Electric heating material for anti-icing and deicing structure function integrated wing and preparation method and application of electric heating material

Abstract

The invention provides an anti-icing and de-icing structure function integrated electric heating material for wings and a preparation method and application thereof, and relates to the technical field of aerospace anti-icing and de-icing, and the preparation method comprises the following steps: taking fiber cloth obtained by weaving pre-oxidized fibers and carbon fibers as a raw material, and carbonizing the fiber cloth to obtain the electric heating material, and packaging the electric heating material to obtain the electric heating material for the anti-icing and de-icing structure and function integrated wing. Wherein the pre-oxidized fiber is a PAN (Polyacrylonitrile)-based pre-oxidized fiber. According to the preparation method of the electric heating material for the anti-icing and de-icing structure and function integrated wing, the electric heating efficiency of the aircraft wing can be remarkably improved while the material is uniformly heated.

Description

Technical Field

[0001] The present invention relates to the field of aerospace anti-icing technology, and in particular to an electric heating material for an aircraft wing with an integrated anti-icing structure and function, and a preparation method and application thereof. Background Art

[0002] Aircraft surface icing refers to the phenomenon that under low temperature and high content of supercooled water droplets, the surface of the aircraft will form an ice layer after colliding with supercooled water droplets in the atmosphere. At present, the key parts of the aircraft that are prone to icing mainly include the wings, horizontal tail, windshield, atmospheric data sensor, engine air intake and other parts. Among them, the wing is the main part of the aircraft that generates lift. The accumulation of ice 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 affect the aircraft's lift-to-drag ratio and lift coefficient, resulting in reduced take-off and landing performance, and hindering the aircraft from generating sufficient lift. After analyzing the flight measured data and the relevant data of the ice wind tunnel test: when a layer of ice is formed on the outer skin of the aircraft wing, the lift of the aircraft will be reduced 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 pilot control, and may cause stalling, and even crashes.

[0003] In the prior art, aircraft wing anti-icing systems are mainly divided into three categories: solution anti-icing systems, external force deicing systems, and thermodynamic anti-icing systems. Among them, solution anti-icing can only be used to prevent wing icing, and the main research is to prepare antifreeze liquid and spray it on the leading edge of the wing through a high-pressure pump. The disadvantage of this method is that it can only cope with short-term icing. If the aircraft is in an icing environment for a long time, this method is not applicable; external force deicing is mainly pulse deicing. The pulse deicing method is to use a capacitor bank to discharge to the coil, and the coil generates a strong magnetic field, which generates a high amplitude and extremely short duration mechanical force on the aircraft skin, causing the ice to break and fall off. However, in practical applications, the pulse deicing method has obvious disadvantages: the relationship between the pulse circuit parameters 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 anti-icing system is mainly to use high heat to melt and evaporate ice or directly sublimate it. This method is limited by the size of the heat flow.

[0004] With the continuous development of anti-icing technology, researchers have proposed many new anti-icing technologies, among which the most representative is the electric heating anti-icing method. Its principle is to convert electrical energy into thermal energy, and then heat the aircraft parts to achieve the purpose of anti-icing. At present, electric heating anti-icing has become the most widely used anti-icing method due to its significant advantages such as simple structure, small size, light weight, low energy consumption, high efficiency and easy maintenance. In response to severe weather or the surface area of ​​complex aircraft parts, it becomes necessary to use electric heating anti-icing.

[0005] Therefore, modern anti-icing technology is mainly focused on electric heating anti-icing, and electric heating anti-icing is therefore known as the most promising anti-icing method. On traditional alloy structure aircraft, due to the high thermal conductivity of metal, the electric heating method usually uses heating tubes or copper mesh, which are buried inside the aircraft and can be powered on to achieve the effect. At present, composite aircraft are developing rapidly, and there is a trend of adopting all-composite materials in wings, fuselages and other parts. Compared with metal materials, composite materials are lighter, which can reduce aircraft fuel consumption and improve operating efficiency. Secondly, composite materials have excellent corrosion resistance and are suitable for high humidity and active salt spray environments. Due to their natural electrical insulation properties, composite materials reduce the risk of leakage and short circuit, and reduce the impact of electromagnetic interference. These characteristics make composite materials more advantageous in efficient, safe and lightweight aviation applications. However, due to their unique thermal conductivity, if traditional electric heating or wire heating materials such as heating tubes or copper mesh are used, the material may heat unevenly, the heating efficiency is low, the thermal stress is large, and fatigue and other adverse consequences may occur.

[0006] In view of this, the present invention is proposed. Summary of the invention

[0007] One of the purposes of the present invention is to provide a method for preparing an electrothermal material for an aircraft wing with an integrated anti-icing structure function, so as to at least solve one of the technical problems existing in the prior art. The method for preparing an electrothermal material for an aircraft wing with an integrated anti-icing structure function provided by the present invention can significantly improve the electric heating efficiency of the aircraft wing while uniformly heating the material.

[0008] The second object of the present invention is to provide an electric heating material for an aircraft wing with an integrated anti-icing structure and functions, prepared by a method for preparing the electric heating material for an aircraft wing with an integrated anti-icing structure and functions.

[0009] The third object of the present invention is to provide a method for preparing an electrothermal material for an aircraft wing with an integrated anti-icing structure or the use of the electrothermal material for an aircraft wing with an integrated anti-icing structure in the preparation of an electric thermal anti-icing structure with an integrated wing.

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

[0011] In a first aspect, the present invention provides a method for preparing an electrothermal material for an aircraft wing with an integrated anti-icing structure function, comprising the following steps:

[0012] Using a fiber cloth woven from preoxidized 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 function;

[0013] Wherein, the pre-oxidized yarn is PAN-based pre-oxidized yarn.

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

[0015] Preferably, the volume content of pre-oxidized yarn in the woven plain fabric is 20% to 40%;

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

[0017] Further, the first fiber cloth is used as a raw material and subjected to a first carbonization treatment to obtain an electric heating material for a wing leading edge;

[0018] The second fiber cloth is used as a raw material and subjected to a second carbonization treatment to obtain an electric heating material for the upper wing surface of the wing;

[0019] The third fiber cloth is used as a raw material, and a third carbonization treatment is performed to obtain an electric heating material for the lower wing surface;

[0020] The first carbonization treatment, the second carbonization treatment and the third carbonization treatment have different treatment temperatures.

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

[0022] Further, the first carbonization process includes: in an inert gas atmosphere, heating to 250-350° C. at a rate of 4.5-5.5° C. / min, and then heating to a first carbonization temperature at a rate of 2.5-3.5° C. / min, to perform a first carbonization treatment;

[0023] Preferably, the first carbonization temperature is 750-850°C, and the first carbonization treatment time is 60-80 minutes;

[0024] Preferably, before the first carbonization treatment, the first fiber cloth is subjected to ultrasonic cleaning and drying treatment in sequence, the ultrasonic cleaning time is preferably 25-35 minutes, the drying temperature is preferably 75-85° C., and the drying time is preferably 0.5-1.5 hours;

[0025] Preferably, after the first carbonization treatment, a conductive silver paste and a copper tape with a terminal are sequentially applied to the electric heating material for the wing leading edge.

[0026] Further, the second carbonization process includes: in an inert gas atmosphere, heating to 250-350° C. at a rate of 4.5-5.5° C. / min, and then heating to a second carbonization temperature at a rate of 2.5-3.5° C. / min, to perform a second carbonization treatment;

[0027] Preferably, the second carbonization temperature is 650-750°C, and the second carbonization treatment time is 50-70 minutes;

[0028] Preferably, before the second carbonization treatment, the second fiber cloth is subjected to ultrasonic cleaning and drying treatment in sequence, the ultrasonic cleaning time is preferably 25-35 minutes, the drying temperature is preferably 75-85° C., and the drying time is preferably 0.5-1.5 hours;

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

[0030] Further, the process of the third carbonization treatment includes: in an inert gas atmosphere, heating to 250-350° C. at a rate of 4.5-5.5° C. / min, and then heating to a third carbonization temperature at a rate of 2.5-3.5° C. / min, and performing the third carbonization treatment;

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

[0032] Preferably, before the third carbonization treatment, the third fiber cloth is subjected to ultrasonic cleaning and drying treatment in sequence, the ultrasonic cleaning time is preferably 25-35 minutes, the drying temperature is preferably 75-85° C., and the drying time is preferably 0.5-1.5 hours;

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

[0034] In a second aspect, the present invention provides an electric heating material for an aircraft wing with an integrated anti-icing structure and functions, which is prepared by the method for preparing the electric heating material for an aircraft wing with an integrated anti-icing structure and functions.

[0035] In a third aspect, the present invention provides a method for preparing the electrothermal material for an anti-icing structure with integrated functions for an aircraft wing, or the use of the electrothermal material for an anti-icing structure with integrated functions for an aircraft wing in preparing an electrothermal anti-icing structure with integrated functions for an aircraft wing.

[0036] Furthermore, the electric heating anti-icing and deicing structure 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, and the electric heating layer is prepared by using the electric heating material for the anti-icing and deicing structure function integrated wing;

[0037] Preferably, the upper insulating layer and the lower insulating layer both comprise glass fiber composite materials;

[0038] Preferably, the inner skin and the outer skin both comprise unidirectional carbon fiber composite laminates;

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

[0040] Preferably, the inner surface of the inner skin has a heat insulation layer, and copper foil wires are led out from both ends of the electric heating layer to supply power and generate heat for itself;

[0041] Preferably, the wing is manufactured by integrated molding using a hot-pressing process.

[0042] Preferably, the autoclave process comprises: 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 reducing the temperature to room temperature;

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

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

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

[0046] The present invention provides a method for preparing an electric heating material for an aircraft wing with an integrated anti-icing structure function. The method adopts a fiber cloth obtained by weaving pre-oxidized yarns and carbon fibers as a raw material. The fiber cloth is woven from pre-oxidized yarns and carbon fibers and then subjected to a carbonization treatment as a conductive and thermally conductive enhanced phase. The electric heating material is prepared using a preferred carbonization process. The electric heating material can significantly improve the electric heating efficiency of an aircraft wing while achieving uniform heating of the material. DETAILED DESCRIPTION

[0047] Unless otherwise defined herein, scientific and technical terms used in conjunction with the present invention shall have the meanings commonly understood by those of ordinary skill in the art. The meaning and scope of the terms should be clear, however, in the case of any potential ambiguity, the definitions provided herein take precedence over any dictionary or external definitions. In this application, unless otherwise stated, the use of "or" means "and / or". In addition, the use of the term "including" and other forms is non-limiting.

[0048] The technical solution of the present invention will be clearly and completely described below in conjunction with the embodiments. Obviously, the described embodiments are part of the embodiments of the present invention, rather than all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0049] A first aspect of the present invention provides a method for preparing an electrothermal material for an aircraft wing with an integrated anti-icing structure and function, comprising the following steps:

[0050] The fiber cloth woven from pre-oxidized yarn and carbon fiber is used as raw material, the fiber cloth is carbonized to obtain an electric heating material, and the electric heating material is packaged to obtain the electric heating material for the wing with integrated anti-icing structure function; wherein the pre-oxidized yarn is PAN-based pre-oxidized yarn.

[0051] In the present invention, a fiber cloth obtained by weaving preoxidized yarn and carbon fiber is used as a raw material, and the fiber cloth is woven from preoxidized yarn and carbon fiber and then carbonized at high temperature as a conductive and thermal conductive enhancement phase. An optimal carbonization process is used to prepare an electric heating material. The electric heating material can significantly improve the electric heating efficiency of an aircraft wing while ensuring uniform heating of the material.

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

[0053] Preferably, the volume content of the pre-oxidized yarn in the woven plain fabric is 20% to 40%, for example, it can be 20%, 25%, 30%, 35%, 40%, etc.;

[0054] In the present invention, in order to meet the strength and heating performance requirements of the wing electric heater, the volume fraction of the pre-oxidized yarn in the fiber cloth is between 20% and 40%.

[0055] Preferably, the thickness of the woven plain fabric is 400-500 μm, for example, 400 μm, 450 μm, 500 μm, etc.

[0056] In some preferred embodiments, the first fiber cloth is used as a raw material and subjected to a first carbonization treatment to obtain an electric heating material for a wing leading edge;

[0057] Using the second fiber cloth as a raw material, a second carbonization treatment is performed to obtain an electric heating material for the upper wing surface of the wing;

[0058] The third fiber cloth is used as a raw material and subjected to a third carbonization treatment to obtain an electric heating material for the lower wing surface;

[0059] wherein the treatment temperatures of the first carbonization treatment, the second carbonization treatment and the third carbonization treatment are different;

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

[0061] In the present invention, according to different wing heating zones, the wing heating zones are: wing leading edge, wing upper wing surface and wing lower wing surface. Three pieces of fiber cloth are carbonized at different temperatures to obtain wing leading edge electric heating material, wing upper wing surface electric heating material and wing lower wing surface electric heating material respectively. Different heating powers are required for wing deicing parts to meet different resistivity requirements.

[0062] The present invention adopts high-temperature carbonization, places the fiber cloth into a high-temperature vacuum pyrolysis furnace, introduces Ar gas as a protective gas after vacuuming, and adopts different carbonization processes according to the different electric heating plate strengths and heating performances required for different heating zones 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 from pre-oxidized yarn and carbon fiber, wherein the volume content of the pre-oxidized yarn in the woven plain cloth is 20% to 40%, and the thickness of the woven plain cloth is 400 to 500 μm.

[0064] In some preferred embodiments, the first carbonization process comprises: in an inert gas atmosphere, heating to 250-350°C, such as 250°C, 300°C, 350°C, etc., at a rate of 4.5-5.5°C / min (for example, 4.5°C / min, 5°C / min, 5.5°C / min, etc.), and then heating to a first carbonization temperature at a rate of 2.5-3.5°C / min (for example, 2.5°C / min, 3°C / min, 3.5°C / min, etc.), to perform a first carbonization treatment;

[0065] Preferably, the first carbonization temperature is 750-850°C, for example, 750°C, 800°C, 850°C, etc., and the first carbonization treatment time is 60-80 minutes, for example, 60 minutes, 70 minutes, 80 minutes, etc.;

[0066] Preferably, before the first carbonization treatment, the first fiber cloth is subjected to ultrasonic cleaning and drying treatment in sequence, the ultrasonic cleaning time is preferably 25-35 min, for example, 25 min, 30 min, 35 min, etc., the drying temperature is preferably 75-85°C, for example, 75°C, 80°C, 85°C, etc., the drying time is preferably 0.5-1.5h, for example, 0.5h, 1h, 1.5h, etc.

[0067] Preferably, after the first carbonization treatment, a conductive silver paste and a 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: in an inert gas atmosphere, heating to 250-350°C, such as 250°C, 300°C, 350°C, etc., at a rate of 4.5-5.5°C / min (for example, 4.5°C / min, 5°C / min, 5.5°C / min, etc.), and then heating to a second carbonization temperature at a rate of 2.5-3.5°C / min (for example, 2.5°C / min, 3°C / min, 3.5°C / min, etc.), and performing a second carbonization treatment;

[0069] Preferably, the second carbonization temperature is 650-750°C, for example, 650°C, 700°C, 750°C, etc., and the second carbonization treatment time is 50-70 minutes, for example, 50 minutes, 60 minutes, 70 minutes, etc.;

[0070] Preferably, before the second carbonization treatment, the second fiber cloth is subjected to ultrasonic cleaning and drying treatment in sequence, the ultrasonic cleaning time is preferably 25-35 minutes, for example, 25 minutes, 30 minutes, 35 minutes, etc., the drying temperature is preferably 75-85°C, for example, 75°C, 80°C, 85°C, etc., the drying time is preferably 0.5-1.5 hours, for example, 0.5 hours, 1 hour, 1.5 hours, etc.;

[0071] Preferably, after the second carbonization treatment, a conductive silver paste and a copper tape with a connection terminal are sequentially applied to the electric heating material for the upper wing surface.

[0072] In some preferred embodiments, the process of the third carbonization treatment comprises: in an inert gas atmosphere, heating to 250-350°C at a rate of 4.5-5.5°C / min (for example, 4.5°C / min, 5°C / min, 5.5°C / min, etc.), for example, 250°C, 300°C, 350°C, etc., and then heating to a third carbonization temperature at a rate of 2.5-3.5°C / min (for example, 2.5°C / min, 3°C / min, 3.5°C / min, etc.), and performing the third carbonization treatment;

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

[0074] Preferably, before the third carbonization treatment, the third fiber cloth is subjected to ultrasonic cleaning and drying treatment in sequence, the ultrasonic cleaning time is preferably 25-35 min, for example, 25 min, 30 min, 35 min, etc., the drying temperature is preferably 75-85° C., for example, 75° C., 80° C., 85° C., etc., the drying time is preferably 0.5-1.5 h, for example, 0.5 h, 1 h, 1.5 h, etc.;

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

[0076] In some preferred embodiments, in the present invention, the dried wing leading edge electric heater, the wing upper surface electric heater and the wing lower surface electric heater are fixed with graphite fixtures to ensure that the carbonization process is smooth and not deformed.

[0077] A second aspect of the present invention provides an electric heating material for an aircraft wing with an integrated anti-icing structure and functions, which is prepared by the method for preparing the electric heating material for an aircraft wing with an integrated anti-icing structure and functions.

[0078] In the present invention, the electric heating material for an aircraft wing with an integrated deicing structure function prepared by the method for preparing the electric heating material for an aircraft wing with an integrated deicing structure function is an electric heating plate, which is used to de-ice the wing or slat of an aircraft. The electric heating plate consists of three parts, namely, a leading edge electric heating plate, an upper wing surface electric heating plate and a lower wing surface electric heating surface.

[0079] The third aspect of the present invention provides a method for preparing the electrothermal material for an anti-icing structure with integrated functions for an aircraft wing, or the use of the electrothermal material for an anti-icing structure with integrated functions for an aircraft wing in preparing an electrothermal anti-icing structure with integrated functions for an aircraft wing.

[0080] The integrated wing provided by the present invention is an integrated wing with high-efficiency electric heating anti-icing structure function, which is prepared by fiber-reinforced resin prepreg integrated layer and then through autoclave process, and the required electric heater resistance range is selected according to different heating zones of the wing. The integrated wing is composed of outer skin, upper insulation layer, electric heating layer, lower insulation layer and inner skin layer from outside to inside in accordance with the multi-layer structure, and the whole structure is integrated by autoclave process.

[0081] In some preferred embodiments, the wing with integrated electric thermal anti-icing structure function 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, and the electric heating layer is prepared by using the electric heating material;

[0082] Preferably, the upper insulating layer and the lower insulating layer both comprise glass fiber composite materials;

[0083] Preferably, the inner skin and the outer skin both comprise unidirectional carbon fiber composite laminates;

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

[0085] Preferably, the inner surface of the inner skin has a heat insulation layer, and copper foil wires are led out from both ends of the electric heating layer to supply power and generate heat.

[0086] In some preferred embodiments, the wing is manufactured by integrated molding using an autoclave process.

[0087] In some preferred embodiments, the autoclave process comprises: 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 reducing the temperature to room temperature;

[0088] Preferably, the first temperature is 80-100°C, for example, 80°C, 90°C, 100°C, etc.; the first insulation time is 55-65min, for example, 55min, 60min, 65min, etc.;

[0089] Preferably, the second temperature is 120-140°C, such as 120°C, 130°C, 140°C, etc., and the second insulation time is 110-130min, such as 110min, 120min, 130min, etc.

[0090] In the present invention, the specific process of the autoclave is: at 200-300Pa, the temperature is raised from room temperature to 80-100°C within 60 minutes, and then kept at 80-100°C for 60 minutes; then, the temperature is raised to 120-140°C within 30 minutes, and kept at this temperature for 110-130 minutes; finally, the temperature is lowered to room temperature within 120 minutes.

[0091] The present invention is further described below by way of 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] This embodiment provides a method for preparing an electric heating material for an aircraft wing with an integrated anti-icing structure and function, comprising the following steps:

[0094] (1) First, PAN-based preoxidized fibers and carbon fibers are woven into plain cloth as raw materials for wing heating plates. The woven fiber cloth has a thickness of 450 μm and a volume fraction of preoxidized fibers of 30%.

[0095] (2) According to the different wing heating zones, the woven electric heating sheet fiber cloth is cut into pieces of appropriate size and recorded as the wing leading edge electric heating sheet, the upper wing surface electric heating sheet and the lower wing surface electric heating sheet. According to the different heating powers required for the wing deicing parts, the three different electric heating sheets are carbonized at different temperatures to meet the requirements of different resistivities.

[0096] (2.1.1) Place the wing leading edge heater in anhydrous ethanol and clean it ultrasonically for 30 minutes to remove surface impurities.

[0097] (2.1.2) Place the ultrasonically treated wing leading edge heater in an oven and dry it thoroughly. Set the oven temperature to 80°C and the drying time to 1 hour.

[0098] (2.1.3) Fix the dried wing leading edge heater with graphite fixture to ensure that it is smooth and does not deform during the carbonization process.

[0099] (2.1.4) Place the graphite tooling equipped with the wing leading edge heater in a high-temperature pyrolysis furnace for high-temperature carbonization. During the high-temperature carbonization process, evacuate the air and introduce Ar gas as a protective gas. The heating rate from room temperature to 300°C is 5°C / min; the heating rate from 300°C to 800°C is 3°C / min, and the carbonization time at 800°C is 70 minutes.

[0100] (2.1.5) After carbonization is completed, cool naturally and remove the wing leading edge heating plate.

[0101] (2.1.6) Apply conductive silver paste evenly on both ends of the wing leading edge heater as electrodes. After the conductive silver paste solidifies, lay copper tape with wiring terminals on the surface and conduct a power-on test.

[0102] (2.2.1) Similarly, the wing upper surface heater was placed in anhydrous ethanol and ultrasonically cleaned for 30 minutes to remove surface impurities.

[0103] (2.2.2) Place the ultrasonically treated wing upper surface heater in an oven and dry it thoroughly. Set the oven temperature to 80°C and the drying time to 1 hour.

[0104] (2.2.3) Fix the dried upper wing surface heater with graphite fixture to ensure smoothness and no deformation during the carbonization process.

[0105] (2.2.4) Place the graphite tooling equipped with the wing upper wing surface electric heater in a high-temperature pyrolysis furnace for high-temperature carbonization treatment. During the high-temperature carbonization process, evacuate the air and introduce Ar gas as a protective gas. The heating rate from room temperature to 300°C is 5°C / min; the heating rate from 300°C to 700°C is 3°C / min, and the carbonization time at 700°C is 60 minutes.

[0106] (2.2.5) After carbonization is completed, cool naturally and remove the heating plate on the wing surface.

[0107] (2.2.6) Apply conductive silver paste evenly on both ends of the wing upper surface heating plate as electrodes. After the conductive silver paste solidifies, lay copper tape with wiring terminals on the surface and conduct a power-on test.

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

[0109] (2.3.2) Place the ultrasonically treated lower wing heating plate in an oven and dry it thoroughly. Set the oven temperature to 80°C and the drying time to 1 hour.

[0110] (2.3.3) Fix the dried lower wing heating plate with graphite fixture to ensure smoothness and no deformation during the carbonization process.

[0111] (2.3.4) Place the graphite tooling equipped with the wing lower wing surface electric heater in a high-temperature pyrolysis furnace for high-temperature carbonization treatment. During the high-temperature carbonization process, evacuate the air and introduce Ar gas as a protective gas. The heating rate from room temperature to 300°C is 5°C / min; the heating rate from 300°C to 600°C is 3°C / min, and the carbonization time at 600°C is 60 minutes.

[0112] (2.3.5) After carbonization is completed, cool naturally and remove the heating plate on the lower wing surface.

[0113] (2.3.6) Apply conductive silver paste evenly to both ends of the heater on the lower wing surface as electrodes. After the conductive silver paste solidifies, lay copper tape with wiring terminals on the surface and conduct a power-on test.

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

[0115] Example 2

[0116] This embodiment provides a method for preparing an electric heating material for an aircraft wing with an integrated anti-icing structure and function, comprising the following steps:

[0117] (1) First, PAN-based preoxidized fibers and carbon fibers are woven into plain cloth as raw materials for wing heating plates. The woven fiber cloth has a thickness of 400 μm and a volume fraction of preoxidized fibers of 40%.

[0118] (2) According to the different wing heating zones, the woven electric heating sheet fiber cloth is cut into pieces of appropriate size and recorded as the wing leading edge electric heating sheet, the upper wing surface electric heating sheet and the lower wing surface electric heating sheet. According to the different heating powers required for the wing deicing parts, the three different electric heating sheets are carbonized at different temperatures to meet the requirements of different resistivities.

[0119] (2.1.1) Place the wing leading edge heater in anhydrous ethanol and clean it ultrasonically for 25 minutes to remove surface impurities.

[0120] (2.1.2) Place the ultrasonically treated wing leading edge heater in an oven and dry it thoroughly. Set the oven temperature to 85°C and the drying time to 0.5 hours.

[0121] (2.1.3) Fix the dried wing leading edge heater with graphite fixture to ensure that it is smooth and does not deform during the carbonization process.

[0122] (2.1.4) Place the graphite tooling equipped with the wing leading edge heater in a high-temperature pyrolysis furnace for high-temperature carbonization. During the high-temperature carbonization process, evacuate the air and introduce Ar gas as a protective gas. The heating rate from room temperature to 250°C is 5.5°C / min; the heating rate from 250-850°C is 2.5°C / min, and the carbonization time at 850°C is 60 minutes.

[0123] (2.1.5) After carbonization is completed, cool naturally and remove the wing leading edge heating plate.

[0124] (2.1.6) Apply conductive silver paste evenly on both ends of the wing leading edge heater as electrodes. After the conductive silver paste solidifies, lay copper tape with wiring terminals on the surface and conduct a power-on test.

[0125] (2.2.1) Similarly, the wing upper surface heater was placed in anhydrous ethanol and ultrasonically cleaned for 30 minutes to remove surface impurities.

[0126] (2.2.2) Place the ultrasonically treated wing upper surface heater in an oven and dry it thoroughly. The oven temperature is set at 85°C and the drying time is set to 0.5 hours.

[0127] (2.2.3) Fix the dried upper wing surface heater with graphite fixture to ensure smoothness and no deformation during the carbonization process.

[0128] (2.2.4) Place the graphite tooling equipped with the wing upper wing surface electric heater in a high-temperature pyrolysis furnace for high-temperature carbonization treatment. During the high-temperature carbonization process, evacuate the air and introduce Ar gas as a protective gas. The heating rate from room temperature to 250°C is 5.5°C / min; the heating rate from 300-750°C is 2.5°C / min, and the carbonization time at 750°C is 50 minutes.

[0129] (2.2.5) After carbonization is completed, cool naturally and remove the heating plate on the wing surface.

[0130] (2.2.6) Apply conductive silver paste evenly on both ends of the wing upper surface heating plate as electrodes. After the conductive silver paste solidifies, lay copper tape with wiring terminals on the surface and conduct a power-on test.

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

[0132] (2.3.2) Place the ultrasonically treated lower wing heating plate in an oven and dry it thoroughly. The oven temperature is set at 85°C and the drying time is set to 0.5 hours.

[0133] (2.3.3) Fix the dried lower wing heating plate with graphite fixture to ensure smoothness and no deformation during the carbonization process.

[0134] (2.3.4) Place the graphite tooling equipped with the wing lower wing surface electric heater in a high-temperature pyrolysis furnace for high-temperature carbonization treatment. During the high-temperature carbonization process, evacuate the air and introduce Ar gas as a protective gas. The heating rate from room temperature to 250°C is 5.5°C / min; the heating rate from 300-650°C is 2.5°C / min, and the carbonization time at 650°C is 50 minutes.

[0135] (2.3.5) After carbonization is completed, cool naturally and remove the heating plate on the lower wing surface.

[0136] (2.3.6) Apply conductive silver paste evenly to both ends of the heater on the lower wing surface as electrodes. After the conductive silver paste solidifies, lay copper tape with wiring terminals on the surface and conduct a power-on test.

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

[0138] Example 3

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

[0140] (1) First, PAN-based preoxidized fibers and carbon fibers are woven into plain cloth as raw materials for wing heating plates. The woven fiber cloth has a thickness of 500 μm and a volume fraction of preoxidized fibers of 20%.

[0141] (2) According to the different wing heating zones, the woven electric heating sheet fiber cloth is cut into pieces of appropriate size and recorded as the wing leading edge electric heating sheet, the upper wing surface electric heating sheet and the lower wing surface electric heating sheet. According to the different heating powers required for the wing deicing parts, the three different electric heating sheets are carbonized at different temperatures to meet the requirements of different resistivities.

[0142] (2.1.1) Place the wing leading edge heater in anhydrous ethanol and clean it ultrasonically for 35 minutes to remove surface impurities.

[0143] (2.1.2) Place the ultrasonically treated wing leading edge heater in an oven and dry it thoroughly. Set the oven temperature to 75°C and the drying time to 1.5 hours.

[0144] (2.1.3) Fix the dried wing leading edge heater with graphite fixture to ensure that it is smooth and does not deform during the carbonization process.

[0145] (2.1.4) Place the graphite tooling equipped with the wing leading edge heater in a high-temperature pyrolysis furnace for high-temperature carbonization. During the high-temperature carbonization process, evacuate the air and introduce Ar gas as a protective gas. The heating rate from room temperature to 350°C is 4.5°C / min; the heating rate from 250-750°C is 3.5°C / min, and the carbonization time at 750°C is 80 minutes.

[0146] (2.1.5) After carbonization is completed, cool naturally and remove the wing leading edge heating plate.

[0147] (2.1.6) Apply conductive silver paste evenly on both ends of the wing leading edge heater as electrodes. After the conductive silver paste solidifies, lay copper tape with wiring terminals on the surface and conduct a power-on test.

[0148] (2.2.1) Similarly, the wing upper surface heater was placed in anhydrous ethanol and ultrasonically cleaned for 30 minutes to remove surface impurities.

[0149] (2.2.2) Place the ultrasonically treated wing upper surface heater in an oven and dry it thoroughly. Set the oven temperature to 75°C and the drying time to 1.5 hours.

[0150] (2.2.3) Fix the dried upper wing surface heater with graphite fixture to ensure smoothness and no deformation during the carbonization process.

[0151] (2.2.4) Place the graphite tooling equipped with the wing upper wing surface electric heater in a high-temperature pyrolysis furnace for high-temperature carbonization treatment. During the high-temperature carbonization process, evacuate the air and introduce Ar gas as a protective gas. The heating rate from room temperature to 350°C is 4.5°C / min; the heating rate from 300-650°C is 3.5°C / min, and the carbonization time at 650°C is 70 minutes.

[0152] (2.2.5) After carbonization is completed, cool naturally and remove the heating plate on the wing surface.

[0153] (2.2.6) Apply conductive silver paste evenly on both ends of the wing upper surface heating plate as electrodes. After the conductive silver paste solidifies, lay copper tape with wiring terminals on the surface and conduct a power-on test.

[0154] (2.3.1) Similarly, the heater on the lower wing surface was placed in anhydrous ethanol and ultrasonically cleaned for 30 minutes to remove surface impurities.

[0155] (2.3.2) Place the ultrasonically treated wing lower surface heater in an oven and dry it thoroughly. Set the oven temperature to 75°C and the drying time to 1.5 hours.

[0156] (2.3.3) Fix the dried lower wing heating plate with graphite fixture to ensure smoothness and no deformation during the carbonization process.

[0157] (2.3.4) Place the graphite tooling equipped with the wing lower wing heating plate in a high-temperature pyrolysis furnace for high-temperature carbonization treatment. During the high-temperature carbonization process, evacuate the air and introduce Ar gas as a protective gas. The heating rate from room temperature to 350°C is 4.5°C / min; the heating rate from 300-550°C is 3.5°C / min, and the carbonization time at 550°C is 70 minutes.

[0158] (2.3.5) After carbonization is completed, cool naturally and remove the heating plate on the lower wing surface.

[0159] (2.3.6) Apply conductive silver paste evenly to both ends of the heater on the lower wing surface as electrodes. After the conductive silver paste solidifies, lay copper tape with wiring terminals on the surface and conduct a power-on test.

[0160] (3) The leading edge heating plate, the upper wing surface heating plate and the edge portion of the lower wing surface heating plate are encapsulated with conductive adhesive to obtain an integrated wing electric heating structure.

[0161] Example 4

[0162] This embodiment provides a method for preparing an electrothermal material for an aircraft wing with integrated anti-icing structure and function, which is different from the embodiment 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 in Example 1.

[0165] Example 5

[0166] This embodiment provides a method for preparing an electrothermal material for an aircraft wing with integrated anti-icing structure and function, which is different from the embodiment 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 those in Example 1.

[0169] Example 6

[0170] This embodiment provides a method for preparing an electrothermal material for an aircraft wing with integrated anti-icing structure and function, which is different from the embodiment 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 those in Example 1.

[0173] Example 7

[0174] This embodiment provides a method for preparing an electrothermal material for an aircraft wing with integrated anti-icing structure and function, which is different from the embodiment 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 those in Example 1.

[0177] Example 8

[0178] This embodiment provides a method for preparing an electrothermal material for an aircraft wing with integrated anti-icing structure and function, which is different from the embodiment 1 in that:

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

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

[0181] Example 9

[0182] This embodiment provides a method for preparing an electrothermal material for an aircraft wing with integrated anti-icing structure and function, which is different from the embodiment 1 in that:

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

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

[0185] Example 10

[0186] This embodiment provides a method for preparing an electrothermal material for an aircraft wing with integrated anti-icing structure and function, which is different from the embodiment 1 in that:

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

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

[0189] Embodiment 11

[0190] This embodiment provides a method for preparing an electrothermal material for an aircraft wing with integrated anti-icing structure and function, which is different from the embodiment 1 in that:

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

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

[0193] Application Example 1-11

[0194] Application Examples 1-11 provide an integrated wing with an electric heating anti-icing structure function, respectively using the integrated wing electric heating layer structure prepared in Examples 1-11, and the preparation process is as follows:

[0195] (1) The isolation film, PTFE cloth, inner skin, lower insulation layer, integrated wing electric heating layer prepared in Examples 1-11, upper insulation layer, outer skin, PTFE cloth, adhesive tape, and isolation film are tightly laid on the wing mold, and then placed in a vacuum bag, evacuated, and placed in an autoclave for hot pressing. The autoclave process is: at 250Pa, the temperature is raised from room temperature to 90°C within 60 minutes, and then kept at 90°C for 60 minutes; then, the temperature is raised to 130°C within 30 minutes, and kept at this temperature for 120 minutes; finally, the temperature is lowered to room temperature within 120 minutes.

[0196] (2) After being taken out from the autoclave, the vacuum bag is removed and demolding is carried out, and then the isolation film, adhesive tape, polytetrafluoroethylene cloth and other auxiliary materials are removed to obtain a high-efficiency electric heating anti-icing structure and function integrated wing.

[0197] Application Example 12

[0198] This application example provides an integrated wing with an electric thermal anti-icing structure function. The difference from Application Example 1 is that in the autoclave process, under 200Pa, the temperature is raised from room temperature to 80°C within 60 minutes, and then kept at 80°C for 55 minutes; then, the temperature is raised to 140°C within 30 minutes, and kept at this temperature for 110 minutes; finally, the temperature is lowered to room temperature within 120 minutes.

[0199] Application Example 13

[0200] This application example provides an integrated wing with an electric thermal anti-icing structure function. The difference from Application Example 1 is that in the autoclave process, under 300Pa, the temperature is raised from room temperature to 100°C within 60 minutes, and then kept at 100°C for 65 minutes; then, the temperature is raised to 120°C within 30 minutes, and kept at this temperature for 130 minutes; finally, the temperature is lowered to room temperature within 120 minutes.

[0201] Comparative Example 1

[0202] This comparative example provides a method for preparing an electric heating material for an aircraft wing with an integrated anti-icing structure function, which is different from Example 1 in that:

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

[0204] Comparative Example 2

[0205] This comparative example provides a method for preparing an electric heating material for an aircraft wing with an integrated anti-icing structure function, which is different from Example 1 in that:

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

[0207] Comparative Example 3

[0208] This comparative example provides a method for preparing an electric heating material for an aircraft wing with an integrated anti-icing structure function, which is different from Example 1 in that:

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

[0210] Comparative Example 4

[0211] This comparative example provides a method for preparing an electric heating material for an aircraft wing with an integrated anti-icing structure function, which is different from Example 1 in that:

[0212] In step (1), only carbon fiber is used as raw material, and PAN-based pre-oxidized fiber is not added.

[0213] Comparative Example 5

[0214] The electric heating material of this comparative example adopts copper mesh.

[0215] Comparative Application Examples 1-5

[0216] Comparative Application Examples 1-5 provide a method for preparing an integrated wing, and the integrated wing electric heating layer structures prepared by Comparative Examples 1-5 are respectively used, and the preparation method is consistent with that of Application Example 1.

[0217] Test Case

[0218] Test samples: the integrated wing with electric thermal anti-icing structure function prepared in Application Example 1-13 and the integrated wing prepared in Comparative Application Example 1-5.

[0219] Test method: Connect the integrated wing to a DC power supply, control the voltage at 120V, record the current after it stabilizes, and then calculate the power density. Use an infrared thermal imager to detect the surface temperature of the material, obtain the temperature distribution diagram, and then calculate the maximum temperature difference on the surface. The temperature difference reflects the heating uniformity of the material. The smaller the temperature difference, the more uniform the heating of the material.

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

[0221]

[0222]

[0223]

[0224] Referring to the data in Table 1, in the present invention, it can be known from Application Example 1, Application Example 4 and Application Example 5 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 it is to the transformation of the pre-oxidized yarn to the carbon fiber. At this time, the lower the resistance of the fiber cloth, the higher the heating power density, and vice versa.

[0225] It can be seen from Application Examples 1, 6 and 7 that if the carbonization temperature is not within the specific carbonization range of the present invention, 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 invention, compared with Application Example 1, the resistance of the electric heating material of Application Example 7 is smaller, and the heating efficiency of the product of Application Example 7 is too large and difficult 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 invention, compared with Application Example 1, the electric heating power density of the product of Application Example 6 becomes smaller, affecting the electric heating efficiency of the product.

[0226] It can be seen from Application Examples 1, 8 and 9 that the higher the pre-oxidized wire content, the greater the resistance and the lower the heating power density; compared with Application Example 1, the proportion of pre-oxidized wire in Application Example 11 is greater than a specific range, and its heating power density is relatively low, which affects the electrothermal efficiency of the product; compared with Application Example 1, the proportion of pre-oxidized wire in Application Example 10 is less than a specific range, and although its heating power density is increased, it leads to a smaller resistance of the electrothermal material, and the heating efficiency of the product is too large and difficult to control, which affects the heating uniformity of the product.

[0227] Comparative Application Examples 1-3 cannot achieve the effect of meeting the requirements of different resistivity according to the different heating powers required for deicing parts of the wing. According to Comparative Application Examples 4 and 5, the products lack component pre-oxidized wire and use existing copper mesh materials as the electric heating layer. The performance of the products in Comparative Application Examples 4 and 5 is far inferior to that of the product in 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 heating power density.

[0229] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, rather than to limit it. Although the present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art should understand that they can still modify the technical solutions described in the aforementioned embodiments, or replace some or all of the technical features therein with equivalents. However, these modifications or replacements do not cause the essence of the corresponding technical solutions to deviate from the scope of the technical solutions of the embodiments of the present invention.

Claims

1. A method for preparing an electric heating material for an aircraft wing with integrated anti-icing and de-icing structure function, characterized in that: The following steps are involved: Using a fiber cloth woven from preoxidized 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 function; Wherein, the pre-oxidized yarn is PAN-based pre-oxidized yarn.

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 fiber cloth is a woven plain cloth; Preferably, the volume content of pre-oxidized yarn in the woven plain fabric is 20% to 40%; Preferably, the thickness of the woven plain fabric is 400-500 μm.

3. 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: Using the first fiber cloth as a raw material, performing a first carbonization treatment 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 wing surface of the wing; The third fiber cloth is used as a raw material and subjected to a third carbonization treatment to obtain an electric heating material for the lower wing surface; The first carbonization treatment, the second carbonization treatment and the third carbonization treatment have different treatment temperatures.

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 3, characterized in that: The first fiber cloth, the second fiber cloth and the third fiber cloth are all woven plain cloths woven from pre-oxidized yarn and carbon fiber.

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 3, characterized in that: The first carbonization process comprises: in an inert gas atmosphere, heating to 250-350° C. at a rate of 4.5-5.5° C. / min, and then heating to a first carbonization temperature at a rate of 2.5-3.5° C. / min, to perform a first carbonization treatment; Preferably, the first carbonization temperature is 750-850°C, and the first carbonization treatment time is 60-80 minutes; Preferably, before the first carbonization treatment, the first fiber cloth is subjected to ultrasonic cleaning and drying treatment in sequence, the ultrasonic cleaning time is preferably 25-35 minutes, the drying temperature is preferably 75-85° C., and the drying time is preferably 0.5-1.5 hours; Preferably, after the first carbonization treatment, a conductive silver paste and a copper tape with a terminal are sequentially applied to the electric heating material for the wing leading edge.

6. The method for preparing the electric heating material for an aircraft wing with integrated anti-icing and de-icing structure function according to claim 3, characterized in that: The second carbonization process comprises: in an inert gas atmosphere, heating to 250-350°C at a rate of 4.5-5.5°C / min, and then heating to a second carbonization temperature at a rate of 2.5-3.5°C / min, to perform a second carbonization treatment; Preferably, the second carbonization temperature is 650-750°C, and the second carbonization treatment time is 50-70 minutes; Preferably, before the second carbonization treatment, the second fiber cloth is subjected to ultrasonic cleaning and drying treatment in sequence, the ultrasonic cleaning time is preferably 25-35 minutes, the drying temperature is preferably 75-85° C., and the drying time is preferably 0.5-1.5 hours; Preferably, after the second carbonization treatment, a conductive silver paste and a copper tape with a connection terminal are sequentially applied to the electric heating material for the upper wing surface.

7. The method for preparing the electric heating material for an aircraft wing with integrated anti-icing and de-icing structure function according to claim 3, characterized in that: The third carbonization process comprises: in an inert gas atmosphere, heating to 250-350°C at a rate of 4.5-5.5°C / min, and then heating to a third carbonization temperature at a rate of 2.5-3.5°C / min, and performing the third carbonization process; Preferably, the third carbonization temperature is 550-650° C., and the third carbonization treatment time is 50-70 min; Preferably, before the third carbonization treatment, the third fiber cloth is subjected to ultrasonic cleaning and drying treatment in sequence, the ultrasonic cleaning time is preferably 25-35 minutes, the drying temperature is preferably 75-85° C., and the drying time is preferably 0.5-1.5 hours; Preferably, after the third carbonization treatment, a conductive silver paste and a copper tape with a terminal are sequentially applied to the electric heating material for the lower wing surface.

8. The electrothermal material for an aircraft wing with an integrated anti-icing structure and function prepared by the method for preparing the electrothermal material for an aircraft wing with an integrated anti-icing structure and function as described in any one of claims 1 to 7.

9. The method for preparing the electrothermal material for an aircraft wing with an integrated anti-icing structure and functions as described in any one of claims 1 to 7 or the use of the electrothermal material for an aircraft wing with an integrated anti-icing structure and functions as described in claim 8 in preparing an electric thermal anti-icing structure and functions integrated wing.

10. The use according to claim 9, characterized in that The electric heating anti-icing and de-icing structure and function integrated wing is set to 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, and the electric heating layer is made of the electric heating material for the anti-icing and de-icing structure and function integrated wing; Preferably, the upper insulating layer and the lower insulating layer both comprise glass fiber composite materials; Preferably, the inner skin and the outer skin both comprise unidirectional carbon fiber composite laminates; Preferably, the inner surface of the outer skin has a carbon nanotube / reduced graphene oxide thermal conductive coating; Preferably, the inner surface of the inner skin has a heat insulation layer, and copper foil wires are led out from both ends of the electric heating layer to supply power and generate heat for itself; Preferably, the wing is made by integrated molding using a hot-pressing process; Preferably, the autoclave process comprises: 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 reducing the temperature to room temperature; Preferably, the first temperature is 80-100° C., and the first insulation time is 55-65 min; Preferably, the second temperature is 120-140° C., and the second insulation time is 110-130 min.

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