An airfoil structure suitable for anti-icing and de-icing

Abstract

This invention relates to the field of aviation equipment technology and discloses an airfoil structure suitable for anti-icing and de-icing, comprising: a shell and an electric heating element; by setting the electric heating element inside the shell, forming a first heating layer on the upper and lower surfaces of the inner wall of the shell respectively, and forming a second heating layer at the leading edge, the first and second heating layers are electrically connected and connected to an external power source through an electrode layer, so as to realize power supply to the electric heating element and control the temperature distribution of different parts. After the electrode layer becomes conductive, a first temperature zone is formed in the first heating layer and a second temperature zone is formed in the second heating layer. The temperature of the first temperature zone is lower than the temperature of the second temperature zone, so as to ensure that a higher temperature is maintained at the leading edge of the airfoil structure to meet the requirements of de-icing and anti-icing. The airfoil structure suitable for anti-icing and de-icing provided by this invention can perform differentiated heating according to the icing characteristics of different parts of the airfoil structure, reducing energy consumption and improving energy utilization while ensuring that anti-icing and de-icing requirements are met.

Description

Technical Field

[0001] This invention relates to the field of aviation equipment technology, and more specifically to an airfoil structure suitable for anti-icing and de-icing. Background Technology

[0002] As a crucial aerodynamic component of an aircraft, the design and performance optimization of the wing directly impact aircraft handling, fuel efficiency, and flight safety. However, when aircraft fly in icing-prone airspace, the low temperatures cause wings to easily ice over, affecting the aircraft's aerodynamic and flight dynamic characteristics, and in severe cases, potentially leading to loss of control. Therefore, solving the wing icing problem is of great significance for improving aircraft handling and ensuring safe flight.

[0003] Currently, most wing de-icing systems use engine-induced bleed air to raise the temperature of the wing's leading edge surface, thus achieving de-icing. While this method is reliable and effective, it suffers from complex structural design, and the engine-induced bleed air de-icing process also results in some loss of engine thrust, leading to high energy consumption.

[0004] In addition, commonly used de-icing technology is electric heating, which uses Joule heating to convert electrical energy into heat energy. The resulting heat raises the wing surface temperature, thus achieving the de-icing effect. Traditional electric heating de-icing systems generally use resistance wires and conductive films as heating elements, which have poor heat conduction uniformity and conformability. In actual wing de-icing processes, the leading edge of the wing usually requires a higher de-icing temperature. Whether using bleed air de-icing technology or electric heating de-icing technology, the overall temperature needs to be set high enough. This results in excess heat being generated on the upper and lower wing surfaces, leading to increased energy consumption and low energy efficiency. Summary of the Invention

[0005] In view of this, the present invention provides an airfoil structure suitable for anti-icing and de-icing, so as to solve the problems of existing airfoil structures being unable to form different temperature zones on the same material to meet the anti-icing and de-icing needs of different parts, resulting in high energy consumption and low utilization rate.

[0006] To solve the above-mentioned technical problems, the technical solution of the present invention is as follows:

[0007] This invention provides an airfoil structure suitable for anti-icing and de-icing, comprising: a shell and an electric heating element; the electric heating element is disposed inside the shell, and a first heating layer is formed on both the upper and lower wing surfaces of the inner wall of the shell, and a second heating layer is formed on the leading edge of the inner wall of the shell. The first heating layer and the second heating layer are electrically connected, and an electrode layer is disposed on the outer side of the first heating layer; the electrode layer is connected to an external power source to supply power to the electric heating element, thereby enabling the first heating layer to have a first temperature zone and the second heating layer to have a second temperature zone, wherein the temperature of the first temperature zone is lower than the temperature of the second temperature zone.

[0008] It has the following advantages:

[0009] This invention provides an airfoil structure suitable for anti-icing and de-icing. By incorporating an electric heating element within the shell, and forming a first heating layer on the upper and lower surfaces of the inner wall of the shell, and a second heating layer at the leading edge, the first and second heating layers are electrically connected and connected to an external power source via an electrode layer. This allows for power supply to the electric heating element and control of temperature distribution in different areas. After the electrode layer becomes conductive, a first temperature zone is formed in the first heating layer, and a second temperature zone is formed in the second heating layer. The temperature in the first temperature zone is lower than that in the second temperature zone, ensuring a higher temperature at the leading edge of the airfoil structure to meet de-icing and anti-icing requirements. This airfoil structure provides differentiated heating based on the icing characteristics of different parts of the airfoil structure, ensuring that anti-icing and de-icing requirements are met while reducing energy consumption and improving energy efficiency.

[0010] According to some embodiments of the present invention, the first heating layer is woven from a first fiber monomer, the first fiber monomer comprising, from the inside out, a fiber monofilament, a graphene layer and a first metal layer in the radial direction; or the first fiber monomer comprising, from the inside out, a fiber monofilament, a graphene layer and a metal compound layer in sequence.

[0011] According to some embodiments of the present invention, the second heating layer is woven from a second fiber monomer, the second fiber monomer comprising fiber monofilaments and a graphene layer from the inside to the outside in the radial direction.

[0012] According to some embodiments of the present invention, the first metal layer or the metal compound layer is deposited onto the graphene layer of the second heating layer by vapor deposition to obtain the first heating layer; the first metal layer is copper, tin, bismuth or iron, and the metal compound layer is bismuth trioxide.

[0013] According to some embodiments of the present invention, the thickness of the first metal layer or the metal compound layer is less than or equal to 100 nm.

[0014] According to some embodiments of the present invention, the electrode layer covers the graphene layer of the second heating layer, the electrode layer is distributed in a strip shape, and the electrode layer is a second metal layer.

[0015] According to some embodiments of the present invention, the heating response speeds of the first temperature zone and the second temperature zone are consistent.

[0016] According to some embodiments of the present invention, the cooling response speeds of the first temperature zone and the second temperature zone are consistent.

[0017] According to some embodiments of the present invention, the fiber monofilament is quartz fiber, glass fiber, ceramic fiber, carbon fiber, alumina fiber or boron fiber.

[0018] According to some embodiments of the present invention, the housing includes a surface coating, a thermally conductive layer and an insulating layer arranged sequentially from the outside of the housing toward the electric heating element, and an insulating layer, a thermally conductive layer and a surface coating arranged sequentially from the electric heating element toward the inside of the housing. Attached Figure Description

[0019] To more clearly illustrate the specific embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the specific embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of the present invention. For those skilled in the art, other drawings can be obtained from these drawings without creative effort.

[0020] Figure 1 This is a schematic diagram of an airfoil structure suitable for anti-icing and de-icing provided in some embodiments of the present invention;

[0021] Figure 2 This is a planar unfolded schematic diagram of the electric heating element provided in some embodiments of the present invention;

[0022] Figure 3 This is a schematic cross-sectional view of the first fiber monomer of the first heating layer provided in some embodiments of the present invention;

[0023] Figure 4 This is a cross-sectional planar unfolded schematic diagram of the electrode layer attached to the second fiber monomer in some embodiments of the present invention;

[0024] Figure 5 This is a schematic diagram showing the unfolded cross-sectional plan of the second fiber monomer of the second heating layer provided in some embodiments of the present invention;

[0025] Figure 6 These are microscopic morphology images of the surface of the first heating layer provided in some embodiments of the present invention;

[0026] Figure 7 These are comparative images of the surface microstructures of the first heating layer and the second heating layer provided in some embodiments of the present invention.

[0027] Figure 8 The above are infrared radiation diagrams of the electric heating element provided in some embodiments of the present invention at a working voltage of 45V.

[0028] Figure 9 The above are time-temperature curves of the electric heating element provided in some embodiments of the present invention at a working voltage of 45V.

[0029] Figure 10 This is an equivalent circuit diagram between monofilaments within a fiber bundle.

[0030] Figure 11 This is an equivalent circuit diagram of the warp and weft fiber bundles of a fiber fabric.

[0031] Explanation of reference numerals in the attached figures:

[0032] 1. Shell; 2. Electric heating element; 21. First heating layer; 22. Second heating layer; 23. Electrode layer; 3. Fiber monofilament; 4. Graphene layer; 5. First metal layer. Detailed Implementation

[0033] To make the objectives, technical solutions, and advantages of the embodiments of the present invention clearer, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0034] In the description of this invention, it should be noted that the terms "center," "upper," "lower," "left," "right," "vertical," "horizontal," "inner," and "outer," etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are used only for the convenience of describing the invention and for simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on the invention. Furthermore, the terms "first," "second," and "third" are used for descriptive purposes only and should not be construed as indicating or implying relative importance.

[0035] In the description of this invention, it should be noted that, unless otherwise explicitly specified and limited, the terms "installation," "connection," and "linking" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; and they can refer to the internal connection of two components. Those skilled in the art can understand the specific meaning of the above terms in this invention based on the specific circumstances.

[0036] Furthermore, the technical features involved in the different embodiments of the present invention described below can be combined with each other as long as they do not conflict with each other.

[0037] Reference Figure 1 and Figure 2As shown, the present invention provides an airfoil structure suitable for anti-icing and de-icing, comprising: a shell 1 and an electric heating element 2; the electric heating element 2 is disposed inside the shell 1, and a first heating layer 21 is formed on both the upper and lower wing surfaces of the inner wall of the shell 1, and a second heating layer 22 is formed on the leading edge of the inner wall of the shell 1; the first heating layer 21 and the second heating layer 22 are electrically connected, and an electrode layer 23 is disposed on the outer side of the first heating layer 21; the electrode layer 23 is connected to an external power source to supply power to the electric heating element 2, thereby making the first heating layer 21 have a first temperature zone, and the second heating layer 22 have a second temperature zone, wherein the temperature of the first temperature zone is lower than the temperature of the second temperature zone.

[0038] Specifically, this invention provides an airfoil structure suitable for anti-icing and de-icing. By incorporating an electric heating element 2 inside a shell 1, and forming a first heating layer 21 on the upper and lower surfaces of the inner wall of the shell 1, and a second heating layer 22 at the leading edge, the first and second heating layers 21 are electrically connected and connected to an external power source via an electrode layer 23. This allows for power supply to the electric heating element 2 and control of temperature distribution in different areas. After the electrode layer 23 becomes conductive, a first temperature zone is formed in the first heating layer 21, and a second temperature zone is formed in the second heating layer 22. The temperature of the first temperature zone is lower than that of the second temperature zone, ensuring a higher temperature at the leading edge of the airfoil structure to meet anti-icing and de-icing requirements. This airfoil structure, suitable for anti-icing and de-icing, allows for differentiated heating based on the icing characteristics of different parts of the airfoil structure, ensuring that anti-icing and de-icing requirements are met while reducing energy consumption and improving energy efficiency.

[0039] It is understandable that the electric heating element 2 creates multiple heating zones within the same shell material 1, forming different temperature zones to meet the differentiated de-icing needs of different locations on the airfoil structure, thereby improving de-icing efficiency and targeting. Different heating zones are set with corresponding temperatures according to actual anti-icing requirements, avoiding overheating of non-critical areas and effectively reducing overall energy consumption. The electric heating element 2 is uniformly connected to an external power source through the electrode layer 23, resulting in a simple circuit structure, short heat transfer path, and high energy transfer efficiency, thus improving overall energy utilization. The airfoil structure described in this invention is suitable for various operating environments, especially for use in environments prone to icing such as low temperature and high humidity, and has broad application prospects.

[0040] Reference Figure 3 As shown, in some embodiments of the present invention, the first heating layer 21 is woven from a first fiber monomer, which includes a fiber monofilament 3, a graphene layer 4 and a first metal layer 5 radially from the inside to the outside; or the first fiber monomer includes a fiber monofilament 3, a graphene layer 4 and a metal compound layer sequentially from the inside to the outside.

[0041] Reference Figure 5 As shown, in some embodiments of the present invention, the second heating layer 22 is woven from a second fiber monomer, wherein the first fiber monomer includes fiber monofilaments 3 and a graphene layer 4 radially from the inside to the outside.

[0042] In some embodiments of the present invention, the first metal layer 5 or the metal compound layer is deposited onto the graphene layer 4 of the second heating layer 22 by vapor deposition to obtain the first heating layer 21; the first metal layer 5 is copper, tin, bismuth or iron, and the metal compound layer is bismuth trioxide.

[0043] Specifically, in a specific embodiment of the present invention, the fiber monofilaments 3 and graphene layer 4 selected for the first and second fiber monomers are made of the same material, and the graphene layer 4 has a uniform thickness. Several fiber monofilaments 3 are bound into fiber bundles, and the fiber bundles are woven to form a fiber fabric. In the preparation process of the electric heating element 2, a graphene layer 4 is uniformly deposited and grown on the fiber fabric to form a second heating layer 22. According to the different anti-icing requirements at different positions of the airfoil structure, a mold is used to shield the leading edge portion relative to the airfoil structure. The mold can be a high-temperature resistant quartz mold, so that the portions opposite to the upper and lower wing surfaces of the airfoil structure are exposed. Subsequently, a metal or metal compound targeting material is deposited on the exposed surface of the second heating layer 22 using a vacuum evaporation method. The metal targeting material can be copper, tin, bismuth, or iron, and the metal compound targeting material can be bismuth trioxide, thereby forming a first heating layer 21 on the upper and lower wing surfaces of the airfoil structure.

[0044] It is understood that, in specific embodiments of the present invention, the fiber monofilament 3 is selected from glass fiber, and the average sheet resistance of the second heating layer 22 formed by the fiber monofilament 3 and the graphene layer 4 is 800Ω / sq; the first metal layer 5 is made of copper and has a deposition thickness of 50nm.

[0045] Specifically, in Figures 6 to 9 In the text, GGFF represents the second fiber monomer without deposited metallic copper, i.e., the second heating layer 22; GGFF-Cu represents the first fiber monomer with deposited metallic copper, i.e., the first heating layer 21; GGFF-Cu1 and GGFF-Cu2 represent the first heating layers 21 located in two different regions in the electric heating element.

[0046] After depositing a 50nm copper metal layer in the first heating layer 21 with a sheet resistance of 800Ω / sq, the surface morphologies of the first heating layer 21 and the second heating layer 22 were compared, as follows: Figure 6 and Figure 7 As shown. Among them Figure 6 The image shows the microstructure of the first heating layer 21. It can be seen that there are no obvious particles on the surface, and the first metal layer 5 is uniformly coated on the glass fiber. Figure 7Comparing the surface morphology of the first heating layer 21 and the second heating layer 22, the images of the two regions under a scanning electron microscope only show differences in brightness due to differences in conductivity. There is no instance of the metal layer covering the gaps between monofilaments or the pores between warp and weft fiber bundles. This proves that the nanoscale first metal layer 5 uniformly coats each fiber monomer. The gaps between the monofilaments of the first heating layer 21 and the second heating layer 22, as well as the pores between fiber bundles, still exist and do not affect the original overall structure and flexibility. If a thicker first metal layer 5 is laminated using other processes, it may lead to reduced interlayer strength and cracking after curing; it may also affect resin penetration, resulting in localized low resin content and affecting the strength of the structural component.

[0047] In some embodiments of the present invention, the thickness of the first metal layer 5 or the metal compound layer is less than or equal to 100 nm.

[0048] Specifically, inorganic fiber fabrics can be selected according to specific needs, and graphene can be deposited on the inorganic fiber fabrics to form second heating layers 22 with different sheet resistances. The average sheet resistance of the second heating layer 22 can be selected from: 100Ω / sq, 200Ω / sq, 500Ω / sq, 800Ω / sq, 1000Ω / sq, 3000Ω / sq, 5000Ω / sq, etc. Furthermore, a metal layer or a metal compound layer is deposited on the surface of the second heating layer 22 to obtain a first heating layer 21. The thickness of the first metal layer 5 and the metal compound layer can be determined according to actual needs, and can be selected from 15nm, 30nm, 40nm, 50nm and 100nm, etc.

[0049] Reference Figure 4 As shown, in some embodiments of the present invention, the electrode layer 23 covers the graphene layer 4 of the second heating layer 22, the electrode layer 23 is distributed in a strip shape, and the electrode layer 23 is a second metal layer. The electrode layer can be prepared using processes such as spraying, coating, screen printing, or inkjet printing, depending on the conductivity requirements of the electrode; the present invention does not impose specific limitations.

[0050] Specifically, in the fabrication process of the electric heating element 2, a graphene layer 4 is uniformly deposited and grown on a fiber fabric to form a second heating layer 22. Based on the varying anti-icing requirements at different locations of the airfoil structure, a mold is used to shield the leading edge and side electrode portions relative to the airfoil structure. The mold can be a high-temperature resistant quartz mold, exposing the portions opposite to the upper and lower airfoil surfaces. Subsequently, a metal or metal compound targeting material is deposited on the exposed surface of the second heating layer 22 using vacuum evaporation. The metal targeting material can be copper, tin, bismuth, or iron, and the metal compound targeting material can be bismuth trioxide, thus forming a first heating layer 21 on the upper and lower airfoil surfaces. After removing the mold shielding, a second metal layer, made of a conductive metal, is applied to the surface of the second heating layer 22 on the side electrode portions to form an electrode layer 23. The specific conductive metal material can be copper or silver. The thickness of the electrode layer 23 is 40-80μm, and copper foil is welded at the boundary to lead out the electrode. The width and thickness of the electrode are adjusted according to the actual current carrying requirements.

[0051] In some embodiments of the present invention, the heating response speeds of the first temperature zone and the second temperature zone are consistent.

[0052] In some embodiments of the present invention, the cooling response speeds of the first temperature zone and the second temperature zone are consistent.

[0053] Specifically, the fiber monofilament 3 is glass fiber, and the second heating layer 22 has an average sheet resistance of 800Ω / sq. A first metal layer 5 of 50nm is deposited on the second heating layer 22. The first metal layer 5 is made of copper to form the first heating layer 21. An AC voltage is applied to the electric heating element 2 using an adjustable power supply, and the surface temperature of the electric heating element 2 rises. An infrared thermal imager is used to scan and record the radiated heat and observe the uniformity of its surface temperature.

[0054] Temperature diagram as shown Figure 8 As shown, there is a significant temperature difference between the saturation temperatures of the first heating layer 21 and the second heating layer 22, proving that depositing the first metal layer 5 onto the second heating layer 22 via vacuum evaporation can effectively change the saturation temperature of the heating zone. A 45V AC voltage was continuously applied for 110 seconds, followed by a 90-second cooling period. The average temperature of the first heating layer 21 and the second heating layer 22 was recorded, resulting in a surface temperature change curve over time, as shown in the figure. Figure 9The temperatures of both the first heating layer 21 and the second heating layer 22 rapidly increased within 15 seconds, reaching saturation temperature within 40 seconds. The saturation temperature of the second heating layer 22 was approximately 112°C, while that of the first heating layer 21 was approximately 92°C, a temperature difference of approximately 20°C. After the power was turned off, the surface temperatures of the three regions of the electric heating element rapidly decreased, returning to their initial temperatures after approximately 20 seconds. This indicates that the deposition of the first metal layer 5 only altered the sheet resistance, resulting in a temperature difference between the two regions after power was applied; it did not affect the excellent electrical and thermal conductivity of the graphene glass fiber fabric, and the heating and cooling response rates remained essentially unchanged.

[0055] The first heating layer 21 is obtained by depositing the first metal layer 5 on the surface of the second heating layer 22 using a vapor deposition method. At this time, the resistance R of the entire electric heating element 2 can be divided into three parts, namely the resistance R of the fiber monofilament. n Contact resistance R between fiber monofilaments con1 The contact resistance R between the warp fiber bundle and the weft fiber bundle con2 The resistances R1 and R2 between each fiber filament are connected in parallel, and then the contact resistance R between the fiber filaments is... con1 Therefore, the total resistance R of a bundle of fiber monomers is in series. x(y) Including the resistance R of each fiber filament n Contact resistance R between the fiber monofilament and the fiber con1 The equivalent circuit diagram is as follows: Figure 10 As shown; the resistance R of the warp fiber bundle x With resistance R of weft fiber bundle y Parallel connection, then contact resistance R at the junction of the bundles. con2 Series connection, equivalent circuit diagram as follows Figure 11 As shown, the total resistance R of the entire fabric includes the resistance R of each fiber bundle. x(y) Contact resistance R between the fiber bundle and the fiber bundle con2 According to Ohm's law, the total resistance in a series circuit is equal to the sum of the resistances of each individual component. Therefore, the contact resistance R between the individual fiber filaments is... con1 The decrease in resistance R of the fiber bundle leads to x(y) The decrease in the contact resistance R at the junction of the beams con2 The decrease in ...

[0056] Therefore, the addition of the first metal layer 5 is equivalent to providing a conductive path between fiber monofilaments and between warp fiber bundles and weft fiber bundles, reducing contact resistance, reducing total resistance R, and reducing sheet resistance.

[0057] According to some embodiments of the present invention, the fiber monofilament 3 is quartz fiber, glass fiber, ceramic fiber, carbon fiber, alumina fiber or boron fiber, and the fiber fabric woven from the fiber monofilament can be selected from quartz fiber fabric, glass fiber fabric, ceramic fiber fabric, carbon fiber fabric, alumina fiber fabric or boron fiber fabric.

[0058] According to some embodiments of the present invention, the housing 1 includes a surface coating, a heat-conducting layer and an insulating layer arranged sequentially from the outside of the housing toward the electric heating element 2, and an insulating layer, a heat-conducting layer and a surface coating arranged sequentially from the electric heating element 2 toward the inside of the housing.

[0059] Although embodiments of the invention have been described in conjunction with the accompanying drawings, those skilled in the art can make various modifications and variations without departing from the spirit and scope of the invention, and such modifications and variations all fall within the scope defined by the appended claims.

Claims

1. An airfoil structure suitable for anti-icing and de-icing, characterized in that, include: Shell (1); An electric heating element (2) is disposed inside the housing (1), and a first heating layer (21) is formed on the upper and lower wing surfaces of the inner wall of the housing (1), and a second heating layer (22) is formed on the front edge of the inner wall of the housing (1). The first heating layer (21) and the second heating layer (22) are electrically connected, and an electrode layer (23) is disposed on the outer side of the first heating layer (21). The electrode layer (23) is connected to an external power source to supply power to the electric heating element (2), thereby making the first heating layer (21) have a first temperature zone and the second heating layer (22) have a second temperature zone, with the temperature of the first temperature zone being lower than the temperature of the second temperature zone; The first heating layer (21) is woven from a first fiber monomer, which includes a fiber monofilament (3), a graphene layer (4) and a first metal layer (5) in the radial direction from the inside to the outside; or the first fiber monomer includes a fiber monofilament (3), a graphene layer (4) and a metal compound layer in the radial direction from the inside to the outside. The second heating layer (22) is woven from a second fiber monomer, which includes a fiber monofilament (3) and a graphene layer (4) in the radial direction from the inside to the outside.

2. The airfoil structure suitable for anti-icing and de-icing according to claim 1, characterized in that, The first metal layer (5) or the metal compound layer is deposited onto the graphene layer (4) of the second heating layer (22) by vapor deposition to obtain the first heating layer (21); the first metal layer (5) is copper, tin, bismuth or iron, and the metal compound layer is bismuth trioxide.

3. The airfoil structure suitable for anti-icing and de-icing according to claim 2, characterized in that, The thickness of the first metal layer (5) or the metal compound layer is less than or equal to 100 nm.

4. The airfoil structure suitable for anti-icing and de-icing according to claim 1, characterized in that, The electrode layer (23) covers the graphene layer (4) of the second heating layer (22), the electrode layer (23) is distributed in a strip shape, and the electrode layer (23) is a second metal layer.

5. The airfoil structure suitable for anti-icing and de-icing according to any one of claims 1-4, characterized in that, The heating response speeds of the first temperature zone and the second temperature zone are the same.

6. The airfoil structure suitable for anti-icing and de-icing according to any one of claims 1-4, characterized in that, The cooling response speeds of the first temperature zone and the second temperature zone are consistent.

7. The airfoil structure suitable for anti-icing and de-icing according to claim 1, characterized in that, The fiber monofilament (3) is quartz fiber, glass fiber, ceramic fiber, carbon fiber, alumina fiber or boron fiber.

8. The airfoil structure suitable for anti-icing and de-icing according to claim 1, characterized in that, The housing (1) includes a surface coating, a heat-conducting layer and an insulating layer arranged sequentially from the outside of the housing toward the electric heating element (2), and an insulating layer, a heat-conducting layer and a surface coating arranged sequentially from the electric heating element (2) toward the inside of the housing.

Images