Aircraft anti-icing / de-icing system

Abstract

This application relates to an aircraft anti-icing / de-icing system. The system includes a zinc oxide / acetic acid superhydrophobic coating, a graphene heating device, a temperature sensor, a control device, and an onboard power supply. The superhydrophobic coating and the graphene heating device are respectively disposed on the outer and inner surfaces of the aircraft wing. The graphene heating device, temperature sensor, control device, and onboard power supply are electrically connected. The temperature sensor collects temperature parameters from the aircraft wing surface and transmits these parameters to the control device. When the temperature parameter is lower than a preset temperature, the control device controls the onboard power supply to power the graphene heating device to activate it. When the temperature parameter is not lower than the preset temperature, the control device controls the onboard power supply to stop powering the graphene heating device to shut it down. The aircraft anti-icing / de-icing system of this application reduces the icing intensity on the wing surface, provides uniform heating, high efficiency, high thermal energy utilization, and low energy consumption.

Description

Technical Field

[0001] This application relates to the field of aircraft anti-icing and de-icing technology, and in particular to an aircraft anti-icing / de-icing system. Background Technology

[0002] In the design and operation of aircraft, anti-icing / removal technology is particularly important, especially in cold and wet weather conditions, where the formation of frost can significantly affect the performance and safety of aircraft.

[0003] Traditional de-icing technologies typically employ electrothermal de-icing systems, generally using metal resistance wires. However, due to limitations in material properties, uneven heating can occur, leading to some areas of the wing being more efficient while others fail to meet de-icing requirements. This results in some areas not being removed in time, impacting flight safety. Furthermore, these technologies also suffer from high energy consumption and high icing intensity on the wing surface. Summary of the Invention

[0004] Based on this, and in response to the above problems, this application provides an aircraft anti-icing / de-icing system that features uniform heating, low energy consumption, rapid response, and reduced icing intensity on the wing surface.

[0005] This application provides an aircraft anti-icing / de-icing system, which includes a zinc oxide / acetic acid superhydrophobic coating, a graphene heating device, a temperature sensor, a control device, and an onboard power supply device; wherein...

[0006] The superhydrophobic coating and the graphene heating device are respectively located on the outer and inner surfaces of the aircraft wing;

[0007] Electrical connections exist between the graphene heating device, temperature sensor, control device, and airborne power supply; the temperature sensor is used to collect temperature parameters from the surface of the aircraft wing and transmit these parameters to the control device.

[0008] When the temperature parameter is lower than the preset temperature, the control device controls the airborne power supply to supply power to the graphene heating device in order to start the graphene heating device.

[0009] When the temperature parameter is not lower than the preset temperature, the control device controls the airborne power supply to stop supplying power to the graphene heating device, thereby shutting down the graphene heating device.

[0010] In some embodiments, the preparation of the zinc oxide / acetic acid superhydrophobic coating includes the following steps:

[0011] S1. Epoxy resin and ethyl acetate are mixed and stirred to obtain the first solution;

[0012] S2. Add zinc oxide to the first solution, heat and stir to obtain the second solution;

[0013] S3. Add ethanol to the second solution, and then perform stirring, cooling, ultrasonication and cooling treatment in sequence. Next, add curing agent to the second solution and stir to obtain the superhydrophobic spraying solution.

[0014] In steps S1-S3, the mass ratio of zinc oxide, ethanol, epoxy resin, ethyl acetate and curing agent is 1:(1~2):(1~2):(3~8):(1 / 3~2 / 3).

[0015] S4. Prepare a reaction solution by using ethanol:acetic acid:stearic acid in a mass ratio of (25~30):(3~5):(1~3);

[0016] S5. Spray the superhydrophobic coating solution onto the outer surface of the aircraft wing, remove it after curing, place it in the reaction solution for a preset reaction time, remove it, and cure it to obtain a zinc oxide / acetic acid superhydrophobic coating.

[0017] In some embodiments, the graphene heating device includes a multilayer glass fiber prepreg and a graphene heating element disposed within the multilayer glass fiber prepreg.

[0018] In some embodiments, the graphene heating element includes a graphene film and electrodes.

[0019] In some embodiments, the sheet resistance R of the graphene film is 1Ω to 3Ω.

[0020] In some embodiments, the electrode is a copper foil electrode with a thickness of 0.05 mm to 0.1 mm.

[0021] In some embodiments, the preparation of the graphene heating element includes the following steps:

[0022] S10. Cut the graphene film and electrodes;

[0023] S20. Fix the electrode on a single layer of glass fiber prepreg and evacuate the vacuum.

[0024] S30. Next, the graphene film is attached to a single layer of glass fiber prepreg, and conductive silver paste is used to bond the graphene film to the electrode. After curing, a vacuum is drawn to obtain the graphene heating element.

[0025] In some implementations, the temperature sensor is positioned longitudinally in the middle of the graphene heating device and chordally between the graphene heating device and the aircraft wing.

[0026] In some implementations, the temperature sensor is a type K thermocouple temperature sensor.

[0027] In some embodiments, the control device includes a temperature monitoring module, a data analysis module, and a temperature control module; wherein,

[0028] The temperature detection module acquires real-time temperature data of the aircraft wing surface through temperature sensors to detect temperature changes;

[0029] The data analysis module compares and analyzes the temperature data with the preset temperature to determine the prevention / elimination requirements;

[0030] The temperature control module controls the heating power and time of the graphene heating device according to the prevention / elimination requirements.

[0031] This application involves applying a zinc oxide / acetic acid superhydrophobic coating to the surface of an aircraft wing. This coating increases the contact angle between the aircraft wing surface and water, reduces the roll-off angle, and improves the rollability of water droplets. It can effectively reduce the retention and accumulation of water on the aircraft wing surface, significantly reduce the formation of frost on the aircraft wing surface, and reduce the icing strength of the aircraft wing surface, making the ice layer easier to remove.

[0032] This application incorporates a graphene heating device that provides uniform heating, enabling timely removal of ice and snow from all areas of the wing and rapidly raising the wing surface temperature to the required level. This results in high thermal efficiency and low energy consumption.

[0033] This application, by incorporating temperature sensors and control devices, enables real-time monitoring of surface temperature changes on aircraft wings. Based on a comparison of temperature parameters with preset temperatures, it precisely controls the activation and deactivation of the graphene heating device. When the wing surface temperature reaches or exceeds the preset temperature, the heating device automatically stops operating, avoiding unnecessary energy consumption and achieving energy savings. Simultaneously, it automatically adjusts the heating power, optimizing it according to actual conditions, thus improving the anti-icing capability of the aircraft wings under changing climatic conditions. Attached Figure Description

[0034] Figure 1 This is a schematic diagram and a partially enlarged view of an aircraft anti-icing / de-icing system according to one embodiment of this application.

[0035] Figure 2 This is a process flow diagram of the preparation process of the zinc oxide / acetic acid superhydrophobic coating in one embodiment of this application.

[0036] Figure 3 This is an overall schematic diagram of the graphene heating device in one embodiment of this application.

[0037] Figure 4 This is a schematic diagram of the graphene heating element in one embodiment of this application.

[0038] Explanation of reference numerals in the attached figures

[0039] 1. Aircraft wing; 2. Zinc oxide / acetic acid superhydrophobic coating; 3. Graphene heating device; 31. Glass fiber prepreg; 32. Graphene heating element; 321. Graphene film; 322. Electrode; 4. Temperature sensor; 5. Control device; 6. Airborne power supply;

[0040] D1, thickness of the graphene heating device; L2, length of the graphene film; b, spacing between two adjacent graphene films. Detailed Implementation

[0041] A detailed reference is now provided to embodiments of this application, one or more of which are described below. Each embodiment is provided for explanation and not for limitation. In fact, it will be apparent to those skilled in the art that various modifications and variations can be made to this application without departing from its scope or spirit. For example, features described or illustrated as part of one embodiment may be used in another embodiment to produce further embodiments.

[0042] Therefore, this application is intended to cover such modifications and variations falling within the scope of the appended claims and their equivalents. Other objects, features, and aspects of this application are disclosed in or will be apparent from the following detailed description. It will be understood by those skilled in the art that this discussion is merely a description of exemplary embodiments and is not intended to limit the broader aspects of this application.

[0043] In this application, the technical features described in an open manner include closed technical solutions composed of the listed features, and also include open technical solutions containing the listed features.

[0044] In this application, numerical ranges are referred to as continuous unless otherwise specified, and include the minimum and maximum values ​​of the range, as well as every value between the minimum and maximum values. Furthermore, when the range refers to integers, it includes every integer between the minimum and maximum values ​​of the range. Additionally, when multiple ranges are provided to describe a feature or characteristic, the ranges may be merged. In other words, unless otherwise specified, all ranges disclosed herein should be understood to include any and all subranges to which they are incorporated.

[0045] In this article, when referring to units for data ranges, if the unit is only followed by the right endpoint, it means that the units for the left and right endpoints are the same. For example, 100~150 nm means that the units for the left endpoint "100" and the right endpoint "150" are both nm (nanometers).

[0046] Unless otherwise specified, all embodiments and optional embodiments of this application can be combined to form new technical solutions.

[0047] Unless otherwise specified, all technical features and optional technical features of this application can be combined with each other to form a new technical solution.

[0048] Unless otherwise specified, all steps in this application may be performed sequentially or randomly, preferably sequentially. For example, the method includes steps (a) and (b), indicating that the method may include steps (a) and (b) performed sequentially, or it may include steps (b) and (a) performed sequentially. For example, the mention that the method may also include step (c) indicates that step (c) may be added to the method in any order; for example, the method may include steps (a), (b), and (c), or it may include steps (a), (c), and (b), or it may include steps (c), (a), and (b), etc.

[0049] Unless otherwise specified, the terms "comprising" and "including" as used in this application can be open-ended or closed-ended. For example, "comprising" and "including" can mean that other components not listed may also be included, or that only the listed components may be included.

[0050] Unless otherwise specified, the term "or" is inclusive in this application. For example, the phrase "A or B" means "A, B, or both A and B". More specifically, the condition "A or B" is satisfied by any of the following conditions: A is true (or exists) and B is false (or does not exist); A is false (or does not exist) and B is true (or exists); or both A and B are true (or exist).

[0051] like Figure 1-3 As shown, this application provides an aircraft anti-icing / de-icing system, which includes a zinc oxide / acetic acid superhydrophobic coating 2, a graphene heating device 3, a temperature sensor 4, a control device 5, and an onboard power supply 6. The superhydrophobic coating and the graphene heating device 3 are respectively disposed on the outer and inner surfaces of the aircraft wing 1. The graphene heating device 3, the temperature sensor 4, the control device 5, and the onboard power supply 6 are electrically connected. The temperature sensor 4 is used to collect temperature parameters of the aircraft wing 1 surface and transmit the temperature parameters to the control device 5.

[0052] When the temperature parameter is lower than the preset temperature, the control device 5 controls the airborne power supply device 6 to supply power to the graphene heating device 3 to start the graphene heating device 3.

[0053] When the temperature parameter is not lower than the preset temperature, the control device 5 controls the airborne power supply device 6 to stop supplying power to the graphene heating device 3, so as to shut down the graphene heating device 3.

[0054] The aircraft anti-icing / de-icing system provided in this application enables low-heat anti-icing / de-icing of aircraft wings under icing weather conditions, real-time detection of temperature changes on the wing surface, and real-time adjustment of the wing surface heating rate and surface temperature, thereby reducing the energy consumption of the aircraft anti-icing / de-icing system and enhancing the aircraft's endurance and all-weather combat capability.

[0055] The working principle of the above-mentioned aircraft anti-icing / de-icing system is as follows: When the aircraft enters the anti-icing requirement zone, the temperature sensor 4 collects the surface temperature parameters of the aircraft wing 1 in real time and transmits the temperature data to the control device 5. The control device 5 compares and analyzes the temperature data with the preset temperature (anti-icing threshold, the temperature that may cause frost formation). Once the temperature parameter is detected to be lower than the preset temperature, the control device 5 controls the onboard power supply device 6 to supply power to the graphene heating device 3 to start the graphene heating device 3. The graphene heating device 3 begins to generate heat to prevent frost formation.

[0056] The aircraft anti-icing / de-icing system provided in this application adopts a wet anti-icing strategy, performing low-heat anti-icing. The control device 5 monitors the surface temperature of the aircraft wing 1 in real time. When the graphene heating device 3 heats to the preset temperature, the control device 5 controls the power and switch of the onboard power supply device 6 to maintain the surface of the aircraft wing 1 within the set temperature range. When the aircraft leaves the anti-icing requirement area, the control device 5 analyzes and processes the temperature data in real time. When it detects that the temperature parameter is greater than or equal to the preset temperature, the control device 5 controls the onboard power supply device 6 to stop supplying power to the graphene heating device 3, thereby shutting down the graphene heating device 3 and completing low-heat anti-icing.

[0057] It is understood that "wet anti-icing" in this application refers to an anti-icing strategy in which the wing surface is not heated to an excessively high temperature during aircraft flight, but only to the ice melting temperature, so that a water film flows on the wing surface and the water on the wing surface cannot be completely evaporated.

[0058] In this application, "low-heat anti-icing" refers to an anti-icing strategy in aircraft electric heating anti-icing that uses lower heating power and PID temperature control to keep the temperature at the ice melting temperature in order to reduce energy consumption. For example, wing anti-icing can be completed as soon as the wing surface temperature reaches 15°C.

[0059] like Figure 4 As shown, in some embodiments, the preparation of the zinc oxide / acetic acid superhydrophobic coating 2 includes the following steps:

[0060] S1. Epoxy resin and ethyl acetate are mixed and stirred to obtain the first solution.

[0061] S2. Add zinc oxide to the first solution, heat and stir to obtain the second solution.

[0062] S3. Add ethanol to the second solution, and then perform stirring, cooling, ultrasonication and cooling treatment in sequence. Next, add curing agent to the second solution and stir to obtain the superhydrophobic spraying solution.

[0063] In steps S1-S3, the mass ratio of zinc oxide, ethanol, epoxy resin, ethyl acetate and curing agent is 1:(1~2):(1~2):(3~8):(1 / 3~2 / 3).

[0064] S4. Prepare a reaction solution by using the mass ratio of ethanol:acetic acid:stearic acid of (25~30):(3~5):(1~3).

[0065] S5. The superhydrophobic coating solution is sprayed onto the outer surface of the aircraft wing 1, cured, and then removed and placed in the reaction solution for a preset time before being removed and cured to obtain the zinc oxide / acetic acid superhydrophobic coating 2.

[0066] In some embodiments, the stirring process in step S1 specifically refers to stirring with a magnetic stirrer until the epoxy resin is fully dissolved in ethyl acetate.

[0067] In some embodiments, the heating and stirring process in step S2 specifically refers to stirring at 50°C to 70°C for 15 to 30 minutes using a magnetic stirrer until the zinc oxide powder is completely dissolved in the first solution.

[0068] In one specific embodiment, step S2 is as follows: zinc oxide is added to the first solution, and the solution is heated to 60°C and stirred for 20 minutes using a magnetic stirrer to obtain the second solution.

[0069] In some embodiments, the zinc oxide used in step S2 is nanoscale zinc oxide powder, which has a large specific surface area and excellent optical properties, and plays a role in enhancing the coating performance in superhydrophobic coatings.

[0070] In one specific embodiment, step S3 is as follows: ethanol is added to the second solution, and after stirring with a magnetic stirrer for 10 minutes, the solution is cooled. After the cooling is completed, the solution is ultrasonically treated with an ultrasonic cell disruptor. After ultrasonic treatment, the solution is further magnetically stirred for 10 minutes and then cooled. Next, curing agent D230 is added to the second solution, and after stirring for 20 minutes, a superhydrophobic spraying solution is obtained.

[0071] Understandably, an ultrasonic cell disruptor refers to a device that uses ultrasonic vibrations to mix, disperse, and pulverize solid particles in a liquid, often used to improve the homogeneity of a solution.

[0072] In one specific embodiment, step S4 is: preparing a reaction solution by means of a mass ratio of ethanol:acetic acid:stearic acid of 25:3:1.

[0073] In some embodiments, the spraying distance in step S5 is 20cm~30cm, including but not limited to 20cm, 22cm, 24cm, 26cm, 28cm, and 30cm. The number of sprayed layers is 10~20. In one specific embodiment, step S5 is as follows: the superhydrophobic spraying solution is sprayed onto the outer surface of the aircraft wing 1 at a distance of 25cm, a total of 15 layers are sprayed, and after curing in an oven at 80°C for 5 hours, it is taken out and placed in a reaction solution. After 6 minutes, it is taken out and placed in an oven at 80°C for another 5 hours to obtain the zinc oxide / acetic acid superhydrophobic coating 2.

[0074] In some embodiments, the graphene heating device 3 includes a multilayer glass fiber prepreg 31 and a graphene heating element 32, wherein the graphene heating element 32 is disposed within the multilayer glass fiber prepreg 31.

[0075] In some embodiments, the graphene heating element 32 includes a graphene film 321 and an electrode 322.

[0076] In some embodiments, the graphene film 321 is a flexible graphene film 321, and the sheet resistance R of the graphene film 321 is 1Ω to 3Ω. Preferably, the sheet resistance R of the graphene film 321 is 1Ω.

[0077] As is understandable, sheet resistance refers to the resistance of a thin film material, which is the ratio between the film current and voltage, and is measured in ohms per square meter. In this article, sheet resistance R=1 represents the resistive characteristics of the graphene heating material.

[0078] In some embodiments, electrode 322 is a copper foil electrode 322, and the thickness of the copper foil electrode 322 is 0.05 mm to 0.1 mm. Preferably, the thickness of the copper foil electrode 322 is 0.08 mm.

[0079] In some embodiments, the preparation of the graphene heating element 32 includes the following steps:

[0080] S10. Cut the graphene film 321 and the electrode 322;

[0081] S20. Fix electrode 322 onto single-layer glass fiber prepreg 31 and evacuate the vacuum.

[0082] S30. Next, the graphene film 321 is attached to the single-layer glass fiber prepreg 31, and the graphene film 321 is bonded to the electrode 322 using conductive silver paste. After curing, the process is vacuumed to obtain the graphene heating element 32.

[0083] In some embodiments, the preparation of the graphene heating element 32 includes the following steps:

[0084] The graphene film 321 and the copper foil electrode 322 are cut according to the circuit design diagram;

[0085] According to the circuit design diagram, the copper foil electrode 322 is fixed on the single-layer glass fiber prepreg 31. The vacuum is drawn to a vacuum degree of 80 kPa and maintained for 10 min, so that the copper foil electrode 322 and the single-layer glass fiber prepreg 31 are tightly bonded.

[0086] Next, according to the circuit design diagram, the graphene film 321 is attached to the single-layer glass fiber prepreg 31 with the copper foil electrode 322 attached. The graphene film 321 and the copper foil electrode 322 are tightly bonded using conductive silver paste. The curing process is carried out at room temperature for 30 minutes, and a vacuum is drawn to a vacuum degree of 80 kPa and held for 10 minutes to ensure that the graphene film 321 and the single-layer glass fiber prepreg 31 are tightly bonded, thus obtaining the graphene heating element 32.

[0087] In some embodiments, the graphene heating device 3 is prepared using the following method, including the following steps:

[0088] S100. Cut the multilayer glass fiber prepreg 31 for later use;

[0089] S200, Apply release agent to the mold surface and place a pre-made vacuum bag;

[0090] S300. Multiple layers of fiberglass prepreg 31 are laid on the surface of the mold in multiple stages, and vacuum treatment is performed after each laying.

[0091] S400, then lay a single layer of glass fiber prepreg 31, glass fiber prepreg 31 with graphene heating element 32 and a separator, and then vacuum process.

[0092] S500. A multilayer glass fiber prepreg 31 is laid on the surface of the isolation membrane away from the graphene heating element 32, and then vacuumed.

[0093] S600, trim excess edges of the prepreg, leaving margins for demolding process;

[0094] S700, then lay the isolation membrane, breathable felt and vacuum bag film in sequence, and then vacuum process;

[0095] S800, placed in an oven, heated at 120±10℃ for 2.5±0.5h, cooled and demolded to obtain graphene heating device 3.

[0096] In some embodiments, the vacuuming process in steps S100 to S800 above is to vacuum up to a vacuum level of 80 kPa and maintain it for 10 min.

[0097] In some embodiments, the graphene heating device 3 has a thickness D1 of 2.08 mm, a length L1 of 350 mm, and a width W1 of 200 mm.

[0098] In some embodiments, in the graphene heating element 32, the graphene film 321 has a thickness D2 of 0.08 mm, a length L2 of 336 mm, a width W2 of 7 mm, and a spacing b of 3 mm between two adjacent graphene films 321. In some embodiments, the electrode 322 has a thickness D3 of 0.08 mm and a width W3 of 7 mm.

[0099] In some embodiments, the thickness D4 of the single-layer glass fiber prepreg 31 is 0.2 mm.

[0100] In one specific embodiment, the preparation of the graphene heating device 3 includes the following steps:

[0101] S100. Cut the multi-layer glass fiber prepreg 31 with a single layer thickness of 0.2mm and set it aside. Number the multi-layer glass fiber prepreg 31 as #1 to #10, where #3 glass fiber prepreg 31 refers to the glass fiber prepreg 31 with graphene heating element 32 attached.

[0102] S200, apply release agent to the mold surface and let it stand for 30 minutes, then pre-make vacuum bags;

[0103] S300. First, lay 3 layers of glass fiber prepreg 31 (#10, #9, #8) on the surface of the mold, and then vacuum it. Continue to lay 3 layers of glass fiber prepreg 31 (#7, #6, #5) and vacuum it.

[0104] S400, then lay #4, #3 fiberglass prepreg 31 and release film, and vacuum process;

[0105] S500, Two layers of glass fiber prepreg 31 (#2, #1) are laid on the side of the isolation membrane away from the graphene heating element 32, and vacuum treatment is performed;

[0106] S600, trim the excess edges of the fiberglass prepreg 31, leaving a margin for the demolding process;

[0107] S700, then lay the isolation membrane, breathable felt and vacuum bag film in sequence, and then vacuum process;

[0108] S800. Place the mold in an oven, heat at 120°C for 2.5 hours, then cool and demold to obtain the graphene heating device 3.

[0109] In some embodiments, the temperature sensor 4 is located in the middle of the graphene heating device 3 in the spanwise direction and in the chordwise direction between the graphene heating device 3 and the aircraft wing 1.

[0110] In some embodiments, the temperature sensor 4 is a K-type thermocouple temperature sensor 4, and there are multiple K-type thermocouple temperature sensors 4. The number of them is not particularly limited in this application and can be adjusted according to actual needs.

[0111] In a specific example, there are five K-type thermocouple temperature sensors 4. The five temperature sensors 4 are evenly distributed in the spanwise direction in the middle of the graphene heating device 3, and in the chordwise direction between the graphene heating device 3 and the aircraft wing 1.

[0112] In some embodiments, the control device 5 includes a temperature monitoring module, a data analysis module, and a temperature control module; wherein,

[0113] The temperature detection module acquires the temperature data of the aircraft wing 1 surface in real time through temperature sensor 4, so as to detect temperature changes in real time and determine the current flight environment and the risk of icing on the aircraft surface.

[0114] The data analysis module compares and analyzes temperature data with preset temperatures, assesses anti-icing / de-icing needs in real time, and makes decisions on necessary heating measures based on preset temperatures.

[0115] The temperature control module precisely controls the heating power and time of the graphene heating device 3 based on real-time temperature data and anti-icing / de-icing requirements, thereby optimizing heating efficiency.

[0116] It is understandable that controlling the heating power specifically means that, based on data acquired in real time from the temperature sensor 4, the control device 5 can adjust the output power of the onboard power supply device 6 to precisely control the heating power of the graphene heating device 3. Through this process, the control device 5 can achieve precise temperature rise control, ensuring that the aircraft surface is within a suitable temperature range and preventing the formation of frost.

[0117] Optimizing heating efficiency specifically means that the control device 5 can automatically adjust the heating power and heating time of the graphene heating device 3 according to environmental changes and the aircraft's flight status, thereby optimizing the heating effect and reducing energy consumption. This enables the aircraft anti-icing / de-icing system provided in this application to not only effectively prevent icing but also improve overall energy efficiency.

[0118] The airborne power supply unit 6 in this application provides a stable power supply for the entire aircraft anti-icing / de-icing system, including the graphene heating device 3 and the control device 5, and is an indispensable and important component of the system. The airborne power supply unit 6 can adjust its power in real time according to the commands transmitted by the control device 5; when anti-icing is required, the airborne power supply unit 6 can provide up to 700W of power to the graphene heating device 3 of the corresponding size in this application, that is, provide 10 kW / m² to the graphene heating device 3. 2 The heating power density; when the surface temperature of the aircraft wing 1 approaches the preset temperature during the heating process, the airborne power supply device 6 will reduce the power output to reduce the impact of temperature shock and better control the temperature within the set range.

[0119] It is understandable that heating power density refers to the heating power per unit area, usually expressed in watts per square meter (W / m²). The 10 kW / m² mentioned in this article indicates the high-efficiency heating capacity of the graphene heating device 3.

[0120] In some embodiments, the aircraft wing 1 is made of nickel-chromium alloy-clad iron. This nickel-chromium alloy-clad iron provides the necessary mechanical strength and support for the anti-icing / de-icing system provided in this application. It also provides a stable substrate for the superhydrophobic coating and the graphene heating device 3, ensuring stability under various flight conditions. The nickel-chromium alloy-clad iron has excellent thermal conductivity, which helps to quickly transfer the heat generated by the graphene heating device 3 to the outer surface of the nickel-chromium alloy-clad iron.

[0121] In some implementations, the installation process of temperature sensor 4 is as follows: The graphene heating device 3 is adhered to the leading edge of the aircraft wing model using epoxy adhesive, secured with a pad and C-clamps to ensure a tight fit, and cured at room temperature for 48 hours. The wires of temperature sensor 4 are fixed to the surface of the aircraft wing model using 3M low-temperature double-sided tape and aluminum foil, extending from the bottom of the model. The temperature measuring points of temperature sensor 4 are fixed to the corresponding positions of the graphene heating device 3 according to their numbers using K-3880 epoxy thermally conductive adhesive, with a small amount of aluminum foil used to fix the position and prevent displacement during the installation of the iron sheath. A release cloth is applied to the edge of the aircraft wing model where the graphene heating device 3 is installed to treat any excess adhesive. K-3880 epoxy thermally conductive adhesive is evenly applied to the surface of the graphene heating device 3. The nickel-chromium alloy iron sheath is tightly adhered to the graphene heating device 3, secured with a pad and C-clamps to ensure a tight fit, and cured at room temperature for 72 hours. The installation of temperature sensor 4 is now complete.

[0122] Table 1 below shows the performance test results of the zinc oxide / acetic acid superhydrophobic coating 2 provided in this application.

[0123]

[0124] According to the data in Table 1, this application provides a zinc oxide / acetic acid superhydrophobic coating 2 on the surface of the aircraft wing 1. This coating can increase the contact angle between the surface of the aircraft wing 1 and water, reduce the roll-off angle, improve the rollability of water droplets, effectively reduce the retention and accumulation of water on the surface of the aircraft wing 1, significantly reduce the formation of frost on the surface of the aircraft wing 1, and reduce the icing strength on the surface of the aircraft wing 1, making the ice layer easier to remove.

[0125] This application incorporates a graphene heating device 3, which provides uniform heating, enabling timely removal of ice and snow from all areas of the wing and raising the wing surface temperature to the required level within a short time. This results in high heating efficiency, high thermal energy utilization, and low energy consumption.

[0126] This application, by setting a temperature sensor 4 and a control device 5, can monitor the surface temperature changes of the aircraft wing 1 in real time. Based on a comparison of the temperature parameters with a preset temperature, it precisely controls the activation and deactivation of the graphene heating device 3. When the surface temperature of the aircraft wing 1 reaches or exceeds the preset temperature, the heating device automatically stops working, avoiding unnecessary energy consumption and thus achieving energy saving. Simultaneously, it automatically adjusts the heating power dynamically according to changes in the wing surface temperature, reducing overall energy consumption and improving the anti-icing capability of the aircraft wing 1 under changing climatic conditions.

[0127] This application integrates a high-sensitivity temperature sensor 4 and a control device 5, which can monitor the temperature changes on the wing surface in real time. Based on the feedback from the temperature sensor 4, the control device 5 automatically optimizes the heating power, thereby improving the response speed of the anti-icing / de-icing system and significantly improving the efficiency of anti-icing / de-icing.

[0128] The technical features of the above embodiments can be combined in any way. For the sake of brevity, not all possible combinations of the technical features in the above embodiments are described. However, as long as there is no contradiction in the combination of these technical features, they should be considered to be within the scope of this specification.

[0129] The above embodiments merely illustrate several implementation methods of this application, and while the descriptions are relatively specific and detailed, they should not be construed as limiting the scope of the patent application. It should be noted that those skilled in the art can make various modifications and improvements without departing from the concept of this application, and these all fall within the protection scope of this application. Therefore, the protection scope of this patent application should be determined by the appended claims.

Claims

1. An aircraft anti-icing / de-icing system, characterized in that, This includes a zinc oxide / acetic acid superhydrophobic coating, a graphene heating device, a temperature sensor, a control device, and an onboard power supply; among which, The superhydrophobic coating and graphene heating device are respectively disposed on the outer and inner surfaces of the aircraft wing; The graphene heating device, temperature sensor, control device, and airborne power supply are electrically connected; the temperature sensor is used to collect temperature parameters of the aircraft wing surface and transmit the temperature parameters to the control device. When the temperature parameter is lower than the preset temperature, the control device controls the airborne power supply to supply power to the graphene heating device to start the graphene heating device. When the temperature parameter is not lower than the preset temperature, the control device controls the airborne power supply device to stop supplying power to the graphene heating device, so as to shut down the graphene heating device. The preparation of the zinc oxide / acetic acid superhydrophobic coating includes the following steps: S1. Epoxy resin and ethyl acetate are mixed and stirred to obtain the first solution; S2. Add zinc oxide to the first solution, heat and stir to obtain the second solution; S3. Add ethanol to the second solution, and perform stirring, cooling, ultrasonication and cooling treatment in sequence. Then add curing agent to the second solution and stir to obtain superhydrophobic spraying solution. In steps S1-S3, the mass ratio of zinc oxide, ethanol, epoxy resin, ethyl acetate and curing agent is 1:(1~2):(1~2):(3~8):(1 / 3~2 / 3). S4. Prepare a reaction solution by using ethanol:acetic acid:stearic acid in a mass ratio of (25~30):(3~5):(1~3); S5. The superhydrophobic spraying solution is sprayed onto the outer surface of the aircraft wing, cured, and then removed. After being placed in the reaction solution for a preset time, it is removed and cured to obtain a zinc oxide / acetic acid superhydrophobic coating.

2. The aircraft anti-icing / de-icing system according to claim 1, characterized in that, The graphene heating device includes a multilayer glass fiber prepreg and a graphene heating element, wherein the graphene heating element is disposed within the multilayer glass fiber prepreg.

3. The aircraft anti-icing / de-icing system according to claim 2, characterized in that, The graphene heating element includes a graphene film and electrodes.

4. The aircraft anti-icing / de-icing system according to claim 3, characterized in that, The sheet resistance R of the graphene film is 1Ω~3Ω.

5. The aircraft anti-icing / de-icing system according to claim 3, characterized in that, The electrode is a copper foil electrode with a thickness of 0.05 mm to 0.1 mm.

6. The aircraft anti-icing / de-icing system according to claim 3, characterized in that, The preparation of the graphene heating element includes the following steps: S10. Cut the graphene film and the electrode; S20. Fix the electrode on a single layer of glass fiber prepreg and evacuate the vacuum. S30. Next, the graphene film is attached to the single-layer glass fiber prepreg, and the graphene film is bonded to the electrode using conductive silver paste. After curing, a vacuum is drawn to obtain the graphene heating element.

7. The aircraft anti-icing / de-icing system according to any one of claims 1 to 6, characterized in that, The temperature sensor is located in the middle of the graphene heating device in the spanwise direction and in the chordwise direction between the graphene heating device and the aircraft wing.

8. The aircraft anti-icing / de-icing system according to any one of claims 1 to 6, characterized in that, The temperature sensor is a K-type thermocouple temperature sensor.

9. The aircraft anti-icing / de-icing system according to any one of claims 1 to 6, characterized in that, The control device includes a temperature monitoring module, a data analysis module, and a temperature control module; The temperature detection module acquires temperature data of the aircraft wing surface in real time through the temperature sensor to detect temperature changes; The data analysis module compares and analyzes the temperature data with the preset temperature to determine the prevention / elimination requirements; The temperature control module controls the heating power and time of the graphene heating device according to the prevention / elimination requirements.

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