Aircraft wing anti-icing and deicing PID temperature control device, temperature control method and aircraft

Abstract

The invention discloses an aircraft wing anti-icing and de-icing PID temperature control device and method and an aircraft, and belongs to the technical field of industrial equipment de-icing equipment.The aircraft wing anti-icing and de-icing PID temperature control device comprises a heating module, a temperature collecting module, an on-off module and a PID controller, the surface of an aircraft body structure is divided into a plurality of independent areas which at least comprise a windward area and a leeward area, the windward area and the leeward area are each provided with a heating module, the PID controller is electrically connected with the temperature collecting module and the on-off module, the temperature collecting module can measure the temperature of the windward area and the temperature of the leeward area and transmit temperature signals to the PID controller, and the PID controller can control on-off of the on-off module. According to the invention, the heating zone can be controlled according to the temperature difference between the windward side and the leeward side of the machine body structure, the heating and cooling period does not need to be manually set, automatic response can be carried out along with the environment change, and the electric energy loss caused by the excessive heating of the leeward side of the machine body structure is saved.

Description

Technical Field

[0001] The present invention relates to the technical field of industrial equipment deicing equipment, and in particular to an aircraft wing anti-icing PID temperature control device, a temperature control method and an aircraft. Background Art

[0002] Aircraft wing icing is a significant threat to aviation safety, especially in cold climates or during high-altitude cruising. Ice accumulation on the wing surface can impair aerodynamic performance, leading to reduced lift, increased drag, and even loss of control. Traditional anti-icing technologies primarily include hot air bleed systems and electric heating systems, but these systems suffer from the following limitations: First, high energy consumption: Traditional electric heating systems employ continuous or periodic large-area heating, accounting for 3% to 5% of the aircraft's total energy consumption (e.g., the electric heating power of a Boeing 737 reaches 20 to 30 kW). Second, response lag: Fixed heating modes cannot dynamically adapt to varying icing rates, resulting in overheating (wasted energy) or underheating (incomplete deicing). Third, a lack of zone control: The degree of icing on the windward and leeward sides of a wing varies significantly, but existing systems often employ a uniform heating strategy, resulting in low efficiency. Therefore, there is an urgent need for an aircraft wing anti-icing device that can switch heating zones based on the temperature difference between the windward and leeward sides for on-demand heating, thereby reducing energy loss. Summary of the Invention

[0003] The purpose of the present invention is to provide an aircraft wing anti-icing PID temperature control device, a temperature control method and an aircraft to solve the problems existing in the above-mentioned prior art. The device can dynamically respond to different icing environments according to the difference between the actual temperature and the target temperature, maintain the surface temperature above the freezing point to prevent icing, and realize electric heating deicing of the heated wing surface in the case of existing ice. The electric heating efficiency is high, and the device can switch the heating zone according to the temperature difference between the windward side and the leeward side for on-demand heating. Compared with a single large-area heating method, the energy loss is greatly reduced.

[0004] To achieve the above object, the present invention provides the following solutions:

[0005] The present invention provides an aircraft wing anti-icing PID temperature control device, comprising: a heating module, a temperature acquisition module, an on-off module and a PID controller. The surface of an aircraft body structure is divided into multiple independent areas. The aircraft body structure is a structure on an aircraft wing that requires anti-icing. The multiple independent areas include at least a windward area and a leeward area. The windward area and the leeward area are respectively provided with the heating module and the temperature acquisition module. The PID controller is electrically connected to the temperature acquisition module and the on-off module respectively. The temperature acquisition module can respectively measure the temperature of the windward area and the leeward area and transmit the temperature signal to the PID controller. The PID controller can control the on-off of the on-off module to control whether the heating module in the windward area and the heating module in the leeward area are heated.

[0006] Preferably, the heating module is an anti-icing electric heating film, which includes a hydrophobic layer, an electric heating layer, an insulating layer and a flexible substrate arranged in sequence from top to bottom. The hydrophobic layer is used for anti-icing and ice-repelling. The electric heating layer is electrically connected to the on-off module. The on-off module is used to control the heating and on-off of the electric heating layer. The insulating layer is used to insulate and insulate the electric heating layer and the body structure. The flexible substrate is used to adhere to the body structure.

[0007] Preferably, the electric heating layer is connected to a positive electrode and a negative electrode, the positive electrode and the negative electrode are both copper foil electrodes, and the copper foil electrodes are connected to the on-off module.

[0008] Preferably, the on-off module is a solid-state relay, which includes a plurality of switches for controlling the on-off of heating modules in different independent areas of the body structure.

[0009] Preferably, the solid-state relay includes a first switch, a second switch and a third switch, and the body structure is divided into a windward area, a first leeward area and a second leeward area. The first switch, the windward area, the first leeward area, the second leeward area are connected in series with the power supply, the first leeward area is connected in parallel with the second switch, and the second leeward area is connected in parallel with the third switch.

[0010] Preferably, the temperature acquisition module includes a thermocouple, and the thermocouple is located between the heating module and the body structure.

[0011] Preferably, the PID controller includes a host computer and a slave computer. The host computer is equipped with an anti-icing temperature control system with functions of human-computer interaction interface, temperature monitoring, temperature warning and data storage. The slave computer converts the control signal transmitted by the host computer into a specific execution instruction for controlling the on and off of multiple switches of the solid-state relay.

[0012] Preferably, the hydrophobic layer is a low surface energy resin-based polymer coating material, the electric heating layer is a resin-based polymer coating material made of conductive electric heating filler, the thermal insulation layer is a resin-based polymer coating material made of thermal insulation filler, and the flexible substrate is a flexible polymer film with adhesive backing.

[0013] The present invention also provides an aircraft wing anti-icing PID temperature control method, which divides the fuselage structure into at least one windward area and at least one leeward area according to different convective heat exchange conditions of the fuselage structure. When the actual temperature difference between the windward area and the leeward area measured by the temperature acquisition module is greater than the set temperature tolerance, the heating module corresponding to the windward area is turned on to heat the windward area alone. When the actual temperature difference between the leeward area and the windward area measured by the temperature acquisition module is less than the set temperature tolerance, the heating module corresponding to the windward area is turned on to heat the windward area, and at the same time, the heating module corresponding to the leeward area is turned on to heat the leeward area.

[0014] The present invention also provides an aircraft, characterized in that it comprises a wing body, and the aircraft wing anti-icing PID temperature control device is provided on the wing body.

[0015] Compared with the prior art, the present invention has achieved the following technical effects:

[0016] The present invention divides the surface of the body structure into multiple independent areas, including at least a windward area and a leeward area. Each independent area is respectively provided with a heating module. The temperature of the windward area and the leeward area is respectively measured by a temperature acquisition module, and the temperature signal is transmitted to a PID controller. The PID controller can control whether the heating modules in the windward area and the heating modules in the leeward area are heated. The present invention can control the heating partition according to the temperature difference between the windward side and the leeward side of the body structure. There is no need to manually set the heating and cooling cycles. It can automatically respond to environmental changes, saving energy loss caused by excessive heating of the leeward side of the body structure. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the following briefly introduces the drawings required for use in the embodiments. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying any creative work.

[0018] Figure 1 Schematic diagram of the application structure of the anti-icing electric heating film in an embodiment of the present invention;

[0019] Figure 2 Schematic diagram of the functional structural layers of the anti-icing and de-icing electrothermal film in an embodiment of the present invention;

[0020] Figure 3 This is a system block diagram of an anti-icing PID temperature control device according to an embodiment of the present invention;

[0021] Figure 4 This is a circuit diagram of a zoned heating control strategy according to an embodiment of the present invention;

[0022] Figure 5 The temperature changes of each area of ​​the wing in the embodiment of the present invention without using the zone heating strategy;

[0023] Figure 6 The temperature changes in each area of ​​the wing using the zoned heating strategy in the embodiment of the present invention.

[0024] Among them, 1. Anti-icing electric heating film; 2. Copper foil electrode; 3. Body structure; 4. Thermocouple; 5. Hydrophobic layer; 6. Electric heating layer; 7. Insulation layer; 8. Flexible substrate; 9. First switch; 10. Second switch; 11. Third switch; 12. Windward area; 13. First leeward area; 14. Second leeward area. DETAILED DESCRIPTION

[0025] The following will clearly and completely describe the technical solutions in the embodiments of the present invention in conjunction with the accompanying drawings. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making creative efforts are within the scope of protection of the present invention.

[0026] The purpose of the present invention is to provide an aircraft wing anti-icing PID temperature control device, a temperature control method and an aircraft to solve the problems existing in the above-mentioned prior art. The device can dynamically respond to different icing environments according to the difference between the actual temperature and the target temperature, maintain the surface temperature above the freezing point to prevent icing, and realize electric heating deicing of the heated wing surface in the case of existing ice. The electric heating efficiency is high, and the device can switch the heating zone according to the temperature difference between the windward side and the leeward side for on-demand heating. Compared with a single large-area heating method, the energy loss is greatly reduced.

[0027] In order to make the above-mentioned objects, features and advantages of the present invention more obvious and easy to understand, the present invention is further described in detail below with reference to the accompanying drawings and specific embodiments.

[0028] like Figures 1 to 6As shown, the present invention provides an aircraft wing anti-icing PID temperature control device, including: a heating module, a temperature acquisition module, an on-off module and a PID controller. The surface of the fuselage structure 3 is divided into multiple independent areas. The fuselage structure 3 is a structure on the aircraft wing that requires anti-icing. The multiple independent areas include at least a windward area 12 and a leeward area. The windward area 12 and the leeward area are respectively provided with a heating module and a temperature acquisition module. The PID controller is electrically connected to the temperature acquisition module and the on-off module respectively. The temperature acquisition module can measure the temperature of the windward area 12 and the leeward area respectively, and transmit the temperature signal to the PID controller. The PID controller can control the on-off of the on-off module to control whether the heating module in the windward area 12 and the heating module in the leeward area are heated.

[0029] It is to be understood that the “anti-icing and de-icing” mentioned in this application refers to “anti-icing and de-icing”.

[0030] The present invention divides the surface of the body structure 3 into multiple independent areas, including at least a windward area 12 and a leeward area. Each independent area is respectively provided with a heating module. The temperature of the windward area 12 and the leeward area is respectively measured by a temperature acquisition module, and the temperature signal is transmitted to a PID controller. The PID controller can control whether the heating module in the windward area 12 and the heating module in the leeward area are heated. The present invention can control the heating partition according to the temperature difference between the windward side and the leeward side of the body structure 3. There is no need to manually set the heating and cooling cycles. It can automatically respond to environmental changes, saving energy loss caused by excessive heating of the leeward side of the body structure 3.

[0031] Furthermore, the fuselage structure 3 is a wing leading edge type structure that requires anti-icing operations.

[0032] Furthermore, each independent area is covered by a heating module, and the heating module completely covers the entire area of ​​each independent area.

[0033] As a preferred embodiment, the heating module is an anti-icing electric heating film 1, which includes a hydrophobic layer 5, an electric heating layer 6, an insulating layer 7 and a flexible substrate 8 arranged in sequence from top to bottom. The hydrophobic layer 5 is used for anti-icing and ice-repelling. The electric heating layer 6 is electrically connected to the on-off module. The on-off module is used to control the heating and on-off of the electric heating layer 6. The insulating layer 7 is used to insulate and insulate the electric heating layer 6 and the body structure 3. The flexible substrate 8 is used to adhere to the body structure 3. The present invention uses an anti-icing electric heating film 1 to be directly applied to the surface of the body structure 3 for heating. The hydrophobic properties of the hydrophobic layer 5 on the surface of the anti-icing electric heating film 1 can effectively reduce the ice adhesion strength. The insulating layer 7 of the bottom layer can induce heat to be conducted toward the surface, and can achieve efficient utilization of electrical energy in the anti-icing process with lower energy consumption.

[0034] Furthermore, the heating module is a heating wire embedded in multiple independent areas of the body structure 3 in the form of a serpentine loop or a grid array. The heating wire can be a metal heating wire of nickel-chromium alloy or iron-chromium-aluminum alloy, or a non-metallic heating wire of carbon fiber composite material.

[0035] As a preferred embodiment, the electric heating layer 6 is connected to a positive electrode and a negative electrode, both of which are copper foil electrodes 2, and the copper foil electrodes 2 are connected to the on-off module.

[0036] As a preferred embodiment, the on-off module is a solid-state relay, which includes multiple switches for controlling the on-off of heating modules in different independent areas of the body structure 3. The solid-state relay has an input control end and an output control end. The input control end is connected to the PID controller, and the output control end is connected to the copper foil electrode 2. The multiple switches of the solid-state relay are respectively connected to the anti-icing electric heating film 1 and the power supply. The circuit design ensures that by controlling the on-off of different switches of the solid-state relay, different heating zones of the anti-icing electric heating film 1 can be switched. The control signal sent by the PID controller controls the on-off of each switch respectively, and then controls the on-off of the heating module in each independent area respectively. Furthermore, the PID controller controls the current in the solid-state relay adjustment circuit according to the difference between the actual temperature and the target temperature, thereby achieving dynamic response to different icing environments.

[0037] As a preferred embodiment, the solid-state relay includes a first switch 9, a second switch 10 and a third switch 11, and the body structure 3 is divided into a windward area 12, a first leeward area 13 and a second leeward area 14. The first switch 9, the windward area 12, the first leeward area 13, the second leeward area 14 are connected in series with the power supply, the first leeward area 13 is connected in parallel with the second switch 10, and the second leeward area 14 is connected in parallel with the third switch 11.

[0038] As a preferred embodiment, the temperature acquisition module includes a thermocouple 4 , which is located between the heating module and the body structure 3 .

[0039] Furthermore, each independent area is provided with a thermocouple 4, which obtains multi-channel temperature information of each independent area and transmits it to the PID controller.

[0040] Furthermore, the thermocouple 4 is of PT100 type, and its temperature range includes -30°C to 100°C. The thermocouple 4 uses PTFE silver-plated wire to prevent the temperature signal from being interfered with by the external environment, and can be used in low temperature, freezing or humid environments.

[0041] Furthermore, the thermocouple 4 is in the form of a nanowire embedded thermocouple, a thin film thermocouple or a printed flexible thermocouple.

[0042] Furthermore, the temperature acquisition module is a thermistor embedded in the anti-icing electric heating film 1 .

[0043] Furthermore, the temperature acquisition module is a fiber Bragg grating temperature sensor embedded in the anti-icing electric heating film 1 .

[0044] As a preferred embodiment, the PID controller includes a host computer and a slave computer. The host computer is equipped with an anti-icing temperature control system with functions of human-computer interaction interface, temperature monitoring, temperature warning and data storage. The slave computer converts the control signal transmitted by the host computer into a specific execution instruction for controlling the on and off of multiple switches of the solid-state relay.

[0045] Furthermore, the host computer is a personal computer (PC) platform Labview development environment, and the slave computer is an STM32F103 single-chip industrial control board. Labview is a graphical programming language that uses icons instead of text lines to create applications.

[0046] As a preferred embodiment, the hydrophobic layer 5 is a low surface energy resin-based polymer coating material with high insulation and hydrophobic properties. Its surface is hydrophobic and ice-repellent, has low ice adhesion strength, and is easy to remove ice accumulation by external force or heating. The electric heating layer 6 is a resin-based polymer coating material made of conductive electric heating filler, which has high electrothermal conversion efficiency and stable temperature rise characteristics. The thermal insulation layer 7 is a resin-based polymer coating material made of thermal insulation filler, which has high insulation and thermal insulation properties. The flexible substrate 8 is a flexible polymer film with a backing adhesive. The flexible substrate 8 and its backing adhesive are guaranteed not to fail in the temperature range of -30°C to 100°C, and can be used in low temperature, freezing or humid environments.

[0047] Furthermore, the conductive and electrothermal filler is carbon nanotube or low melting point alloy.

[0048] Furthermore, the thermal insulation filler is zirconia, silicon-based ceramics or aerogel.

[0049] Furthermore, a water-based epoxy resin coating containing 4 parts of a water-based epoxy resin (Epodux 82-34), 8 parts of 3M hollow glass microspheres, and 18 parts of deionized water was evenly dispersed, and then 1 part of an amine epoxy curing agent T31 was added and mixed evenly to obtain a thermal insulation primer. The thermal insulation primer was then scraped onto the surface of a flexible polyimide (PI) film with a backing adhesive. After curing at room temperature for 8 hours, a thermal insulation layer 7 with a thickness of 100 μm was obtained on the film surface. Epodux 82-34 is a high-performance two-component epoxy resin adhesive / potting material.

[0050] Furthermore, after uniformly dispersing a water-based epoxy resin coating containing 8 parts of conductive carbon nanotubes, 16 parts of water-based epoxy resin (Epodux82-34), and 40 parts of deionized water, 4 parts of an amine epoxy curing agent T31 were added and mixed evenly to obtain an electric heating coating. The electric heating coating was scraped onto the surface of the PI film coated with a thermal insulation layer 7 and provided with copper electrodes. After curing at room temperature for 8 hours, an electric heating layer 6 with a thickness of 50 μm was obtained on the surface of the thermal insulation layer 7.

[0051] Furthermore, 5 parts of fluorine-modified epoxy resin, 5 parts of toluene solvent, and 0.5 parts of amine curing agent T31 were evenly mixed to obtain a hydrophobic coating. The hydrophobic coating was sprayed on the surface of the electric heating layer 6 and then cured at room temperature for 8 hours to obtain an anti-icing electric heating film 1.

[0052] The present invention also provides an aircraft wing anti-icing PID temperature control method, which divides the body structure 3 into at least one windward area 12 and at least one leeward area according to different convective heat transfer conditions of the body structure 3. According to the ambient temperature, wind speed and rainfall, the system sets a temperature tolerance between the windward area 12 and the leeward area. When the actual temperature difference between the windward area 12 and the leeward area measured by the temperature acquisition module is greater than the set temperature tolerance, the heating module corresponding to the windward area 12 is turned on to heat the windward area 12. When the actual temperature difference between the leeward area and the windward area measured by the temperature acquisition module is greater than the set temperature tolerance, the heating module corresponding to the windward area 12 is turned on to heat the windward area 12. When the actual temperature difference in the wind area 12 is less than the set temperature tolerance, the heating module corresponding to the windward area 12 is turned on to heat the windward area 12, and at the same time, the heating module corresponding to the leeward area is turned on to heat the leeward area. Since the convection heat exchange conditions on the windward side and the leeward side of the fuselage structure 3 are different, while ensuring the anti-icing requirements of each area of ​​the fuselage structure 3, compared with the single full-area heating method, the aircraft wing anti-icing PID temperature control method of the present invention effectively reduces the power loss caused by uneven heating and improves the utilization rate of heat energy in the wing anti-icing process.

[0053] Furthermore, the partition areas of the windward region 12 and the leeward region are determined by wing flow simulation and ice wind tunnel tests.

[0054] Furthermore, the body structure 3 is divided into three areas according to different convection heat transfer conditions of the body structure 3, namely the windward area 12, the first leeward area 13, and the second leeward area 14. The windward area 12 is provided with a first heating module, the first leeward area 13 is provided with a second heating module, and the second leeward area 14 is provided with a third heating module. The on-off module includes a first switch 9, a second switch 10 and a third switch 11; two parallel copper foils are used as positive and negative electrodes on both sides of the electric heating layer 6 of each area and are connected to the solid-state relay. The two adjacent areas share the same copper foil electrode 2 and are controlled by the same solid-state relay switch. When the first temperature measured by the temperature acquisition module is When the actual temperature difference between the leeward area 13 and the windward area 12, and the actual temperature difference between the second leeward area 14 and the windward area 12 are both less than the set temperature tolerance, the first switch 9 is closed, the second switch 10 and the third switch 11 are disconnected, and the first heating module, the second heating module and the third heating module are turned on at the same time to heat the entire area of ​​the body structure 3. The lower computer controls the first switch 9 to be turned on and off at high speed through a PWM (multiple pulse width modulation) control signal. The duty cycle of the PWM control signal is determined by the difference between the ambient temperature and the target temperature, thereby realizing temperature control of the entire area of ​​the body structure 3; when the actual temperature difference between the first leeward area 13 and the windward area 12, and the second leeward area 14 and the windward area 12 measured by the temperature acquisition module are less than the set temperature tolerance, the first switch 9 is closed, and the second switch 10 and the third switch 11 are disconnected. The first heating module, the second heating module and the third heating module are turned on at the same time to heat the entire area of ​​the body structure 3. When the actual temperature difference between the windward area 14 and the windward area 12 is greater than the set temperature tolerance, the first switch 9, the second switch 10 and the third switch 11 are all closed, the first leeward area 13 and the second leeward area 14 are short-circuited, the first heating module heats the windward area 12, the second heating module and the third heating module do not work, and the body structure 3 is in a single-zone heating state of the windward area 12; when the actual temperature difference between the first leeward area 13 and the windward area 12 measured by the temperature acquisition module is less than the set temperature tolerance, and the actual temperature difference between the second leeward area 14 and the windward area 12 measured by the temperature acquisition module is greater than the set temperature tolerance, the first switch 9 and the third switch 11 are ... and the first leeward area 13 and the second leeward area 14 are short-circuited. The second switch 10 is disconnected, the second leeward area 14 is short-circuited, the first heating module heats the windward area 12, the second heating module heats the first leeward area 13, and the third heating module does not work; when the actual temperature difference between the first leeward area 13 and the windward area 12 measured by the temperature acquisition module is greater than the set temperature tolerance, and the actual temperature difference between the second leeward area 14 and the windward area 12 measured by the temperature acquisition module is less than the set temperature tolerance, the first switch 9 and the second switch 10 are closed, the third switch 11 is disconnected, the first leeward area 13 is short-circuited, the first heating module heats the windward area 12, the third heating module heats the second leeward area 14, and the second heating module does not work.

[0055] Furthermore, to prevent overcurrent problems caused by sudden drops in resistance, the system can perform power voltage regulation before switching heating areas. This allows it to specifically adjust the power density of parts of the fuselage structure, such as the windward area of ​​the leading edge of the wing, which is prone to icing, thereby accelerating the ice melting process in the windward area of ​​the leading edge.

[0056] The simulation experiment was carried out in an ice wind tunnel environment at -10℃ and a wind speed of 10m / s. 2 The anti-icing electric heating film 1 was heated, and ice wind tunnel experiments were carried out with and without zone heating control. The system target temperature was 5°C, and the temperature change curve with time was recorded. The experimental results can be found in Figure 5 and Figure 6 Without the aircraft wing anti-icing PID temperature control method of the present invention, only the windward area 12, where heat dissipation requirements are most stringent, achieves the desired temperature control effect, while the temperature in the leeward area exceeds the target temperature, resulting in a waste of electrical energy. In contrast, with the aircraft wing anti-icing PID temperature control method of the present invention, the temperature of each area of ​​the fuselage structure 3 is relatively uniform, both during the system's warm-up phase and steady-state phase, preventing overheating in the leeward area.

[0057] The present invention also provides an aircraft, comprising a wing body, on which an aircraft wing anti-icing PID temperature control device is provided.

[0058] The present invention uses specific examples to illustrate the principles and implementation methods of the present invention. The above examples are only intended to help understand the method and core concept of the present invention. At the same time, those skilled in the art will find that the specific implementation methods and application scopes may vary based on the concept of the present invention. In summary, the contents of this specification should not be construed as limiting the present invention.

Claims

1. An aircraft wing anti-icing PID temperature control device, characterized in that: include: A heating module, a temperature acquisition module, an on-off module and a PID controller, wherein the surface of a body structure (3) is divided into a plurality of independent areas, the body structure (3) is a structure on an aircraft wing that requires anti-icing, the plurality of independent areas at least comprising a windward area (12) and a leeward area, the windward area (12) and the leeward area being respectively provided with the heating module and the temperature acquisition module, the PID controller being respectively electrically connected to the temperature acquisition module and the on-off module, the temperature acquisition module being capable of respectively measuring the temperature of the windward area (12) and the leeward area, and transmitting the temperature signal to the PID controller, the PID controller being capable of controlling the on-off of the on-off module to control whether the heating module of the windward area (12) and the heating module of the leeward area are heated.

2. The aircraft wing anti-icing PID temperature control device according to claim 1, characterized in that: The heating module is an anti-icing electric heating film (1), and the anti-icing electric heating film (1) comprises a hydrophobic layer (5), an electric heating layer (6), a thermal insulation layer (7) and a flexible substrate (8) arranged in sequence from top to bottom. The hydrophobic layer (5) is used for anti-icing and ice-repelling. The electric heating layer (6) is electrically connected to the on-off module. The on-off module is used to control the heating on and off of the electric heating layer (6). The thermal insulation layer (7) is used to insulate and insulate the electric heating layer (6) and the body structure (3). The flexible substrate (8) is used to adhere to the body structure (3).

3. The aircraft wing anti-icing PID temperature control device according to claim 2, characterized in that: The electric heating layer (6) is connected to a positive electrode and a negative electrode, the positive electrode and the negative electrode are both copper foil electrodes (2), and the copper foil electrodes (2) are connected to the on-off module.

4. The aircraft wing anti-icing PID temperature control device according to claim 1, characterized in that: The on-off module is a solid-state relay, which includes a plurality of switches for controlling the on-off of heating modules in different independent areas of the body structure (3).

5. The aircraft wing anti-icing PID temperature control device according to claim 4, characterized in that: The solid-state relay comprises a first switch (9), a second switch (10) and a third switch (11); the body structure (3) is divided into a windward area (12), a first leeward area (13) and a second leeward area (14); the first switch (9), the windward area (12), the first leeward area (13) and the second leeward area (14) are connected in series with a power supply; the first leeward area (13) and the second switch (10) are connected in parallel; and the second leeward area (14) and the third switch (11) are connected in parallel.

6. The aircraft wing anti-icing PID temperature control device according to claim 1, characterized in that: The temperature acquisition module comprises a thermocouple (4), and the thermocouple (4) is located between the heating module and the body structure (3).

7. The aircraft wing anti-icing PID temperature control device according to claim 4, characterized in that: The PID controller includes a host computer and a slave computer. The host computer is equipped with an anti-icing temperature control system with functions of human-computer interaction interface, temperature monitoring, temperature warning and data storage. The slave computer converts the control signal transmitted by the host computer into a specific execution instruction for controlling the on and off of multiple switches of the solid-state relay.

8. The aircraft wing anti-icing PID temperature control device according to claim 2, characterized in that: The hydrophobic layer (5) is a low-surface-energy resin-based polymer coating material, the electric heating layer (6) is a resin-based polymer coating material made of conductive electric heating filler, the thermal insulation layer (7) is a resin-based polymer coating material made of thermal insulation filler, and the flexible substrate (8) is a flexible polymer film with adhesive backing.

9. A PID temperature control method for aircraft wing anti-icing, characterized by: An aircraft wing anti-icing PID temperature control device according to any one of claims 1 to 8 is used, and the fuselage structure (3) is divided into at least one windward area (12) and at least one leeward area according to different convective heat transfer conditions of the fuselage structure (3); when the actual temperature difference between the windward area (12) and the leeward area measured by the temperature acquisition module is greater than the set temperature tolerance, the heating module corresponding to the windward area (12) is turned on to heat the windward area (12); when the actual temperature difference between the leeward area and the windward area (12) measured by the temperature acquisition module is less than the set temperature tolerance, the heating module corresponding to the windward area (12) is turned on to heat the windward area (12) and the heating module corresponding to the leeward area is turned on to heat the leeward area.

10. An aircraft, characterized in that: The invention comprises a wing body, on which the aircraft wing anti-icing PID temperature control device according to any one of claims 1 to 8 is arranged.

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