Aircraft anti-icing / de-icing system

Abstract

The invention relates to an aircraft anti-icing / de-icing system. The system comprises a zinc oxide / acetic acid super-hydrophobic coating, a graphene heating device, a temperature sensor, a control device and an airborne power supply device, the super-hydrophobic coating and the graphene heating device are respectively arranged on the outer surface and the inner surface of an aircraft wing; the graphene heating device, the temperature sensor, the control device and the airborne power supply device are electrically connected; the temperature sensor is used for collecting temperature parameters of the surface of the aircraft wing and transmitting 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 device to supply power to the graphene heating device so as to start the graphene heating device; and when the temperature parameter is not lower than the preset temperature, the control device controls the onboard power supply device to stop supplying power to the graphene heating device so as to turn off the graphene heating device. The airplane anti-icing / de-icing system can reduce the strength of ice attached to the surface of the wing, and is uniform in heating, high in efficiency, high in heat energy utilization rate and low in energy consumption.

Description

Technical Field

[0001] The present application relates to the technical field of aircraft anti-icing and de-icing, and in particular to an aircraft anti-icing / de-icing system. Background Art

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

[0003] Traditional anti-icing / de-icing technology usually uses an electric heating anti-icing / de-icing system, which generally uses metal resistance wires. However, due to the limitations of material properties, the heating will be uneven, which may lead to higher efficiency in some areas of the wing, while other areas cannot meet the requirements of effective de-icing, resulting in the failure to remove ice and snow in some areas in time, affecting flight safety. At the same time, there are problems such as high energy consumption and high ice intensity on the wing surface. Summary of the invention

[0004] Based on this, in order to address the above problems, the present application provides an aircraft anti-icing / de-icing system that has uniform heat generation, low energy consumption, rapid response, and reduces the intensity of ice attached to the wing surface.

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

[0006] The super-hydrophobic coating and graphene heating device are respectively arranged on the outer surface and inner surface of the aircraft wing;

[0007] The graphene heating device, the temperature sensor, the control device and the airborne power supply device are electrically connected; the temperature sensor is used to collect the temperature parameters of the aircraft wing surface and transmit the temperature parameters to the control device;

[0008] When the temperature parameter is lower than a preset temperature, the control device controls the onboard power supply device to supply power to the graphene heating device to start the graphene heating device;

[0009] When the temperature parameter is not lower than the preset temperature, the control device controls the onboard power supply device to stop supplying power to the graphene heating device to turn off the graphene heating device.

[0010] In some embodiments, the preparation of the zinc oxide / acetic acid super-hydrophobic coating comprises the following steps:

[0011] S1, mixing and stirring the epoxy resin and ethyl acetate to obtain a first solution;

[0012] S2, adding zinc oxide to the first solution, heating and stirring to obtain a second solution;

[0013] S3, adding ethanol to the second solution, stirring, cooling, ultrasonic and cooling treatment in sequence, then adding a curing agent to the second solution, stirring and treating, to obtain a super-hydrophobic spray solution;

[0014] Wherein, 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, preparing a reaction solution according to the mass ratio of ethanol: acetic acid: stearic acid of (25-30): (3-5): (1-3);

[0016] S5, spraying the super-hydrophobic spray solution on the outer surface of the aircraft wing, taking it out after curing, placing it in a reaction solution to react for a preset time, taking it out, and curing it to obtain a zinc oxide / acetic acid super-hydrophobic coating.

[0017] In some embodiments, the graphene heating device includes multiple layers of glass fiber prepreg and a graphene heating element, and the graphene heating element is disposed in the multiple layers of glass fiber prepreg.

[0018] In some embodiments, the graphene heater includes a graphene film and an electrode.

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

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

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

[0022] S10, cutting the graphene film and the electrode;

[0023] S20, fixing the electrode on the single-layer glass fiber prepreg and evacuating the vacuum;

[0024] S30, then attaching the graphene film to the single-layer glass fiber prepreg, bonding the graphene film to the electrode using a conductive silver paste, curing, and evacuating to obtain a graphene heating element.

[0025] In some embodiments, the temperature sensor is located in the middle of the graphene heating device in the span direction and is located between the graphene heating device and the aircraft wing in the chord direction.

[0026] In some embodiments, the temperature sensor is a K-type 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 obtains the temperature data of the aircraft wing surface in real time through the temperature sensor to detect temperature changes;

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

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

[0031] The present application provides a zinc oxide / acetic acid super-hydrophobic coating on the surface of an aircraft wing. The coating can increase the contact angle between the aircraft wing surface and water, reduce the rolling angle, improve the rolling property of water droplets, effectively reduce the residence and accumulation of water on the aircraft wing surface, significantly reduce the formation of frost on the aircraft wing surface, and reduce the ice attachment strength of the aircraft wing surface, making the ice layer easier to fall off.

[0032] The present application provides a graphene heating device, which generates heat evenly, so that ice and snow in various areas of the wing can be removed in time, and the surface temperature of the wing can be raised to the required temperature in a short time, with high thermal energy utilization and low energy consumption.

[0033] This application can monitor the surface temperature change of the aircraft wing in real time by setting a temperature sensor and a control device, and accurately control the opening and closing of the graphene heating device according to the comparison result of the temperature parameter and the preset temperature. When the surface temperature of the aircraft wing reaches or exceeds the preset temperature, the heating device automatically stops working, avoiding unnecessary energy consumption, thereby achieving energy saving. At the same time, the heating power is automatically adjusted and optimized according to the actual situation, thereby improving the anti-icing ability of the aircraft wing under changing climate conditions. BRIEF DESCRIPTION OF THE DRAWINGS

[0034] Figure 1 It is an overall schematic diagram and a partially enlarged diagram of an aircraft anti-icing / de-icing system in one embodiment of the present application.

[0035] Figure 2 This is a flow chart of the preparation process of a zinc oxide / acetic acid super-hydrophobic coating in an embodiment of the present application.

[0036] Figure 3 Schematic diagram of the overall graphene heating device in one embodiment of the present application.

[0037] Figure 4 Schematic diagram of the structure of a graphene heating element in one embodiment of the present application.

[0038] Description of Reference Numerals

[0039] 1. Aircraft wing; 2. Zinc oxide / acetic acid super hydrophobic 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 device;

[0040] D1, thickness of graphene heating device; L2, length of graphene film; b, interval between two adjacent graphene films. DETAILED DESCRIPTION

[0041] References to embodiments of the present application will now be provided in detail, one or more embodiments of which are described below. Each embodiment is provided as an explanation rather than a limitation of the present application. In fact, it will be apparent to those skilled in the art that various modifications and variations may be made to the present application without departing from the scope or spirit of the present application. For example, a feature described or described as part of one embodiment may be used in another embodiment to produce a further embodiment.

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

[0043] In the present 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, when it comes to numerical ranges, unless otherwise specified, the above numerical ranges are deemed to be continuous and include the minimum and maximum values ​​of the range, as well as each value between such minimum and maximum values. Further, when a range refers to an integer, each integer between the minimum and maximum values ​​of the range is included. In addition, when multiple ranges are provided to describe features or characteristics, the ranges can be merged. In other words, unless otherwise specified, all ranges disclosed herein should be understood to include any and all subranges included therein.

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

[0046] Unless otherwise specified, all embodiments and optional embodiments of the present application can be combined with each other to form a new technical solution.

[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 of the present application may be performed sequentially or randomly, preferably sequentially. For example, the method includes steps (a) and (b), which means that the method may include steps (a) and (b) performed sequentially, or may include steps (b) and (a) performed sequentially. For example, mentioning that the method may also include step (c) means that step (c) may be added to the method in any order, for example, the method may include steps (a), (b) and (c), or may include steps (a), (c) and (b), or may include steps (c), (a) and (b), etc.

[0049] If there is no special explanation, the "include" and "comprising" mentioned in this application are open-ended or closed-ended. For example, the "include" and "comprising" may mean that other components not listed may also be included or only the listed components may be included or only the listed components may be included.

[0050] If not specifically stated, in this application, the term "or" is inclusive. For example, the phrase "A or B" means "A, B, or both A and B". More specifically, any of the following conditions satisfies the condition "A or B": 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, the present application provides an aircraft anti-icing / de-icing system, which includes a zinc oxide / acetic acid super-hydrophobic coating 2, a graphene heating device 3, a temperature sensor 4, a control device 5, and an onboard power supply device 6. Wherein, the super-hydrophobic coating and the graphene heating device 3 are respectively arranged on the outer surface and the inner surface of the aircraft wing 1. The graphene heating device 3, the temperature sensor 4, the control device 5, and the onboard power supply device 6 are electrically connected. The temperature sensor 4 is used to collect the temperature parameters of the surface of the aircraft wing 1 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 onboard 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 onboard power supply device 6 to stop supplying power to the graphene heating device 3 to turn off the graphene heating device 3 .

[0054] By adopting the aircraft anti-icing / de-icing system provided in the present application, low-temperature anti-icing / de-icing of aircraft wings can be achieved under icing weather conditions, the temperature changes on the wing surface can be detected in real time, and the heating rate and surface temperature of the wing surface can be adjusted in real time, 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 area, 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, and the control device 5 compares and analyzes the temperature data with the preset temperature (the anti-icing threshold, the temperature that may cause frost formation). Once it is detected that the temperature parameter is 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, and the graphene heating device 3 begins to generate heat to prevent frost formation.

[0056] The aircraft anti-icing / de-icing system provided by the present application adopts a wet anti-icing strategy to perform low-heat anti-icing. The control device 5 detects the surface temperature of the aircraft wing 1 in real time. When the graphene heating device 3 is heated to a preset temperature, the control device 5 controls the power and switch of the onboard power supply device 6 to keep 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 is detected 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 to turn off the graphene heating device 3 and complete the low-heat anti-icing.

[0057] It is understandable 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 the flight of the aircraft, but is only heated to the ice melting temperature, a water film flows on the wing surface, and the water on the wing surface cannot completely evaporate.

[0058] "Low-heat anti-icing" in this application refers to an anti-icing strategy in which, in order to reduce energy consumption, a lower heating power is used in the electric heating anti-icing of aircraft, and the temperature is controlled at the ice melting temperature by PID temperature control. For example, the wing surface temperature is controlled to reach 15°C to complete the wing anti-icing immediately.

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

[0060] S1. Mixing and stirring epoxy resin and ethyl acetate to obtain a first solution.

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

[0062] S3, adding ethanol to the second solution, stirring, cooling, ultrasonic and cooling treatment are carried out in sequence, and then a curing agent is added to the second solution, and after stirring, a super-hydrophobic spray solution is obtained.

[0063] Among them, 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 according to the mass ratio of ethanol: acetic acid: stearic acid of (25-30): (3-5): (1-3).

[0065] S5, spraying the super-hydrophobic spray solution on the outer surface of the aircraft wing 1, taking it out after curing, placing it in a reaction solution to react for a preset time, taking it out, and curing it to obtain a zinc oxide / acetic acid super-hydrophobic coating 2.

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

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

[0068] In a specific embodiment, step S2 is: adding zinc oxide to the first solution, heating it to 60° C. with a magnetic stirrer and stirring it for 20 minutes to obtain a second solution.

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

[0070] In a specific embodiment, step S3 is: adding ethanol to the second solution, stirring with a magnetic stirrer for 10 minutes and then cooling the solution, after the cooling treatment is completed, ultrasonic treatment is performed by an ultrasonic cell crusher, and after the ultrasonic treatment, magnetic stirring is continued for 10 minutes to cool the solution, and then a curing agent D230 is added to the second solution, and after stirring for 20 minutes, a super hydrophobic spray solution is obtained.

[0071] It can be understood that an ultrasonic cell crusher refers to: a device that uses ultrasonic vibration to mix, disperse and crush solid particles in a liquid, and is often used to improve the uniformity of a solution.

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

[0073] In some embodiments, the distance of spraying in step S5 is 20cm~30cm, including but not limited to 20cm, 22cm, 24cm, 26cm, 28cm, 30cm. The number of spray layers is 10~20 layers. In a specific embodiment, step S5 is: spray the super hydrophobic spray solution on the outer surface of the aircraft wing 1, the spraying distance is 25cm, a total of 15 layers are sprayed, put into an oven at 80°C for 5h and then take out, place in the reaction solution, take out after 6min, continue to put into an oven at 80°C for 5h, and obtain a zinc oxide / acetic acid super hydrophobic coating 2.

[0074] In some embodiments, the graphene heating device 3 includes multiple layers of glass fiber prepreg 31 and a graphene heating element 32 , and the graphene heating element 32 is disposed in the multiple layers of 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 square resistance R of the graphene film 321 is 1Ω to 3Ω. Preferably, the square resistance R of the graphene film 321 is 1Ω.

[0077] It is understood that sheet resistance refers to the resistance of a thin film material, which is the ratio between the film current and the voltage, and is expressed in ohms per square. In this article, sheet resistance R=1 represents the resistance characteristic of the graphene heating material.

[0078] In some embodiments, the 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, cutting the graphene film 321 and the electrode 322;

[0081] S20, fixing the electrode 322 on the single-layer glass fiber prepreg 31, and evacuating the vacuum;

[0082] S30, then attaching the graphene film 321 to the single-layer glass fiber prepreg 31, using conductive silver paste to bond the graphene film 321 to the electrode 322, curing treatment, and vacuuming to obtain the graphene heating element 32.

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

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

[0085] Fix the copper foil electrode 322 on the single-layer glass fiber prepreg 31 according to the circuit design diagram, and evacuate the vacuum to 80 kPa for 10 minutes to ensure that the copper foil electrode 322 and the single-layer glass fiber prepreg 31 are closely attached.

[0086] Then, 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, and the graphene film 321 and the copper foil electrode 322 are tightly bonded using conductive silver paste. The graphene film 321 is cured at room temperature for 30 minutes, and the vacuum is evacuated to 80 kPa and maintained for 10 minutes, so that the graphene film 321 and the single-layer glass fiber prepreg 31 are tightly attached to obtain the graphene heating element 32.

[0087] In some embodiments, the graphene heating device 3 is prepared by the following preparation method, comprising the following steps:

[0088] S100, cutting the multi-layer glass fiber prepreg 31 for standby use;

[0089] S200, apply a release agent on the mold surface and place it in place to pre-fabricate a vacuum bag;

[0090] S300, laying multiple layers of glass fiber prepreg 31 on the mold surface multiple times, and performing vacuum treatment after each laying;

[0091] S400, then laying a single layer of glass fiber prepreg 31, glass fiber prepreg 31 with graphene heating element 32 and an isolation film, and vacuuming;

[0092] S500, laying multiple layers of glass fiber prepreg 31 on the surface of the isolation film away from the graphene heating element 32, and performing vacuum treatment;

[0093] S600, trim the excess edge of the prepreg and reserve the edge for demoulding process;

[0094] S700, laying an isolation film, a breathable felt and a vacuum bag film in sequence, and performing vacuum treatment;

[0095] S800, placing in an oven, heating at 120±10°C for 2.5±0.5h, then cooling and demoulding to obtain a graphene heating device 3.

[0096] In some embodiments, the vacuuming process in steps S100 to S800 is to evacuate the vacuum to a degree 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 thickness D2 of the graphene film 321 is 0.08 mm, the length L2 is 336 mm, the width W2 is 7 mm, and the interval b between two adjacent graphene films 321 is 3 mm. In some embodiments, the thickness D3 of the electrode 322 is 0.08 mm, and the width W3 is 7 mm.

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

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

[0101] S100, cutting the multi-layer glass fiber prepreg 31 with a single layer thickness of 0.2 mm for standby use; numbering the multi-layer glass fiber prepreg 31 as #1 to #10, wherein the #3 glass fiber prepreg 31 refers to the glass fiber prepreg 31 with the graphene heating element 32 attached thereto;

[0102] S200, apply release agent on the mold surface and leave it for 30 minutes to pre-make a vacuum bag;

[0103] S300, firstly lay 3 layers of glass fiber prepreg 31 (#10, #9, #8) on the mold surface, and perform vacuum treatment, and then continue to lay 3 layers of glass fiber prepreg 31 (#7, #6, #5), and perform vacuum treatment;

[0104] S400, then lay #4, #3 glass fiber prepreg 31 and isolation film, and perform vacuum treatment;

[0105] S500, laying two layers of glass fiber prepreg 31 (#2, #1) on the surface of the isolation film away from the graphene heating element 32, and performing vacuum treatment;

[0106] S600, cutting the excess edge of the glass fiber prepreg 31, and reserving a demoulding process edge;

[0107] S700, laying an isolation film, a breathable felt and a vacuum bag film in sequence, and performing vacuum treatment;

[0108] S800, placing the mold in an oven, heating at 120° C. for 2.5 h, cooling and demoulding, and obtaining a 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 span direction and is located between the graphene heating device 3 and the aircraft wing 1 in the chord direction.

[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 the K-type thermocouple temperature sensors 4 is not particularly limited in the present application and can be adjusted according to actual needs.

[0111] In a specific example, the number of the K-type thermocouple temperature sensors 4 is 5. The 5 temperature sensors 4 are evenly distributed in the middle of the graphene heating device 3 in the span direction and are located between the graphene heating device 3 and the aircraft wing 1 in the chord direction.

[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 obtains the temperature data of the surface of the aircraft wing 1 in real time through the temperature sensor 4, so as to detect the temperature change in real time and judge the current flight environment and the icing risk of the aircraft surface.

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

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

[0116] It can be understood that controlling the heating power specifically means that based on the data obtained 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 accurately control the heating power of the graphene heating device 3. Through this process, the control device 5 can achieve accurate temperature rise control to ensure that the aircraft surface is within a suitable temperature range to prevent the formation of frost.

[0117] Optimizing heating efficiency specifically means that the control device 5 can also automatically adjust the heating power and heating time of the graphene heating device 3 according to environmental changes and the flight status of the aircraft, optimize the heating effect, and reduce energy consumption. This makes the aircraft anti-icing / de-icing system provided by the present application not only effective in anti-icing, but also improves the overall energy efficiency.

[0118] The onboard power supply device 6 in the present 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 part of the system. The onboard power supply device 6 can adjust the power in real time according to the instructions transmitted by the control device 5; when there is a need for anti-icing, the onboard power supply device 6 can provide up to 700W of power for the graphene heating device 3 of the corresponding size in the present application, that is, 10 kW / m 2 After the surface temperature of the aircraft wing 1 during the heating process approaches the preset temperature, the onboard power supply device 6 will reduce the power output size, reduce the impact of temperature shock, and better control the temperature within the set range.

[0119] It is understood that the heating power density refers to the heating power per unit area, which is usually expressed in watts per square meter (W / m²). The 10 kW / m² mentioned in the article represents the efficient heating capacity of the graphene heating device 3.

[0120] In some embodiments, the aircraft wing 1 is made of nickel-chromium alloy clad iron material, which provides the necessary mechanical strength and support capacity for the anti-icing / de-icing system provided by the present application, and provides a stable matrix for the super-hydrophobic coating and the graphene heating device 3, ensuring stability under various flight conditions. The nickel-chromium alloy clad iron has good 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 embodiments, the installation process of the temperature sensor 4 is as follows: the graphene heating device 3 is pasted to the leading edge of the body of the aircraft wing model with epoxy glue, and clamped with a pad and a C-type clamp to ensure a close fit, and cured at room temperature for 48 hours. Use 3M low-temperature double-sided tape and aluminum foil to fix the wire and the temperature sensor 4 line to the surface of the aircraft wing model, extending from the bottom of the model. The temperature measuring points of the temperature sensor 4 are fixed to the corresponding positions of the graphene heating device 3 with K-3880 epoxy thermal conductive glue according to the number, and a small amount of aluminum foil is used to fix the position to avoid displacement during the installation of the iron package; the edge of the graphene heating device 3 installed on the aircraft wing model is pasted with a release cloth to deal with the overflow glue; K-3880 epoxy thermal conductive glue is evenly applied on the surface of the graphene heating device 3; the nickel-chromium alloy iron package is tightly pasted to the graphene heating device 3, and clamped with a pad and a C-type clamp to ensure a close fit, and cured at room temperature for 72 hours; the installation of the temperature sensor 4 is completed.

[0122] As shown in Table 1 below, it is a performance test table of the zinc oxide / acetic acid super-hydrophobic coating 2 provided in the present application.

[0123]

[0124] According to the data in Table 1, the present application provides a zinc oxide / acetic acid super-hydrophobic coating 2 on the surface of the aircraft wing 1. The coating can increase the contact angle between the surface of the aircraft wing 1 and water, reduce the rolling angle, and improve the rolling property of water droplets. It can effectively reduce the residence 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 ice attachment strength on the surface of the aircraft wing 1, so that the ice layer is easier to fall off.

[0125] The present application sets up a graphene heating device 3, which generates heat evenly, so that ice and snow in various areas of the wing can be removed in time, and the surface temperature of the wing can be raised to the required temperature in a short time, with high heating efficiency, high thermal energy utilization rate and low energy consumption.

[0126] The present application can monitor the surface temperature change of the aircraft wing 1 in real time by setting the temperature sensor 4 and the control device 5, and accurately control the opening and closing of the graphene heating device 3 according to the comparison result of the temperature parameter and the preset temperature. 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, thereby achieving energy saving. At the same time, the heating power is automatically adjusted, and dynamically adjusted according to the change of the wing surface temperature, which reduces the overall energy consumption and improves the anti-icing ability of the aircraft wing 1 under changing climate conditions.

[0127] The present application integrates a highly sensitive temperature sensor 4 and a control device 5, which can monitor the temperature changes on the wing surface in real time. The control device 5 automatically optimizes the heating power according to the feedback from the temperature sensor 4, thereby improving the response speed of the anti-icing / de-icing system and greatly improving the efficiency of the anti-icing / de-icing.

[0128] The technical features of the above embodiments may be combined arbitrarily. To make the description concise, 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 only express several implementation methods of the present application, and the descriptions thereof are relatively specific and detailed, but they cannot be understood as limiting the scope of the patent application. It should be pointed out that, for a person of ordinary skill in the art, several variations and improvements can be made without departing from the concept of the present application, and these all belong to the protection scope of the present application. Therefore, the protection scope of the patent application shall be subject to the attached claims.

Claims

1. An aircraft anti-icing / de-icing system, characterized in that: It includes a zinc oxide / acetic acid super-hydrophobic coating, a graphene heating device, a temperature sensor, a control device, and an airborne power supply device; wherein, The super-hydrophobic coating and the graphene heating device are respectively arranged on the outer surface and the inner surface of the aircraft wing; The graphene heating device, the temperature sensor, the control device and the airborne power supply device are electrically connected; the temperature sensor is used to collect the temperature parameters of the aircraft wing surface and transmit the temperature parameters to the control device; When the temperature parameter is lower than a preset temperature, the control device controls the onboard power supply device 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 onboard power supply device to stop supplying power to the graphene heating device to turn off the graphene heating device.

2. The aircraft anti-icing / de-icing system according to claim 1, characterized in that: The preparation of the zinc oxide / acetic acid super-hydrophobic coating comprises the following steps: S1, mixing and stirring the epoxy resin and ethyl acetate to obtain a first solution; S2, adding zinc oxide to the first solution, heating and stirring to obtain a second solution; S3, adding ethanol to the second solution, stirring, cooling, ultrasonic and cooling treatment in sequence, then adding a curing agent to the second solution, stirring and treating to obtain a super-hydrophobic spray solution; Wherein, in steps S1-S3, the mass ratio of the zinc oxide, ethanol, epoxy resin, ethyl acetate and the curing agent is 1: (1-2): (1-2): (3-8): (1 / 3-2 / 3); S4, preparing a reaction solution according to the mass ratio of ethanol: acetic acid: stearic acid of (25-30): (3-5): (1-3); S5, spraying the super-hydrophobic spray solution on the outer surface of the aircraft wing, taking it out after curing, placing it in the reaction solution to react for a preset time, taking it out, and curing it to obtain a zinc oxide / acetic acid super-hydrophobic coating.

3. The aircraft anti-icing / de-icing system according to claim 1, characterized in that: The graphene heating device comprises a multi-layer glass fiber prepreg and a graphene heating element, and the graphene heating element is arranged in the multi-layer glass fiber prepreg.

4. The aircraft anti-icing / de-icing system according to claim 3, characterized in that: The graphene heating element comprises a graphene film and an electrode.

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

6. The aircraft anti-icing / de-icing system according to claim 4, characterized in that: The electrode is a copper foil electrode, and the thickness of the copper foil electrode is 0.05 mm to 0.1 mm.

7. The aircraft anti-icing / de-icing system according to claim 4, characterized in that: The preparation of the graphene heating element comprises the following steps: S10, cutting the graphene film and the electrode; S20, fixing the electrode on a single layer of glass fiber prepreg and evacuating the electrode; S30, then attaching the graphene film to the single-layer glass fiber prepreg, bonding the graphene film to the electrode using a conductive silver paste, curing, and evacuating to obtain a graphene heating element.

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

9. The aircraft anti-icing / de-icing system according to any one of claims 1 to 7, characterized in that: The temperature sensor is a K-type thermocouple temperature sensor.

10. The aircraft anti-icing / de-icing system according to any one of claims 1 to 7, 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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