An aircraft and its surface flexible anti-icing / deicing composite film and preparation method thereof

Abstract

An aircraft and a surface flexible anti-icing / deicing composite film and a preparation method thereof, wherein the surface of the aircraft parts has a surface flexible anti-icing / deicing composite film, and the film comprises: a first insulating film, formed by thermal spraying, magnetron sputtering, ion beam assisted deposition, chemical vapor deposition or magnetic filtration cathode vacuum arc source deposition on the substrate surface; a flexible electric heating film, located on the first insulating film, and set according to different working voltages and unit area power requirements; a second insulating film, located on the flexible electric heating film, formed by thermal spraying, magnetron sputtering, ion beam assisted deposition or chemical vapor deposition on the surface of the flexible electric heating film; and a super-hydrophobic film, located on the second insulating film, and formed by magnetron sputtering, ion beam assisted deposition or magnetic filtration cathode vacuum arc source deposition on the surface of the second insulating film. The present invention also discloses a preparation method of the surface flexible anti-icing / deicing composite film.

Description

Technical Field

[0001] The invention relates to aircraft deicing technology, in particular to an aircraft and a surface flexible anti-icing / deicing composite film based on active and passive coupling and a preparation method thereof. Background Art

[0002] Aircraft icing is the phenomenon of ice accumulation on certain parts of the aircraft fuselage surface. It is prone to occur on protruding parts such as the leading edge of the wing and tail, windshield, pitot tube, antenna, engine air intake, etc. Wind tunnel tests have shown that when there is half an inch of ice accumulation on the leading edge of the wing, it will reduce lift by 50% and increase drag by 60%. In addition, windshield icing will affect the pilot's visual flight, pitot tube icing will cause important flight data such as flight altitude and speed to be inaccurately displayed, and antenna icing will affect air-to-ground communications or cause navigation interruption. Under extreme conditions such as low temperature, high humidity, and high speed flight, the ice thickness can reach 2 to 3 inches within 5 minutes, and high-intensity de-icing operations are required at this time.

[0003] Thermal deicing is one of the more practical active deicing methods at present. In this process, the activation of the thermal deicing system depends on the pilot's field of vision. If ice forms in a position that the pilot cannot observe, it is difficult to de-ice. Moreover, the shutdown of the thermal deicing system after deicing also depends on the pilot's observation, which requires more energy consumption and takes a long time to de-ice. In recent years, through in-depth research on the mechanism of icing, functional anti-icing films have gradually come into people's sight as a passive anti-icing method. Many studies have shown that super-hydrophobic surfaces can indeed delay the freezing time, reduce the amount of ice, and reduce ice adhesion. However, super-hydrophobic materials are generally organic materials. There are great problems with the mechanical strength, high temperature resistance and service life of this material. After experiencing multiple high-temperature icing-deicing tests, it is easy to age and decompose, and the micro-nanostructure that penetrates into the ice layer will be damaged. Continuous cycles cause the material surface to lose its super-hydrophobic properties.

[0004] The prior art on the anti-icing / deicing method combining super-hydrophobic surface with electric heat, such as the anti-icing and deicing system based on active and passive coupling, uses the input heat to melt ice at the tip of the heating wire, which is efficient in deicing, economical and environmentally friendly. However, the bonding method is adopted between the layers, and the bonding strength needs to be improved. In addition, the thermal conductive wire runs through the super-hydrophobic film and the thermal insulation layer, and the tip is exposed to the air, which is very easy to deform at high altitudes, and the circuit safety cannot be guaranteed. The practicality needs to be discussed; and the wind speed tube composite film, in which the first transition layer, the conductive layer, the second transition layer, the thermal conductive layer, the third transition layer, and the hydrophobic layer are deposited on the surface of the wind speed tube substrate in sequence. Although the composite film has comprehensive conductive , thermal conductivity and hydrophobic properties, but the hydrophobic layer is an inorganic hydrophobic layer, and the surface has not been modified in any way, and the hydrophobic ability needs to be improved; the energy-saving anti-icing film composited with a super-hydrophobic film and a heating film, a thermal insulation film, a waterproof protective film with thermal conductivity, and a hydrophobic coating are sprayed on the surface of the substrate in sequence. Although it can play the role of heating and hydrophobic deicing, its high temperature resistance needs to be improved; the anti-icing composite film includes a metal film layer, a metal nitride film layer, a nanorod-shaped zinc oxide layer, and a hydrophobic layer deposited in sequence. The film has excellent super-hydrophobic properties and can achieve obvious anti-icing effect, but the heating power and insulation performance need to be improved.

[0005] In addition, the preparation of aircraft parts adopts the method of substrate → processing pre-buried cable duct → filling heating wire → welding buried cable duct → polishing → preparing hydrophobic film on the surface. However, defects such as pores, incomplete welding and welding cracks are easily generated in the welding process, which seriously affect the bonding strength of the surface hydrophobic film in a high temperature environment, and there is a risk of short circuit and leakage of the heating route. Summary of the invention

[0006] The technical problem to be solved by the present invention is to provide an aircraft and a flexible anti-icing / de-icing composite film on its surface and a preparation method thereof in response to the above-mentioned defects of the prior art, so as to overcome the defects in the prior art such as low buried welding forming rate of heating wires of aircraft parts, poor anti-icing effect of the film, and short life of the film when used in high temperature environment, so as to improve the reliability of aircraft parts during operation.

[0007] In order to achieve the above object, the present invention provides a surface flexible anti-icing / deicing composite film, which comprises:

[0008] A first insulating film is disposed on the surface of the substrate to be protected from / de-iced, wherein the first insulating film is an inorganic insulating film formed by thermal spraying, magnetron sputtering, ion beam assisted deposition, chemical vapor deposition or magnetic filtered cathode vacuum arc source deposition on the surface of the substrate;

[0009] A flexible electric heating film, located on the first insulating film, wherein the flexible electric heating film is arranged according to different working voltages and power per unit area requirements;

[0010] A second insulating film, located on the flexible electric heating film, wherein the second insulating film is an inorganic insulating film formed on the surface of the flexible electric heating film by thermal spraying, magnetron sputtering, ion beam assisted deposition or chemical vapor deposition; and

[0011] A super-hydrophobic film is located on the second insulating film. The super-hydrophobic film is a CrN-based film formed by depositing on the surface of the second insulating film by magnetron sputtering, ion beam assisted deposition or magnetic filtration cathode vacuum arc source. The surface of the CrN-based film has a super-hydrophobic structure.

[0012] The above-mentioned surface flexible anti-icing / de-icing composite film, wherein the flexible electric heating film is set to a flexible resistance route that meets the set heating requirements through a template method.

[0013] In the above-mentioned surface flexible anti-icing / de-icing composite film, the first insulating film is an inorganic insulating film of silicon oxide, silicon nitride, aluminum oxide or aluminum nitride, and the thickness of the first insulating film is 50-200um.

[0014] The above-mentioned surface flexible anti-icing / deicing composite film, wherein the flexible electric heating film is formed on the surface of the first insulating film by magnetron sputtering, ion beam assisted deposition or magnetic filtered cathode vacuum arc source deposition.

[0015] The above-mentioned surface flexible anti-icing / de-icing composite film, wherein the flexible electric heating film is a pure metal film of Ni, Cr, Cu or Zn or a NiCr alloy film, and the thickness of the flexible electric heating film is 5-20um.

[0016] In the above-mentioned surface flexible anti-icing / de-icing composite film, the second insulating film is an inorganic insulating film of silicon oxide, silicon nitride, aluminum oxide or aluminum nitride, and the thickness of the second inorganic insulating film is 25-100um.

[0017] The above-mentioned surface flexible anti-icing / de-icing composite film, wherein the super-hydrophobic film is a CrN, CrNiN, CrAlN or CrAlSiN film, and the thickness of the super-hydrophobic film is 2-10 um.

[0018] In order to better achieve the above-mentioned object, the present invention also provides a method for preparing a surface flexible anti-icing / deicing composite film, which comprises the following steps:

[0019] S100, cleaning and drying the substrate surface of the required anti-icing / de-icing part;

[0020] S200, preparing a first insulating film, and depositing an inorganic insulating film on the surface of the substrate by thermal spraying, magnetron sputtering, ion beam assisted deposition, chemical vapor deposition or magnetic filtered cathode vacuum arc source deposition;

[0021] S300, preparing a flexible electric heating film on the first insulating film, wherein the flexible electric heating film is set according to different working voltages and power per unit area requirements;

[0022] S400, preparing a second insulating film, and forming an inorganic insulating film on the surface of the flexible electric heating film by thermal spraying, magnetron sputtering, ion beam assisted deposition or chemical vapor deposition;

[0023] S500, forming a CrN-based film on the surface of the second insulating film by magnetron sputtering, ion beam assisted deposition or magnetic filtered cathode vacuum arc source deposition; and

[0024] S600, preparing a micro-convex structure on the surface of the CrN-based film, and finally forming a CrN-based film with a super-hydrophobic structure.

[0025] In the above-mentioned method for preparing the surface flexible anti-icing / de-icing composite film, the cleaning in step S100 includes:

[0026] S101, soaking the substrate in tetrachloroethylene for 10 to 30 minutes to remove surface grease;

[0027] S102, ultrasonically cleaning the substrate for 10 to 20 minutes;

[0028] S103, placing the substrate in an acetone solution for ultrasonic cleaning for 10 to 20 minutes;

[0029] S104, placing the substrate in an alcohol solution for ultrasonic cleaning for 10 to 20 minutes;

[0030] S105, placing the substrate in a deionized beam solution for ultrasonic cleaning 2 to 5 times, each time for 10 to 20 minutes; and

[0031] S106, placing the substrate in a 70° C. oven and drying for 10 to 30 minutes.

[0032] In the above-mentioned method for preparing the surface flexible anti-icing / deicing composite film, in step S200, a gradient Al2O3 film is deposited on the surface of the substrate by magnetron sputtering.

[0033] The method for preparing the surface flexible anti-icing / de-icing composite film, wherein step S200 further comprises:

[0034] S201, placing the substrate into a vacuum coating chamber, turning on a vacuum pump unit to evacuate the vacuum coating chamber, and heating the vacuum coating chamber at the same time;

[0035] S202, when the temperature reaches the set value and the vacuum degree is less than 8×10 -4When the flow rate is 0.5 Pa, close the throttle valve, introduce 1.0-2.0 Pa of Ar, turn on the power to sputter the Al target, and the sputtering power is 0.4-0.6 kw;

[0036] S203, introducing O2 into the vacuum coating chamber while coating, reducing the amount of Ar introduced, and maintaining the pressure of the vacuum coating chamber unchanged, so that the flow ratio of O2 to Ar reaches 3:1 to 4:1; and

[0037] S204, after 6 to 10 hours of coating, turn off the power supply and gas source, reduce the temperature to less than 100° C., open the vacuum coating chamber and take out the substrate.

[0038] In the above-mentioned method for preparing the surface flexible anti-icing / deicing composite film, in step S300, the plated material is deposited on the template surface by a template method, and then the template is removed to obtain a flexible electric heating film with the standard size of the template.

[0039] The method for preparing the surface flexible anti-icing / deicing composite film, wherein in step S300, a NiCr alloy film is deposited on the surface of a template placed on the surface of the first insulating film by magnetron sputtering, the Ar flow rate is 50-70 sccm, and the vacuum degree of the vacuum chamber is maintained at 1.3×10 -2 ~1.6×10 -2 Pa, the sputtering power is 0.4-0.6kw, and the coating time is 5-8 hours.

[0040] In the above-mentioned method for preparing a surface flexible anti-icing / de-icing composite film, in step S400, the second insulating film is an AlN film, the template placed on the surface of the first insulating film 2 is removed, and the AlN film is deposited on the surface of the first insulating film and the flexible electric heating film by magnetron sputtering.

[0041] The method for preparing the surface flexible anti-icing / de-icing composite film, wherein step S400 further comprises:

[0042] S401, placing the substrate into a vacuum coating chamber, turning on a vacuum pump unit to evacuate the vacuum coating chamber, and heating the vacuum coating chamber at the same time;

[0043] S402, when the temperature reaches the set value and the vacuum degree is less than 8×10 -4 When the flow rate is Pa, close the throttle valve and introduce N2 and Ar flow, with the flow ratio of N2:Ar=1:1~2:1;

[0044] S403, turning on the power to sputter the Al target, with the sputtering power being 0.4-0.6kw; and

[0045] S404, after 3 to 4 hours of coating, turn off the power supply and gas source, reduce the temperature to less than 100° C., open the vacuum coating chamber and take out the substrate.

[0046] The method for preparing the above-mentioned surface flexible anti-icing / deicing composite film, wherein in step S500, a CrNiN film is deposited on the surface of the second insulating film by using a magnetic filtered cathode vacuum arc source deposition, the CrNi target arc source current is 60-80A, the nitrogen flow rate is 50-70sccm, and the vacuum degree of the vacuum chamber is 1.3×10 -2 ~1.6×10 -2 Pa, the deposition negative bias is 100-300 V, the duty cycle is 70-90%, and the deposition time is 2-3 hours.

[0047] In the above-mentioned method for preparing the surface flexible anti-icing / deicing composite film, in step S600, the micro-protrusion structure is prepared on the surface of the CrNiN film by using a wet sandblasting method.

[0048] In the above-mentioned method for preparing the surface flexible anti-icing / deicing composite film, the wet sandblasting method uses 2000-5000 mesh white corundum sand, the sandblasting pressure is 0.2-0.4Pa, the sandblasting angle is 45-60°, and the sandblasting time is 30-60s.

[0049] In order to better achieve the above-mentioned purpose, the present invention further provides an aircraft, wherein the surfaces of the aircraft components have the above-mentioned surface flexible anti-icing / de-icing composite film.

[0050] The technical effects of the present invention are:

[0051] The aircraft and its flexible anti-icing / de-icing composite film based on the active and passive coupling surface and the preparation method of the aircraft of the present invention combine the advantages of simple operation and strong controllability of active de-icing with significant effect of passive de-icing, and can overcome the defects of low buried welding forming rate of heating wires of aircraft parts in the prior art, poor anti-icing effect of the film, and short life of the film when used in high temperature environment, and can effectively prevent icing / de-icing and improve the reliability of aircraft parts during operation.

[0052] The present invention is described in detail below with reference to the accompanying drawings and specific embodiments, but is not intended to limit the present invention. BRIEF DESCRIPTION OF THE DRAWINGS

[0053] Figure 1 A schematic diagram of a composite film structure according to an embodiment of the present invention;

[0054] Figure 2 Schematic diagram of the microstructure of a super-hydrophobic film according to an embodiment of the present invention.

[0055] Among them, the reference numerals

[0056] 1. Matrix

[0057] 2First insulating film

[0058] 3Flexible electric heating film

[0059] 4. Second insulating film

[0060] 5Super hydrophobic film

[0061] 51 micro-convex

[0062] 52 Air gap

[0063] 6 Water Drops DETAILED DESCRIPTION

[0064] The structural principle and working principle of the present invention are described in detail below in conjunction with the accompanying drawings:

[0065] See also Figure 1 , Figure 1 The composite film structure schematic diagram of an embodiment of the present invention. The aircraft surface flexible anti-icing / de-icing composite film of the present invention comprises: a first insulating film 2, which is arranged on the surface of a substrate 1 at the part of the aircraft required for anti-icing / de-icing, and the first insulating film 2 is an inorganic insulating film formed by thermal spraying, magnetron sputtering, ion beam assisted deposition, chemical vapor deposition or magnetic filtration cathode vacuum arc source deposition on the surface of the substrate 1; a flexible electric heating film 3, which is located on the first insulating film 2, and the flexible electric heating film 3 is set according to different working voltages and unit area power requirements. The flexible electric heating film 3 can also be set by a template method to be a flexible resistance circuit that meets the set heating requirements. line; a second insulating film 4, located on the flexible electric heating film 3, the flexible electric heating film 3 is sandwiched between the first insulating film 2 and the second insulating film 4; the second insulating film 4 is an inorganic insulating film formed on the surface of the flexible electric heating film 3 by thermal spraying, magnetron sputtering, ion beam assisted deposition or chemical vapor deposition; and a super-hydrophobic film 5, located on the second insulating film 4, the super-hydrophobic film 5 is a CrN-based film formed on the surface of the second insulating film 4 by magnetron sputtering, ion beam assisted deposition or magnetic filtration cathode vacuum arc source deposition, and the surface of the CrN-based film has a super-hydrophobic structure.

[0066] See also Figure 2 , Figure 2 Schematic diagram of the microstructure of a super-hydrophobic film 5 according to an embodiment of the present invention. The super-hydrophobic structure on the surface of the CrN-based film of this embodiment is a micro-protrusion 51 structure prepared on the surface of the CrN-based film. The micro-protrusion 51 structure is a plurality of uniformly and continuously distributed nano-scale micro-protrusions, with air gaps 52 between the protrusions. The structure has a good blocking effect on water droplets 6 similar to the surface of a lotus leaf.

[0067] In this embodiment, the first insulating film 2 is an inorganic insulating film of silicon oxide, silicon nitride, aluminum oxide or aluminum nitride, and the thickness of the first insulating film 2 is 50-200um, which plays a certain role in heat insulation and insulation. When the first insulating film 2 is prepared by magnetron sputtering, a metal Ti injection layer can be prepared first, and the injection dose is 1000-2000mC to improve the adhesion strength between the first insulating film 2 and the substrate 1.

[0068] The flexible electric heating film 3 is formed on the surface of the first insulating film 2 by magnetron sputtering, ion beam assisted deposition or magnetic filtration cathode vacuum arc source deposition. The flexible electric heating film 3 is a pure metal film of Ni, Cr, Cu or Zn or a NiCr alloy film. The thickness of the flexible electric heating film 3 is 5-20um and has a strong thermal conductivity. After depositing AlN film on the surface of the first insulating film 2 and the flexible electric heating film 3 by magnetron sputtering technology, the substrate 1 is placed in a vacuum heat treatment furnace, evacuated and heated to maintain 600-800°C, and then oxygen is introduced to maintain the air pressure at 0.01-0.05MPa, and thermal oxidation treatment is performed for 2-6 hours. Al2O3 is generated in situ on the surface of the AlN film to reduce the porosity of the AlN film and improve its insulation performance.

[0069] The second insulating film 4 is an inorganic insulating film of silicon oxide, silicon nitride, aluminum oxide or aluminum nitride, and the thickness of the second inorganic insulating film is 25-100 um.

[0070] The super hydrophobic film 5 is a CrN, CrNiN, CrAlN or CrAlSiN film, and the thickness of the super hydrophobic film 5 is 2-10 um. The surface of the CrN-based film can be modified to have a "lotus leaf-like" super hydrophobic structure by sandblasting, shot peening, laser surface treatment, etc. When the CrN-based film is prepared by magnetic filtration cathode vacuum arc deposition, the surface of the substrate 1 is cleaned by a magnetic filtration cathode vacuum arc source to improve the adhesion strength between the CrN-based film and the second insulating film 4.

[0071] The method for preparing the above-mentioned flexible anti-icing / de-icing composite film on the surface of an aircraft, which ultimately forms a multi-layer structure, a composite function and an efficient anti-icing / de-icing film, comprises the following steps:

[0072] Step S100, cleaning and drying the surface of the substrate 1 at the part of the aircraft that needs to be protected from / de-iced;

[0073] Step S200, preparing a first insulating film 2, by thermal spraying, magnetron sputtering, ion beam assisted deposition, chemical vapor deposition or magnetic filtered cathode vacuum arc source deposition on the surface of the substrate 1 to form an inorganic insulating film;

[0074] Step S300, preparing a flexible electric heating film 3 on the first insulating film 2, wherein the flexible electric heating film 3 is set according to different working voltages and power per unit area requirements;

[0075] Step S400, preparing a second insulating film 4, and forming an inorganic insulating film on the surface of the flexible electric heating film 3 by thermal spraying, magnetron sputtering, ion beam assisted deposition or chemical vapor deposition;

[0076] Step S500, forming a CrN-based film on the surface of the second insulating film 4 by magnetron sputtering, ion beam assisted deposition or magnetic filtered cathode vacuum arc source deposition; and

[0077] Step S600: preparing a micro-protrusion 51 structure on the surface of the CrN-based film, and finally forming a CrN-based film with a super-hydrophobic structure.

[0078] The cleaning in step S100 includes:

[0079] Step S101, soaking the substrate 1 in tetrachloroethylene for 10 to 30 minutes to remove surface grease;

[0080] Step S102, ultrasonically cleaning the substrate 1 for 10 to 20 minutes;

[0081] Step S103, placing the substrate 1 in an acetone solution for ultrasonic cleaning for 10 to 20 minutes;

[0082] Step S104, placing the substrate 1 in an alcohol solution for ultrasonic cleaning for 10 to 20 minutes;

[0083] Step S105, placing the substrate 1 in a deionized beam solution for ultrasonic cleaning 2 to 5 times, each time for 10 to 20 minutes; and

[0084] Step S106, placing the substrate 1 in a 70° C. oven and drying for 10 to 30 minutes.

[0085] In step S200 of this embodiment, a gradient Al2O3 film is deposited on the surface of the substrate 1 by magnetron sputtering. The method further comprises:

[0086] Step S201, placing the substrate 1 into a vacuum coating chamber, turning on a vacuum pump unit to evacuate the vacuum coating chamber, and heating the vacuum coating chamber at the same time;

[0087] Step S202: When the temperature reaches the set value and the vacuum degree is less than 8×10 -4 When the flow rate is 0.5 Pa, close the throttle valve, introduce 1.0-2.0 Pa of Ar, turn on the power to sputter the Al target, and the sputtering power is 0.4-0.6 kw;

[0088] Step S203, introducing O2 into the vacuum coating chamber while coating, reducing the amount of Ar introduced, and maintaining the pressure of the vacuum coating chamber unchanged, so that the flow ratio of O2 to Ar reaches 3:1 to 4:1; and

[0089] Step S204 , after 6 to 10 hours of coating, turn off the power supply and gas source, reduce the temperature to less than 100° C., open the vacuum coating chamber and take out the substrate 1 .

[0090] In step S300 of this embodiment, the plated material is deposited on the template surface by the template method, and then the template is removed to obtain a flexible electric heating film 3 with the standard size of the template. The NiCr alloy film is deposited on the template surface placed on the surface of the first insulating film 2 by magnetron sputtering, and the Ar flow rate is preferably 50-70 sccm, and the vacuum degree of the vacuum chamber is maintained at 1.3×10 -2 ~1.6×10 -2 Pa, the sputtering power is preferably 0.4-0.6 kw, and the coating time is preferably 5-8 hours.

[0091] In step S400 of this embodiment, the second insulating film 4 is an AlN film, the template placed on the surface of the first insulating film 2 is removed, and the AlN film is deposited on the surface of the first insulating film 2 and the flexible electric heating film 3 by magnetron sputtering. Further comprising:

[0092] Step S401, placing the substrate 1 into a vacuum coating chamber, turning on a vacuum pump unit to evacuate the vacuum coating chamber, and heating the vacuum coating chamber at the same time;

[0093] Step S402: When the temperature reaches the set value and the vacuum degree is less than 8×10 -4 When the pressure reaches Pa, close the throttle valve and introduce N2 and Ar flow rates, with the flow rate ratio preferably being N2:Ar = 1:1 to 2:1;

[0094] Step S403, turning on the power to sputter the Al target, the sputtering power is preferably 0.4-0.6kw; and

[0095] Step S404: After 3 to 4 hours of coating, the power supply and the gas source are turned off, the temperature is reduced to less than 100° C., and the vacuum coating chamber is opened to take out the substrate 1.

[0096] In step S500 of this embodiment, a CrNiN film is deposited on the surface of the second insulating film 4 by using a magnetic filtered cathode vacuum arc source deposition, the CrNi target arc source current is preferably 60-80A, the nitrogen flow rate is preferably 50-70sccm, and the vacuum degree of the vacuum chamber is preferably 1.3×10 -2 ~1.6×10 -2Pa, the deposition negative bias voltage is preferably 100-300 V, the duty cycle is preferably 70-90%, and the deposition time is preferably 2-3 hours.

[0097] In step S600 of this embodiment, the micro-protrusion 51 structure is prepared on the surface of the CrNiN film by wet sandblasting. The wet sandblasting method uses 2000-5000 mesh white corundum sand, the sandblasting pressure is preferably 0.2-0.4 Pa, the sandblasting angle is preferably 45-60°, and the sandblasting time is preferably 30-60s.

[0098] The surface flexible anti-icing / deicing composite film of the present invention and its preparation method can be applied to aerospace, shipbuilding, wind power generation and other fields, especially aircraft such as airplanes. The aircraft surface flexible anti-icing / deicing composite film can be prepared on the surface of aircraft parts such as aircraft propellers.

[0099] The present invention combines the advantages of active deicing and passive deicing on the surface of an aircraft, and not only breaks through the problem that the surface of the super-hydrophobic coating in the prior art becomes ineffective after being covered with ice, but also improves the disadvantage of high energy consumption of electric thermal deicing. It is an efficient and convenient anti-icing / deicing method based on active and passive coupling; a layer-by-layer multi-step construction method is adopted to place the flexible electric heating film 3 between the first insulating film 2 and the second insulating film 4, and the flexible electric heating film 3 will not be oxidized during the heating process, thereby ensuring the resistance stability; the CrN super-hydrophobic film 5 in direct contact with water is separated from the flexible electric heating film 3 to prevent the super-hydrophobic film 5 from failing or breaking, and liquid from entering the flexible electric heating film 3 to cause a short circuit, thereby ensuring the circuit safety; a magnetron sputtering device can be used to complete the preparation of all coatings, and the process is simple, convenient, efficient, highly repeatable, and has certain economic value and safety value; it can also be applied to a variety of different occasions, and the shape and thickness of the prepared coating can be adjusted according to different application fields to change the resistance value of the electric heating film to adapt to different usage requirements such as aircraft propellers, wind turbines and automotive parts.

[0100] In addition, the present invention effectively solves the problem of short film life when used in a high temperature environment, and improves the high temperature resistance of the film. The surface flexible anti-icing / deicing composite film prepared by the present invention is an inorganic coating, and its high temperature resistance can reach 600°C, while the hydrophobic coating of the prior art is not more than 400°C, which limits the heating power; the first insulating film 2 has a bonding strength of more than 30Gpa, the flexible electric heating film 3 has a bonding strength of more than 40N, the second insulating film 4 has a bonding strength of more than 30Gpa, the super-hydrophobic film 5 has a bonding strength of more than 80N, and the hardness exceeds 2000HV, the high bonding strength of each coating ensures that the coating will not fall off during the heating process, and the high hardness ensures that the surface coating is resistant to wind and sand erosion during the flight of the aircraft; that is, the high bonding strength and high hardness jointly ensure the high temperature resistance of the surface flexible anti-icing / deicing composite film, and then ensure the heating power of the surface flexible anti-icing / deicing composite film; the first insulating film 2 and the second insulating film 4 use oxides or nitrogen oxides, which are much higher than the insulation capacity of nitrides, ensuring the safety of the circuits in the flexible electric heating film 3.

[0101] Of course, the present invention may have many other embodiments. Without departing from the spirit and essence of the present invention, those skilled in the art may make various corresponding changes and modifications based on the present invention, but these corresponding changes and modifications should all fall within the scope of protection of the claims attached to the present invention.

Claims

1. A surface flexible anti-icing / de-icing composite film, characterized in that: include: A first insulating film is disposed on the surface of the substrate to be protected from / de-icing, wherein the first insulating film is an inorganic insulating film formed by thermal spraying, magnetron sputtering, ion beam assisted deposition, chemical vapor deposition or magnetic filtered cathode vacuum arc source deposition on the surface of the substrate; the bonding strength of the first insulating film exceeds 30 GPa; A flexible electric heating film is located on the first insulating film, and the flexible electric heating film is set according to different working voltages and power per unit area requirements; the flexible electric heating film is set to a flexible resistance route that meets the set heating requirements by a template method; the flexible electric heating film is formed on the surface of the first insulating film by magnetron sputtering, ion beam assisted deposition or magnetic filtration cathode vacuum arc source deposition; the flexible electric heating film is a pure metal film of Ni, Cr, Cu or Zn or a NiCr alloy film, the thickness of the flexible electric heating film is 5-20um, and the bonding strength exceeds 40N; A second insulating film is located on the flexible electric heating film, and the second insulating film is an inorganic insulating film formed on the surface of the flexible electric heating film by thermal spraying, magnetron sputtering, ion beam assisted deposition or chemical vapor deposition; the bonding strength of the second insulating film exceeds 30 GPa; and A super-hydrophobic film, located on the second insulating film, wherein the super-hydrophobic film is a CrN-based film formed by magnetron sputtering, ion beam assisted deposition or magnetic filtration cathode vacuum arc source deposition on the surface of the second insulating film, wherein the surface of the CrN-based film has a super-hydrophobic structure, wherein the super-hydrophobic structure is a micro-convex structure prepared on the surface of the CrN-based film, wherein the micro-convex structure is a plurality of uniformly and continuously distributed nano-scale micro-convex platforms, and an air gap is formed between adjacent nano-scale micro-convex platforms to block water droplets; the super-hydrophobic film is a CrN, CrNiN, CrAlN or CrAlSiN film, wherein the thickness of the super-hydrophobic film is 2-10um, the bonding strength exceeds 80N, and the hardness exceeds 2000HV; Among them, the high bonding strength and high hardness of each coating together ensure the high temperature resistance and heating power of the surface flexible anti-icing / de-icing composite film.

2. The surface flexible anti-icing / de-icing composite film according to claim 1, characterized in that: The first insulating film is an inorganic insulating film of silicon oxide, silicon nitride, aluminum oxide or aluminum nitride, and the thickness of the first insulating film is 50-200 um.

3. The surface flexible anti-icing / de-icing composite film according to claim 1 or 2, characterized in that: The second insulating film is an inorganic insulating film of silicon oxide, silicon nitride, aluminum oxide or aluminum nitride, and the thickness of the second insulating film is 25-100 um.

4. A method for preparing a surface flexible anti-icing / deicing composite film, characterized in that: The method for preparing the surface flexible anti-icing / deicing composite film according to any one of claims 1 to 3 comprises the following steps: S100, cleaning and drying the substrate surface of the required anti-icing / de-icing part; S200, preparing a first insulating film, and depositing an inorganic insulating film on the surface of the substrate by thermal spraying, magnetron sputtering, ion beam assisted deposition, chemical vapor deposition or magnetic filtered cathode vacuum arc source deposition; S300, preparing a flexible electric heating film on the first insulating film, wherein the flexible electric heating film is set according to different working voltages and power per unit area requirements; the flexible electric heating film is set to a flexible resistance route that meets the set heating requirements by a template method; the flexible electric heating film is formed on the surface of the first insulating film by magnetron sputtering, ion beam assisted deposition or magnetic filtration cathode vacuum arc source deposition; the flexible electric heating film is a pure metal film of Ni, Cr, Cu or Zn or a NiCr alloy film, and the thickness of the flexible electric heating film is 5-20 um; S400, preparing a second insulating film, and forming an inorganic insulating film on the surface of the flexible electric heating film by thermal spraying, magnetron sputtering, ion beam assisted deposition or chemical vapor deposition; S500, forming a CrN-based film on the surface of the second insulating film by magnetron sputtering, ion beam assisted deposition or magnetic filtered cathode vacuum arc source deposition; and S600, preparing a micro-convex structure on the surface of the CrN-based film, and finally forming a CrN-based film with a super-hydrophobic structure; the CrN-based film is a CrN, CrNiN, CrAlN or CrAlSiN film, and the thickness of the CrN-based film is 2-10 um.

5. The method for preparing a surface flexible anti-icing / deicing composite film according to claim 4, characterized in that: The cleaning in step S100 includes: S101, soaking the substrate in tetrachloroethylene for 10 to 30 minutes to remove surface grease; S102, ultrasonically cleaning the substrate for 10 to 20 minutes; S103, placing the substrate in an acetone solution for ultrasonic cleaning for 10 to 20 minutes; S104, placing the substrate in an alcohol solution for ultrasonic cleaning for 10 to 20 minutes; S105, placing the substrate in a deionized beam solution for ultrasonic cleaning 2 to 5 times, each time for 10 to 20 minutes; and S106, placing the substrate in a 70° C. oven and drying for 10 to 30 minutes.

6. The method for preparing a surface flexible anti-icing / deicing composite film according to claim 4, characterized in that: In step S200, a gradient Al2O3 film is deposited on the surface of the substrate by magnetron sputtering.

7. The method for preparing a surface flexible anti-icing / de-icing composite film according to claim 6, characterized in that: Step S200 further includes: S201, placing the substrate into a vacuum coating chamber, turning on a vacuum pump unit to evacuate the vacuum coating chamber, and heating the vacuum coating chamber at the same time; S202, when the temperature reaches the set value and the vacuum degree is less than 8×10 -4 When the flow rate is 0.5 Pa, close the throttle valve, introduce 1.0-2.0 Pa of Ar, turn on the power to sputter the Al target, and the sputtering power is 0.4-0.6 kW; S203, introducing O2 into the vacuum coating chamber while coating, reducing the amount of Ar introduced, and maintaining the pressure of the vacuum coating chamber unchanged, so that the flow ratio of O2 to Ar reaches 3:1 to 4:1; and S204, after 6 to 10 hours of coating, turn off the power supply and gas source, reduce the temperature to less than 100° C., open the vacuum coating chamber and take out the substrate.

8. The method for preparing a surface flexible anti-icing / deicing composite film according to claim 4, characterized in that: In step S300, the plated material is deposited onto the surface of the template by a template method, and then the template is removed to obtain a flexible electric heating film with the standard size of the template.

9. The method for preparing a surface flexible anti-icing / deicing composite film according to claim 8, characterized in that: In step S300, a NiCr alloy film is deposited on the surface of a template placed on the surface of the first insulating film by magnetron sputtering, the Ar flow rate is 50-70 sccm, and the vacuum degree of the vacuum chamber is maintained at 1.3×10 -2 ~1.6×10 -2 Pa, the sputtering power is 0.4-0.6kW, and the coating time is 5-8 hours.

10. The method for preparing a surface flexible anti-icing / deicing composite film according to claim 8, characterized in that: In step S400, the second insulating film is an AlN film, the template placed on the surface of the first insulating film is removed, and the AlN film is deposited on the surfaces of the first insulating film and the flexible electric heating film by magnetron sputtering.

11. The method for preparing a surface flexible anti-icing / deicing composite film according to claim 10, characterized in that: Step S400 further includes: S401, placing the substrate into a vacuum coating chamber, turning on a vacuum pump unit to evacuate the vacuum coating chamber, and heating the vacuum coating chamber at the same time; S402, when the temperature reaches the set value and the vacuum degree is less than 8×10 -4 When the flow rate is Pa, close the throttle valve and introduce N2 and Ar with a flow ratio of N2:Ar=1:1~2:1; S403, turning on the power to sputter the Al target, with the sputtering power being 0.4-0.6 kW; and S404, after 3 to 4 hours of coating, turn off the power supply and gas source, reduce the temperature to less than 100° C., open the vacuum coating chamber and take out the substrate.

12. The method for preparing a surface flexible anti-icing / de-icing composite film according to claim 4, characterized in that: In step S500, a CrNiN film is deposited on the surface of the second insulating film by using a magnetic filtered cathode vacuum arc source deposition, the CrNi target arc source current is 60-80A, the nitrogen flow rate is 50-70sccm, and the vacuum degree of the vacuum chamber is 1.3×10 -2 ~1.6×10 -2 Pa, the deposition negative bias is 100-300 V, the duty cycle is 70-90%, and the deposition time is 2-3 hours.

13. The method for preparing a surface flexible anti-icing / de-icing composite film according to claim 12, characterized in that: In step S600, the micro-protrusion structure is prepared on the surface of the CrNiN film by using a wet sandblasting method.

14. The method for preparing a surface flexible anti-icing / de-icing composite film according to claim 13, characterized in that: The wet sandblasting method uses 2000-5000 mesh white corundum sand, the sandblasting pressure is 0.2-0.4 Pa, the sandblasting angle is 45-60°, and the sandblasting time is 30-60s.

15. An aircraft, characterized in that: The surface of the aircraft component has the surface flexible anti-icing / deicing composite film described in any one of claims 1-3, and is obtained by the preparation method of the surface flexible anti-icing / deicing composite film described in any one of claims 4-14.

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