor. The system also includes a base and a connecting bracket mounted on the base for connecting to the drone. The self-regulating liquid air tank, the self-heating system, and the jet system are all fixedly installed on the base. The system also includes a controller, which is electrically connected to the self-regulating liquid air tank, the self-heating system, and the jet system.

2. The high altitude power facility de-icing apparatus utilizing liquid energy storage air of claim 1, wherein: The self-stabilizing liquid air tank includes a first air tank and a second air tank. The outlet of the first air tank is equipped with a first pressure gauge, and the outlet of the second air tank is equipped with a second pressure gauge. The high-pressure pipeline at the outlet of the self-stabilizing liquid air tank is equipped with a first electromagnetic pressure reducing valve and a third pressure gauge.

3. The high altitude power facility de-icing apparatus utilizing liquid energy storage air of claim 2, wherein: The self-heating system includes multiple heating elements connected in series. Each heating element includes a cylindrical cavity and a connecting shaft located at the center of the cavity. Circular honeycomb heating plates are sequentially sleeved on the connecting shaft, and heating cavities are formed between adjacent honeycomb heating plates. Each honeycomb heating plate has a heat source inside its honeycomb holes. The heat source is an electric heating wire. The high-pressure hose at the outlet of the self-heating system is equipped with a second electromagnetic pressure reducing valve, a fourth pressure gauge, and a temperature sensor.

4. The high altitude power facility de-icing apparatus utilizing liquid energy storage air of claim 3, wherein: The jet system includes an adjustable lifting air pressure support, a movable straight pipe, a jet straight pipe, a self-excited oscillating 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 movable straight pipe is mounted on the adjustable front air pressure support and the adjustable rear air pressure support. A Laval nozzle is located at the rear end of the movable straight pipe, and a jet straight pipe is located at the front end of the movable straight pipe. A self-excited oscillating nozzle is located at the outlet of the jet straight pipe. 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 located on the outer edge of the movable straight pipe. The pressure regulating piston is integrally set with the movable straight pipe. The pressure regulating chamber is slidably sleeved on the outside of 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. A third electromagnetic pressure reducing valve is also provided on the air inlet pipe.

5. The high altitude power facility de-icing apparatus utilizing liquid energy storage air of claim 4, wherein: It also includes a camera and an ultrasonic sensor mounted on the base. 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 first pressure gauge, the second pressure gauge, the third pressure gauge, the fourth pressure gauge, the temperature sensor, the camera, and the ultrasonic sensor.

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