Modular deicing and anti-icing system and method with electric heating and lightning strike compatibility

Abstract

The application discloses a modular anti-icing and deicing system compatible with electric heating and lightning protection and an anti-icing and deicing method, relates to the technical field of aircraft anti-icing and deicing, and comprises an anti-icing and deicing controller and at least one modular anti-icing and deicing assembly; a temperature sensor is used for detecting the temperature of the modular anti-icing and deicing assembly; the temperature sensor and a flexible electric heating film are electrically connected with the anti-icing and deicing controller respectively; an outer protective skin, the flexible electric heating film and an insulating and heat-insulating layer are sequentially arranged from outside to inside; one end of a lightning conduction interface is connected with the outer protective skin; and the other end of the lightning conduction interface is used for being connected with a fuselage. The real-time temperature of the modular anti-icing and deicing assembly is sensed through the temperature sensor, the heating state of the modular anti-icing and deicing assembly is controlled, and the anti-icing or deicing of the surface of the aircraft skin is realized. The outer protective skin and the anti-icing and deicing controller both have lightning protection measures, and all-weather safe operation under thunderstorm weather is ensured.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of aircraft deicing, and in particular to a modular deicing system compatible with electric heating and lightning protection and a deicing method. BACKGROUND

[0002] Aircraft icing refers to the phenomenon of ice accumulation on the surface of an aircraft body when the aircraft is parked on the ground or is flying through clouds. Aircraft icing can occur on the wings, tail, air inlet leading edge and windshield, and can seriously damage the aerodynamic shape, reduce lift, increase drag, and damage the control stability. Severe icing can cause a crash. Traditional aircraft deicing technologies include mechanical deicing, liquid deicing and thermal deicing, among which the most widely used are thermal deicing technologies such as hot air deicing and electric heating deicing. However, the hot air deicing method has a high temperature and cannot be applied to composite skin, and the introduction of hot air can significantly reduce the performance of the engine, greatly limiting its application range; the traditional electric heating deicing method is mostly placed inside the air inlet or sensor, or inside the wing and tail skin. The former uses continuous heating to prevent ice accumulation through Joule heating, and the latter usually has a large area and high energy consumption, and uses intermittent heating to deice. However, the metal heating sheet and heating wire used in the traditional electric heating method have poor fatigue resistance and are prone to failure in flight vibration, resulting in high maintenance costs. The newly developed electric heating deicing coating (film) is generally directly sprayed on the outside of the skin, has better fatigue resistance, and has better heat transfer efficiency and response speed than the traditional built-in electric heating method; however, without an external protective plate, there is a risk of damage from sand and stone impact, and the coating spraying and maintenance process requires a long aircraft time. In addition, the electrical conductivity of the electric heating coating material and the electrode increases the risk of lightning strikes. SUMMARY

[0003] The purpose of the present application is to provide a modular deicing system compatible with electric heating and lightning protection and a deicing method to solve the problems of the prior art. The flexible electric heating film has fatigue resistance, the external protective skin enhances the impact resistance, and the external protective skin and the deicing controller both have lightning protection measures.

[0004] To achieve the above purpose, the present application provides the following solutions:

[0005] This invention provides a modular anti-icing and de-icing system compatible with electric heating and lightning protection, including an anti-icing and de-icing controller and at least one modular anti-icing and de-icing component. The modular anti-icing and de-icing component includes an outer protective skin, a flexible electric heating film, an insulating heat insulation layer, a temperature sensor, and a lightning current conduction interface. The temperature sensor is used to detect the temperature of the modular anti-icing and de-icing component. The temperature sensor and the flexible electric heating film are electrically connected to the anti-icing and de-icing controller, respectively. The outer protective skin, the flexible electric heating film, and the insulating heat insulation layer are arranged sequentially from the outside to the inside. One end of the lightning current conduction interface is connected to the outer protective skin, and the other end of the lightning current conduction interface is used to connect to the fuselage.

[0006] Preferably, the temperature sensor is located between the flexible electric heating film and the insulating heat insulation layer, or the temperature sensor is located between the flexible electric heating film and the outer protective skin.

[0007] Preferably, the anti-icing controller includes a device power interface, a communication interface, a sensor signal interface, and a load power supply interface. The device power interface is used to connect to the power supply device of the anti-icing controller, the communication interface is used to connect to the host computer, the sensor signal interface is used to connect to the temperature sensor, and the load power supply interface is used to connect to the flexible electric heating film.

[0008] Preferably, the temperature sensor is connected to the sensing signal interface via a sensing signal cable, the flexible electric heating film is connected to the load power supply interface via a load power supply cable, both the sensing signal interface and the load power supply interface are designed with lightning protection circuits, the sensing signal interface is provided with an optocoupler, and the load power supply interface is provided with a surge protector and / or a fuse.

[0009] Preferably, the flexible electric heating film includes a flexible insulating layer, a polymer-based conductive film, and at least two flexible electrodes. The flexible insulating layer is located between the outer protective skin and the insulating and heat-insulating layer. The polymer-based conductive film and the flexible electrodes are both located in the flexible insulating layer. The polymer-based conductive film and the flexible electrodes are connected. One end of a flexible electrode terminal passes through the flexible insulating layer and is connected to one of the flexible electrodes. The other end of the flexible electrode terminal passes through the insulating and heat-insulating layer and is electrically connected to the anti-icing and de-icing controller.

[0010] Preferably, the formula for calculating the resistance value R of the flexible electric heating film is as follows:

[0011] R = U 2 / (P d ×L×w)

[0012] Where U is the load supply voltage; P dThe design anti-icing power density is the heating power per unit area of ​​the flexible electric heating film; L is the length of the flexible electrode; and w is the spacing between adjacent flexible electrodes.

[0013] Preferably, the outer protective skin is made of metal; or, the outer protective skin comprises a composite material plate and a copper mesh, wherein the copper mesh is embedded in the composite material plate.

[0014] This invention also provides an anti-icing and de-icing method using the aforementioned modular anti-icing and de-icing system that is compatible with electric heating and lightning protection, comprising the following operating modes:

[0015] Working Mode 1: The temperature sensor detects the real-time temperature of the modular anti-icing component and transmits it to the anti-icing controller for logical judgment. The controller then controls the load power supply interface to output or not output load voltage, driving the modular anti-icing component to heat or not heat. Ultimately, the temperature of the modular anti-icing component is controlled at a certain stable target temperature or temperature range, thus achieving anti-icing of the outer protective skin surface.

[0016] Working Mode 2: The anti-icing controller uses a specific control law to control the output or non-output of load voltage at the load power supply interface, driving the modular anti-icing component to heat or not heat, so that the surface ice accumulation reaches a certain amount and is then removed by heating, ensuring that the surface ice accumulation does not exceed the upper limit of ice capacity.

[0017] Preferably, in the second working mode, the temperature sensor senses the real-time temperature of the modular anti-icing component and transmits it to the anti-icing controller for logical judgment, and adjusts the control law in real time.

[0018] The present invention achieves the following technical effects compared to the prior art:

[0019] This invention uses a temperature sensor to sense the real-time temperature of the modular anti-icing and de-icing assembly, which is then transmitted to the anti-icing and de-icing controller for logical judgment. The controller then controls the heating state of the modular anti-icing and de-icing assembly, ultimately maintaining its temperature at a stable target temperature or range, thus achieving anti-icing or de-icing of the aircraft skin surface. This invention uses modular anti-icing and de-icing components to heat the skin, offering advantages such as simple installation and maintenance, easy standardization and interchangeability. Installed on the outermost edge of the wing and tail, the heating directly acts on the icing interface, resulting in rapid thermal response, high heating efficiency, and energy-saving anti-icing. Both the outer protective skin and the anti-icing and de-icing controller of this invention have lightning protection measures, ensuring safe operation in all weather conditions, including thunderstorms. This invention is applicable to anti-icing and de-icing of various fixed-wing aircraft, including wings, tails, and even air intake lips, and can also be applied to helicopter rotors, wind turbine blades, etc. Attached Figure Description

[0020] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0021] Figure 1 This is a schematic diagram of the modular anti-icing and de-icing system compatible with electric heating and lightning protection according to the present invention;

[0022] Figure 2 This is a detailed structural diagram of the modular anti-icing and de-icing component of the present invention;

[0023] Figure 3 Details of the flexible electrode terminal structure of the present invention Figure 1 ;

[0024] Figure 4 Details of the flexible electrode terminal structure of the present invention Figure 2 ;

[0025] Figure 5 This is a schematic diagram of the lightning protection design of the anti-icing controller of the present invention;

[0026] Figure 6 This is a schematic diagram of the lightning current conduction interface of the modular anti-icing and de-icing assembly of the present invention. Figure 1 ;

[0027] Figure 7 This is a schematic diagram of the lightning current conduction interface of the modular anti-icing and de-icing assembly of the present invention. Figure 2 ;

[0028] Figure 8 This is a schematic diagram of the lightning current conduction interface of the modular anti-icing and de-icing assembly of the present invention. Figure 3 ;

[0029] Figure 9 This is a schematic diagram of the lightning current conduction interface of the modular anti-icing and de-icing assembly of the present invention. Figure 4 ;

[0030] Figure 10 This is an example of the installation structure of the multi-component parallel anti-icing system of the present invention in the wing, tail, and air intake;

[0031] Among them: 1-modular anti-icing and de-icing assembly, 11-outer protective skin, 12-flexible electric heating film, 121-flexible insulation layer, 122-polymer-based conductive film, 123-flexible electrode, 124-flexible electrode terminal, 13-insulation and heat insulation layer, 14-temperature sensor, 15-lightning current conduction interface.

[0032] 2-Anti-icing controller, 21-Equipment power interface, 22-Communication interface, 23-Sensor signal interface, 231-N-channel optocoupler, 241-Surge protector / fuse, 24-Load power supply interface;

[0033] 3-Load power supply cable;

[0034] 4-Sensor signal cable. Detailed Implementation

[0035] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0036] The purpose of this invention is to provide a modular anti-icing and de-icing system and method that is compatible with electric heating and lightning protection, so as to solve the problems existing in the prior art. The flexible electric heating film has fatigue resistance, the outer protective skin enhances the impact resistance, and both the outer protective skin and the anti-icing controller have lightning protection measures.

[0037] To make the above-mentioned objects, features and advantages of the present invention more apparent and understandable, the present invention will be further described in detail below with reference to the accompanying drawings and specific embodiments.

[0038] like Figures 1 to 10As shown: This embodiment provides a modular anti-icing and de-icing system compatible with electric heating and lightning protection, including an anti-icing and de-icing controller 2 and at least one modular anti-icing and de-icing component 1. The modular anti-icing and de-icing component 1 is directly installed on the outermost leading edge of the aircraft wing, tail, or air intake. The shape of the modular anti-icing and de-icing component 1 conforms to the shape of the installation location. The modular anti-icing and de-icing component 1 can be bolted to the fuselage. It is usually installed in a distributed manner with multiple components. The modular anti-icing and de-icing component 1 is used to replace the skin or part of the skin at the installation location. The modular anti-icing and de-icing component 1 includes an outer protective skin 11, a flexible electric heating film 12, an insulating heat insulation layer 13, a temperature sensor 14, and a lightning current conduction interface 15, arranged in the order of outer protective skin 11, flexible electric heating film 12, and insulating heat insulation layer 13 from the outside in. The internal fixing is an integrated buckle module, and the fixing method can be threaded / bolted connection, riveting, adhesive bonding, etc. The flexible electric heating film 12 and the outer protective skin 11 are tightly bonded with a thin layer of thermally conductive silicone grease to prevent cavitation from causing heat transfer loss. The temperature sensor 14 is used to detect the temperature of the modular anti-icing component 1 in real time. The temperature sensor 14 and the flexible electric heating film 12 are electrically connected to the anti-icing controller 2, which can be installed inside the aircraft fuselage. The outer protective skin 11, the flexible electric heating film 12 and the insulating heat insulation layer 13 are arranged sequentially from the outside to the inside. The lightning guide interface 15 is located at the mounting surface of the outer protective skin 11 and the wing, tail or air intake. One end of the lightning guide interface 15 is connected to the outer protective skin 11, and the other end of the lightning guide interface 15 is used to connect to the fuselage. In this embodiment, the temperature sensor 14 senses the real-time temperature of the modular anti-icing component 1, transmits it to the anti-icing controller 2 for logical judgment, and controls the heating state of the modular anti-icing component 1. Ultimately, the temperature of the modular anti-icing component 1 is controlled at a stable target temperature or temperature range, achieving anti-icing or de-icing of the aircraft skin surface. This embodiment uses the modular anti-icing component 1 to heat the skin, which has advantages such as simple installation and maintenance, easy standardization and interchangeability; and being installed on the outermost edge of the wing and tail, the heating directly acts on the icing interface, offering advantages such as rapid thermal response, high heating efficiency, and energy saving in anti-icing; both the outer protective skin 11 and the anti-icing controller 2 in this embodiment have lightning protection measures to ensure safe operation in all weather conditions during thunderstorms. This embodiment is applicable to anti-icing of various fixed-wing aircraft, including wings, tails, and even air intake lips, and can also be applied to anti-icing of helicopter rotors, wind turbine blades, etc.

[0039] Specifically, in this embodiment, the outer protective skin 11 is a thin plate with high strength, good impact resistance, good thermal conductivity, and lightning protection. Metal plates, such as aluminum alloy, stainless steel, or copper, are preferred, with a thickness not exceeding 2mm. Alternatively, composite material plates meeting the above performance requirements can be used, with a thickness not exceeding 1mm to minimize heat loss. A copper mesh must be embedded inside the composite material plate to ensure effective current conduction during lightning strikes. For the outer protective skin 11 made of metal materials, such as… Figure 6 As shown, the lightning current conduction interface 15 can directly conduct lightning current to the machine body by means of screw fastening, such as... Figure 7 As shown, the lightning current conduction interface 15 can directly conduct lightning current to the body via cable conduction; for the composite material outer protective skin 11, such as Figure 8 As shown, the copper mesh embedded in the composite material directly conducts the lightning current to the machine body through a screw-fastened current-conducting method, such as... Figure 9 As shown, the copper mesh embedded in the composite material directly conducts the lightning current to the machine body through cable current conduction.

[0040] In this embodiment, the temperature sensor 14 is located between the flexible electric heating film 12 and the insulating heat insulation layer 13, or the temperature sensor 14 is located between the flexible electric heating film 12 and the outer protective skin 11. The temperature sensor 14 and the flexible insulating layer 121 of the flexible heating film are tightly fixed with thermally conductive silicone grease.

[0041] In this embodiment, the flexible electric heating film 12 includes a flexible insulating layer 121, a polymer-based conductive film 122, and at least two flexible electrodes 123. The flexible insulating layer 121 is located between the outer protective skin 11 and the insulating and heat-insulating layer 13. The polymer-based conductive film 122 and the flexible electrodes 123 are both located within the flexible insulating layer 121 and are connected. One end of a flexible electrode terminal 124 passes through the flexible insulating layer 121 and is connected to a flexible electrode 123 by brazing, resistance welding, or other methods. Figure 3 As shown, the other end of the flexible electrode terminal 124 passes through the insulating and heat-insulating layer 13 and is connected to the load power supply cable 3 by bolt connection, as shown. Figure 4 As shown, the other end of the flexible electrode terminal 124 passes through the insulating and heat-insulating layer 13 and is connected to the load power supply cable 3 by crimping.

[0042] In this embodiment, the flexible electrode 123 of the flexible electric heating film 12 should be in close contact with the polymer-based conductive film 122 and the bottom end of the flexible electrode terminal 124 to ensure electrical continuity; the flexible insulating layer 121 should completely cover the polymer-based conductive film 122, the flexible electrode 123 and the bottom end of the terminal to ensure good insulation, and only expose the top end of the flexible electrode terminal 124 in a suitable position to connect the load power supply cable 3.

[0043] In this embodiment, the formula for calculating the resistance value R of the flexible electric heating film 12 is as follows:

[0044] R = U 2 / (P d ×L×w)

[0045] Where U is the load supply voltage; P d The designed anti-icing power density is the heating power per unit area of ​​the flexible electric heating film 12; L is the length of the flexible electrode 123; w is the spacing between adjacent flexible electrodes 123. Methods for adjusting the resistance value R of the flexible electric heating film 12 include adjusting the thickness of the polymer-based conductive film 122, the ratio of the length L of the flexible electrode 123 to the electrode spacing w, and the doping ratio of the conductive filler.

[0046] In this embodiment, the flexible electrode 123 can be made of thin copper foil, copper wire braided tape, silver-plated cloth, copper-plated cloth, highly conductive carbon fiber, sputtered metal and alloy layer polymer film, etc.; the polymer conductive film includes intrinsically conductive polymers such as polyacetylene, polypyrrole, polythiophene and polyaniline, and also includes composite polymer conductive materials formed by doping conductive fillers such as carbon nanotubes, graphite, graphene, carbon nanofibers, metal nanopowders, etc. into the flexible polymer; the flexible insulating layer 121 can be made of polymer materials with good insulation and flexibility such as polyimide, polyethylene, waterborne polyurethane, etc., and can also be reinforced by embedding thin glass fiber cloth, etc.; the flexible electrode terminal 124 is a copper post with a diameter of 2 to 10 mm.

[0047] In this embodiment, the insulating and heat-insulating layer 13 needs to be made of materials with good insulation performance, poor thermal conductivity, good heat insulation performance, and low thermal conductivity, such as glass fiber-based composite materials, porous materials, glass mats, and polymer films doped with hollow glass microspheres.

[0048] In this embodiment, the anti-icing controller 2 includes a power interface 21, a communication interface 22, a sensor signal interface 23, and a load power supply interface 24. The power interface 21 is used to connect to the power supply equipment of the anti-icing controller 2, which can be 28V DC or other airborne power supplies. The communication interface 22 is used to connect to the host computer and communicate with the aircraft for control commands, temperature data, status information, fault information, etc., which can be RS422 / 485 / 232 or Ethernet. The sensor signal interface 23 is used to connect to the temperature sensor 14 and receive the temperature data from the temperature sensor 14. The load power supply interface 24 is used to connect to the flexible electric heating film 12 and provide load power from the anti-icing controller 2 to the modular anti-icing assembly 1. It can be 28V, 110V, 115V, 270V, 540V, 690V or other airborne DC / AC power supplies or 60V, 72V, 120V or other customized DC / AC power supplies. The power interface 21, communication interface 22, sensor signal interface 23, and load power supply interface 24 of the equipment should be properly shielded and waterproofed.

[0049] In this embodiment, both the sensor signal interface 23 and the load power supply interface 24 are designed with lightning protection circuits to ensure complete isolation between the lightning current and the internal circuit of the anti-icing controller 2 and other airborne equipment when the modular anti-icing component 1 is struck by lightning. The sensor signal interface 23 uses N-channel optocouplers 231 to achieve opto-isolation of the temperature sensor 14 signal. The load power supply interface 24 is equipped with a surge protector 241 and / or a fuse 241 to prevent the lightning current from damaging the equipment when struck by lightning.

[0050] In this embodiment, the temperature sensor 14 is connected to the sensing signal interface 23 via the sensing signal cable 4, and the flexible electric heating film 12 is connected to the load power supply interface 24 via the load power supply cable 3. The load power supply cable 3 includes the connection point, wiring harness, shielding layer, and connector between the electrodes of the flexible electric heating film 12 and the load power supply interface 24 of the anti-icing controller 2. The connection point can be selected by welding, riveting, or terminal block connection according to actual requirements. The wiring harness is selected according to the required conductive cross-sectional area based on the current passing through it, and whether or not to set a shielding layer is selected according to actual needs. The connector should be a socket (or plug) corresponding to the plug (or socket) of the load power supply interface 24 of the anti-icing controller 2 to ensure proper shielding and waterproofing.

[0051] In this embodiment, the sensing signal cable 4 includes the connection point, wiring harness, shielding layer, and connectors between the temperature sensor 14 and the sensing signal interface 23 of the anti-icing controller 2. The connection point can be selected by welding, riveting, or post connection according to actual requirements, and the connection point should be shielded as much as possible, such as by using mutually insulating copper foil tape. The wiring harness generally uses a conductive cross-sectional area of ​​0.5 mm². 2Shielded wires of 2 and below are acceptable; connectors should be selected with sockets (or plugs) corresponding to the plugs (or sockets) of the sensor signal interface 23 of the anti-icing controller 2, and appropriate shielding and waterproofing treatment should be ensured.

[0052] This embodiment of a modular anti-icing and de-icing system compatible with electric heating and lightning protection uses a flexible electric heating film 12 with excellent fatigue resistance as the heating element. The flexible electric heating film 12 is encapsulated, with its outer side tightly bonded to the outer protective skin 11, improving heat transfer efficiency and enhancing impact resistance. The inner side of the flexible electric heating film 12 is bonded to an insulating and heat-insulating layer 13 to reduce heat loss. The modular structure has advantages such as simple installation and maintenance, and easy standardization and interchangeability. The real-time temperature of the modular anti-icing component 1 is sensed by the temperature sensor 14 and transmitted to the anti-icing and de-icing controller 2 for logical judgment. The controller then controls the heating state of the modular anti-icing and de-icing component 1, ultimately controlling its temperature to a stable target temperature or temperature range, thus achieving anti-icing or de-icing of the aircraft wing, tail, and leading edge skin surfaces. Simultaneously, both the outer protective skin 11 and the anti-icing and de-icing controller 2 in this embodiment have lightning protection measures to ensure safe operation in all weather conditions during thunderstorms. This embodiment is applicable to de-icing of various fixed-wing aircraft such as wings, tail fins, and even air intake lips, and can also be applied to de-icing of helicopter rotors, wind turbine blades, etc.

[0053] Example 2

[0054] This embodiment provides an anti-icing and de-icing method using the modular anti-icing and de-icing system compatible with electric heating and lightning protection as described in Embodiment 1, including the following operating modes:

[0055] Working mode 1: Temperature sensor 14 senses the real-time temperature of modular anti-icing component 1 and transmits it to anti-icing controller 2 for logical judgment (such as judging whether the target temperature value or range of heating has been reached). Then, it controls the load power supply interface 24 to output or not output load voltage, driving the modular anti-icing component 1 to heat or not heat. Finally, the temperature of the modular anti-icing component 1 is controlled at a certain stable target temperature or temperature range (above the freezing point), so as to achieve anti-icing on the surface of the outer protective skin 11.

[0056] Operating Mode 2: The anti-icing controller 2 uses a specific control law (such as continuous heating for 20 seconds, stopping heating for 40 seconds, etc.) to control the load power supply interface 24 to output or not output load voltage, driving the modular anti-icing component 1 to heat or not heat, so that the surface ice accumulation reaches a certain amount and is then removed by heating, ensuring that the surface ice accumulation does not exceed the ice capacity limit. The temperature sensor 14 senses the real-time temperature of the modular anti-icing component 1. It may not participate in the logic judgment of the anti-icing controller 2, or it may transmit the temperature to the anti-icing controller 2 for logic judgment, adjusting the control law in real time (such as adjusting the continuous heating / stop heating time from 20 seconds / 40 seconds to 30 seconds / 30 seconds, etc.).

[0057] This specification uses specific examples to illustrate the principles and implementation methods of the present invention. The descriptions of the above embodiments are only for the purpose of helping to understand the method and core ideas of the present invention. Furthermore, those skilled in the art will recognize that, based on the ideas of the present invention, there will be changes in the specific implementation methods and application scope. Therefore, the content of this specification should not be construed as a limitation of the present invention.

Claims

1. A modular anti-icing and de-icing system compatible with electric heating and lightning protection, characterized in that: The system includes an anti-icing controller and at least one modular anti-icing component. The modular anti-icing component includes an outer protective skin, a flexible electric heating film, an insulating heat insulation layer, a temperature sensor, and a lightning conductor interface. The temperature sensor is used to detect the temperature of the modular anti-icing component. The temperature sensor and the flexible electric heating film are electrically connected to the anti-icing controller. The outer protective skin, the flexible electric heating film, and the insulating heat insulation layer are arranged sequentially from the outside to the inside. The lightning conductor interface is located at the mounting surface of the outer protective skin and the wing, tail, or air intake. One end of the lightning conductor interface is connected to the outer protective skin, and the other end is used to connect to the fuselage. The flexible electric heating film includes a flexible insulating layer, a polymer-based conductive film, and at least two flexible electrodes. The flexible insulating layer is located between the outer protective skin and the insulating and heat-insulating layer. The polymer-based conductive film and the flexible electrodes are both located in the flexible insulating layer. The polymer-based conductive film and the flexible electrodes are connected. One end of a flexible electrode terminal passes through the flexible insulating layer and is connected to the flexible electrode. The other end of the flexible electrode terminal passes through the insulating and heat-insulating layer and is electrically connected to the anti-icing and de-icing controller. The formula for calculating the resistance value R of the flexible electric heating film is as follows: R=U 2 / (P d ×L×w) Where U is the load supply voltage; P d The designed anti-icing power density is the heating power per unit area of ​​the flexible electric heating film; L is the length of the flexible electrode; w is the spacing between adjacent flexible electrodes. The outer protective skin is made of metal; or, the outer protective skin comprises a composite material plate and a copper mesh, wherein the copper mesh is embedded in the composite material plate.

2. The modular anti-icing and de-icing system compatible with electric heating and lightning protection according to claim 1, characterized in that: The temperature sensor is located between the flexible electric heating film and the insulating heat insulation layer, or the temperature sensor is located between the flexible electric heating film and the outer protective skin.

3. The modular anti-icing and de-icing system compatible with electric heating and lightning protection according to claim 1, characterized in that: The anti-icing controller includes a power interface, a communication interface, a sensor signal interface, and a load power supply interface. The power interface is used to connect to the power supply equipment of the anti-icing controller. The communication interface is used to connect to the host computer. The sensor signal interface is used to connect to the temperature sensor. The load power supply interface is used to connect to the flexible electric heating film.

4. The modular anti-icing and de-icing system compatible with electric heating and lightning protection according to claim 3, characterized in that: The temperature sensor is connected to the sensing signal interface via a sensing signal cable, and the flexible electric heating film is connected to the load power supply interface via a load power supply cable. Both the sensing signal interface and the load power supply interface are designed with lightning protection circuits. The sensing signal interface is equipped with an optocoupler, and the load power supply interface is equipped with a surge protector and / or a fuse.

5. A method for de-icing using a modular de-icing system compatible with electric heating and lightning protection as described in any one of claims 1-4: characterized in that: The following working modes are included: Working Mode 1: The temperature sensor detects the real-time temperature of the modular anti-icing component and transmits it to the anti-icing controller for logical judgment. The controller then controls the load power supply interface to output or not output load voltage, driving the modular anti-icing component to heat or not heat. Ultimately, the temperature of the modular anti-icing component is controlled at a certain stable target temperature or temperature range, thus achieving anti-icing of the outer protective skin surface. Working Mode 2: The anti-icing controller uses a specific control law to control the output or non-output of load voltage at the load power supply interface, driving the modular anti-icing component to heat or not heat, so that the surface ice accumulation reaches a certain amount and is then removed by heating, ensuring that the surface ice accumulation does not exceed the upper limit of ice capacity.

6. The anti-icing and de-icing method according to claim 5, characterized in that: In the second working mode, the temperature sensor detects the real-time temperature of the modular anti-icing component and transmits it to the anti-icing controller for logical judgment, adjusting the control law in real time.

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