Anti-icing structure function integrated wing electric heating material, preparation method and application thereof

Abstract

The application provides an electric heating material for an ice-preventing and removing structure-function integrated wing and a preparation method and application thereof, and relates to the technical field of aerospace ice-preventing and removing, and comprises the following steps: taking a fiber cloth obtained by braiding pre-oxidized yarn and carbon fibers as a raw material, performing carbonization treatment on the fiber cloth to obtain an electric heating material, and performing encapsulation treatment on the electric heating material to obtain the electric heating material for the ice-preventing and removing structure-function integrated wing; wherein the pre-oxidized yarn is PAN-based pre-oxidized yarn. The preparation method of the electric heating material for the ice-preventing and removing structure-function integrated wing can significantly improve the electric heating efficiency of the aircraft wing while uniformly heating the material.

Description

TECHNICAL FIELD

[0001] The present application relates to the field of aerospace deicing technology, in particular to an electric heating material for a deicing structure and function integrated wing and a preparation method and application thereof. BACKGROUND

[0002] Ice formation on the surface of an aircraft refers to the phenomenon that the surface of the aircraft collides with supercooled water droplets in the atmosphere under meteorological conditions of low temperature and high supercooled water droplet content to form an ice layer. Currently, the key parts prone to icing of an aircraft mainly include the surface of the wing, the horizontal tail, the windshield, the atmospheric data sensor, and the engine inlet, etc. Among them, the wing is the main part for generating lift of the aircraft, and the ice accumulation on the wing will cause the surface flatness to decrease and the shape to change, which will destroy the airflow on the surface of the aircraft, directly affecting the lift-drag ratio and the lift coefficient of the aircraft, causing the take-off and landing performance to decrease, and hindering the aircraft to generate sufficient lift. Through analysis of flight test data and ice wind tunnel test data: when the outer skin of the aircraft wing generates an ice layer, the lift of the aircraft will decrease to 70% of the original, and the drag will increase to 140% of the original. This will seriously endanger the flight safety of the aircraft, increase the difficulty of the pilot's control, and may cause a stall phenomenon, and even a crash accident.

[0003] In the prior art, the aircraft wing deicing system is mainly divided into three categories: solution deicing system, external force deicing system, and thermodynamic deicing system. Among them, the solution deicing can only be used to prevent the wing from icing, mainly to study the preparation of antifreeze solution, and to spray on the leading edge of the wing through a high-pressure pump. The disadvantage of this method is that it can only deal with short-term icing. If the aircraft is in an icing environment for a long time, this method is not applicable; the external force deicing mainly refers to pulse deicing. The pulse deicing method is to discharge the capacitor group to the coil to generate a strong magnetic field, which generates a mechanical force with high amplitude and extremely short duration on the aircraft skin, so that the ice breaks and falls off. However, in practical application, the pulse deicing method has obvious disadvantages: the relationship between the parameters of the pulse circuit is complex, and it is difficult to obtain the optimal pulse circuit and the calculation of the deicing electric pulse excitation. The principle of the thermodynamic deicing system is mainly to use high heat to melt and evaporate the ice or directly sublimate, which is limited by the size of the heat flow.

[0004] With the continuous development of deicing technology, researchers have proposed many new deicing technologies, among which the most representative is the electric heating deicing method. The principle is to convert electrical energy into heat energy, and then heat the aircraft components to achieve the purpose of deicing. At present, the electric heating deicing has the advantages of simple structure, small size, light weight, low energy consumption, high efficiency, and convenient maintenance, etc., and has become the most widely used deicing method. In response to severe environmental weather or the surface area of complex aircraft components, it is necessary to use electric heating deicing.

[0005] Therefore, modern ice prevention technology is mainly focused on electric heating ice prevention, and electric heating ice prevention is therefore known as the most promising ice prevention method. On a traditional alloy structure aircraft, due to the high thermal conductivity of the metal, the electric heating method usually uses heating pipes or copper meshes, which are embedded in the aircraft interior and can achieve the effect by being electrified. At present, composite aircraft are developing rapidly, and there is a trend of using all composite materials for wings, fuselages and other parts. Compared with metal materials, composite materials are lighter in weight, can reduce aircraft fuel consumption and improve operating efficiency, and are excellent in corrosion resistance and suitable for high humidity and salt spray environments. Due to its natural electrical insulation performance, composite materials reduce the risk of electric leakage and short circuit and reduce the influence of electromagnetic interference, which makes composite materials more advantageous in efficient, safe and lightweight aviation applications. However, due to the unique thermal conductivity of composite materials, if traditional heating pipes or copper meshes or other electric heating or wire heating materials are used, it may cause uneven heating of the material, low heating efficiency, large thermal stress and fatigue and other adverse consequences.

[0006] In view of this, the present application is proposed. SUMMARY

[0007] One of the purposes of the present application is to provide a preparation method of an electric heating material for an ice prevention structure function integrated wing, which at least solves one of the technical problems in the prior art. The preparation method of the electric heating material for the ice prevention structure function integrated wing provided by the present application can significantly improve the electric heating efficiency of the aircraft wing while the material heats evenly.

[0008] The second purpose of the present application is to provide an electric heating material for an ice prevention structure function integrated wing prepared by the preparation method of the electric heating material for the ice prevention structure function integrated wing.

[0009] The third purpose of the present application is to provide a preparation method of an electric heating material for an ice prevention structure function integrated wing or an application of the electric heating material for the ice prevention structure function integrated wing in the preparation of an electric heating ice prevention structure function integrated wing.

[0010] In order to achieve the above-mentioned purposes of the present application, the following technical solutions are adopted:

[0011] In a first aspect, the present application provides a preparation method of an electric heating material for an ice prevention structure function integrated wing, comprising the following steps:

[0012] The fiber cloth obtained by braiding pre-oxidized yarn and carbon fiber is used as a raw material, the fiber cloth is subjected to carbonization treatment to obtain an electric heating material, and the electric heating material is subjected to encapsulation treatment to obtain the electric heating material for the ice prevention structure function integrated wing.

[0013] The pre-oxidized yarn is a PAN-based pre-oxidized yarn.

[0014] Further, the fiber cloth is a woven plain cloth;

[0015] Preferably, the volume content of the pre-oxidized fiber of the woven plain cloth is 20%-40%;

[0016] Preferably, the thickness of the woven plain cloth is 400-500 μm.

[0017] Further, the first carbonization treatment is performed on the first fiber cloth to obtain the electrothermal material for the leading edge of the wing;

[0018] The second carbonization treatment is performed on the second fiber cloth to obtain the electrothermal material for the upper surface of the wing;

[0019] The third carbonization treatment is performed on the third fiber cloth to obtain the electrothermal material for the lower surface of the wing;

[0020] The processing temperature of the first carbonization treatment, the second carbonization treatment and the third carbonization treatment is different.

[0021] Further, the first fiber cloth, the second fiber cloth and the third fiber cloth are all woven plain cloths woven by pre-oxidized fibers and carbon fibers.

[0022] Further, the first carbonization process comprises: under the inert gas atmosphere, heating at a rate of 4.5-5.5 ℃ / min to 250-350 ℃, and then heating at a rate of 2.5-3.5 ℃ / min to the first carbonization temperature, and performing the first carbonization treatment;

[0023] Preferably, the first carbonization temperature is 750-850 ℃, and the time of the first carbonization treatment is 60-80 min;

[0024] Preferably, before the first carbonization treatment, the first fiber cloth is sequentially subjected to ultrasonic cleaning and drying treatment, the ultrasonic cleaning time is preferably 25-35 min, the drying temperature is preferably 75-85 ℃, and the drying time is preferably 0.5-1.5 h;

[0025] Preferably, after the first carbonization treatment, the electrothermal material for the leading edge of the wing is sequentially applied with conductive silver paste and copper tape with terminal.

[0026] Further, the second carbonization process comprises: under the inert gas atmosphere, heating at a rate of 4.5-5.5 ℃ / min to 250-350 ℃, and then heating at a rate of 2.5-3.5 ℃ / min to the second carbonization temperature, and performing the second carbonization treatment;

[0027] Preferably, the second carbonization temperature is 650-750℃, and the second carbonization treatment time is 50-70min.

[0028] Preferably, before the second carbonization treatment, the second fiber cloth is sequentially subjected to ultrasonic cleaning and drying treatment, the ultrasonic cleaning time is preferably 25-35min, the drying temperature is preferably 75-85℃, and the drying time is preferably 0.5-1.5h.

[0029] Preferably, after the second carbonization treatment, conductive silver paste and copper tape with terminal are sequentially applied to the electrothermal material for the upper wing surface of the wing.

[0030] Further, the third carbonization treatment process comprises: under the inert gas atmosphere, heating to 250-350℃ at a rate of 4.5-5.5℃ / min, and then heating to a third carbonization temperature at a rate of 2.5-3.5℃ / min, and performing third carbonization treatment.

[0031] Preferably, the third carbonization temperature is 550-650℃, and the third carbonization treatment time is 50-70min.

[0032] Preferably, before the third carbonization treatment, the third fiber cloth is sequentially subjected to ultrasonic cleaning and drying treatment, the ultrasonic cleaning time is preferably 25-35min, the drying temperature is preferably 75-85℃, and the drying time is preferably 0.5-1.5h.

[0033] Preferably, after the third carbonization treatment, conductive silver paste and copper tape with terminal are sequentially applied to the electrothermal material for the lower wing surface of the wing.

[0034] In a second aspect, the present application provides an electrothermal material for an ice-preventing and structure-function integrated wing prepared by the preparation method of the electrothermal material.

[0035] In a third aspect, the present application provides an application of the preparation method of the electrothermal material for an ice-preventing and structure-function integrated wing or the electrothermal material for an ice-preventing and structure-function integrated wing in the preparation of an electrothermal ice-preventing and structure-function integrated wing.

[0036] Further, the electrothermal ice-preventing and structure-function integrated wing is provided as a multi-layer structure, which comprises, from the outside to the inside, an outer skin, an upper insulating layer, an electric heating layer, a lower insulating layer, and an inner skin, and the electric heating layer is prepared by the electrothermal material for an ice-preventing and structure-function integrated wing.

[0037] Preferably, the upper insulating layer and the lower insulating layer each comprise a glass fiber composite material.

[0038] Preferably, the inner skin and the outer skin each comprise a unidirectional carbon fiber composite laminate;

[0039] Preferably, the inner surface of the outer skin has a carbon nanotube / reduced graphene oxide heat-conducting coating;

[0040] Preferably, the inner surface of the inner skin has a thermal insulation layer, and the electric heating layer is powered and heated by a pair of copper foil wires leading out from both ends of the electric heating layer;

[0041] Preferably, the wing is integrally formed by a heat press tank process.

[0042] Preferably, the heat press tank process comprises the following steps: heating to a first temperature at 200-300 Pa, first temperature holding for a first time, then heating to a second temperature, second temperature holding for a second time, and then temperature reduction to room temperature.

[0043] Preferably, the first temperature is 80-100 DEG C, and the first time is 55-65 min.

[0044] Preferably, the second temperature is 120-140 DEG C, and the second time is 110-130 min.

[0045] Compared with the prior art, the present application has the following beneficial effects:

[0046] The preparation method of the anti-icing structure and function integrated wing electric heating material provided by the present application uses pre-oxidized yarn and carbon fiber woven fabric as raw materials, uses pre-oxidized yarn and carbon fiber woven fabric after carbonization treatment as a conductive and heat-conductive reinforcing phase, and uses an optimized carbonization process to prepare the electric heating material. The electric heating material can significantly improve the electric heating efficiency of the aircraft wing while the material heats evenly. DETAILED DESCRIPTION

[0047] Unless otherwise defined herein, scientific and technical terms used in connection with the present application shall have the meanings that are commonly understood by those of ordinary skill in the art. Clear indications to the contrary are required to establish that any term in this application is intended to have a different meaning from that understood by those of ordinary skill in the art. In this application, the use of "or" means "and / or" unless otherwise stated. Furthermore, the use of the term "including", as well as other forms, such as "include", is not limiting.

[0048] The technical solutions of the present application will be described below in conjunction with the embodiments. Obviously, the described embodiments are only a part of the embodiments of the present application, rather than all the embodiments. Based on the embodiments in the present application, all other embodiments obtained by those of ordinary skill in the art without creative labor are within the scope of protection of the present application.

[0049] The application provides a preparation method of an electric heating material for an ice-preventing and structure-function integrated wing.

[0050] The electric heating material is obtained by carbonizing a fiber cloth obtained by weaving pre-oxidized filaments and carbon fibers, and packaging the electric heating material.

[0051] In the application, the fiber cloth obtained by weaving pre-oxidized filaments and carbon fibers is used as a raw material, the fiber cloth obtained by weaving pre-oxidized filaments and carbon fibers is carbonized at a high temperature to serve as a conductive and heat-conductive reinforcing phase, and an optimized carbonization process is used to prepare the electric heating material.

[0052] In some preferred embodiments, the fiber cloth is a woven plain cloth.

[0053] Preferably, the woven plain cloth has a pre-oxidized filament volume content of 20% to 40%, for example, 20%, 25%, 30%, 35%, 40%, or the like.

[0054] In the application, to meet the strength and heating performance requirements of the wing electric heating sheet, the pre-oxidized filament volume fraction in the fiber cloth is between 20% and 40%.

[0055] Preferably, the woven plain cloth has a thickness of 400 to 500 μm, for example, 400 μm, 450 μm, 500 μm, or the like.

[0056] In some preferred embodiments, a first fiber cloth is used as a raw material, a first carbonization treatment is performed, and an electric heating material for a wing leading edge is obtained.

[0057] A second fiber cloth is used as a raw material, a second carbonization treatment is performed, and an electric heating material for a wing upper surface is obtained.

[0058] A third fiber cloth is used as a raw material, a third carbonization treatment is performed, and an electric heating material for a wing lower surface is obtained.

[0059] The first carbonization treatment, the second carbonization treatment, and the third carbonization treatment have different treatment temperatures.

[0060] The electric heating material for the wing leading edge, the electric heating material for the wing upper surface, and the electric heating material for the wing lower surface are packaged to obtain the electric heating material for the ice-preventing and structure-function integrated wing.

[0061] In the present application, according to different heating partitions of the wing, the wing heating partitions are: wing leading edge, wing upper surface and wing lower surface, three pieces of fiber cloth are carbonized at different temperatures respectively to obtain wing leading edge electric heating material, wing upper surface electric heating material and wing lower surface electric heating material, and different carbonization processes are adopted according to different required heating power of the wing deicing part to meet the requirement of different resistivity.

[0062] In the present application, high-temperature carbonization is adopted, the fiber cloth is placed into a high-temperature vacuum pyrolysis furnace, Ar gas is introduced as a protective gas after vacuumizing, and different carbonization processes are adopted according to different required heating performance and strength of the heating sheet of different heating partitions of the wing.

[0063] In some preferred embodiments, the first fiber cloth, the second fiber cloth and the third fiber cloth are all woven plain cloth woven by pre-oxidized yarn and carbon fiber, wherein the volume content of the pre-oxidized yarn of the woven plain cloth is 20%-40%, and the thickness of the woven plain cloth is 400-500 μm.

[0064] In some preferred embodiments, the first carbonization process comprises: heating at a rate of 4.5-5.5 ℃ / min (for example, it can be 4.5 ℃ / min, 5 ℃ / min, 5.5 ℃ / min, etc.) to 250-350 ℃ (for example, it can be 250 ℃, 300 ℃, 350 ℃, etc.), and then heating at a rate of 2.5-3.5 ℃ / min (for example, it can be 2.5 ℃ / min, 3 ℃ / min, 3.5 ℃ / min, etc.) to the first carbonization temperature, and performing first carbonization treatment;

[0065] Preferably, the first carbonization temperature is 750-850 ℃ (for example, it can be 750 ℃, 800 ℃, 850 ℃, etc.), and the first carbonization treatment time is 60-80 min (for example, it can be 60 min, 70 min, 80 min, etc.);

[0066] Preferably, before the first carbonization treatment, the first fiber cloth is sequentially subjected to ultrasonic cleaning and drying treatment, the ultrasonic cleaning time is preferably 25-35 min (for example, it can be 25 min, 30 min, 35 min, etc.), the drying temperature is preferably 75-85 ℃ (for example, it can be 75 ℃, 80 ℃, 85 ℃, etc.), and the drying time is preferably 0.5-1.5 h (for example, it can be 0.5 h, 1 h, 1.5 h, etc.).

[0067] Preferably, after the first carbonization treatment, conductive silver paste and copper tape with a terminal are sequentially applied to the electric heating material for the wing leading edge.

[0068] In some preferred embodiments, the second carbonization process comprises: heating to 250-350℃, for example 250℃, 300℃, 350℃, etc., at a rate of 4.5-5.5℃ / min, for example 4.5℃ / min, 5℃ / min, 5.5℃ / min, etc., and then heating to a second carbonization temperature at a rate of 2.5-3.5℃ / min, for example 2.5℃ / min, 3℃ / min, 3.5℃ / min, etc., for the second carbonization treatment;

[0069] Preferably, the second carbonization temperature is 650-750℃, for example 650℃, 700℃, 750℃, etc., and the second carbonization treatment is performed for 50-70min, for example 50min, 60min, 70min, etc.

[0070] Preferably, the second fiber cloth is subjected to ultrasonic cleaning and drying treatment in sequence before the second carbonization treatment. The ultrasonic cleaning time is preferably 25-35min, for example 25min, 30min, 35min, etc., the drying temperature is preferably 75-85℃, for example 75℃, 80℃, 85℃, etc., and the drying time is preferably 0.5-1.5h, for example 0.5h, 1h, 1.5h, etc.

[0071] Preferably, after the second carbonization treatment, conductive silver paste and copper tape with terminal are applied in sequence on the electrothermal material for the upper surface of the wing.

[0072] In some preferred embodiments, the third carbonization process comprises: heating to 250-350℃, for example 250℃, 300℃, 350℃, etc., at a rate of 4.5-5.5℃ / min, for example 4.5℃ / min, 5℃ / min, 5.5℃ / min, etc., and then heating to a third carbonization temperature at a rate of 2.5-3.5℃ / min, for example 2.5℃ / min, 3℃ / min, 3.5℃ / min, etc., for the third carbonization treatment.

[0073] Preferably, the third carbonization temperature is 550-650℃, for example 550℃, 600℃, 650℃, etc., and the third carbonization treatment is performed for 50-70min, for example 50min, 60min, 70min, etc.

[0074] Preferably, before the third carbonization treatment, the third fiber cloth is sequentially subjected to ultrasonic cleaning and drying treatment, the ultrasonic cleaning time is preferably 25-35 min, for example, it can be 25 min, 30 min, 35 min, etc., the drying temperature is preferably 75-85℃, for example, it can be 75℃, 80℃, 85℃, etc., and the drying time is preferably 0.5-1.5h, for example, it can be 0.5h, 1h, 1.5h, etc.

[0075] Preferably, after the third carbonization treatment, conductive silver paste and copper tape with terminal are sequentially applied to the electrothermal material for the lower wing surface of the wing.

[0076] In some preferred embodiments, in the present application, the wing leading edge electrothermal sheet, the wing upper surface electrothermal sheet and the wing lower surface electrothermal sheet after drying are fixed with graphite tooling to ensure that the carbonization process is flat and not deformed.

[0077] The present application provides a preparation method of the anti-icing structure and function integrated wing electrothermal material.

[0078] In the present application, the anti-icing structure and function integrated wing electrothermal material prepared by the preparation method of the anti-icing structure and function integrated wing electrothermal material is an electrothermal sheet, which is used for deicing the wing or slotted wing of an aircraft, and the electrothermal sheet is composed of three parts, i.e., a leading edge electrothermal sheet, an upper surface electrothermal sheet and a lower surface electrothermal sheet.

[0079] The present application provides a preparation method of the anti-icing structure and function integrated wing electrothermal material.

[0080] The present application provides an integrated wing, which is a high-efficiency electrothermal anti-icing structure and function integrated wing, prepared by integrally laying fiber-reinforced resin prepreg and then performing autoclave process, and selecting the required electrothermal sheet resistance range according to different heating zones of the wing.

[0081] In some preferred embodiments, the electrothermal anti-icing structure and function integrated wing is provided as a multi-layer structure, which comprises, from outside to inside, an outer skin, an upper insulating layer, an electrothermal layer, a lower insulating layer and an inner skin, and the electrothermal layer is prepared from the electrothermal material;

[0082] Preferably, the upper insulating layer and the lower insulating layer each comprise a glass fiber composite material.

[0083] Preferably, the inner skin and the outer skin each comprise a unidirectional carbon fiber composite laminate;

[0084] Preferably, the inner surface of the outer skin has a carbon nanotube / reduced graphene oxide heat-conducting coating;

[0085] Preferably, the inner surface of the inner skin has a thermal insulation layer, and the electric heating layer is powered by a pair of copper foil wires leading out from both ends of the electric heating layer.

[0086] In some preferred embodiments, the wing is integrally formed by a autoclave process.

[0087] In some preferred embodiments, the autoclave process comprises the following steps: increasing the temperature to a first temperature under 200-300 Pa, maintaining the first temperature for a first time, then increasing the temperature to a second temperature, maintaining the second temperature for a second time, and then decreasing the temperature to room temperature.

[0088] Preferably, the first temperature is 80-100℃, for example, it can be 80℃, 90℃, 100℃, etc., and the first time is 55-65 min, for example, it can be 55 min, 60 min, 65 min, etc.

[0089] Preferably, the second temperature is 120-140℃, for example, it can be 120℃, 130℃, 140℃, etc., and the second time is 110-130 min, for example, it can be 110 min, 120 min, 130 min, etc.

[0090] In the present application, the specific process of the autoclave is as follows: increasing the temperature from room temperature to 80-100℃ within 60 min, then maintaining the temperature at 80-100℃ for 60 min; then increasing the temperature to 120-140℃ within 30 min, and maintaining the temperature at 120-140℃ for 110-130 min; finally, decreasing the temperature to room temperature within 120 min.

[0091] The present application will be further described by examples. Unless otherwise specified, the materials in the examples are prepared according to existing methods or directly purchased from the market.

[0092] Example 1

[0093] The present example provides a preparation method of an electric heating material for a deicing structure and function integrated wing, comprising the following steps:

[0094] (1) First, PAN-based pre-oxidized yarn and carbon fiber are woven into a plain cloth as the raw material of the wing electric heating sheet, and the thickness of the fiber cloth is 450 μm, and the volume fraction of the pre-oxidized yarn in the fiber cloth is 30%.

[0095] (2) According to the different heating zones of the wing, the woven electric heating film fabric is cut into appropriate sizes, which are marked as wing leading edge electric heating film, upper wing surface electric heating film and lower wing surface electric heating film. According to the different heating power required by the deicing part of the wing, the three different electric heating films are carbonized at different temperatures respectively to meet the demand of different resistivity.

[0096] (2.1.1) Put the wing leading edge electric heating film into anhydrous ethanol and ultrasonically clean for 30 minutes to remove surface impurities.

[0097] (2.1.2) Put the ultrasonically cleaned wing leading edge electric heating film into an oven for sufficient drying, with the oven temperature set at 80℃ and the time set for 1 hour.

[0098] (2.1.3) Fix the dried wing leading edge electric heating film with graphite tooling to ensure flatness and no deformation during carbonization.

[0099] (2.1.4) Put the graphite tooling with the wing leading edge electric heating film into a high-temperature pyrolysis furnace for high-temperature carbonization treatment. During high-temperature carbonization, vacuumize and introduce Ar gas as protective gas. The temperature rises at a rate of 5℃ / min from room temperature to 300℃, and at a rate of 3℃ / min from 300℃ to 800℃, with a carbonization time of 70min at 800℃.

[0100] (2.1.5) After carbonization, naturally cool down and take out the wing leading edge electric heating film.

[0101] (2.1.6) Evenly apply conductive silver paste as electrodes on both ends of the wing leading edge electric heating film. After the conductive silver paste solidifies, lay copper tape with terminal on the surface and conduct a test.

[0102] (2.2.1) Similarly, put the wing upper surface electric heating film into anhydrous ethanol and ultrasonically clean for 30 minutes to remove surface impurities.

[0103] (2.2.2) Put the ultrasonically cleaned wing upper surface electric heating film into an oven for sufficient drying, with the oven temperature set at 80℃ and the time set for 1 hour.

[0104] (2.2.3) Fix the dried wing upper surface electric heating film with graphite tooling to ensure flatness and no deformation during carbonization.

[0105] (2.2.4) Put the graphite tooling with the wing upper surface electric heating film into a high-temperature pyrolysis furnace for high-temperature carbonization treatment. During high-temperature carbonization, vacuumize and introduce Ar gas as protective gas. The temperature rises at a rate of 5℃ / min from room temperature to 300℃, and at a rate of 3℃ / min from 300℃ to 700℃, with a carbonization time of 60min at 700℃.

[0106] (2.2.5) After carbonization, the wing upper surface heating element is taken out after natural cooling.

[0107] (2.2.6) The wing upper surface heating element is coated with conductive silver paste as electrodes at both ends, and after the conductive silver paste is solidified, a copper strip with a terminal is laid on the surface and tested for electrical conduction.

[0108] (2.3.1) Similarly, the wing lower surface heating element is placed in anhydrous ethanol and ultrasonically cleaned for 30 minutes to remove surface impurities.

[0109] (2.3.2) The wing lower surface heating element after ultrasonic cleaning is placed in an oven for thorough drying, with the oven temperature set at 80°C and the time set for 1 hour.

[0110] (2.3.3) The dried wing lower surface heating element is fixed with graphite fixtures to ensure flatness and prevent deformation during carbonization.

[0111] (2.3.4) The graphite fixture with the wing lower surface heating element is placed in a high-temperature pyrolysis furnace for high-temperature carbonization treatment. During high-temperature carbonization, vacuum is drawn and Ar gas is introduced as a protective gas. The temperature is raised from room temperature to 300°C at a rate of 5°C / min, and from 300°C to 600°C at a rate of 3°C / min, with a carbonization time of 60 minutes at 600°C.

[0112] (2.3.5) After carbonization, the wing lower surface heating element is taken out after natural cooling.

[0113] (2.3.6) The wing lower surface heating element is coated with conductive silver paste as electrodes at both ends, and after the conductive silver paste is solidified, a copper strip with a terminal is laid on the surface and tested for electrical conduction.

[0114] (3) The edge parts of the wing leading edge heating element, the wing upper surface heating element and the wing lower surface heating element are packaged with conductive adhesive to obtain an integrated wing electric heating structure.

[0115] Example 2

[0116] The present embodiment provides a preparation method of an anti-icing structure function integrated wing electric heating material, comprising the following steps:

[0117] (1) First, PAN-based pre-oxidized yarn and carbon fiber are woven into a plain cloth as the wing heating element raw material, with a thickness of 400 μm and a pre-oxidized yarn volume fraction of 40% in the fiber cloth.

[0118] (2) According to the different heating partition of the wing, the woven electric heating film fabric is cut into the wing leading edge electric heating film, the upper wing surface electric heating film and the lower wing surface electric heating film. According to the different heating power required by the deicing part of the wing, the three different electric heating films are carbonized at different temperatures to meet the different resistivity requirements.

[0119] (2.1.1) Put the wing leading edge electric heating film into anhydrous ethanol and ultrasonic clean for 25 minutes to remove surface impurities.

[0120] (2.1.2) Put the ultrasonic cleaned wing leading edge electric heating film into the oven and dry it thoroughly. The oven temperature is set at 85℃ and the time is set at 0.5 hours.

[0121] (2.1.3) Fix the dried wing leading edge electric heating film with graphite tool to ensure that the carbonization process is flat and not deformed.

[0122] (2.1.4) Put the graphite tool with the wing leading edge electric heating film into the high temperature pyrolysis furnace for high temperature carbonization treatment. During the high temperature carbonization process, vacuumize and introduce Ar gas as protective gas. The temperature rises from room temperature to 250℃ at a rate of 5.5℃ / min, and from 250-850℃ at a rate of 2.5℃ / min. The carbonization time at 850℃ is 60min.

[0123] (2.1.5) After carbonization, cool naturally and take out the wing leading edge electric heating film.

[0124] (2.1.6) Evenly apply conductive silver paste as electrodes on both ends of the wing leading edge electric heating film. After the conductive silver paste solidifies, lay copper tape with terminal on the surface and conduct a test.

[0125] (2.2.1) Similarly, put the wing upper surface electric heating film into anhydrous ethanol and ultrasonic clean for 30 minutes to remove surface impurities.

[0126] (2.2.2) Put the ultrasonic cleaned wing upper surface electric heating film into the oven and dry it thoroughly. The oven temperature is set at 85℃ and the time is set at 0.5 hours.

[0127] (2.2.3) Fix the dried wing upper surface electric heating film with graphite tool to ensure that the carbonization process is flat and not deformed.

[0128] (2.2.4) Put the graphite tool with the wing upper surface electric heating film into the high temperature pyrolysis furnace for high temperature carbonization treatment. During the high temperature carbonization process, vacuumize and introduce Ar gas as protective gas. The temperature rises from room temperature to 250℃ at a rate of 5.5℃ / min, and from 300-750℃ at a rate of 2.5℃ / min. The carbonization time at 750℃ is 50min.

[0129] (2.2.5) After carbonization, the wing upper surface heating element is taken out after natural cooling.

[0130] (2.2.6) The wing upper surface heating element is coated with conductive silver paste as electrodes at both ends, and after the conductive silver paste is solidified, a copper tape with a terminal is laid on the surface and an electrical test is performed.

[0131] (2.3.1) Similarly, the wing lower surface heating element is placed in anhydrous ethanol and ultrasonically cleaned for 30 minutes to remove surface impurities.

[0132] (2.3.2) The wing lower surface heating element after ultrasonic cleaning is placed in an oven for thorough drying, with the oven temperature set at 85°C and the time set for 0.5 hours.

[0133] (2.3.3) The dried wing lower surface heating element is fixed with graphite fixtures to ensure flatness and no deformation during carbonization.

[0134] (2.3.4) The graphite fixture with the wing lower surface heating element is placed in a high-temperature pyrolysis furnace for high-temperature carbonization treatment. During high-temperature carbonization, vacuum is drawn and Ar gas is introduced as a protective gas. The temperature is raised from room temperature to 250°C at a rate of 5.5°C / min, and from 300°C to 650°C at a rate of 2.5°C / min, with a carbonization time of 50 minutes at 650°C.

[0135] (2.3.5) After carbonization, the wing lower surface heating element is taken out after natural cooling.

[0136] (2.3.6) The wing lower surface heating element is coated with conductive silver paste as electrodes at both ends, and after the conductive silver paste is solidified, a copper tape with a terminal is laid on the surface and an electrical test is performed.

[0137] (3) The edge parts of the wing leading edge heating element, the wing upper surface heating element and the wing lower surface heating element are packaged with conductive adhesive to obtain an integrated wing electric heating structure.

[0138] Example 3

[0139] The present embodiment provides a method for preparing an anti-icing structure function integrated wing electric heating material, comprising the following steps:

[0140] (1) First, PAN-based pre-oxidized yarn and carbon fiber are woven into a plain cloth as the wing heating element raw material, with a thickness of 500 μm and a pre-oxidized yarn volume fraction of 20% in the fiber cloth.

[0141] (2) According to the different heating partition of the wing, the woven electric heating film fabric is cut into the wing leading edge electric heating film, the upper wing surface electric heating film and the lower wing surface electric heating film. According to the different heating power required by the deicing part of the wing, the three different electric heating films are carbonized at different temperatures to meet the different resistivity requirements.

[0142] (2.1.1) Put the wing leading edge electric heating film into anhydrous ethanol and ultrasonic clean for 35 minutes to remove surface impurities.

[0143] (2.1.2) Put the ultrasonic cleaned wing leading edge electric heating film into an oven for sufficient drying, and set the oven temperature at 75℃ and the time at 1.5 hours.

[0144] (2.1.3) Fix the dried wing leading edge electric heating film with graphite tool to ensure the flatness during carbonization.

[0145] (2.1.4) Put the graphite tool with the wing leading edge electric heating film into a high temperature pyrolysis furnace for high temperature carbonization. During the high temperature carbonization, vacuumize and introduce Ar gas as protective gas. The temperature rises from room temperature to 350℃ at a rate of 4.5℃ / min, and from 250-750℃ at a rate of 3.5℃ / min, and the carbonization time at 750℃ is 80 minutes.

[0146] (2.1.5) After carbonization, naturally cool down and take out the wing leading edge electric heating film.

[0147] (2.1.6) Evenly coat the both ends of the wing leading edge electric heating film with conductive silver paste as electrodes, and after the conductive silver paste solidifies, lay copper tape with terminal on the surface and conduct a test.

[0148] (2.2.1) Similarly, put the wing upper surface electric heating film into anhydrous ethanol and ultrasonic clean for 30 minutes to remove surface impurities.

[0149] (2.2.2) Put the ultrasonic cleaned wing upper surface electric heating film into an oven for sufficient drying, and set the oven temperature at 75℃ and the time at 1.5 hours.

[0150] (2.2.3) Fix the dried wing upper surface electric heating film with graphite tool to ensure the flatness during carbonization.

[0151] (2.2.4) Put the graphite tool with the wing upper surface electric heating film into a high temperature pyrolysis furnace for high temperature carbonization. During the high temperature carbonization, vacuumize and introduce Ar gas as protective gas. The temperature rises from room temperature to 350℃ at a rate of 4.5℃ / min, and from 300-650℃ at a rate of 3.5℃ / min, and the carbonization time at 650℃ is 70 minutes.

[0152] (2.2.5) After carbonization, the upper surface of the wing electric heating film is taken out after natural cooling.

[0153] (2.2.6) The upper surface of the wing electric heating film is evenly coated with conductive silver paste as electrodes. After the conductive silver paste is solidified, a copper strip with a terminal is laid on the surface and an electrical test is performed.

[0154] (2.3.1) Similarly, the lower surface of the wing electric heating film is placed in anhydrous ethanol and ultrasonically cleaned for 30 minutes to remove surface impurities.

[0155] (2.3.2) The ultrasonically cleaned lower surface of the wing electric heating film is placed in an oven for thorough drying, with the oven temperature set at 75°C and the time set at 1.5 hours.

[0156] (2.3.3) The dried lower surface of the wing electric heating film is fixed with a graphite tool to ensure flatness and prevent deformation during carbonization.

[0157] (2.3.4) The graphite tool containing the lower surface of the wing electric heating film is placed in a high-temperature pyrolysis furnace for high-temperature carbonization. During high-temperature carbonization, vacuum is drawn and Ar gas is introduced as a protective gas. The temperature is raised from room temperature to 350°C at a rate of 4.5°C / min, and from 300°C to 550°C at a rate of 3.5°C / min, with a carbonization time of 70 minutes at 550°C.

[0158] (2.3.5) After carbonization, the lower surface of the wing electric heating film is taken out after natural cooling.

[0159] (2.3.6) The lower surface of the wing electric heating film is evenly coated with conductive silver paste as electrodes. After the conductive silver paste is solidified, a copper strip with a terminal is laid on the surface and an electrical test is performed.

[0160] (3) The edge parts of the above-mentioned wing leading edge electric heating film, upper surface electric heating film and lower surface electric heating film are packaged with conductive adhesive to obtain an integrated wing electric heating structure.

[0161] Example 4

[0162] The preparation method of the electric heating material for the anti-icing structure function integrated wing provided in this embodiment is different from that of Example 1 in that:

[0163] The first carbonization temperature is 780°C, the second carbonization temperature is 680°C, and the third carbonization temperature is 580°C.

[0164] The remaining steps are consistent with those of Example 1.

[0165] Example 5

[0166] The preparation method of the electric heating material for the anti-icing structure function integrated wing provided in this embodiment is different from that of Example 1 in that:

[0167] The first carbonization temperature is 820°C, the second carbonization temperature is 720°C, and the third carbonization temperature is 620°C.

[0168] The remaining steps are consistent with Example 1.

[0169] Example 6

[0170] The present example provides a preparation method of an electric heating material for a wing with integrated ice-prevention and structural functions, which is different from Example 1 in that:

[0171] The first carbonization temperature is 700°C, the second carbonization temperature is 600°C, and the third carbonization temperature is 500°C.

[0172] The remaining steps are consistent with Example 1.

[0173] Example 7

[0174] The present example provides a preparation method of an electric heating material for a wing with integrated ice-prevention and structural functions, which is different from Example 1 in that:

[0175] The first carbonization temperature is 900°C, the second carbonization temperature is 800°C, and the third carbonization temperature is 700°C.

[0176] The remaining steps are consistent with Example 1.

[0177] Example 8

[0178] The present example provides a preparation method of an electric heating material for a wing with integrated ice-prevention and structural functions, which is different from Example 1 in that:

[0179] The volume content of the pre-oxidized yarn in the first fiber cloth, the second fiber cloth, and the third fiber cloth is 25%.

[0180] The remaining steps are consistent with Example 1.

[0181] Example 9

[0182] The present example provides a preparation method of an electric heating material for a wing with integrated ice-prevention and structural functions, which is different from Example 1 in that:

[0183] The volume content of the pre-oxidized yarn in the first fiber cloth, the second fiber cloth, and the third fiber cloth is 35%.

[0184] The remaining steps are consistent with Example 1.

[0185] Example 10

[0186] The present example provides a preparation method of an electric heating material for a wing with integrated ice-prevention and structural functions, which is different from Example 1 in that:

[0187] The volume content of the pre-oxidized filaments in the first fiber cloth, the second fiber cloth and the third fiber cloth is 19%;

[0188] The remaining steps are consistent with those of Example 1.

[0189] Example 11

[0190] The present example provides a preparation method of an electric heating material for an ice-prevention and structure-function integrated wing, which is different from Example 1 in that:

[0191] The volume content of the pre-oxidized filaments in the first fiber cloth, the second fiber cloth and the third fiber cloth is 41%;

[0192] The remaining steps are consistent with those of Example 1.

[0193] Application Examples 1-11

[0194] Application Examples 1-11 provide an electric heating ice-prevention and structure-function integrated wing, which respectively adopts the integrated wing electric heating layer structure prepared by Example 1-11, and the preparation process is as follows:

[0195] (1) The isolation film, the Teflon cloth, the inner skin, the lower insulation layer, the integrated wing electric heating layer prepared by Example 1-11, the upper insulation layer, the outer skin, the Teflon cloth, the adhesive absorbing cloth and the isolation film are tightly laid on the wing mold, and then placed in a vacuum bag, and after vacuumizing, placed in a hot press tank for hot pressing. The hot press tank process is: under 250 Pa, the temperature is raised from room temperature to 90℃ within 60 min, and then kept at 90℃ for 60 min; then, the temperature is raised to 130℃ within 30 min, and kept at the temperature for 120 min; finally, the temperature is lowered to room temperature within 120 min.

[0196] (2) After taking out from the hot press tank, the vacuum bag is removed and demolded, and then the auxiliary materials such as the isolation film, the adhesive absorbing cloth and the Teflon cloth are removed, to obtain the high-efficiency electric heating ice-prevention and structure-function integrated wing.

[0197] Application Example 12

[0198] The present application example provides an electric heating ice-prevention and structure-function integrated wing, which is different from Application Example 1 in that: in the hot press tank process, under 200 Pa, the temperature is raised from room temperature to 80℃ within 60 min, and then kept at 80℃ for 55 min; then, the temperature is raised to 140℃ within 30 min, and kept at the temperature for 110 min; finally, the temperature is lowered to room temperature within 120 min.

[0199] Application Example 13

[0200] The application example provides an electric heating anti-icing structure function integrated wing, which is different from the application example 1 in that, in the autoclave process, the temperature is increased from room temperature to 100 DEG C within 60 min at 300 Pa, and then the temperature is kept at 100 DEG C for 65 min; then, the temperature is increased to 120 DEG C within 30 min, and the temperature is kept at 120 DEG C for 130 min; finally, the temperature is decreased to room temperature within 120 min.

[0201] Comparative example 1

[0202] The preparation method of the electric heating material for the anti-icing structure function integrated wing provided by the comparative example is different from that of the embodiment 1 in that:

[0203] The manufacturing process of the electric heating sheet on the upper surface of the wing and the electric heating sheet on the lower surface of the wing is the same as that of the electric heating sheet on the leading edge of the wing.

[0204] Comparative example 2

[0205] The preparation method of the electric heating material for the anti-icing structure function integrated wing provided by the comparative example is different from that of the embodiment 1 in that:

[0206] The manufacturing process of the electric heating sheet on the leading edge of the wing and the electric heating sheet on the lower surface of the wing is the same as that of the electric heating sheet on the upper surface of the wing.

[0207] Comparative example 3

[0208] The preparation method of the electric heating material for the anti-icing structure function integrated wing provided by the comparative example is different from that of the embodiment 1 in that:

[0209] The manufacturing process of the electric heating sheet on the leading edge of the wing and the electric heating sheet on the upper surface of the wing is the same as that of the electric heating sheet on the lower surface of the wing.

[0210] Comparative example 4

[0211] The preparation method of the electric heating material for the anti-icing structure function integrated wing provided by the comparative example is different from that of the embodiment 1 in that:

[0212] In step (1), only carbon fibers are used as raw materials, and no PAN-based pre-oxidized yarn is added.

[0213] Comparative example 5

[0214] The electric heating material of the comparative example is a copper mesh.

[0215] Comparative application examples 1-5

[0216] The comparative application examples 1-5 provide a preparation method of an integrated wing, which respectively uses the integrated wing electric heating layer structures prepared by the comparative examples 1-5, and the preparation method is consistent with that of the application example 1.

[0217] Test example

[0218] Test sample: The electric heating and deicing structure and function integrated wing prepared from application example 1-13 and the integrated wing prepared from comparative application example 1-5.

[0219] Test method: The integrated wing is connected to a direct current power supply, the voltage is controlled at 120V, and the current is recorded after stabilization, and then the power density is calculated, the surface temperature of the material is detected using an infrared thermal imager, the temperature distribution map is obtained, and the maximum surface temperature difference is calculated. Among them, the temperature difference reflects the heating uniformity of the material, and the smaller the temperature difference, the more uniform the material heating.

[0220] The test results are shown in Table 1.

[0221]

[0222]

[0223]

[0224] Referring to the data in Table 1, in the present application, through application example 1, application example 4, and application example 5, it can be known that the resistance of the fiber cloth can be regulated by the carbonization heat treatment temperature. The higher the heat treatment temperature, the more conducive to the conversion of the pre-oxidized yarn to carbon fiber, and at this time, the resistance of the fiber cloth is lower, and the heating power density is higher. Conversely, the heating power density is lower.

[0225] Through application example 1, application example 6, and application example 7, it can be known that if the carbonization temperature is not within the specific range of carbonization of the present application, the performance of the product is not as good as that of application example 1. When the carbonization temperature is higher than the upper limit of the carbonization temperature of the present application, compared with application example 1, the resistance of the electric heating material of application example 7 is smaller, the heating efficiency of the product of application example 7 is too large and not easy to control, affecting the heating uniformity of the product. When the carbonization temperature is lower than the lower limit of the carbonization temperature of the present application, compared with application example 1, the electric heating power density of the product of application example 6 is smaller, affecting the electric heating efficiency of the product.

[0226] Through application example 1, application example 8, and application example 9, it can be known that the higher the pre-oxidized yarn content, the greater the resistance, and the lower the heating power density. Compared with application example 1, the proportion of pre-oxidized yarn in application example 11 is greater than the specific range, and the heating power density is lower, affecting the electric heating efficiency of the product. Compared with application example 1, the proportion of pre-oxidized yarn in application example 10 is less than the specific range, and although the heating power density is increased, the resistance of the electric heating material is small, the heating efficiency of the product is too large and not easy to control, affecting the heating uniformity of the product.

[0227] The comparative application examples 1-3 cannot achieve the effect of meeting the demand of different resistivity according to the different heating power required by the deicing part of the wing. According to the comparative application examples 4 and 5, the product lacks component pre-oxidized yarn and uses existing copper mesh material as the electric heating layer, and the performance of the products of the comparative application examples 4 and 5 is far inferior to that of the product of the application example 1.

[0228] In addition, the heat treatment temperature of the fiber cloth can be designed according to actual requirements to obtain the expected heat power density.

[0229] Finally, it should be noted that: the above embodiments are only used to illustrate the technical solutions of the present application, and not to limit them; although the present application has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that: it can still modify the technical solutions recorded in the foregoing embodiments, or make equivalent replacement for part or all of the technical features; and these modifications or replacements do not make the essence of the corresponding technical solutions deviate from the scope of the technical solutions of the embodiments of the present application.

Claims

1. A method for preparing an electric heating material for an aircraft wing with integrated anti-icing and de-icing structure, characterized in that: The following steps are involved: Using a fiber cloth woven from pre-oxidized yarn and carbon fiber as a raw material, carbonizing the fiber cloth to obtain an electric heating material, and packaging the electric heating material to obtain the electric heating material for the wing with integrated anti-icing structure and function; Wherein, the pre-oxidized yarn is PAN-based pre-oxidized yarn; Using the first fiber cloth as a raw material, a first carbonization treatment is performed to obtain an electric heating material for a wing leading edge; Using the second fiber cloth as a raw material, a second carbonization treatment is performed to obtain an electric heating material for the upper surface of the wing; Using the third fiber cloth as raw material, a third carbonization treatment is performed to obtain an electric heating material for the lower wing surface; wherein the treatment temperatures of the first carbonization treatment, the second carbonization treatment, and the third carbonization treatment are different; The first fiber cloth, the second fiber cloth and the third fiber cloth are all woven plain cloths made of pre-oxidized yarn and carbon fiber; The temperature of the first carbonization is 750-850°C; The temperature of the second carbonization is 650-750°C; The temperature of the third carbonization is 550-650°C.

2. The method for preparing the electric heating material for an aircraft wing with integrated anti-icing and de-icing structure function according to claim 1, characterized in that: The volume content of the pre-oxidized yarn in the woven plain cloth is 20% to 40%.

3. The method for preparing the electric heating material for an aircraft wing with integrated anti-icing and de-icing structure and function according to claim 1, characterized in that: The thickness of the woven plain cloth is 400-500 μm.

4. The method for preparing the electric heating material for an aircraft wing with integrated anti-icing and de-icing structure function according to claim 1, characterized in that: The first carbonization process includes: in an inert gas atmosphere, heating the temperature to 250-350° C. at a rate of 4.5-5.5° C. / min, and then heating the temperature to the first carbonization temperature at a rate of 2.5-3.5° C. / min to perform the first carbonization treatment.

5. The method for preparing the electric heating material for an aircraft wing with integrated anti-icing and de-icing structure function according to claim 1, characterized in that: The time of the first carbonization treatment is 60 to 80 minutes.

6. The method for preparing the electric heating material for an aircraft wing with integrated anti-icing and de-icing structure and function according to claim 1, characterized in that: Before the first carbonization treatment, the first fiber cloth is subjected to ultrasonic cleaning and drying treatment in sequence, with the ultrasonic cleaning time being 25-35 minutes, the drying temperature being 75-85° C., and the drying time being 0.5-1.5 hours.

7. The method for preparing the electric heating material for an aircraft wing with integrated anti-icing and de-icing structure and function according to claim 1, characterized in that: After the first carbonization treatment, conductive silver paste and copper tape with connection terminals are sequentially applied on the electric heating material for the wing leading edge.

8. The method for preparing the electric heating material for an aircraft wing with integrated anti-icing and de-icing structure function according to claim 1, characterized in that: The second carbonization process includes: in an inert gas atmosphere, heating the temperature to 250-350° C. at a rate of 4.5-5.5° C. / min, and then heating the temperature to a second carbonization temperature at a rate of 2.5-3.5° C. / min to perform a second carbonization treatment.

9. The method for preparing the electric heating material for an aircraft wing with integrated anti-icing and de-icing structure and function according to claim 1, characterized in that: The second carbonization treatment time is 50 to 70 minutes.

10. The method for preparing the electric heating material for an aircraft wing with integrated anti-icing and de-icing structure and function according to claim 1, characterized in that: Before the second carbonization treatment, the second fiber cloth is subjected to ultrasonic cleaning and drying treatment in sequence, with the ultrasonic cleaning time being 25-35 minutes, the drying temperature being 75-85° C., and the drying time being 0.5-1.5 hours.

11. The method for preparing an electric heating material for an aircraft wing with integrated anti-icing and de-icing structure and function according to claim 1, characterized in that: After the second carbonization treatment, a conductive silver paste and a copper tape with a connection terminal are sequentially applied on the electric heating material for the upper wing surface.

12. The method for preparing the electric heating material for an aircraft wing with integrated anti-icing and de-icing structure and function according to claim 1, characterized in that: The third carbonization treatment process includes: in an inert gas atmosphere, heating the temperature to 250-350° C. at a rate of 4.5-5.5° C. / min, then heating the temperature to the third carbonization temperature at a rate of 2.5-3.5° C. / min, and performing the third carbonization treatment.

13. The method for preparing the electric heating material for an aircraft wing with integrated anti-icing and de-icing structure and function according to claim 1, characterized in that: The third carbonization treatment takes 50 to 70 minutes.

14. The method for preparing the electric heating material for an aircraft wing with integrated anti-icing and de-icing structure and function according to claim 1, characterized in that: Before the third carbonization treatment, the third fiber cloth is subjected to ultrasonic cleaning and drying treatment in sequence, with the ultrasonic cleaning time being 25-35 minutes, the drying temperature being 75-85° C., and the drying time being 0.5-1.5 hours.

15. The method for preparing the electric heating material for an aircraft wing with integrated anti-icing and de-icing structure and function according to claim 1, characterized in that: After the third carbonization treatment, conductive silver paste and copper tape with connection terminals are sequentially applied on the electric heating material for the lower wing surface.

16. The electrothermal material for an aircraft wing with an integrated anti-icing and deicing structure and function, prepared by the method for preparing the electrothermal material for an aircraft wing with an integrated anti-icing and deicing structure and function according to any one of claims 1 to 15.

17. A method for preparing an electrothermal material for an aircraft wing with an integrated anti-icing structure and functions according to any one of claims 1 to 15, or use of the electrothermal material for an aircraft wing with an integrated anti-icing structure and functions according to claim 16 in preparing an electric heating anti-icing structure and functions integrated aircraft wing.

18. The use according to claim 17, characterized in that The electric heating anti-icing structure and function integrated wing is configured as a multi-layer structure, which includes an outer skin, an upper insulating layer, an electric heating layer, a lower insulating layer and an inner skin layer from the outside to the inside. The electric heating layer is prepared using the electric heating material for the anti-icing structure and function integrated wing.

19. The use according to claim 18, characterized in that The upper insulating layer and the lower insulating layer both include glass fiber composite material.

20. The use according to claim 18, characterized in that The inner skin and the outer skin both comprise unidirectional carbon fiber composite laminates.

21. The use according to claim 18, characterized in that The inner surface of the outer skin is provided with a carbon nanotube / reduced graphene oxide thermal conductive coating.

22. The use according to claim 18, characterized in that The inner surface of the inner skin is provided with a heat insulating layer, and copper foil wires are led out from both ends of the electric heating layer to supply power and generate heat for the electric heating layer.

23. The use according to claim 18, characterized in that The wing is manufactured by integrated molding using a hot-pressing process.

24. The use according to claim 23, characterized in that The autoclave process includes: heating to a first temperature at 200-300 Pa, performing a first heat preservation at the first temperature, then heating to a second temperature, performing a second heat preservation at the second temperature, and then cooling the temperature to room temperature.

25. The use according to claim 24, characterized in that The first temperature is 80-100° C., and the first insulation time is 55-65 minutes.

26. The use according to claim 24, characterized in that The second temperature is 120-140° C., and the second insulation time is 110-130 min.

Images